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Sample records for 4th stage turbine

  1. Crescentic ramp turbine stage

    NASA Technical Reports Server (NTRS)

    Lee, Ching-Pang (Inventor); Tam, Anna (Inventor); Kirtley, Kevin Richard (Inventor); Lamson, Scott Henry (Inventor)

    2007-01-01

    A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform includes a crescentic ramp increasing in height from the leading and trailing edges toward the midchord of the airfoil along the pressure side thereof.

  2. PREDICTING TURBINE STAGE PERFORMANCE

    NASA Technical Reports Server (NTRS)

    Boyle, R. J.

    1994-01-01

    This program was developed to predict turbine stage performance taking into account the effects of complex passage geometries. The method uses a quasi-3D inviscid-flow analysis iteratively coupled to calculated losses so that changes in losses result in changes in the flow distribution. In this manner the effects of both the geometry on the flow distribution and the flow distribution on losses are accounted for. The flow may be subsonic or shock-free transonic. The blade row may be fixed or rotating, and the blades may be twisted and leaned. This program has been applied to axial and radial turbines, and is helpful in the analysis of mixed flow machines. This program is a combination of the flow analysis programs MERIDL and TSONIC coupled to the boundary layer program BLAYER. The subsonic flow solution is obtained by a finite difference, stream function analysis. Transonic blade-to-blade solutions are obtained using information from the finite difference, stream function solution with a reduced flow factor. Upstream and downstream flow variables may vary from hub to shroud and provision is made to correct for loss of stagnation pressure. Boundary layer analyses are made to determine profile and end-wall friction losses. Empirical loss models are used to account for incidence, secondary flow, disc windage, and clearance losses. The total losses are then used to calculate stator, rotor, and stage efficiency. This program is written in FORTRAN IV for batch execution and has been implemented on an IBM 370/3033 under TSS with a central memory requirement of approximately 4.5 Megs of 8 bit bytes. This program was developed in 1985.

  3. Two stage turbine for rockets

    NASA Astrophysics Data System (ADS)

    Veres, Joseph P.

    1993-11-01

    The aerodynamic design and rig test evaluation of a small counter-rotating turbine system is described. The advanced turbine airfoils were designed and tested by Pratt & Whitney. The technology represented by this turbine is being developed for a turbopump to be used in an advanced upper stage rocket engine. The advanced engine will use a hydrogen expander cycle and achieve high performance through efficient combustion of hydrogen/oxygen propellants, high combustion pressure, and high area ratio exhaust nozzle expansion. Engine performance goals require that the turbopump drive turbines achieve high efficiency at low gas flow rates. The low mass flow rates and high operating pressures result in very small airfoil heights and diameters. The high efficiency and small size requirements present a challenging turbine design problem. The shrouded axial turbine blades are 50 percent reaction with a maximum thickness to chord ratio near 1. At 6 deg from the tangential direction, the nozzle and blade exit flow angles are well below the traditional design minimum limits. The blade turning angle of 160 deg also exceeds the maximum limits used in traditional turbine designs.

  4. Two stage turbine for rockets

    NASA Technical Reports Server (NTRS)

    Veres, Joseph P.

    1993-01-01

    The aerodynamic design and rig test evaluation of a small counter-rotating turbine system is described. The advanced turbine airfoils were designed and tested by Pratt & Whitney. The technology represented by this turbine is being developed for a turbopump to be used in an advanced upper stage rocket engine. The advanced engine will use a hydrogen expander cycle and achieve high performance through efficient combustion of hydrogen/oxygen propellants, high combustion pressure, and high area ratio exhaust nozzle expansion. Engine performance goals require that the turbopump drive turbines achieve high efficiency at low gas flow rates. The low mass flow rates and high operating pressures result in very small airfoil heights and diameters. The high efficiency and small size requirements present a challenging turbine design problem. The shrouded axial turbine blades are 50 percent reaction with a maximum thickness to chord ratio near 1. At 6 deg from the tangential direction, the nozzle and blade exit flow angles are well below the traditional design minimum limits. The blade turning angle of 160 deg also exceeds the maximum limits used in traditional turbine designs.

  5. VEGA 4th Stage Direct Re-Entry Survivability Analysis and Casualty Risk Assessment

    NASA Astrophysics Data System (ADS)

    Battie, F.; Fossati, T.; Gallucci, S.

    2013-08-01

    A key task in launch vehicle (LV) system design process consists in the estimation of upper stage fragmentation during atmospheric re-entry once accomplished the launcher mission, and the related probability of making on-ground casualties. As a European launcher operating from French Guyana, VEGA has to abide by ESA debris mitigation rules, and by the French Law on Space Operations (LOS). The second flight of VEGA aims at demonstrating the versatility of the launcher by performing a multi-payload launch with different target orbits. From a safety point of view, the compliance of VEGA to the LOS will also be extended through the performance of the direct deorbiting of its upper stage, the AVUM, at the end of its mission. Indeed, during the qualification flight, VEGA had submitted to the safety authorities the derogation envisaged by the LOS: under certain conditions, it allows the indirect re-entry of the launcher's upper stage, provided it shall do so in less than 25 years.

  6. Second Stage Turbine Bucket Airfoil.

    DOEpatents

    Xu, Liming; Ahmadi, Majid; Humanchuk, David John; Moretto, Nicholas; Delehanty, Richard Edward

    2003-05-06

    The second-stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I wherein Z is a perpendicular distance from a plane normal to a radius of the turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at the radially innermost aerodynamic section of the airfoil and X and Y are coordinate values defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the bucket.

  7. Field Verification Program for Small Wind Turbines: Quarterly Report for October-December 2000; 4th Quarter, Iss. No.3

    SciTech Connect

    Cardinal, J.

    2001-07-03

    This newsletter provides a brief overview of the Field Verification Program for Small Wind Turbines conducted out of the NWTC and a description of current activities. The newsletter also contains case studies of current projects.

  8. Turbine stage aerodynamics and heat transfer prediction

    NASA Technical Reports Server (NTRS)

    Griffin, Lisa W.; Mcconnaughey, H. V.

    1989-01-01

    A numerical study of the aerodynamic and thermal environment associated with axial turbine stages is presented. Computations were performed using a modification of the unsteady NASA Ames viscous code, ROTOR1, and an improved version of the NASA Lewis steady inviscid cascade system MERIDL-TSONIC coupled with boundary layer codes BLAYER and STAN5. Two different turbine stages were analyzed: the first stage of the United Technologies Research Center Large Scale Rotating Rig (LSRR) and the first stage of the Space Shuttle Main Engine (SSME) high pressure fuel turbopump turbine. The time-averaged airfoil midspan pressure and heat transfer profiles were predicted for numerous thermal boundary conditions including adiabatic wall, prescribed surface temperature, and prescribed heat flux. Computed solutions are compared with each other and with experimental data in the case of the LSRR calculations. Modified ROTOR1 predictions of unsteady pressure envelopes and instantaneous contour plots are also presented for the SSME geometry. Relative merits of the two computational approaches are discussed.

  9. Effect of Detonation through a Turbine Stage

    NASA Technical Reports Server (NTRS)

    Ellis, Matthew T.

    2004-01-01

    Pulse detonation engines (PDE) have been investigated as a more efficient means of propulsion due to its constant volume combustion rather than the more often used constant pressure combustion of other propulsion systems. It has been proposed that a hybrid PDE-gas turbine engine would be a feasible means of improving the efficiency of the typical constant pressure combustion gas turbine cycle. In this proposed system, multiple pulse detonation tubes would replace the conventional combustor. Also, some of the compressor stages may be removed due to the pressure rise gained across the detonation wave. The benefits of higher thermal efficiency and reduced compressor size may come at a cost. The first question that arises is the unsteadiness in the flow created by the pulse detonation tubes. A constant pressure combustor has the advantage of supplying a steady and large mass flow rate. The use of the pulse detonation tubes will create an unsteady mass flow which will have currently unknown effects on the turbine located downstream of the combustor. Using multiple pulse detonation tubes will hopefully improve the unsteadiness. The interaction between the turbine and the shock waves exiting the tubes will also have an unknown effect. Noise levels are also a concern with this hybrid system. These unknown effects are being investigated using TURBO, an unsteady turbomachinery flow simulation code developed at Mississippi State University. A baseline case corresponding to a system using a constant pressure combustor with the same mass flow rate achieved with the pulse detonation hybrid system will be investigated first.

  10. Investigation of unsteady flow in axial turbine stage

    NASA Astrophysics Data System (ADS)

    Jelínek, Tomáš; Němec, Martin

    2012-04-01

    The never ending process to increase the efficiency of turbine stages introduced an idea to create an axial turbine stage test rig as part of closed loop transonic wind tunnel at Vyzkumny a zkusebni letecky ustav (VZLU). Studying of unsteady flow field behaviours in turbine stages is nowadays essential in the development process. Therefore, the test rig was designed with focusing on possibility of detailed studying of unsteady flow fields in turbine stages. New methodologies and new instrumentations were developed at VZLU and successfully integrated to gain valuable information from experiments with turbine stages. Two different turbine stages were tested during the facility introduction process. The measurement of these two models demonstrated how flexible the test rig is. One of them was an enlarged model of small gas turbine stage. The other was scaled-down model of stage of intermediate-pressure steam turbine. The external characteristics of both models were acquired during experiments as well as the detailed unsteady flow field measurement. Turbine stages were tested in various regimes in order to check the capabilities of the facility, methodology and instrumentation together. The paper presents results of unsteady flow field investigation in the enlarged turbine stage with unshrouded rotor. The interaction of structures developed in a stator with the rotor flow field is depicted and the influence of turbine load on evolution of secondary flows in rotor is analysed.

  11. Numerical prediction of axial turbine stage aerodynamics

    NASA Technical Reports Server (NTRS)

    Mcconnaughey, H. V.; Griffin, L. W.

    1990-01-01

    A preliminary assessment is made of two NASA-developed unsteady turbine stage computer codes. The methodology and previous partial validation of the codes are briefly outlined. Application of these codes to a Space Shuttle main engine turbine for two sets of operating conditions is then described. Steady and unsteady, two and three-dimensional results are presented, compared, and discussed. These results include time-mean and instantaneous airfoil pressure distributions and pressure fluctuations, streamlines on the airfoil surfaces and endwalls, and relative total pressure contours at different axial locations in the rotor passage. Although not available at the time of this writing, experimental data for one of the operating conditions simulated is forthcoming and will be used to assess the accuracy of the unsteady, as well as, the steady predictions presented. Issues related to code usage and resource requirements of the two codes are also discussed.

  12. Second-stage turbine bucket airfoil

    DOEpatents

    Wang, John Zhiqiang; By, Robert Romany; Sims, Calvin L.; Hyde, Susan Marie

    2002-01-01

    The second-stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I wherein Z is a perpendicular distance from a plane normal to a radius of the turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at the radially innermost aerodynamic section of the airfoil and X and Y are coordinate values defining the airfoil profile at each distance Z. The X and Y values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the bucket. The second-stage wheel has sixty buckets.

  13. Third-stage turbine bucket airfoil

    DOEpatents

    Pirolla, Peter Paul; Siden, Gunnar Leif; Humanchuk, David John; Brassfield, Steven Robert; Wilson, Paul Stuart

    2002-01-01

    The third-stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I wherein Z is a perpendicular distance from a plane normal to a radius of the turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at the radially innermost aerodynamic section of the airfoil and X and Y are coordinates defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the bucket.

  14. Multi-stage internal gear/turbine fuel pump

    DOEpatents

    Maier, Eugen; Raney, Michael Raymond

    2004-07-06

    A multi-stage internal gear/turbine fuel pump for a vehicle includes a housing having an inlet and an outlet and a motor disposed in the housing. The multi-stage internal gear/turbine fuel pump also includes a shaft extending axially and disposed in the housing. The multi-stage internal gear/turbine fuel pump further includes a plurality of pumping modules disposed axially along the shaft. One of the pumping modules is a turbine pumping module and another of the pumping modules is a gerotor pumping module for rotation by the motor to pump fuel from the inlet to the outlet.

  15. Staged combustion with piston engine and turbine engine supercharger

    DOEpatents

    Fischer, Larry E.; Anderson, Brian L.; O'Brien, Kevin C.

    2011-11-01

    A combustion engine method and system provides increased fuel efficiency and reduces polluting exhaust emissions by burning fuel in a two-stage combustion system. Fuel is combusted in a piston engine in a first stage producing piston engine exhaust gases. Fuel contained in the piston engine exhaust gases is combusted in a second stage turbine engine. Turbine engine exhaust gases are used to supercharge the piston engine.

  16. Staged combustion with piston engine and turbine engine supercharger

    DOEpatents

    Fischer, Larry E.; Anderson, Brian L.; O'Brien, Kevin C.

    2006-05-09

    A combustion engine method and system provides increased fuel efficiency and reduces polluting exhaust emissions by burning fuel in a two-stage combustion system. Fuel is combusted in a piston engine in a first stage producing piston engine exhaust gases. Fuel contained in the piston engine exhaust gases is combusted in a second stage turbine engine. Turbine engine exhaust gases are used to supercharge the piston engine.

  17. Experimental measurements in a highly loaded low pressure turbine stage

    NASA Astrophysics Data System (ADS)

    Schmitz, John Thomas

    The performance and detailed flow physics of a transonic, low-pressure turbine (LPT) stage with design Zw=1.35, DeltahT/ U2 = 2.8, φ = 0.78, and eta = 90.5% has been investigated experimentally. Recent developments in boundary layer transition modeling were utilized in the aerodynamic design of the stage. Measurements were acquired in a recently developed, high-speed turbine facility constructed to investigate the effects that Reynolds number, nozzle exit flow, freestream turbulence, vane-blade spacing, and rim seal flows have on the loss generating mechanisms of a highly loaded LPT stage. Flow control techniques were applied at the stage inlet with the intent of reducing a source of stage losses. A research dissertation designed to provide understanding of the loss mechanisms that reduce the effectiveness of the Notre Dame Highly Loaded Turbine Stage 01 (ND-HiLT01) is described.

  18. Measurement of airfoil heat transfer coefficients on a turbine stage

    NASA Astrophysics Data System (ADS)

    Dring, Robert P.; Blair, Michael F.; Joslyn, H. David

    1986-10-01

    The Primary basis for heat transfer analysis of turbine airfoils is experimental data obtained in linear cascades. These data were very valuable in identifying the major heat transfer and fluid flow features of a turbine airfoil. The first program objective is to obtain a detailed set of heat transfer coefficients along the midspan of a stator and a rotor in a rotating turbine stage. The data are to be compared to some standard analysis of blade boundary layer heat transfer which is in use today. A second program objective is to obtain a detailed set of heat transfer coefficients along the midspan of a stator located in the wake of an upstream turbine stage.

  19. Effects of hydroelectric turbine passage on fish early life stages

    SciTech Connect

    Cada, G.F.

    1991-01-01

    Turbine-passage mortality has been studied extensively for juveniles and adults of migratory fish species, but few studies have directly quantified mortality of fish eggs and larvae. An analysis of literature relating to component stresses of turbine passage (i.e., pressure changes, blade contact, and shear) indicates that mortality of early life stages of fish would be relatively low at low-head, bulb turbine installations. The shear forces and pressure regimes normally experienced are insufficient to cause high mortality rates. The probability of contact with turbine blades is related to the size of the fish; less than 5% of entrained ichthyoplankton would be killed by the blades in a bulb turbine. Other sources of mortality (e.g., cavitation and entrainment of fish acclimated to deep water) are controlled by operation of the facility and thus are mitigable. Because turbine-passage mortality among fish early life stages can be very difficult to estimate directly, it may be more fruitful to base the need for mitigation at any given site on detailed knowledge of turbine characteristics and the susceptibility of the fish community to entrainment. 7 refs., 1 fig.

  20. Computer Program Predicts Turbine-Stage Performance

    NASA Technical Reports Server (NTRS)

    Boyle, Robert J.; Haas, Jeffrey E.; Katsanis, Theodore

    1988-01-01

    MTSBL updated version of flow-analysis programs MERIDL and TSONIC coupled to boundary-layer program BLAYER. Method uses quasi-three-dimensional, inviscid, stream-function flow analysis iteratively coupled to calculated losses so changes in losses result in changes in flow distribution. Manner effects both configuration on flow distribution and flow distribution on losses taken into account in prediction of performance of stage. Written in FORTRAN IV.

  1. Turbine nozzle stage having thermocouple guide tube

    DOEpatents

    Schotsch, Margaret Jones; Kirkpatrick, Francis Lawrence; Lapine, Eric Michael

    2002-01-01

    A guide tube is fixed adjacent opposite ends in outer and inner covers of a nozzle stage segment. The guide tube is serpentine in shape between the outer and inner covers and extends through a nozzle vane. An insert is disposed in the nozzle vane and has apertures to accommodate serpentine portions of the guide tube. Cooling steam is also supplied through chambers of the insert on opposite sides of a central insert chamber containing the guide tube. The opposite ends of the guide tube are fixed to sleeves, in turn fixed to the outer and inner covers.

  2. Highly loaded multi-stage fan drive turbine: Performance of final three configurations

    NASA Technical Reports Server (NTRS)

    Cherry, D. G.; Thomas, M. W.

    1974-01-01

    Results for a three-stage highly loaded fan drive turbine follow-on test program are presented. The effects of combinations of tandem and leaned bladerows on three-stage turbine performance were tested. The three-stage turbine with a tandem stator in stage two exhibited a total-to-total efficiency of approximately 0.887 as compared to 0.886 for the plain blade turbine base case.

  3. Stereoscopic particle image velocimetry in a transonic turbine stage

    NASA Astrophysics Data System (ADS)

    Lang, H.; Mørck, T.; Woisetschläger, J.

    2002-06-01

    In order to investigate the flow field in axial turbine stages, a continuously operating transonic test turbine facility for high pressure ratios was designed at Graz University of Technology, Austria. This test facility allows optical access to the rotor and to the stator trailing edge. The three-dimensional velocity distribution in the region of stator-rotor interaction was investigated by stereoscopic particle image velocimetry. To obtain the three-dimensional velocity vectors in one plane at the mid-section of the turbine blades, a calibration-based method was used. Light-sheet delivery, seeding and triggering to four pre-defined rotor-stator positions are discussed, and an insight into the rotor-stator interaction is given, including vortex shedding in the stator wake.

  4. Cold-air investigation of a 3 1/2-stage fan-drive turbine with a stage loading factor of 4 designed for an integral lift engine. 1: Turbine design and performance of first stage

    NASA Technical Reports Server (NTRS)

    Whitney, W. J.; Schum, H. J.; Behning, F. P.

    1975-01-01

    The design of the 3 1/2-stage turbine is described, and the cold-air performance of the first stage, modified for axial inlet conditions, is presented. The performance of the modified single-stage turbine and of two comtemporary high-stage-loading-factor turbines is compared with that estimated with a reference prediction method.

  5. Engine tests on a cooled gas turbine stage

    NASA Astrophysics Data System (ADS)

    Graf, H. J.

    1985-09-01

    A new cooling system was designed for the 45 MW gas turbine type 8. Extensive tests were carried out in a new power station to verify the reliability of the cooled components. Wall temperatures were measured using thermocouples, thermal paints and pyrometers. Cooling air temperature, pressure and mass flow measurements allowed a detailed analysis of the first stage under operating conditions. The results and comparisons with design calculations are presented. The applicability and accuracy of the three measuring techniques are discussed.

  6. Measurement of airfoil heat transfer coefficients on a turbine stage

    NASA Astrophysics Data System (ADS)

    Dring, Robert P.; Blair, Michael F.; Joslyn, H. David

    1987-10-01

    A combined experimental and analytical program was conducted to examine the impact of a number of variables on the midspan heat transfer coefficients of the three airfoil rows in a one and one-half stage large scale turbine model. Variables included stator/rotor axial spacing, Reynolds number, turbine inlet turbulence, flow coefficient, relevant stator 1/stator 2 circumferential position, and rotation. Heat transfer data were acquired on the suction and pressure surfaces of the three airfoils. High density data were also acquired in the leading edge stagnation regions. Extensive documentation of the steady and unsteady aerodynamics was acquired. Finally, heat transfer data were compared with both a steady and an unsteady boundary layer analysis.

  7. Investigation of azimuthal staging concepts in annular gas turbines

    NASA Astrophysics Data System (ADS)

    Noiray, Nicolas; Bothien, Mirko; Schuermans, Bruno

    2011-10-01

    In this work, the influence of azimuthal staging concepts on the thermoacoustic behavior of annular combustion chambers is assessed theoretically and numerically. Staging is a well-known and effective method to abate thermoacoustic pulsations in combustion chambers. However, in the case of, for example, fuel staging the associated inhomogeneity of equivalence ratio may result in increased levels of NOx emissions. In order to minimize this unwanted effect a staging concept is required in which the transfer functions of the burners are changed while affecting the equivalence ratio as little as possible. In order to achieve this goal, a theoretical framework for predicting the influence of staging concepts on pulsations has been developed. Both linear and nonlinear analytical approaches are presented and it is shown that the dynamics of azimuthal modes can be described by coupled Van der Pol oscillators. A criterion based on the thermoacoustic coupling strength and on the asymmetry degree provides the modal behavior in the annular combustor, i.e. standing or traveling waves. The model predictions have been verified by numerical simulations of a heavy-duty gas turbine using an in-house thermoacoustic network-modeling tool. The interaction between the heat release of the flame and the acoustic field was modeled using measured transfer functions and source terms. These numerical simulations confirmed the original theoretical considerations.

  8. Detailed Validation Assessment of Turbine Stage Disc Cavity Rotating Flows

    NASA Astrophysics Data System (ADS)

    Kanjiyani, Shezan

    The subject of this thesis is concerned with the amount of cooling air assigned to seal high pressure turbine rim cavities which is critical for performance as well as component life. Insufficient air leads to excessive hot annulus gas ingestion and its penetration deep into the cavity compromising disc life. Excessive purge air, adversely affects performance. Experiments on a rotating turbine stage rig which included a rotor-stator forward disc cavity were performed at Arizona State University. The turbine rig has 22 vanes and 28 blades, while the rim cavity is composed of a single-tooth rim lab seal and a rim platform overlap seal. Time-averaged static pressures were measured in the gas path and the cavity, while mainstream gas ingestion into the cavity was determined by measuring the concentration distribution of tracer gas (carbon dioxide). Additionally, particle image velocimetry (PIV) was used to measure fluid velocity inside the rim cavity between the lab seal and the overlap. The data from the experiments were compared to an 360-degree unsteady RANS (URANS) CFD simulations. Although not able to match the time-averaged test data satisfactorily, the CFD simulations brought to light the unsteadiness present in the flow during the experiment which the slower response data did not fully capture. To interrogate the validity of URANS simulations in capturing complex rotating flow physics, the scope of this work also included to validating the CFD tool by comparing its predictions against experimental LDV data in a closed rotor-stator cavity. The enclosed cavity has a stationary shroud, a rotating hub, and mass flow does not enter or exit the system. A full 360 degree numerical simulation was performed comparing Fluent LES, with URANS turbulence models. Results from these investigations point to URANS state of art under-predicting closed cavity tangential velocity by 32% to 43%, and open rim cavity effectiveness by 50% compared to test data. The goal of this thesis

  9. The 4th Thermodynamic Principle?

    SciTech Connect

    Montero Garcia, Jose de la Luz; Novoa Blanco, Jesus Francisco

    2007-04-28

    It should be emphasized that the 4th Principle above formulated is a thermodynamic principle and, at the same time, is mechanical-quantum and relativist, as it should inevitably be and its absence has been one of main the theoretical limitations of the physical theory until today.We show that the theoretical discovery of Dimensional Primitive Octet of Matter, the 4th Thermodynamic Principle, the Quantum Hexet of Matter, the Global Hexagonal Subsystem of Fundamental Constants of Energy and the Measurement or Connected Global Scale or Universal Existential Interval of the Matter is that it is possible to be arrived at a global formulation of the four 'forces' or fundamental interactions of nature. The Einstein's golden dream is possible.

  10. First-stage high pressure turbine bucket airfoil

    DOEpatents

    Brown, Theresa A.; Ahmadi, Majid; Clemens, Eugene; Perry, II, Jacob C.; Holiday, Allyn K.; Delehanty, Richard A.; Jacala, Ariel Caesar

    2004-05-25

    The first-stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein Z is a perpendicular distance from a plane normal to a radius of the turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at the radially innermost aerodynamic section of the airfoil and X and Y are coordinates defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the bucket.

  11. Self-regulating fuel staging port for turbine combustor

    DOEpatents

    Van Nieuwenhuizen, William F.; Fox, Timothy A.; Williams, Steven

    2014-07-08

    A port (60) for axially staging fuel and air into a combustion gas flow path 28 of a turbine combustor (10A). A port enclosure (63) forms an air path through a combustor wall (30). Fuel injectors (64) in the enclosure provide convergent fuel streams (72) that oppose each other, thus converting velocity pressure to static pressure. This forms a flow stagnation zone (74) that acts as a valve on airflow (40, 41) through the port, in which the air outflow (41) is inversely proportion to the fuel flow (25). The fuel flow rate is controlled (65) in proportion to engine load. At high loads, more fuel and less air flow through the port, making more air available to the premixing assemblies (36).

  12. Axially staged combustion system for a gas turbine engine

    DOEpatents

    Bland, Robert J.

    2009-12-15

    An axially staged combustion system is provided for a gas turbine engine comprising a main body structure having a plurality of first and second injectors. First structure provides fuel to at least one of the first injectors. The fuel provided to the one first injector is adapted to mix with air and ignite to produce a flame such that the flame associated with the one first injector defines a flame front having an average length when measured from a reference surface of the main body structure. Each of the second injectors comprising a section extending from the reference surface of the main body structure through the flame front and having a length greater than the average length of the flame front. Second structure provides fuel to at least one of the second injectors. The fuel passes through the one second injector and exits the one second injector at a location axially spaced from the flame front.

  13. Application of the balancing holes on the turbine stage discs with higher root reaction

    NASA Astrophysics Data System (ADS)

    Mrózek, Lukáš; Tajč, Ladislav; Hoznedl, Michal; Miczán, Martin

    2016-03-01

    The influence of the flow area of balancing holes in the discs of a steam turbine on its thermodynamic efficiency is examined for turbine stages operating in the increased root reaction regime. The interstage seal flooding with steam is modelled. The impact is given on stage reaction changes, on mass flow adjustments, and on overpressure operating in the rotor disc.

  14. Investigation of Single-Stage Modified Turbine of Mark 25 Torpedo Power Plant

    NASA Technical Reports Server (NTRS)

    Hoyt, Jack W.

    1947-01-01

    Efficiency investigations have been made on a single-stage modification of the turbine of a Mark 25 aerial torpedo to determine the performance of the unit with five different turbine nozzles. The output of the turbine blades was computed by analyzing the windage and mechanical-friction losses of the unit. The turbine was faund to be most efficient with a cast nozzle having sharp-edged inlets to the nine nozzle ports. An analysis af the effectiveness af the first and second stages of the standard Mark 25 torpedo turbine indicates that the first- stage turbine contributes nearly all the brake power produced at blade-jet speed ratios above 0.26.

  15. Mathematical modeling and optimization of flow structure in stage of francis turbine of micro gas turbine power plant

    NASA Astrophysics Data System (ADS)

    Kartashev, A. L.; Vaulin, S. D.; Kartasheva, M. A.; Martynov, A. A.; Safonov, E. V.

    2016-06-01

    This article presents information about the main distinguishing features of microturbine power plants. The justification of the use of Francis turbine in microturbine power plants with rated power of 100 kW is given. Initial analytical engineering calculations of the turbine (without using computational fluid dynamics) with appropriate calculation methods are considered. The parametric study of nozzle blade and whole turbine stage using ANSYS CFX is descripted. The calculations determined the optimal geometry on the criterion of maximizing efficiency at total pressure ratio. The calculation results are presented in graphical form, as well as the velocity and pressure fields at the interscapular channels of nozzle unit and the impeller.

  16. Cooling supply system for stage 3 bucket of a gas turbine

    DOEpatents

    Eldrid, Sacheverel Quentin; Burns, James Lee; Palmer, Gene David; Leone, Sal Albert; Drlik, Gary Joseph; Gibler, Edward Eugene

    2002-01-01

    In a land based gas turbine including a compressor, a combustor and turbine section including at least three stages, an improvement comprising an inlet into a third stage nozzle from the compressor for feeding cooling air from the compressor to the third stage nozzle; at least one passageway running substantially radially through each airfoil of the third stage nozzle and an associated diaphragm, into an annular space between the rotor and the diaphragm; and passageways communicating between the annular space and individual buckets of the third stage.

  17. CFD analysis of fluid flow in an axial multi-stage partial-admission ORC turbine

    NASA Astrophysics Data System (ADS)

    Surwilo, Jan; Lampart, Piotr; Szymaniak, Mariusz

    2015-10-01

    Basic operational advantages of the Organic Rankine Cycle (ORC) systems and specific issues of turbines working in these systems are discussed. The strategy for CFD simulation of the considered ORC turbine and the main issues of the numerical model are presented. The method of constructing the 3D CAD geometry as well as discretisation of the flow domain are also shown. Main features of partial admission flow in the multi-stage axial turbine are discussed. The influence of partial admission on the working conditions of the subsequent stage supplied at the full circumference is also described.

  18. Lean-rich axial stage combustion in a can-annular gas turbine engine

    DOEpatents

    Laster, Walter R.; Szedlacsek, Peter

    2016-06-14

    An apparatus and method for lean/rich combustion in a gas turbine engine (10), which includes a combustor (12), a transition (14) and a combustor extender (16) that is positioned between the combustor (12) and the transition (14) to connect the combustor (12) to the transition (14). Openings (18) are formed along an outer surface (20) of the combustor extender (16). The gas turbine (10) also includes a fuel manifold (28) to extend along the outer surface (20) of the combustor extender (16), with fuel nozzles (30) to align with the respective openings (18). A method (200) for axial stage combustion in the gas turbine engine (10) is also presented.

  19. Design and cold-air test of single-stage uncooled turbine with high work output

    NASA Technical Reports Server (NTRS)

    Moffitt, T. P.; Szanca, E. M.; Whitney, W. J.; Behning, F. P.

    1980-01-01

    A solid version of a 50.8 cm single stage core turbine designed for high temperature was tested in cold air over a range of speed and pressure ratio. Design equivalent specific work was 76.84 J/g at an engine turbine tip speed of 579.1 m/sec. At design speed and pressure ratio, the total efficiency of the turbine was 88.6 percent, which is 0.6 point lower than the design value of 89.2 percent. The corresponding mass flow was 4.0 percent greater than design.

  20. 17. 4th floor roof, view south, 4th and 5th floor ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    17. 4th floor roof, view south, 4th and 5th floor setback to left and atrium structure to right - Sheffield Farms Milk Plant, 1075 Webster Avenue (southwest corner of 166th Street), Bronx, Bronx County, NY

  1. Numerical analysis of flow interaction of turbine system in two-stage turbocharger of internal combustion engine

    NASA Astrophysics Data System (ADS)

    Liu, Y. B.; Zhuge, W. L.; Zhang, Y. J.; Zhang, S. Y.

    2016-05-01

    To reach the goal of energy conservation and emission reduction, high intake pressure is needed to meet the demand of high power density and high EGR rate for internal combustion engine. Present power density of diesel engine has reached 90KW/L and intake pressure ratio needed is over 5. Two-stage turbocharging system is an effective way to realize high compression ratio. Because turbocharging system compression work derives from exhaust gas energy. Efficiency of exhaust gas energy influenced by design and matching of turbine system is important to performance of high supercharging engine. Conventional turbine system is assembled by single-stage turbocharger turbines and turbine matching is based on turbine MAP measured on test rig. Flow between turbine system is assumed uniform and value of outlet physical quantities of turbine are regarded as the same as ambient value. However, there are three-dimension flow field distortion and outlet physical quantities value change which will influence performance of turbine system as were demonstrated by some studies. For engine equipped with two-stage turbocharging system, optimization of turbine system design will increase efficiency of exhaust gas energy and thereby increase engine power density. However flow interaction of turbine system will change flow in turbine and influence turbine performance. To recognize the interaction characteristics between high pressure turbine and low pressure turbine, flow in turbine system is modeled and simulated numerically. The calculation results suggested that static pressure field at inlet to low pressure turbine increases back pressure of high pressure turbine, however efficiency of high pressure turbine changes little; distorted velocity field at outlet to high pressure turbine results in swirl at inlet to low pressure turbine. Clockwise swirl results in large negative angle of attack at inlet to rotor which causes flow loss in turbine impeller passages and decreases turbine

  2. A comprehensive method for preliminary design optimization of axial gas turbine stages

    NASA Technical Reports Server (NTRS)

    Jenkins, R. M.

    1982-01-01

    A method is presented that performs a rapid, reasonably accurate preliminary pitchline optimization of axial gas turbine annular flowpath geometry, as well as an initial estimate of blade profile shapes, given only a minimum of thermodynamic cycle requirements. No geometric parameters need be specified. The following preliminary design data are determined: (1) the optimum flowpath geometry, within mechanical stress limits; (2) initial estimates of cascade blade shapes; (3) predictions of expected turbine performance. The method uses an inverse calculation technique whereby blade profiles are generated by designing channels to yield a specified velocity distribution on the two walls. Velocity distributions are then used to calculate the cascade loss parameters. Calculated blade shapes are used primarily to determine whether the assumed velocity loadings are physically realistic. Model verification is accomplished by comparison of predicted turbine geometry and performance with four existing single stage turbines.

  3. Design and test of a small two stage counter-rotating turbine for rocket engine application

    NASA Technical Reports Server (NTRS)

    Huber, F. W.; Branstrom, B. R.; Finke, A. K.; Johnson, P. D.; Rowey, R. J.; Veres, J. P.

    1993-01-01

    The aerodynamic design and rig test evaluation of a small counter-rotating turbine system is described. The technology represented by this turbine is being developed for application in an advanced upper stage rocket engine turbopump. This engine will employ an oxygen/hydrogen expander cycle and achieve high performance through efficient combustion, high combustion pressure, and high area ratio exhaust nozzle expansion. Engine performance goals require that the turbopump drive turbines achieve high efficiency at low gas flow rates. The low flow rates result in very small airfoil diameter, height and chord. The high efficiency and small size requirements present a challenging turbine design problem. The unconventional approach employed to meet this challenge is described, along with the detailed design process and resulting airfoil configurations. The method and results of full scale aerodynamic performance evaluation testing of both one and two stage configurations, as well as operation without the secondary stage stator are presented. The overall results of this effort illustrate that advanced aerodynamic design tools and hardware fabrication techniques have provided improved capability to produce small high performance turbines for advanced rocket engines.

  4. A comprehensive method for preliminary design optimization of axial gas turbine stages. II - Code verification

    NASA Technical Reports Server (NTRS)

    Jenkins, R. M.

    1983-01-01

    The present effort represents an extension of previous work wherein a calculation model for performing rapid pitchline optimization of axial gas turbine geometry, including blade profiles, is developed. The model requires no specification of geometric constraints. Output includes aerodynamic performance (adiabatic efficiency), hub-tip flow-path geometry, blade chords, and estimates of blade shape. Presented herein is a verification of the aerodynamic performance portion of the model, whereby detailed turbine test-rig data, including rig geometry, is input to the model to determine whether tested performance can be predicted. An array of seven (7) NASA single-stage axial gas turbine configurations is investigated, ranging in size from 0.6 kg/s to 63.8 kg/s mass flow and in specific work output from 153 J/g to 558 J/g at design (hot) conditions; stage loading factor ranges from 1.15 to 4.66.

  5. Study of Boundary Layer Development in a Two-Stage Low-Pressure Turbine

    NASA Technical Reports Server (NTRS)

    Dorney, Daniel J.; Ashpis, David E.; Halstead, David E.; Wisler, David C.

    1999-01-01

    Experimental data from jet-engine tests have indicated that unsteady blade row interactions and separation can have a significant impact on the efficiency of low-pressure turbine stages. Measured turbine efficiencies at takeoff can be as much as two points higher than those at cruise conditions. Several recent studies have revealed that Reynolds number effects may contribute to the lower efficiencies at cruise conditions. In the current study numerical simulations have been performed to study the boundary layer development in a two-stage low-pressure turbine, and to evaluate the transition models available for low Reynolds number flows in turbomachinery. The results of the simulations have been compared with experimental data, including airfoil loadings and integral boundary layer quantities. The predicted unsteady results display similar trends to the experimental data, but significantly overestimate the amplitude of the unsteadiness. The time-averaged results show close agreement with the experimental data.

  6. Analyzing the influence exerted by individual components of wetness losses on the efficiency of steam turbine stage and compartments

    NASA Astrophysics Data System (ADS)

    Filippov, G. A.; Gribin, V. G.; Avetisyan, A. R.; Lisyanskii, A. S.

    2015-01-01

    The influence exerted by dispersed moisture on the economic efficiency of steam turbine stages and compartments operating in the wet steam region is analyzed. A procedure for generalizing experimental data is proposed that was used for analyzing the previously published results of experiments on determining the influence of different loss components on the efficiency of steam turbine stages and compartments. The influence of coarsely dispersed moisture on the turbine efficiency indicators is shown.

  7. Study of Boundary Layer Development in a Two-Stage Low-Pressure Turbine

    NASA Technical Reports Server (NTRS)

    Dorney, Daniel J.; Ashpis, David E.; Halstead, David E.; Wisler, David C.

    1998-01-01

    Experimental data from jet-engine tests have indicated that unsteady blade row (wake) interactions and separation can have a significant impact on the efficiency of turbine stages. The effects of these interactions can be intensified in low-pressure turbine stages because of the low Reynolds number operating environment. Measured turbine efficiencies at takeoff can be as much as two points higher than those at cruise conditions. Thus, during the last decade a significant amount of effort has been put into determining the effects of transition and turbulence on the performance of low pressure turbine stages. Experimental investigations have been performed, for example, by Hodson et al. and Halstead et al. These investigations have helped identify/clarify the roles that factors such as the Reynolds number, free stream turbulence intensity, pressure gradient and curvature have in the generation of losses. In parallel to the experimental investigations, there have been significant analytical efforts to improve the modeling of transition. Examples of such efforts include the works of Mayle and Gostelow et al. These newer models show promise of providing accurate transition predictions over a wide range of flow conditions, although they have yet to be implemented into the numerical flow analyses used by the turbine design community. Some recent computational investigations of interest include the works of Chernobrovkin and Lakshminarayana and Eulitz and Engel. The focus of the current effort has been to -use a viscous, unsteady quasi-three-dimensional Navier-Stokes analysis to study boundary layer development in a two-stage low-pressure turbine. A two-layer algebraic turbulence model, along with a natural transition model and a bubble transition model, have been used, The geometry used in the simulations has been the subject of extensive experiments. The predicted results have been compared with experimental data, including airfoil loadings and time

  8. Calculation of flow distribution in large radius ratio stages of axial flow turbines and comparison of theory and experiment

    NASA Technical Reports Server (NTRS)

    Herzog, J.

    1974-01-01

    A method of calculating stage parameters and flow distribution of axial turbines is described. The governing equations apply to space between the blade rows and are based on the assumption of rotationally symmetrical, compressible, adiabatic flow conditions. Results are presented for stage design and flow analysis calculations. Theoretical results from the calculation system are compared with experimental data from low pressure steam turbine tests.

  9. Heat-flux measurements and analysis for a rotating turbine stage

    NASA Astrophysics Data System (ADS)

    Dunn, M. G.

    1985-09-01

    A measurement and analysis program is descirbed which utilizes: (1) a Garrett TFE 731-2 high-pressure turbine stage and (2) a Garrett low aspect ratio turbine (LART) stage. The major emphasis of this program has been placed on obtaining accurate measurements of heat-flux distributions in the full-scale rotating turbine stage. The experimental technique being used is the short-duration, shock-tunnel approach, in which fast-response, thin-film thermometers are used to measure the surface temperature histories at prescribed positions on the various component parts. Heat flux values are then inferred from these temperature histories using standard data reduction procedures. A summary and discussion of the TFE 731-2 high pressure turbine results with particular emphasis on nozzle guide vane (NGV) tip endwall data not previously reported are provided. A significantly more brief discussion of the LART stage instrumentation is also included. In addition, a summary discussion of the experimental technique and the associated instrumentation is included.

  10. A Computer Program for Simulating Transient Behavior in Steam Turbine Stage Pressure of AHWR

    SciTech Connect

    Dutta, Anu; Thangamani, I.; Chakraborty, G.; Ghosh, A.K.; Kushwaha, H.S.

    2006-07-01

    It is proposed to couple the Advanced Heavy water reactor (AHWR), which is being developed by Bhabha Atomic Research Centre, India, with a desalination plant. The objective of this coupling is to produce system make-up and domestic water. The proposed desalination plant needs about 1.9 kg/sec of steam and the minimum pressure requirement is 3 bars. The desalination plant can be fed with bled steam extracted from a suitable stage in low pressure turbine. As the turbine stage pressure changes with the load, it is essential to know the availability of bled steam at aforesaid pressure for various load condition. The objective of the present study is to identify a suitable extraction point so as to ensure availability of steam at desired condition for desalination plant, even at part load conditions. In order to fulfill the above objective a steam and feed system analysis code was developed which incorporates the mathematical formulation of different components of the steam and feed system such as, high pressure (HP) and low pressure (LP) turbines, re-heater, feed heaters etc. The dynamic equations are solved simultaneously to obtain the stage pressure at various load conditions. Based on the results obtained, the suitable extraction stage in LP turbine was selected. This enables to determine the lowest possible part load operation up to which availability of desalination plant could be ensured. (authors)

  11. Tests of a 2-Stage, Axial-Flow, 2-Phase Turbine

    NASA Technical Reports Server (NTRS)

    Elliott, D. G.

    1982-01-01

    A two phase flow turbine with two stages of axial flow impulse rotors was tested with three different working fluid mixtures at a shaft power of 30 kW. The turbine efficiency was 0.55 with nitrogen and water of 0.02 quality and 94 m/s velocity, 0.57 with Refrigerant 22 of 0.27 quality and 123 m/s velocity, and 0.30 with steam and water of 0.27 quality and 457 m/s velocity. The efficiencies with nitrogen and water and Refrigerant 22 were 86 percent of theoretical. At that fraction of theoretical, the efficiencies of optimized two phase turbines would be in the low 60 percent range with organic working fluids and in the mid 50 percent range with steam and water. The recommended turbine design is a two stage axial flow impulse turbine followed by a rotary separator for discharge of separate liquid and gas streams and recovery of liquid pressure.

  12. Effects of nozzle-strut integrated design concepton on the subsonic turbine stage flowfield

    NASA Astrophysics Data System (ADS)

    Liu, Jun; Du, Qiang; Liu, Guang; Wang, Pei; Zhu, Junqiang

    2014-10-01

    In order to shorten aero-engine axial length, substituting the traditional long chord thick strut design accompanied with the traditional low pressure(LP) stage nozzle, LP turbine is integrated with intermediate turbine duct (ITD). In the current paper, five vanes of the first stage LP turbine nozzle is replaced with loaded struts for supporting the engine shaft, and providing oil pipes circumferentially which fulfilled the areo-engine structure requirement. However, their bulky geometric size represents a more effective obstacle to flow from high pressure (HP) turbine rotor. These five struts give obvious influence for not only the LP turbine nozzle but also the flowfield within the ITD, and hence cause higher loss. Numerical investigation has been undertaken to observe the influence of the Nozzle-Strut integrated design concept on the flowfield within the ITD and the nearby nozzle blades. According to the computational results, three main conclusions are finally obtained. Firstly, a noticeable low speed area is formed near the strut's leading edge, which is no doubt caused by the potential flow effects. Secondly, more severe radial migration of boundary layer flow adjacent to the strut's pressure side have been found near the nozzle's trailing edge. Such boundary layer migration is obvious, especially close to the shroud domain. Meanwhile, radial pressure gradient aggravates this phenomenon. Thirdly, velocity distribution along the strut's pressure side on nozzle's suction surface differs, which means loading variation of the nozzle. And it will no doubt cause nonuniform flowfield faced by the downstream rotor blade.

  13. Design and Experimental Performance of a Two Stage Partial Admission Turbine, Task B.1/B.4

    NASA Technical Reports Server (NTRS)

    Sutton, R. F.; Boynton, J. L.; Akian, R. A.; Shea, Dan; Roschak, Edmund; Rojas, Lou; Orr, Linsey; Davis, Linda; King, Brad; Bubel, Bill

    1992-01-01

    A three-inch mean diameter, two-stage turbine with partial admission in each stage was experimentally investigated over a range of admissions and angular orientations of admission arcs. Three configurations were tested in which first stage admission varied from 37.4 percent (10 of 29 passages open, 5 per side) to 6.9 percent (2 open, 1 per side). Corresponding second stage admissions were 45.2 percent (14 of 31 passages open, 7 per side) and 12.9 percent (4 open, 2 per side). Angular positions of the second stage admission arcs with respect to the first stage varied over a range of 70 degrees. Design and off-design efficiency and flow characteristics for the three configurations are presented. The results indicated that peak efficiency and the corresponding isentropic velocity ratio decreased as the arcs of admission were decreased. Both efficiency and flow characteristics were sensitive to the second stage nozzle orientation angles.

  14. Cold-air performance of compressor-drive turbine of Department of Energy upgraded automobile gas turbine engine. 2: Stage performance

    NASA Technical Reports Server (NTRS)

    Roelke, R. J.; Haas, J. E.

    1982-01-01

    The aerodynamic performance of the compressor-drive turbine of the DOE upgraded gas turbine engine was determined in low temperature air. The as-received cast rotor blading had a significantly thicker profile than design and a fairly rough surface finish. Because of these blading imperfections a series of stage tests with modified rotors were made. These included the as-cast rotor, a reduced-roughness rotor, and a rotor with blades thinned to near design. Significant performance changes were measured. Tests were also made to determine the effect of Reynolds number on the turbine performance. Comparisons are made between this turbine and the compressor-drive turbine of the DOE baseline gas turbine engine.

  15. Off-Design Performance of a Multi-Stage Supersonic Turbine

    NASA Technical Reports Server (NTRS)

    Dorney, Daniel J.; Griffin, Lisa W.; Huber, Frank; Sondak, Douglas L.

    2003-01-01

    The drive towards high-work turbines has led to designs which can be compact, transonic, supersonic, counter rotating, or use a dense drive gas. These aggressive designs can lead to strong unsteady secondary flows and flow separation. The amplitude and extent of these unsteady flow phenomena can be amplified at off-design operating conditions. Pre-test off-design predictions have been performed for a new two-stage supersonic turbine design that is currently being tested in air. The simulations were performed using a three-dimensional unsteady Navier-Stokes analysis, and the predicted results have been compared with solutions from a validated meanline analysis.

  16. The Effect of Vane-Blade Spacing on Transonic Turbine Stage Performance

    NASA Technical Reports Server (NTRS)

    Kelecy, F. J.; Griffin, J. W.; Delaney, R. A.

    1996-01-01

    This paper presents the results of a computational study on the effect of axial spacing between the vane and blade rows of a transonic turbine stage. The study was performed on the mid-span section of a high-pressure turbine stage using a quasi-3D, unsteady Navier-Stokes solver that provides a fully interactive vane-blade unsteady flow solution. Three different cases were considered, corresponding to axial spacings of 20%, 40%, and 60% of the vane axial chord. The calculated vane and blade pressure distributions for the 40 percent case were found to compare favorably with experimental measurements acquired in a short-duration shock tunnel. In addition, the analysis shows a marked increase in the amplitude of the unsteady pressure fluctuations on the vane and blade surfaces as the spacing decreases. Time-averaged stage adiabatic efficiency predictions for each case are presented to show the effect of spacing on aerodynamic performance.

  17. Effects of Endwall Geometry and Stacking on Two-Stage Supersonic Turbine Performance

    NASA Technical Reports Server (NTRS)

    Dorney, Daniel J.; Griffin, Lisa W.; Huber, Frank W.; Sondak, Douglas L.; Turner, Jim (Technical Monitor)

    2002-01-01

    The drive towards high-work turbines has led to designs which can be compact, transonic, supersonic, counter rotating, or use a dense drive gas. These aggressive designs can lead to strong secondary flows and airfoil flow separation. In many cases the secondary and separated flows can be minimized by contouring the hub/shroud endwalls and/or modifying the airfoil stacking. In this study, three-dimensional unsteady Navier-Stokes simulations were performed to study three different endwall shapes between the first-stage vanes and rotors, as well as two different stackings for the first-stage vanes. The predicted results indicate that changing the stacking of the first-stage vanes can significantly impact endwall separation (and turbine performance) in regions where the endwall profile changes.

  18. Heat transfer and pressure measurements and comparison with prediction for the SSME two-stage turbine

    NASA Technical Reports Server (NTRS)

    Dunn, M. G.; Kim, J.

    1992-01-01

    Time averaged Stanton number and surface pressure distributions are reported for the first stage vane row, the first stage blade row, and the second stage vane row of the Rocketdyne Space Shuttle Main Engine (SSME) two-stage fuel-side turbine. Unsteady pressure envelope measurements for the first blade are also reported. These measurements were made at 10 percent, 50 percent, and 90 percent span on both the pressure and suction surfaces of the first stage components. Additional Stanton number measurements were made on the first stage blade platform, blade tip, and shroud, and at 50 percent span on the second vane. A shock tube was used as a short duration source of heated and pressurized air to which the turbine was subjected. Platinum thin film heat flux gages were used to obtain the heat flux measurements, while miniature silicon diaphragm flush-mounted pressure transducers were used to obtain the pressure measurements. The first stage vane Stanton number distributions are compared with predictions obtained using a version of STAN5 and quasi-3D Navier-Stokes solution. This same quasi-3D N-S code was also used to obtain predictions for the first blade and the second vane.

  19. Design and aerodynamic performance evaluation of a high-work mixed flow turbine stage

    NASA Technical Reports Server (NTRS)

    Neri, Remo N.; Elliott, Thomas J.; Marsh, David N.; Civinskas, Kestutis C.

    1994-01-01

    As axial and radial turbine designs have been pushed to their aerothermodynamic and mechanical limits, the mixed-flow turbine (MFT) concept has been projected to offer performance and durability improvements, especially when ceramic materials are considered. The objective of this NASA/U.S. Army sponsored mixed-flow turbine (AMFT) program was to determine the level of performance attainable with MFT technology within the mechanical constraints of 1997 projected ceramic material properties. The MFT geometry is similar to a radial turbine, exhibiting a large radius change from inlet to exit, but differing in that the inlet flowpath is not purely radial, nor axial, but mixed; it is the inlet geometry that gives rise to the name 'mixed-flow'. The 'mixed' orientation of the turbine inlet offers several advantages over radial designs by allowing a nonzero inlet blade angle yet maintaining radial-element blades. The oblique inlet not only improves the particle-impact survivability of the design, but improves the aerodynamic performance by reducing the incidence at the blade inlet. The difficulty, however, of using mixed-flow geometry lies in the scarcity of detailed data and documented design experience. This paper reports the design of a MFT stage designed with the intent to maximize aerodynamic performance by optimizing design parameters such as stage reaction, rotor incidence, flowpath shape, blade shape, vane geometry, and airfoil counts using 2-D, 3-D inviscid, and 3-D viscous computational fluid dynamics code. The aerodynamic optimization was accomplished while maintaining mechanical integrity with respect to vibration and stress levels in the rotor. A full-scale cold-flow rig test was performed with metallic hardware fabricated to the specifications of the hot ceramic geometry to evaluate the stage performance.

  20. The Attenuation of a Detonation Wave by an Aircraft Engine Axial Turbine Stage

    NASA Technical Reports Server (NTRS)

    VanZante, Dale; Envia, Edmane; Turner, Mark G.

    2007-01-01

    A Constant Volume Combustion Cycle Engine concept consisting of a Pulse Detonation Combustor (PDC) followed by a conventional axial turbine was simulated numerically to determine the attenuation and reflection of a notional PDC pulse by the turbine. The multi-stage, time-accurate, turbomachinery solver TURBO was used to perform the calculation. The solution domain consisted of one notional detonation tube coupled to 5 vane passages and 8 rotor passages representing 1/8th of the annulus. The detonation tube was implemented as an initial value problem with the thermodynamic state of the tube contents, when the detonation wave is about to exit, provided by a 1D code. Pressure time history data from the numerical simulation was compared to experimental data from a similar configuration to verify that the simulation is giving reasonable results. Analysis of the pressure data showed a spectrally averaged attenuation of about 15 dB across the turbine stage. An evaluation of turbine performance is also presented.

  1. A critical evaluation of a three-dimensional Navier-Stokes CFD as a tool to design supersonic turbine stages

    NASA Technical Reports Server (NTRS)

    Hah, C.; Kwon, O.; Shoemaker, M.

    1992-01-01

    Three-dimensional flow phenomena in a supersonic turbine blade row were studied numerically to evaluate CFD as a tool to design supersonic turbine stages. The details of the three-dimensional flow structure inside the supersonic turbine blade row and the overall aerodynamic performance at design and off-design conditions are analyzed and the results are compared between the experimental data and the numerical results.

  2. Simulation of a 3D unsteady flow in an axial turbine stage

    NASA Astrophysics Data System (ADS)

    Straka, Petr

    2012-04-01

    The contribution deals with a numerical simulation of an unsteady flow in an axial turbine stage. The solution is performed using an in-house numerical code developed in the Aeronautical and Test Institute, Plc. in Prague. The numerical code is based on a finite volume discretization of governing equations (Favre averaged Navier-Stokes equations) and a two-equations turbulence model. The temporal integration is based on the implicit second-order backward Euler formula, which is realized through the iteration process in dual time. The proposed numerical method is used for solution of the 3D, unsteady, viscous turbulent flow of a perfect gas in the axial turbine stage. The flow path consists of an input nozzle, stator blade-wheel, rotor blade-wheel, a shroud-seal gap and a diffuser. Attention is paid to the influence of a secondary flow structures, such as generated vortices and flow in shroud-seal gap.

  3. Experimental research of flow parameters on the last stage of the steam turbine 1090 MW

    NASA Astrophysics Data System (ADS)

    Sedlák, Kamil; Hoznedl, Michal; Bednář, Lukáš; Mrózek, Lukáš; Kalista, Robert

    2016-06-01

    This article deals with a brief description of measurement and evaluation of flow parameters at the output from the last stage of the low pressure steam turbine casing for the saturated steam with the nominal power 1090 MW. Measurement was carried out using a seven-hole pneumatic probe traversing along the length of the blade in several peripheral positions under nominal and selected partial modes. The result is knowledge of distribution of the static, dynamic and total pressure along the length of the blade and velocity distribution including their components. This information is the input data for determination of efficiency of the last stage, the loss coefficient of the diffuser and other significant parameters describing efficiency of selected parts of the steam turbine.

  4. Off-design performance of a single-stage transonic turbine

    SciTech Connect

    Woinowsky-Krieger, M.; Lavoie, J.P.; Vlasic, E.P.; Moustapha, S.H.

    1999-04-01

    This paper presents results of rig testing of a transonic, single-stage turbine at off-design conditions. Mapping of the 3.4 pressure ratio, 1.9 stage loading turbine ranged from 70 through 120% of design speed and 75 to 125% of design pressure ratio. Results show expansion efficiency dropping over 4% from 100 to 80% of design speed at design pressure ratio, while remaining within half a percent from 90 to 110% of design pressure ratio at design speed. Efficiency lapse rate from equivalent sea-level to cruise altitude Reynolds numbers at the design point was measured and found to be worth over 1.5%. Analyses of test results using a viscous three-dimensional solver showed very good agreement for the efficiency change with speed.

  5. Numerical analysis of the aeroelastic behaviour for the last turbine stage in 3D transonic flow

    NASA Astrophysics Data System (ADS)

    Gnesin, Vitaly; Kolodyazhnaya, Lyubov

    2004-11-01

    An understanding of the physics of the mutual interaction between gas flow and oscillating blades, and the development of predictive capabilities is essential for improving overall efficiency, durability and reliability. In this study presented the algorithm proposed involving the coupled solution of 3D unsteady flow through a turbine stage and dynamic problem for rotor blades motion by action of aerodynamic forces without separating outer and inner flow fluctuations. There has been performed the calculations for the last stage of the steam turbine under design and off-design regimes. It has investigated the mutual influence of both outer flow non-uniformity and blades oscillations. It has shown that amplitude-frequency spectrum of blade oscillations contains the high frequency harmonics, corresponding to rotor moving one stator blade pitch, and low frequency harmonics caused by blade oscillations and flow non-uniformity downstream from the blade row.

  6. Experimental Measurements and Analysis of Heat Transfer and Gas Dynamics in a Rotating Turbine Stage

    NASA Technical Reports Server (NTRS)

    Dunn, M. G.; Rae, W. J.; George, W. K.

    1985-01-01

    The life-cycle fatigue of a particular component of a high-pressure turbine stage is influenced by the local heat flux and the resulting metal temperature excursions experienced by this component during normal operation. Flow through a turbine stage is seldom uniform and is often influenced by non-uniform incoming gas streams that can result in locally high heat fluxes. In the case of the rotor blades passing through the nozzle guide vane wakes and passages, these local heat rates translate into local temperature fluctuations that will likely affect the fatigue life of the blade. In order to better understand the influence of the heat load on the component life, one would like to have both the local steady-state heat flux and the high-frequency component of the heat flux.

  7. Aeroloads and secondary flows in a transonic mixed flow turbine stage

    NASA Technical Reports Server (NTRS)

    Kirtley, K. R.; Beach, T. A.; Rogo, Cass

    1992-01-01

    A numerical simulation of a transonic mixed flow turbine stage has been carried out using an average passage Navier-Stokes analysis. The mixed flow turbine stage considered here consists of a transonic nozzle vane and a highly loaded rotor. The simulation was run at the design pressure ratio and is assessed by comparing results with those of an established throughflow design system. The three-dimensional aerodynamic loads are studied as well as the development and migration of secondary flows and their contribution to the total pressure loss. The numerical results indicate that strong passage vortices develop in the nozzle vane, mix out quickly, and have little impact on the rotor flow. The rotor is highly loaded near the leading edge. Within the rotor passage, strong spanwise flows and other secondary flows exist along with the tip leakage vortex. The rotor exit loss distribution is similar in character to that found in radial inflow turbines. The secondary flows and non-uniform work extraction also tend to significantly redistribute a non-uniform inlet total temperature profile by the exit of the stage.

  8. Performance Analysis of an Annular Diffuser Under the Influence of a Gas Turbine Stage Exit Flow

    NASA Astrophysics Data System (ADS)

    Blanco, Rafael Rodriguez

    In this investigation the performance of a gas turbine exhaust diffuser subject to the outlet flow conditions of a turbine stage is evaluated. Towards that goal, a fully three-dimensional computational analysis has been performed where several turbine stage-exhaust diffuser configurations have been studied: a turbine stage with a shrouded rotor coupled to a diffuser with increasing divergence angle in the diffuser, and a turbine stage with an unshrouded rotor was also considered for the exhaust diffuser performance analysis. The large load of this investigation was evaluated using a steady state numerical analysis utilizing the "mixing plane" algorithm between the rotating rotor and stationary stator and diffuser rows. Finally, an unsteady analysis is performed on a turbine stage with an unshrouded rotor coupled to an annular exhaust diffuser with an outer wall opening angle of 18°. It has been found that the over the tip leakage flow in the unshrouded rotor emerges as a swirling wall jet at the upper wall of the diffuser. When using the turbine with the shrouded rotor no wall jet was observed, making the flow at the entrance to the diffuser "quasi-uniform". The maximum opening angle of the diffuser upper wall achieved before the diffuser stalls was 12° with a static pressure recovery coefficient of Cp = 0.293. When the wall jet was observed, diffuser opening angles of 18° were possible with a static pressure recovery of Cp = 0.365. Consequently the wall jet energizes the diffuser upper wall boundary layer flow, allows for higher static pressure recovery levels and postpones diffuser stall. By altering the speed of the rotor the effect of the swirl in the turbine exit plane on the performance of the diffuser was explored. In the case where the wall jet was absent the diffuser recovers more pressure when the inlet is swirl-free. In this case the performance of the diffuser is independent on whether the turbine exit flow has co or counter swirl. In the presence of

  9. Numerical simulation of high-swirl flow in axial turbine stage

    NASA Astrophysics Data System (ADS)

    Straka, Petr

    2016-03-01

    This article deals with numerical modelling of flow in an axial turbine stage with prismatic blades which are not equipped with shroud. In this case flow through a radial gap above and below ends of blades leads to generation of strong secondary vortices which significantly affect an effciency of the stage. The main attention is paid to turbulence modelling. Besides a linear model based on Boussinesq approximation a nonlinear model based on higher order closure formula is used. Also an effect of a curvature correction is taken into account.

  10. Cold-air investigation of a 4 1/2 stage turbine with stage-loading factor of 4.66 and high specific work output. 2: Stage group performance

    NASA Technical Reports Server (NTRS)

    Whitney, W. J.; Behning, F. P.; Moffitt, T. P.; Hotz, G. M.

    1980-01-01

    The stage group performance of a 4 1/2 stage turbine with an average stage loading factor of 4.66 and high specific work output was determined in cold air at design equivalent speed. The four stage turbine configuration produced design equivalent work output with an efficiency of 0.856; a barely discernible difference from the 0.855 obtained for the complete 4 1/2 stage turbine in a previous investigation. The turbine was designed and the procedure embodied the following design features: (1) controlled vortex flow, (2) tailored radial work distribution, and (3) control of the location of the boundary-layer transition point on the airfoil suction surface. The efficiency forecast for the 4 1/2 stage turbine was 0.886, and the value predicted using a reference method was 0.862. The stage group performance results were used to determine the individual stage efficiencies for the condition at which design 4 1/2 stage work output was obtained. The efficiencies of stages one and four were about 0.020 lower than the predicted value, that of stage two was 0.014 lower, and that of stage three was about equal to the predicted value. Thus all the stages operated reasonably close to their expected performance levels, and the overall (4 1/2 stage) performance was not degraded by any particularly inefficient component.

  11. Design and experimental investigation of a single-stage turbine with a rotor entering relative Mach number of 2

    NASA Technical Reports Server (NTRS)

    Moffitt, Thomas P

    1958-01-01

    The design and experimental investigation of a single-stage supersonic turbine are presented herein. The turbine was designed for a rotor entering relative Mach number of 2. The maximum equivalent specific work output of the turbine at design speed and approximately design over-all pressure ratio was 32.9 BTU per pound at a static efficiency of 0.414. This static efficiency gave good verification to an independent reference that indicated theoretical static efficiencies for similar single-stage turbines within the range 0.40 to 0.45. An experimental ratio of effective rotor blade momentum thickness to mean camber length was determined to be 0.0014, which compares favorably with the results obtained from several transonic and subsonic turbines. The design procedure for this turbine would have been improved by allowing for more rotor losses by assuming a value of this momentum parameter comparable with those obtained from transonic turbines. Removing a large portion of the rotor suction surface enabled a lower static pressure to be felt at the stator exit, at the expense of higher rotor losses. The net result was an improvement in turbine work output of about 3 percent at design setting conditions. No problems associated with supersonic starting were encountered even under the worst conditions of turbine operation with respect to this problem.

  12. Comparison between measured turbine stage performance and the predicted performance using quasi-3D flow and boundary layer analyses

    NASA Technical Reports Server (NTRS)

    Boyle, R. J.; Haas, J. E.; Katsanis, T.

    1984-01-01

    A method for calculating turbine stage performance is described. The usefulness of the method is demonstrated by comparing measured and predicted efficiencies for nine different stages. Comparisons are made over a range of turbine pressure ratios and rotor speeds. A quasi-3D flow analysis is used to account for complex passage geometries. Boundary layer analyses are done to account for losses due to friction. Empirical loss models are used to account for incidence, secondary flow, disc windage, and clearance losses.

  13. Investigation of flow in axial turbine stage without shroud-seal

    NASA Astrophysics Data System (ADS)

    Straka, Petr; Němec, Martin; Jelínek, Thomáš

    2015-05-01

    This article deals with investigation of the influence of the radial gaps on the efficiency of the axial turbine stage. The investigation was carried out for the axial stage of the low-power turbine with the drum-type rotor without the shroud. In this configuration the flow through the radial gap under the hub-end of the stator blades and above the tip-end of the rotor blades leads to generation of the strong secondary flows, which decrease the efficiency of the stage. This problem was studied by experiment as well as by numerical modelling. The experiment was performed on the test rig equipped with the water brake dynamometer, torque meter and rotatable stator together with the linear probe manipulator. Numerical modelling was carried out for both the steady flow using the "mixing plane" interface and the unsteady flow using the "sliding mesh" interface between the stator and rotor wheels. The influence of the radial gap was studied in two configuration a) positive and b) negative overlapping of the tip-ends of the rotor blades. The efficiency of the axial stage in dependence on the expansion ratio, velocity ratio and the configuration as well as the details of the flow fields are presented in this paper.

  14. Modern technologies for rendering information support to cogeneration steam turbine units in their design and operation stages

    NASA Astrophysics Data System (ADS)

    Brezgin, V. I.; Brodov, Yu. M.; Chubarov, A. A.; Brezgin, D. V.

    2013-08-01

    Application of modern information technologies in different stages of the lifecycle of cogeneration turbines is considered as one of possible ways for improving their competitiveness. Specific features relating to rendering information support for steam turbine units during the periods of their design and operation, which are the main stages of their life cycle, are presented. Three-dimension modeling, adaptive, and parametric design technologies are applied in the equipment design stages. Information support technologies developed by the authors are applied during the operation stage. Information is integrated by using a product lifecycle management (PLM) system.

  15. Computational study of the effects of shroud geometric variation on turbine performance in a 1.5-stage high-loaded turbine

    NASA Astrophysics Data System (ADS)

    Jia, Wei; Liu, Huoxing

    2013-10-01

    Generally speaking, main flow path of gas turbine is assumed to be perfect for standard 3D computation. But in real engine, the turbine annulus geometry is not completely smooth for the presence of the shroud and associated cavity near the end wall. Besides, shroud leakage flow is one of the dominant sources of secondary flow in turbomachinery, which not only causes a deterioration of useful work but also a penalty on turbine efficiency. It has been found that neglect shroud leakage flow makes the computed velocity profiles and loss distribution significantly different to those measured. Even so, the influence of shroud leakage flow is seldom taken into consideration during the routine of turbine design due to insufficient understanding of its impact on end wall flows and turbine performance. In order to evaluate the impact of tip shroud geometry on turbine performance, a 3D computational investigation for 1.5-stage turbine with shrouded blades was performed in this paper. The following geometry parameters were varied respectively: Inlet cavity length and exit cavity length

  16. Development of a transonic front stage of an axial flow compressor for industrial gas turbines

    SciTech Connect

    Katoh, Y.; Ishii, H.; Tsuda, Y.; Yanagida, M. . Mechanical Engineering Research Lab.); Kashiwabara, Y. . Dept. of Mechanical Systems Engineering)

    1994-10-01

    This paper describes the aerodynamic blade design of a highly loaded three-stage compressor, which is a model compressor for the front stage of an industrial gas turbine. Test results are presented that confirm design performance. Some surge and rotating stall measurement results are also discussed. The first stator blade in this test compressor operates in the high subsonic range at the inlet. To reduce the pressure loss due to blade surface shock waves, a shock-free airfoil is designed to replace the first stator blade in an NACA-65 airfoil in a three-stage compressor. Comparison of the performance of both blades shows that the shock-free airfoil blade reduces pressure loss. This paper also presents some experimental results for MCA (multicircular arc) airfoils, which are used for first rotor blades.

  17. Evaluation of Water Injection Effect on NO(x) Formation for a Staged Gas Turbine Combustor

    NASA Technical Reports Server (NTRS)

    Fan, L.; Yang, S. L.; Kundu, K. P.

    1996-01-01

    NO(x) emission control by water injection on a staged turbine combustor (STC) was modeled using the KIVA-2 code with modification. Water is injected into the rich-burn combustion zone of the combustor by a single nozzle. Parametric study for different water injection patterns was performed. Results show NO(x) emission will decrease after water being injected. Water nozzle location also has significant effect for NO formation and fuel ignition. The chemical kinetic model is also sensitive to the excess water. Through this study, a better understanding of the physics and chemical kinetics is obtained, this will enhance the STC design process.

  18. Influence of balancing holes and disc sealing in turbine stages on thermodynamic efficiency and rotor forces

    NASA Astrophysics Data System (ADS)

    Sláma, Václav

    2016-03-01

    This paper deals with CFD analysis of a particular turbine impulse stage including the surrounding parts such as diaphragm seals, shroud seals and a disc axial gap, where balancing holes and a disc sealing is designed. The aim is to investigate effects on efficiency and axial forces by evaluation of a pressure distribution on the rotor disc and respective mass flow balances. As a result of this, the possible methodology of design optimization could be found. The other part of the project is to find the way for a more exact preliminary computation which is essential for increasing efficiency and the reduction of the axial forces.

  19. Instabilities on Nozzle-Wake Loads due to Axial Clearance and Throat Variations in a First Stage Turbine

    NASA Astrophysics Data System (ADS)

    García, J. C.; Sierra, F. Z.

    2013-06-01

    A study of flow unsteadiness in a high pressure first stage turbine is presented. The study is based on numerical simulations of nozzle wake using a relative reference frame sliding mesh. Pressure and loads on first stage blades needed for stage efficiency calculation in turbine design are discussed. Excessive wear occurring at engine operating conditions affects the distance between rotating and non-rotating elements by varying throat size and axial clearance. Consequently, force unsteadiness produces changes on cyclic loads amplitude, which modifies the work produced by first stage. Compared against design, increments of throat minimum area lead to maximum total force, while throat area reductions increased pressure unsteadiness across the axial clearance. Also, the amplitude of load on blade increases as axial clearance length reduces. Harmonics of force on blade were used to calibrate a useful life prediction tool for turbine components through FFT analysis.

  20. Cold-air investigation of a 31/2-stage fan-drive turbine with a stage loading factor of 4 designed for an integral lift engine. 2: Performance of 2-, 3- and 3 1/2-stage configurations

    NASA Technical Reports Server (NTRS)

    Whitney, W. J.

    1977-01-01

    The stage work distribution among the three stages was very close to the design value. The specific work output-mass flow characteristics of the three stages were closely matched. The efficiency of the 3 1/2 stage turbine at design specific work output and design speed was within 0.008 of the estimated value, and this agreement was felt to demonstrate the adequacy of the prediction method in the high stage loading factor regime.

  1. The Epilepsy Foundation's 4th Biennial Epilepsy Pipeline Update Conference.

    PubMed

    French, Jacqueline A; Schachter, Steven C; Sirven, Joseph; Porter, Roger

    2015-05-01

    On June 5 and 6, 2014, the Epilepsy Foundation held its 4th Biennial Epilepsy Pipeline Update Conference, an initiative of the Epilepsy Therapy Project, which showcased the most promising epilepsy innovations from health-care companies and academic laboratories dedicated to pioneering and advancing drugs, biologics, technologies, devices, and diagnostics for epilepsy. Speakers and attendees included emerging biotech and medical technology companies, major pharmaceutical and device companies, as well as investigators and innovators at the cutting-edge of epilepsy. The program included panel discussions on collaboration between small and large companies, how to get products in need of funding to the marketplace, who is currently funding epilepsy and CNS innovation, and how the NIH facilitates early-stage drug development. Finally, the conference featured the third annual "Shark Tank" competition. The presentations are summarized in this paper, which is followed by a compilation of the meeting poster abstracts. PMID:25922152

  2. Control valves and cascades for the first stages of turbines with ultrasupercritical steam parameters

    NASA Astrophysics Data System (ADS)

    Zaryankin, A. E.; Rogalev, N. D.; Rogalev, A. N.; Garanin, I. V.; Osipov, S. K.; Grigoriev, E. Yu.

    2016-06-01

    This paper considers the problems that will unavoidably be encountered in the creation of new-generation turbines operated at ultrasupercritical initial steam parameters, namely, the development of new control and shutoff valves, the reduction of end energy losses in blade cascades and steam leaks in high-pressure cylinders (HPCs), the elimination of effect produced by regenerative steam bleedoffs on the afterextraction stage, the cooling of a blade cascade, etc. Some possible solutions are given for the two first of the listed problems. The conclusion about the need for the transition to new-generation control valves in the development of new advanced steam turbines with ultrasupercritical initial steam parameters has been made. From the viewpoint of their design, the considered new-generation valves differ from the known contemporary constructions by a shaped axially symmetric confusor channel and perforated zones on the streamlined spool surface and the inlet diffuser saddle part. The analysis of the vibration behavior of new-generation valves has demonstrated a decrease in the dynamic loads acting on their stems. To reduce the end energy losses in nozzle or blade cascades with small aspect ratios, it is proposed to use finned shrouds in the interblade channels. The cross section of fins has a triangular profile, and their height must be comparable with the thickness of the boundary layer in the outlet cross section of a cascade and, provisionally, be smaller than 8% of the cascade chord.

  3. Unsteady Aero Computation of a 1 1/2 Stage Large Scale Rotating Turbine

    NASA Technical Reports Server (NTRS)

    To, Wai-Ming

    2012-01-01

    This report is the documentation of the work performed for the Subsonic Rotary Wing Project under the NASA s Fundamental Aeronautics Program. It was funded through Task Number NNC10E420T under GESS-2 Contract NNC06BA07B in the period of 10/1/2010 to 8/31/2011. The objective of the task is to provide support for the development of variable speed power turbine technology through application of computational fluid dynamics analyses. This includes work elements in mesh generation, multistage URANS simulations, and post-processing of the simulation results for comparison with the experimental data. The unsteady CFD calculations were performed with the TURBO code running in multistage single passage (phase lag) mode. Meshes for the blade rows were generated with the NASA developed TCGRID code. The CFD performance is assessed and improvements are recommended for future research in this area. For that, the United Technologies Research Center's 1 1/2 stage Large Scale Rotating Turbine was selected to be the candidate engine configuration for this computational effort because of the completeness and availability of the data.

  4. Effects of Hot Streak Shape on Rotor Heating in a High-Subsonic Single-Stage Turbine

    NASA Technical Reports Server (NTRS)

    Dorney, Daniel J.; Gundy-Burlet, Karen L.; Norvig, Peter (Technical Monitor)

    1999-01-01

    Experimental data have shown that combustor temperature non-uniformities can lead to the excessive heating of first-stage rotor blades in turbines. This heating of the rotor blades can lead to thermal fatigue and degrade turbine performance. The results of recent studies have shown that variations in the circumferential location (clocking) of the hot streak relative to the first-stage vane airfoils can be used to minimize the adverse effects of the hot streak. The effects of the hot streak/airfoil count ratio on the heating patterns of turbine airfoils have also been evaluated. In the present investigation, three-dimensional unsteady Navier-Stokes simulations have been performed for a single-stage high-pressure turbine operating in high subsonic flow. In addition to a simulation of the baseline turbine, simulations have been performed for circular and elliptical hot streaks of varying sizes in an effort to represent different combustor designs. The predicted results for the baseline simulation show good agreement with the available experimental data. The results of the hot streak simulations indicate: that a) elliptical hot streaks mix more rapidly than circular hot streaks, b) for small hot streak surface area the average rotor temperature is not a strong function of hot streak temperature ratio or shape, and c) hot streaks with larger surface area interact with the secondary flows at the rotor hub endwall, generating an additional high temperature region.

  5. Imaging of Combustion Species in a Radially-Staged Gas Turbine Combustor

    NASA Technical Reports Server (NTRS)

    Locke, Randy J.; Hicks, Yolanda R.; Anderson, Robert C.; Ockunzzi, Kelly A.; Schock, Harold J.

    1996-01-01

    Plannar laser-induced fluorescence (PLIF) is used to characterize the complex flowfield of a unique fuel-lean, radially-staged high pressure gas turbine combustor. PLIF images of OH are presented for two fuel injector configurations. PLIF images of NO, the first acquired at these conditions, are presented and compared with gas sample extraction probe measurements. Flow field imaging of nascent C2 chemiluminescence is also investigated. An examination is made of the interaction between adjoining lean premixed prevaporized (LPP) injectors. Fluorescence interferences at conditions approaching 2000 K and 15 atm are observed and attributed to polycyclic aromatic hydrocarbon (PAH) emissions. All images are acquired at a position immediately downstream of the fuel injectors with combustor burning JP-5 fuel.

  6. Unsteady hot streak simulation through a 1-1/2 stage turbine engine

    NASA Astrophysics Data System (ADS)

    Takahashi, R. K.; Ni, R. H.

    1991-06-01

    The temperature redistribution process in a 1-1/2 stage turbine (consisting of a first stator, first rotor, and second stator) was analyzed using an unsteady 3D Euler flow solver. The study concentrated on tracking a hot streak from the inlet of the first stator to the exit of the second stator. The redistribution of the hot streak in the second stator passage was very different from that in the rotor passage, with no signs of temperature segregation in the second stator passage, and with rotor-generated vortices which persist through the second stator passage and partake in redistributing the remains of the hot streak. The unsteady code predicts different time-averaged temperatures and secondary flow in the second stator passage than in the steady multistage code, although the steady code may be sufficient for predicting time-averaged pressure loadings on both rotor and second stator airfoils, and time-averaged secondary flow vortices in the rotor passage.

  7. Imaging of Combustion Species in a Radially-Staged Gas Turbine Combustor

    NASA Technical Reports Server (NTRS)

    Locke, Randy J.; Hicks, Yolanda R.; Anderson, Robert C.; Ockunzzi, Kelly A.; Schock, Harold J.

    1996-01-01

    Planar laser-induced fluorescence (PLIF) is used to characterize the complex flowfield of a unique fuel-lean, radially-staged, high pressure gas turbine combustor. PLIF images of OH are presented for two fuel injector configurations. PLIF images of NO, the first acquired at these conditions, are presented and compared with gas sample extraction probe measurements. Flow field imaging of nascent C2 chemiluminescence is also investigated. An examination is made of the interaction between adjoining lean premixed prevaporized (LPP) injectors. Fluorescence interferences at conditions approaching 2000 K and 15 atm are observed and attributed to polycyclic aromatic hydrocarbon (PAH) emissions. All images are acquired at a position immediately downstream of the fuel injectors with the combustor burning JP-5 fuel.

  8. A shape modification of the balancing slot of the impulse turbine stage with the drum rotor arrangement

    NASA Astrophysics Data System (ADS)

    Yun, Kukchol; Tajč, L.; Kolovratník, M.

    2016-03-01

    At the previous conference in Český Krumlov it was presented how the balancing slots may influence the efficiency of the impulse turbine stage with the drum rotor arrangement. A few options for shape modification of the balancing slot were also suggested. Implementation of the balancing slots and their possible modifications are subject to various design and technological limitations. During the consultation with the turbine designers and technologists, we were able to determine the modification of the balancing slot which, in terms of their design and production technology, will be the most simple and feasible. It is predicted that the suggested shape modification of the balancing slot will improve the efficiency of the turbine stage. This prediction is then supported by CFD simulations.

  9. Design and Experimental Investigation of a Single-stage Turbine with a Downstream Stator

    NASA Technical Reports Server (NTRS)

    Plohr, Henry W; Holeski, Donald E; Forrette, Robert E

    1957-01-01

    The high-work-output turbine had an experimental efficiency of 0.830 at the design point and a maximum efficiency of 0.857. The downstream stator was effective in providing axial flow out of the turbine for almost the whole range of turbine operation.

  10. Comprehensive Structural Dynamic Analysis of the SSME/AT Fuel Pump First-Stage Turbine Blade

    NASA Technical Reports Server (NTRS)

    Brown, A. M.

    1998-01-01

    A detailed structural dynamic analysis of the Pratt & Whitney high-pressure fuel pump first-stage turbine blades has been performed to identify the cause of the tip cracking found in the turbomachinery in November 1997. The analysis was also used to help evaluate potential fixes for the problem. Many of the methods available in structural dynamics were applied, including modal displacement and stress analysis, frequency and transient response to tip loading from the first-stage Blade Outer Gas Seals (BOGS), fourier analysis, and shock spectra analysis of the transient response. The primary findings were that the BOGS tip loading is impulsive in nature, thereby exciting many modes of the blade that exhibit high stress at the tip cracking location. Therefore, a proposed BOGS count change would not help the situation because a clearly identifiable resonance situation does not exist. The recommendations for the resolution of the problem are to maintain the existing BOGS count, eliminate the stress concentration in the blade due to its geometric design, and reduce the applied load on the blade by adding shiplaps in the BOGS.

  11. Analysis of Unsteady Tip and Endwall Heat Transfer in a Highly Loaded Transonic Turbine Stage

    NASA Technical Reports Server (NTRS)

    Shyam, Vikram; Ameri, Ali; Chen, Jen-Ping

    2010-01-01

    In a previous study, vane-rotor shock interactions and heat transfer on the rotor blade of a highly loaded transonic turbine stage were simulated. The geometry consists of a high pressure turbine vane and downstream rotor blade. This study focuses on the physics of flow and heat transfer in the rotor tip, casing and hub regions. The simulation was performed using the Unsteady Reynolds-Averaged Navier-Stokes (URANS) code MSU-TURBO. A low Reynolds number k-epsilon model was utilized to model turbulence. The rotor blade in question has a tip gap height of 2.1 percent of the blade height. The Reynolds number of the flow is approximately 3x10(exp 6) per meter. Unsteadiness was observed at the tip surface that results in intermittent "hot spots". It is demonstrated that unsteadiness in the tip gap is governed by inviscid effects due to high speed flow and is not strongly dependent on pressure ratio across the tip gap contrary to published observations that have primarily dealt with subsonic tip flows. The high relative Mach numbers in the tip gap lead to a choking of the leakage flow that translates to a relative attenuation of losses at higher loading. The efficacy of new tip geometry is discussed to minimize heat flux at the tip while maintaining choked conditions. In addition, an explanation is provided that shows the mechanism behind the rise in stagnation temperature on the casing to values above the absolute total temperature at the inlet. It is concluded that even in steady mode, work transfer to the near tip fluid occurs due to relative shearing by the casing. This is believed to be the first such explanation of the work transfer phenomenon in the open literature. The difference in pattern between steady and time-averaged heat flux at the hub is also explained.

  12. Effects of Tip Clearance and Casing Recess on Heat Transfer and Stage Efficiency in Axial Turbines

    NASA Technical Reports Server (NTRS)

    Ameri, A. A.; Steinthorsson, E.; Rigby, David L.

    1998-01-01

    Calculations were performed to assess the effect of the tip leakage flow on the rate of heat transfer to blade, blade tip and casing. The effect on exit angle and efficiency was also examined. Passage geometries with and without casing recess were considered. The geometry and the flow conditions of the GE-E 3 first stage turbine, which represents a modem gas turbine blade were used for the analysis. Clearance heights of 0%, 1%, 1.5% and 3% of the passage height were considered. For the two largest clearance heights considered, different recess depths were studied. There was an increase in the thermal load on all the heat transfer surfaces considered due to enlargement of the clearance gap. Introduction of recessed casing resulted in a drop in the rate of heat transfer on the pressure side but the picture on the suction side was found to be more complex for the smaller tip clearance height considered. For the larger tip clearance height the effect of casing recess was an orderly reduction in the suction side heat transfer as the casing recess height was increased. There was a marked reduction of heat load and peak values on the blade tip upon introduction of casing recess, however only a small reduction was observed on the casing itself. It was reconfirmed that there is a linear relationship between the efficiency and the tip gap height. It was also observed that the recess casing has a small effect on the efficiency but can have a moderating effect on the flow underturning at smaller tip clearances.

  13. A CFD Analysis of Steam Flow in the Two-Stage Experimental Impulse Turbine with the Drum Rotor Arrangement

    NASA Astrophysics Data System (ADS)

    Yun, Kukchol; Tajč, L.; Kolovratník, M.

    2016-03-01

    The aim of the paper is to present the CFD analysis of the steam flow in the two-stage turbine with a drum rotor and balancing slots. The balancing slot is a part of every rotor blade and it can be used in the same way as balancing holes on the classical rotor disc. The main attention is focused on the explanation of the experimental knowledge about the impact of the slot covering and uncovering on the efficiency of the individual stages and the entire turbine. The pressure and temperature fields and the mass steam flows through the shaft seals, slots and blade cascades are calculated. The impact of the balancing slots covering or uncovering on the reaction and velocity conditions in the stages is evaluated according to the pressure and temperature fields. We have also concentrated on the analysis of the seal steam flow through the balancing slots. The optimized design of the balancing slots has been suggested.

  14. Experimental study of a staged combustion system for stationary gas turbine applications

    NASA Astrophysics Data System (ADS)

    Lamont, Warren G.

    Two optically accessible experimental test rigs were designed and constructed to investigate a staged or distributed combustion system for stationary gas turbine applications. The test rigs were fuelled with natural gas and featured two combustion zones: the main combustion zone (MCZ) and the secondary combustion zone (SCZ). The MCZ is a swirl stabilized dump combustor and the SCZ, which is axially downstream from the MCZ, is formed by a transverse jet injecting a premixed fuel/air mixture into the vitiated stream. After installing and commissioning the test rig, an emission survey was conducted to investigate the SCZ conditions, equivalence ratio and momentum ratio, that produce low NOx emissions and give a higher temperature rise before a simulated high pressure turbine than firing only the MCZ. The emission survey found several operating conditions that show the benefit of combustion staging. These beneficial conditions had an SCZ equivalence ratio between 0.41 and 1.12. The data from the emission survey was then used to create an artificial neural network (ANN). The ANN used a multi-layer feed-forward network architecture and was trained with experimental data using the backpropagation training algorithm. The ANN was then used to create performance maps and optimum operational regions were sought. Lastly, optical diagnostics were used to obtain information on the nature of the SCZ reactive jet. The diagnostics included high speed CH* chemiluminescence, OH planar laser induced fluorescence (PLIF) and dual-pump coherent anti-Stokes Raman scattering (CARS). The chemiluminescence and PLIF were used to qualitatively determine the size and shape of the transverse jet reaction zone. Dual-pump CARS was used to quantitatively determine the temperature and H2/N2 concentration ratio profile at the mid-plane of the transverse jet. Dual-pump CARS data was collected for four operating conditions but only one is presented in this dissertation. For the condition presented, the

  15. A numerical modelling of stator rotor interaction in a turbine stage with oscillating blades

    NASA Astrophysics Data System (ADS)

    Gnesin, V. I.; Kolodyazhnaya, L. V.; Rzadkowski, R.

    2004-11-01

    In real flows unsteady phenomena connected with the circumferential non-uniformity of the main flow and those caused by oscillations of blades are observed only jointly. An understanding of the physics of the mutual interaction between gas flow and oscillating blades and the development of predictive capabilities are essential for improved overall efficiency, durability and reliability. In the study presented, the algorithm proposed involves the coupled solution of 3D unsteady flow through a turbine stage and the dynamics problem for rotor-blade motion by the action of aerodynamic forces, without separating the outer and inner flow fluctuations. The partially integrated method involves the solution of the fluid and structural equations separately, but information is exchanged at each time step, so that solution from one domain is used as a boundary condition for the other domain. 3-D transonic gas flow through the stator and rotor blades in relative motion with periodicity on the whole annulus is described by the unsteady Euler conservation equations, which are integrated using the explicit monotonous finite volume difference scheme of Godunov Kolgan. The structural analysis uses the modal approach and a 3-D finite element model of a blade. The blade motion is assumed to be constituted as a linear combination of the first natural modes of blade oscillations, with the modal coefficients depending on time. A calculation has been done for the last stage of the steam turbine, under design and off-design regimes. The numerical results for unsteady aerodynamic forces due to stator rotor interaction are compared with results obtained while taking into account blade oscillations. The mutual influence of both outer flow non-uniformity and blade oscillations has been investigated. It is shown that the amplitude-frequency spectrum of blade oscillations contains the high-frequency harmonics, corresponding to the rotor moving past one stator blade pitch, and low

  16. Influence of Intercept Valves on Control of Multiple Stages Steam Turbines During the Switching into the Island Operation

    NASA Astrophysics Data System (ADS)

    Laštovka, Ladislav; Hejtmánková, Pavla

    2015-03-01

    This paper presents control of a multiple stages steam turbine which is switched into the island operation. The frequency in an electrical grid is stated on nominal value which is in UCTE grid 50 Hz. When deviation of frequency is higher then 0.2 Hz, the switching of particular steam units into the island operation is only the chance how to maintain the supply of, at least, some small grids. The other possibility how to keep power units in operation, to be prepared for the next synchronization to the grid, is to switch them to operation status in which they supply only their self-consumption. This change of the operating state is the most dynamic load change for the control system of the unit. The multiple stages turbines are equipped with high pressure hydraulic valves for steam turbine governing. Influence of the intercept valve on steam turbine control during the switching process into the island operation is examined in Matlab Simuling software.

  17. Effect of end-wall boundary layer and inlet turbulence on the flow field structures in the turbine stage

    NASA Astrophysics Data System (ADS)

    Jelinek, Tomas; Straka, Petr; Uruba, Vaclav

    2016-06-01

    The article deals with the effects of the inlet flow parameters on the flow field structures in axial turbine stage. The experiment was performed on the axial turbine stage rig with an air as a working medium. The variable inlet channel produced the different inlet turbulence intensity and different inlet end-wall boundary layer thickness, resp. different inlet velocity distribution was applied. The turbulence was measured by CTA probes. The measured parameters of the inlet velocity distribution and turbulence intensity across the inlet channel height are presented. Based on the experimental inlet parameters the CFD fully turbulent calculation of the flow field was made. The differences in outlet kinetic energy loss, outlet vane angle and the turbulence distribution in the vane mid-span section are depicted. Changes of secondary flow structures with the different inlet end-wall boundary layer thickness were observed on the vane outlet parameters.

  18. Turbine-stage heat transfer - Comparison of short-duration measurements with state-of-the-art predictions

    NASA Technical Reports Server (NTRS)

    Rae, W. J.; Taulbee, D. B.; Civinkas, K. C.; Dunn, M. G.

    1986-01-01

    Comparisons are made between calculated and measured heat-transfer distributions on the midspan locations of the stators and rotors of two turbine stages. The agreement is generally good, except in regions near the leading edge, and is better for blading of higher aspect ratio. It is suggested that the discrepancies near the leading edge are caused by free-stream turbulence, and attempts to improve the modeling of this factor show improved agreement.

  19. Time-averaged heat transfer and pressure measurements and comparison with prediction for a two-stage turbine

    NASA Technical Reports Server (NTRS)

    Dunn, M. G.; Kim, J.; Civinskas, K. C.; Boyle, R. J.

    1992-01-01

    Time-averaged Stanton number and surface-pressure distributions are reported for the first-stage vane row and the first-stage blade row of the Rocketdyne Space Shuttle Main Engine two-stage fuel-side turbine. These measurements were made at 10 percent, 50 percent, and 90 percent span on both the pressure and suction surfaces of the component. Stanton-number distributions are also reported for the second-stage vane at 50 percent span. A shock tube is used as a short-duration source of heated and pressurized air to which the turbine is subjected. Platinum thin-film gages are used to obtain the heat-flux measurements and miniature silicone-diaphragm pressure transducers are used to obtain the surface pressure measurements. The first-stage vane Stanton number distributions are compared with predictions obtained using a quasi-3D Navier-Stokes solution and a version of STAN5. This same N-S technique was also used to obtain predictions for the first blade and the second vane.

  20. Design of a 4 1/2 stage turbine with a stage loading factor of 4.66 and high specific work output

    NASA Technical Reports Server (NTRS)

    Webster, P. F.

    1976-01-01

    The aerodynamic design of a highly loaded multistage fan drive turbine is discussed. Turbine flowpath and airfoil sections are presented along with respective pressure and velocity distributions. Vibrational modes are identified in the expected turbine operating range.

  1. Erosion study of final stage blading of low pressure steam turbines

    NASA Astrophysics Data System (ADS)

    Dehouve, J.; Nardin, P.; Zeghmati, M.

    1999-04-01

    In order to increase our knowledge of erosion phenomena, the Steam Turbine Groupe (STG) of ALSTOM has been using an erosion test facility in the C.R.T.V. (Centre de Recherche Turbines à Vapeur). This test facility simulates erosion in low pressure steam turbine cylinders in order to compare the erosion resistance of various blade materials (12% chromium steel, titanium alloys, etc.) and their protection (superficial hardening, coatings, etc.). This test facility also allows us to understand the mechanism causing damage at a macroscopic level (impact energy of the droplets and the loss of eroded volume) and at a microscopic level (residual stress and metallurgic analysis) and therefore to determine an evolution law of material surface damage. In this paper, the behaviour of the materials (12% chromium steel and titanium alloys), which has been analysed by image production measurement methods, will be presented according to different impact velocities.

  2. Investigation of Turbines Suitable for Use in a Turbojet Engine with High Compressor Pressure Ratio and Low Compressor-tip Speed VI: Experimental Performance of Two-stage Turbine

    NASA Technical Reports Server (NTRS)

    Davison, Elmer H; Schum, Harold J; Petrash, Donald A

    1956-01-01

    The brake internal efficiency of the highly loaded two-stage turbine was 0.79 equivalent design work and speed. The maximum brake internal efficiency was 0.84. A radial survey revealed these major defects: (1) the first-rotor throat area was too large, and a large area of underturned flow existed near the tip;(2) considerable underturning existed at the second-stator outlet; and (3) tangential components of velocity at the turbine outlet amounted to 2.5 points in turbine efficiency.

  3. Phase and time-resolved measurements of unsteady heat transfer and pressure in a full-stage rotating turbine

    NASA Technical Reports Server (NTRS)

    Dunn, M. G.

    1989-01-01

    This paper presents detailed phase-resolved heat-flux data obtained on rotor blades and a comparison of simultaneously obtained time-resolved heat-flux and static pressure data obtained on the stationary shroud of a Garrett TFE 731-2 HP full-stage rotating turbine. A shock tube is used to generate a short-duration source of heated and pressurized air and platinum thin-film gages are used to obtain heat-flux measurements. Blade results are presented at several selected blade locations. Shroud surface pressure and heat-flux time histories are presented for comparable locations relative to the blade position.

  4. Gas Turbine Engine Staged Fuel Injection Using Adjacent Bluff Body and Swirler Fuel Injectors

    NASA Technical Reports Server (NTRS)

    Snyder, Timothy S. (Inventor)

    2015-01-01

    A fuel injection array for a gas turbine engine includes a plurality of bluff body injectors and a plurality of swirler injectors. A control operates the plurality of bluff body injectors and swirler injectors such that bluff body injectors are utilized without all of the swirler injectors at least at low power operation. The swirler injectors are utilized at higher power operation.

  5. Increasing reliability of system water heaters for steam-turbine installations at the design stage

    NASA Astrophysics Data System (ADS)

    Brezgin, V. I.; Brodov, Yu. M.; Brezgin, D. V.

    2015-12-01

    A system for designing water heaters of steam-turbine installations based on uniting standards, reference information, and some numerical procedures with design procedures via wide use of parameterization is considered. The developed design system is based on extensive application of modern information technologies.

  6. Optimization of the mean radius flow path of a multi-stage steam turbine with evolution algorithms

    NASA Astrophysics Data System (ADS)

    Huttunen, Jukka; Larjola, Jaakko; Turunen-Saaresti, Teemu; Backman, Jari

    2011-08-01

    A prototype model of the mean radius flow path of a four-stage, high speed 1 MWe axial steam turbine was optimized by using evolution algorithms, DE (differential evolution) algorithm in this case. Also the cost-benefits of the optimization were inspected. The optimization was successfully performed but the accuracy of the optimization was slightly less than hoped when compared to the control modeling executed with the CFD (computational fluid dynamics). The mentioned inaccuracy could have been hardly avoided because of problems with an initial presumption involving semi-empiric calculations and of the uncertainty concerning the absolute areas of qualification of the functions. This kind of algebraic modeling was essential for the success of the optimization because e.g. CFD-calculation could not have been done on each step of the optimization. During the optimization some problems occurred with the adequacy of the computer capacity and with finding a suitable solution that would keep the algorithms within mathematically allowable boundaries but would not restrict the progress of the optimization too much. The rest of the problems were due to the novelty of the application and problems with preciseness when handling the areas of qualification of the functions. Although the accuracy of the optimization results was not exactly in accordance with the objective, they did have a favorable effect on the designing of the turbine. The optimization executed with the help of the DE-algorithm got at least about 3.5 % more power out of the turbine which means about 150 000 € cost-benefit per turbine in the form of additional electricity capacity.

  7. Numerical modelling of the aeroelastic behaviour and variable loads for the turbine stage in 3D transonic flow

    NASA Astrophysics Data System (ADS)

    Gnesin, V. I.; Kolodyazhnaya, L. V.; Rzadkowski, R.

    2005-09-01

    In this study presented the algorithm proposed involves the coupled solution of 3-D unsteady flow through a turbine stage and the dynamics problem for rotor-blade motion by the action of aerodynamic forces, without separating the outer and inner flow fluctuations. The partially integrated method involves the solution of the fluid and structural equations separately, but information is exchanged at each time step, so that solution from one domain is used as a boundary condition for the other domain. 3-D transonic gas flow through the stator and rotor blades in relative motion with periodicity on the whole annulus is described by the unsteady Euler conservation equations, which are integrated using the explicit monotonous finite-volume difference scheme of Godunov-Kolgan. The structural analysis uses the modal approach and a 3-D finite element model of a blade. A calculation has been done for the last stage of the steam turbine, under design and off-design regimes. It is shown that the amplitude-frequency spectrum of blade oscillations contains the high frequency harmonics, corresponding to the rotor moving past one stator blade pitch, and low frequency harmonics caused by blade oscillations and flow nonuniformity downstream from the blade row; moreover, the spectrum involves the harmonics which are not multiples of the rotation frequency.

  8. Flow Field in a Single-Stage Model Air Turbine With Seal Rings and Pre-Swirled Purge Flow

    NASA Astrophysics Data System (ADS)

    Dunn, Dennis M.

    Modern gas turbines operate at high mainstream gas temperatures and pressures, which requires high durability materials. A method of preventing these hot gases from leaking into the turbine cavities is essential for improved reliability and cost reduction. Utilizing bleed-off air from the compressor to cool internal components has been a common solution, but at the cost of decreasing turbine performance. The present work thoroughly describes the complex flow field between the mainstream gas and a single rotor-stator disk cavity, and mechanisms of mainstream gas ingestion. A combined approach of experimental measurement and numerical simulation are performed on the flow in a single-stage model gas turbine. Mainstream gas ingestion into the cavity is further reduced by utilizing two axially overlapping seal rings, one on the rotor disk and the other on the stator wall. Secondary purge air is injected into the rotor-stator cavity pre-swirled through the stator radially inboard of the two seal rings. Flow field predictions from the simulations are compared against experimental measurements of static pressure, velocity, and tracer gas concentration acquired in a nearly identical model configuration. Operational conditions were performed with a main airflow Reynolds number of 7.86e4 and a rotor disk speed of 3000rpm. Additionally the rotational Reynolds number was 8.74 e5 with a purge air nondimensional flow rate cw=4806. The simulation models a 1/14 rotationally periodic sector of the turbine rig, consisting of four rotor blades and four stator vanes. Gambit was used to generate the three-dimensional unstructured grids ranging from 10 to 20 million cells. Effects of turbulence were modeled using the single-equation Spalart-Allmaras as well as the realizable k-epsilon models. Computations were performed using FLUENT for both a simplified steady-state and subsequent time-dependent formulation. Simulation results show larger scale structures across the entire sector angle

  9. 4th International Plant Biomechanics Conference Proceedings (Abstracts)

    SciTech Connect

    Frank W. Telewski; Lothar H. Koehler; Frank W. Ewers

    2003-07-20

    The 4th International Plant Biomechanics Conference facilitated an interdisciplinary exchange between scientists, engineers, and educators addressing the major questions encountered in the field of Plant Biomechanics. Subjects covered by the conference include: Evolution; Ecology; Mechanoreception; Cell Walls; Genetic Modification; Applied Biomechanics of Whole Plants, Plant Products, Fibers & Composites; Fluid Dynamics; Wood & Trees; Fracture Mechanics; Xylem Pressure & Water Transport; Modeling; and Introducing Plant Biomechanics in Secondary School Education.

  10. Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine. Part 1; Experimental Results

    NASA Technical Reports Server (NTRS)

    Bunker, Ronald S.; Bailey, Jeremy C.; Ameri, Ali A.

    1999-01-01

    A combined computational and experimental study has been performed to investigate the detailed distribution of convective heat transfer coefficients on the first stage blade tip surface for a geometry typical of large power generation turbines(>100MW). This paper is concerned with the design and execution of the experimental portion of the study. A stationary blade cascade experiment has been run consisting of three airfoils, the center airfoil having a variable tip gap clearance. The airfoil models the aerodynamic tip section of a high pressure turbine blade with inlet Mach number of 0.30, exit Mach number of 0.75, pressure ratio of 1.45, exit Reynolds number based on axial chord of 2.57 x 10(exp 6), and total turning of about 110 degrees. A hue detection based liquid crystal method is used to obtain the detailed heat transfer coefficient distribution on the blade tip surface for flat, smooth tip surfaces with both sharp and rounded edges. The cascade inlet turbulence intensity level took on values of either 5% or 9%. The cascade also models the casing recess in the shroud surface ahead of the blade. Experimental results are shown for the pressure distribution measurements on the airfoil near the tip gap, on the blade tip surface, and on the opposite shroud surface. Tip surface heat transfer coefficient distributions are shown for sharp-edge and rounded-edge tip geometries at each of the inlet turbulence intensity levels.

  11. The Effect of Inlet Temperature and Pressure on the Efficiency of a Single-stage Impulse Turbine Having a 13.2-inch Pitch-line Diameter Wheel

    NASA Technical Reports Server (NTRS)

    Chanes, Ernest R.; Carman, L. Robert

    1945-01-01

    Efficiency tests have been conducted on a single-stage impulse turbine having a 13.2-inch pitch-line diameter wheel and a cast nozzle diaphram over a range of turbine speeds from 3000 to 17,000 rpm, pressure ratios from 1.5 to 5.0, inlet total temperatures from 1200 deg to 2000 deg R, and inlet total pressures from 18 to 59 inches of mercury absolute. The effect of inlet temperature and pressure on turbine efficiency for constant pressure ration and blade-to-jet speed ration is correlated against a factor derived from the equation for Reynolds number. The degree of correlation indicates that the change in turbine efficiency with inlet temperature and [ressure for constant pressure ration and blade-to-jet speed ration is principally a Reynolds number effect.

  12. Numerical analysis of three-dimensional unsteady hot streak migration and shock interaction in a turbine stage

    SciTech Connect

    Saxer, A.P.; Felici, H.M.

    1996-04-01

    A three-dimensional unsteady flow computation has been performed for a transonic first turbine stage under the influence of streaks of hot gas exiting the combustion chamber. Realistic flow conditions are obtained by using an unequal stator-to-rotor pitch, a single-streak/multistator channel configuration, and periodic boundary conditions. The resulting unsteady shock wave system and the hot streak migration as well as the shock wave/streak interaction are presented and discussed. In addition, the time average of the periodic unsteady solution is analyzed and compared with a steady-state computation. The steady-state solution matches the time-averaged one in terms of the pressure field and the maximum stagnation temperature on the rotor blade surface. However, the rotor blade temperature patterns are different with a stronger radial secondary flow present in the time-averaged solution due to the retention of the circumferential streak variations at the stator/rotor interface.

  13. Aeroelastic stability analysis of a high-energy turbine blade. [for SSME High Pressure Oxidizer TurboPump first stage

    NASA Technical Reports Server (NTRS)

    Smith, Todd E.

    1990-01-01

    The dynamic analysis for the SSME HPOTP first stage turbine blade is presented wherein the rotor aeroelastic stability is assessed. The method employs normal modes analysis to simulate the coupled blade/fluid system. A three-dimensional finite element model of the blade is used in conjunction with a two-dimensional linearized unsteady aerodynamic theory which accounts for steady aerodynamic loading effects. This unsteady aerodynamic model is applied in stacked axisymmetric strips along the airfoil span. The blade dynamic and aerodynamic behaviors are coupled within modal space by expressing the unsteady aerodynamic forces in the frequency domain. A complex eigenvalue problem is solved to determine the stability of the rotor assuming tuned blades. The present analysis indicates that the HPOTP rotor experiences very low aerodynamic damping in the first four vibrational modes. The edgewise mode was found to be dynamically unstable. This mode of the blade became stable when the effect of mechanical damping was considered.

  14. Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine. Part 2; Simulation Results

    NASA Technical Reports Server (NTRS)

    Ameri, A. A.; Bunker, R. S.

    1999-01-01

    A combined experimental and computational study has been performed to investigate the detailed distribution of convective heat transfer coefficients on the first stage blade tip surface for a geometry typical of large power generation turbines (>1OOMW). This paper is concerned with the numerical prediction of the tip surface heat transfer. Good comparison with the experimental measured distribution was achieved through accurate modeling of the most important features of the blade passage and heating arrangement as well as the details of experimental rig likely to affect the tip heat transfer. A sharp edge and a radiused edge tip were considered. The results using the radiused edge tip agreed better with the experimental data. This improved agreement was attributed to the absence of edge separation on the tip of the radiused edge blade.

  15. Mixing in the dome region of a staged gas turbine combustor

    NASA Astrophysics Data System (ADS)

    Sowa, W. A.; Brady, R. A.; Samuelsen, G. S.

    1992-07-01

    To lower NO(x) emissions from gas-turbine engines the effect of dome design and operational changes on the mixing quality in the fuel-rich region is studied. A statistical analysis is employed to establish the parametric sensitivity in this complex flow. A mixing-effectiveness index is defined and used to optimize the gas-species uniformity and the extent of reaction at the exit plane of the dome. Mixing effectiveness is tied to the fuel and air injection locations, the macroscale structure of the dome aerodynamics, and the level of turbulence. Increases in nozzle/air to fuel ratio, reference velocities, and the dome expansion angle increased the level of turbulence. The optimum configuration featured counter-swirling fuel and air streams and produced a strong torroidal recirculation zone, an effective spray angle of 45 degrees, and azimuthal velocities that decayed to zero inside of two duct diameters. The results underscore the system specific nature of mixing optimization.

  16. Unsteady rotor-stator interaction in high speed compressor and turbine stages

    NASA Astrophysics Data System (ADS)

    Trébinjac, I.; Charbonnier, D.; Leboeuf, F.

    2005-12-01

    The blade row interaction can alter the time-mean flow and therefore be of interest for aerodynamic design analysis. Whereas results within low subsonic turbomachines are quite numerous in the literature, there have been far fewer works which give results of blade row interaction within high speed cases. Two cases are related in this paper. First, the effects of an incoming wake on the rotor flow field of a transonic compressor are analyzed. The blade row interaction proved to be positive regarding the total pressure ratio, but negative regarding the losses. The second case concerns a transonic turbine. Particular emphasis is placed on the assessment of the deterministic correlations included in the Averaged Passage Equation System.

  17. Aerodynamic evaluation and frequency prediction for the last stage turbine blade

    SciTech Connect

    Wang, K.D.; Amano, R.S.

    1999-07-01

    In designing a turbine airfoil, a continuous second derivative is desirable to prevent local flow separation and recirculation and a minimum curvature on the airfoil surface helps in decreasing turbulence level that causes potential energy loss in turbine efficiency. To meet this requirement, the design program uses the higher-order Bernstein polynomials to define for both the pressure-side and the suction-side profile curves. Two sets of data are required by the design program. The first is relevant to the geometric parameters that include radius of nose and tail, inlet and exit metal angles, length and orientation of chord, throat and pitch, bend angle, and wedge angle. The second set of data consists of five control variables to determine the suction-side profile and three control variables to determine the pressure-side profile. The program was successfully applied to modify an existing industrial airfoil. Geometric parameters were obtained by direct measurement. Trial and error procedures were employed to determine the values of those eight control variables so that the airfoil could be curve-fitted by running the design program. The shape of the airfoil reproduced by the present model was continuous and smooth. This was utilized in a subsequent computational fluid dynamics performance analysis and was revealed to be satisfactory as it eliminates certain discontinuities in the measured data. A more efficient shape of an airfoil could then be conformed by adjusting geometrical parameters and the control variables. Results obtained by using this program indicate that the present technique can not only effectively optimize an airfoil shape to achieve better aerodynamic performance but also can preserve the original design intents. A viscous flow program was used to aerodynamically analyze the original and the new designs. The produced airfoil was used to perform frequency response computations. The model developed in this study was shown to be useful for flutter

  18. Investigation of Turbines Suitable for Use in a Turbojet Engine with High Compressor Pressure Ratio and Low Compressor-tip Speed VII : Experimental Performance of Modified Two-stage Turbine

    NASA Technical Reports Server (NTRS)

    Davison, Elmer H; Petrash, Donald A; Schum, Harold J

    1956-01-01

    Modifying the original turbine by closing down the first-rotor throat area and shrouding the first and second rotors resulted in an over-all increase in in efficiency of 3.5 percentage points. At equivalent design work and speed the rating and aerodynamic efficiences of the modified turbine were 0.825 and 0.846, respectively. The maximum rating and erodynamic efficiencies were 0.875 and 0.906, respectively. A radial survey indicated improved firstively. A radial survey indicated improved first and second-stage efficiencies but showed that the effective throat areas of the second stator and rotor were too large.

  19. Bifrost: A 4th Generation Launch Architecture Concept

    NASA Astrophysics Data System (ADS)

    Rohrschneider, R. R.; Young, D.; St.Germain, B.; Brown, N.; Crowley, J.; Maatsch, J.; Olds, J. R.

    2002-01-01

    A 4th generation launch architecture is studied for the purpose of drastically reducing launch costs and hence enabling new large mass missions such as space solar power and human exploration of other planets. The architecture consists of a magnetic levitation launch tube placed on the equator with the exit end elevated to approximately 20 km. Several modules exist for sending manned and unmanned payloads into Earth orbit. Analysis of the launch tube operations, launch trajectories, module aerodynamics, propulsion modules, and system costs are presented. Using the hybrid logistics module, it is possible to place payloads into low Earth orbit for just over 100 per lb.

  20. Cooling circuit for steam and air-cooled turbine nozzle stage

    DOEpatents

    Itzel, Gary Michael; Yu, Yufeng

    2002-01-01

    The turbine vane segment includes inner and outer walls with a vane extending therebetween. The vane includes leading and trailing edge cavities and intermediate cavities. An impingement plate is spaced from the outer wall to impingement-cool the outer wall. Post-impingement cooling air flows through holes in the outer wall to form a thin air-cooling film along the outer wall. Cooling air is supplied an insert sleeve with openings in the leading edge cavity for impingement-cooling the leading edge. Holes through the leading edge afford thin-film cooling about the leading edge. Cooling air is provided the trailing edge cavity and passes through holes in the side walls of the vane for thin-film cooling of the trailing edge. Steam flows through a pair of intermediate cavities for impingement-cooling of the side walls. Post-impingement steam flows to the inner wall for impingement-cooling of the inner wall and returns the post-impingement cooling steam through inserts in other intermediate cavities for impingement-cooling the side walls of the vane.

  1. Development of a dry ultra-low NO{sub x} double swirler staged gas turbine combustor

    SciTech Connect

    Sato, H.; Mori, M.; Nakamura, T.

    1998-01-01

    This paper describes the development of an ultra-low NO{sub x} gas turbine combustor for cogeneration systems. The combustor, called a double swirler staged combustor, utilizes three-staged premixed combustion for low NO{sub x} emission. The unique feature of the combustor is its tertiary premix nozzles located downstream of the double swirler premixing nozzles around the combustor liner. Engine output is controlled by simply varying the fuel gas flow, and therefore employs no complex variable geometries for air flow control. Atmospheric combustion tests have demonstrated the superior performance of the combustor. NO{sub x} level is maintained at less than 3 ppm (O{sub 2} = 15%) over the range of engine output between 50 and 100%. Assuming the general relationship that NO{sub x} emission is proportional to the square root of operating pressure, the NO{sub x} level is estimated at less than 9 ppm (O{sub 2} = 15%) at the actual pressure of 0.91 MPa (abs.). Atmospheric tests have also shown high combustion efficiency; more than 99.9% over the range of engine output between 60 and 100%. Emissions of CO and UHC are maintained at 0 and 1 ppm (O{sub 2} = 15%), respectively, at the full engine load.

  2. A 95 GHz, 4th harmonic gyro-oscillator

    SciTech Connect

    Hargreaves, T.A.; Scheitrum, G.P.; Bemis, T.; Higgins, L.

    1994-12-31

    There is currently an interest in medium power ({approximately}100 kW), compact 95 GHz amplifiers for future radar applications. Size, weight, and efficiency are critical for airborne applications. Litton has been investigating a 4th harmonic, 4-cavity gyro-amplifier. The key to success of the amplifier is the axis-encircling electron beam from a new type of electron gun, the advanced center post (ACP) gun. Gun simulations incorporating the actual magnetic field and thermal velocity spread in the emitted electrons show that axial velocity spreads of less than 2% are attainable, which is significantly better than other gun concepts. The amplifier utilizes coaxial-magnetron-type cavities operating in the {pi} mode. In this cavity, vanes extend nearly down to the electron beam`s outside diameter. The majority of the RF stored energy in the system is in the coaxial cavity, so that the resonant frequency and quality factor of each coaxial magnetron cavity may be adjusted by varying only the coaxial cavity. Several components are being tested individually. To test the cavity design, a 4th harmonic oscillator based on a coaxial magnetron cavity has been designed. Results of the oscillator testing will be presented.

  3. Two-stage combustion for reducing pollutant emissions from gas turbine combustors

    NASA Technical Reports Server (NTRS)

    Clayton, R. M.; Lewis, D. H.

    1981-01-01

    Combustion and emission results are presented for a premix combustor fueled with admixtures of JP5 with neat H2 and of JP5 with simulated partial-oxidation product gas. The combustor was operated with inlet-air state conditions typical of cruise power for high performance aviation engines. Ultralow NOx, CO and HC emissions and extended lean burning limits were achieved simultaneously. Laboratory scale studies of the non-catalyzed rich-burning characteristics of several paraffin-series hydrocarbon fuels and of JP5 showed sooting limits at equivalence ratios of about 2.0 and that in order to achieve very rich sootless burning it is necessary to premix the reactants thoroughly and to use high levels of air preheat. The application of two-stage combustion for the reduction of fuel NOx was reviewed. An experimental combustor designed and constructed for two-stage combustion experiments is described.

  4. Experimental determination of gap flow-conditioned forces at turbine stages and their effect on the running stability of simple rotors. Ph.D. Thesis

    NASA Technical Reports Server (NTRS)

    Wohlrab, R.

    1983-01-01

    Instabilities in turbine operation can be caused by forces which are produced in connection with motions involving the oil film in the bearings. An experimental investigation regarding the characteristics of such forces in the case of three typical steam turbine stages is conducted, taking into account the effect of various parameters. Supplementary kinetic tests are carried out to obtain an estimate of the flow forces which are proportional to the velocity. The measurements are based on the theoretical study of the damping characteristics of a vibrational model. A computational analysis of the effect of the measured fluid forces on the stability characteristics of simple rotor model is also conducted.

  5. The Effect of Inlet Pressure and Temperature on the Efficiency of a Single-stage Impulse Turbine Having an 11.0-inch Pitch-line Diameter Wheel

    NASA Technical Reports Server (NTRS)

    Gabriel, David S.; Carmen, Robert L.; Trautwein, Elmer E

    1945-01-01

    Efficiency tests have been conducted on a single-stage impulse engine having an 11-inch pitch-line diameter wheel with inserted buckets and a fabricated nozzle diaphragm. The tests were made to determine the effect of inlet pressure, Inlet temperature, speed, and pressure ratio on the turbine efficiency. An analysis is presented that relates the effect of inlet pressure and temperature to the Reynolds number of the flow. The agreement between the analysis and the experimental data indicates that the changes in turbine efficiency with Inlet pressure and temperature may be principally a Reynolds number effect.

  6. Modeling multi-stage flows and aeroelasticity in transonic gas turbine compressors

    NASA Astrophysics Data System (ADS)

    Culver, Roy Milton

    Modern desire to have turbomachines perform over a large range of conditions raises concerns as to their susceptibility to potentially harmful vibrations induced by the unsteady flows encountered at conditions far from the design point. Machines demonstrating this type of behavior may be damaged by fatigue or be subject to catastrophic failure. Due to these concerns and the relative expense and difficulty in obtaining accurate experimental data for fluid-structure interaction in turbomachines, computations have been and will continue to be an indispensable part of the design and research efforts focused on avoiding such phenomena. While the traditional computational analysis considering a single isolated blade row can aid in understanding the mechanisms that initiate vibrations in turbomachines, study of multiple blade rows may be necessary to completely model the underlying causes of these vibrations. In the present work, the mixing-plane and sliding-mesh methods are used to simulate both steady and unsteady multi-stage transonic compressor flows. The simulations conducted here include the solution of the compressible unsteady Reynolds Averaged Navier Stokes (RANS) Equations. The Spalart Almaras model is used to simulate the effects of turbulence in the flow field. A modal superposition method is used to model fluid-structure interaction resulting from blade vibration. Steady flow through the NASA Stage 35 transonic compressor is computed using the mixing-plane method, and reasonable agreement is obtained with experimental data and previous computations. Steady and unsteady computations are also performed for a modern 1.5-stage transonic compressor design provided by Siemens. For this case, experiments indicate the appearance of low frequency, large amplitude flow oscillations which could potentially lead to unwanted structural vibration. In performing unsteady computations for the Siemens compressor, effects of the periodic domain size for the sliding

  7. Measurement and evaluation of swirl-type flow in labyrinth seals of conventional turbine stages

    NASA Technical Reports Server (NTRS)

    Hauck, L.

    1982-01-01

    The effects of load factor and rotor eccentricity were determined on flow conditions in test series for two stages. The results indicate that swirl-type entry flow follows the rules of potential swirl. Within the labyrinth cavities two spatial separated flow areas are considered. A dominating flow in periphera direction nearly fills the space between the sealing strips and the ceiling of the cavity. Below this flow, an area of axial mass transport is situated, with a slight peripheral component, limited on the nearest surroundings of the seals gap and the rotor surface. Between both flows, an exchange of energy takes place. Within the gaps, flow direction depends on axial velocity and therefore on variable flow contraction. A balance of energy within the seal and the cavities interprets the results of lateral force measurements as an influence of friction at the sealing strips surface and the rotating shaft surface. Stages with their blades put together in buckets by means of shrouding segments are particularly influenced by the rotating speed of the shrouding.

  8. Special Issue: 4th International Workshop on Space Radiation (IWSRR)

    NASA Technical Reports Server (NTRS)

    Cucinotta, Francis A.

    2007-01-01

    This special issue of the journal "Radiation and Environmental Biophysics" contains 20 peer-reviewed papers contributed by leading space radiation researcher's world-wide attending the 4th IWSRR. Manuscripts cover a broad range of topics ranging from radiation environments and transport in shielding and planetary surfaces to new results in understanding the biological effects of protons and high-charge and energy (HZE) nuclei on the risk of cancer, and degenerative diseases such as central nervous system effects, heart disease, and cataracts. The issue provides a snapshot of the state-of-the-art of the research in this field, demonstrating both the important results gathered in the past few years with experiments at accelerators, and the need for more research to quantify the risk and develop countermeasures.

  9. [Time--the 4th dimision in medicine and psychotherapy].

    PubMed

    Bergmann, Günther

    2003-01-01

    Time is presented as well in his historical meaning and as 4th dimension in its medical and psychotherapeutic context. In this medical and psychotherapeutic process it has an important function and is a variable of a process procedure. The difference between "kairos" = (the right point of time) and "chronos" = (the period of time) is historically meanful. The subjective experienced time is as well emphasized by the development of time in the relation to the development of the "self" as in the subjective experience of time in medical and psychotherapeutic situations. There are also changed conceptions and understandings of time running parallel to the development of nature sciences. The importance of time is explained for the medical practice and the meeting with the patient--especially for chronic diseases. The connection of confidence and time is particularly emphasized in the systemic approach. PMID:12764877

  10. European Code against Cancer 4th Edition: Breastfeeding and cancer.

    PubMed

    Scoccianti, Chiara; Key, Timothy J; Anderson, Annie S; Armaroli, Paola; Berrino, Franco; Cecchini, Michele; Boutron-Ruault, Marie-Christine; Leitzmann, Michael; Norat, Teresa; Powers, Hilary; Schüz, Joachim; Wiseman, Martin; Romieu, Isabelle

    2015-12-01

    Breast cancer is the most frequent cancer in women, and incidence rates have been rising in European Union (EU) countries over recent decades due in part to a sharp decline in breastfeeding practices. Evidence for a protective association between breastfeeding and the risk of breast cancer at all ages is convincing, and modest protective relationships between breastfeeding and the risk of endometrial and ovarian cancers have been suggested. The reduction in breast cancer risk is estimated at 2% for an increase of 5 months of lifetime breastfeeding. The longer women breastfeed, the more they are protected against breast cancer. In addition, breastfeeding is associated with several health benefits for both the mother and the breastfed child. Taking all this evidence into account, the 4th edition of the European Code against Cancer recommends: "Breastfeeding reduces the mother's cancer risk. If you can, breastfeed your baby". PMID:26116994

  11. Causes and means of prevention of erosion of exit edges of drive vanes in final stages of K-300-240 turbine

    NASA Astrophysics Data System (ADS)

    Orlik, V. G.; Reznik, L. B.

    1984-02-01

    A method, instruments and devices were developed and model and field studies were performed of the flow of steam and moisture downstream from the last stage of a K-300-240 turbine in the vicinity of the vertical separating rib. The quantity of moisture flowing toward the drive wheel of the last stage over the inner cone of the exhaust tube was measured, and found to decrease with increasing temperature, disappearing at 140 C. When the turbine is loaded, moisture appears on the cone at approximately 60 MW, reaching 60 kg/hr at nominal mode and increasing with decreasing steam superheating temperature, to 80 kg/hr at 60 MW and 365 C. The steam receiving section of the condenser was found to be overloaded since the cross section of its drains was not designed to receive steam with excess moisture content. Excessive twisting of the steam flow beyond the last stage in the direction of rotation was experimentally determined. The quantity of erosion-dangerous moisture downstream from the last stage depends on the temperature difference between turbine exhaust and the machine room in which it is located.

  12. Three-Dimensional Unsteady Simulation of Aerodynamics and Heat Transfer in a Modern High Pressure Turbine Stage

    NASA Technical Reports Server (NTRS)

    Shyam, Vikram; Ameri, Ali

    2009-01-01

    Unsteady 3-D RANS simulations have been performed on a highly loaded transonic turbine stage and results are compared to steady calculations as well as to experiment. A low Reynolds number k-epsilon turbulence model is employed to provide closure for the RANS system. A phase-lag boundary condition is used in the tangential direction. This allows the unsteady simulation to be performed by using only one blade from each of the two rows. The objective of this work is to study the effect of unsteadiness on rotor heat transfer and to glean any insight into unsteady flow physics. The role of the stator wake passing on the pressure distribution at the leading edge is also studied. The simulated heat transfer and pressure results agreed favorably with experiment. The time-averaged heat transfer predicted by the unsteady simulation is higher than the heat transfer predicted by the steady simulation everywhere except at the leading edge. The shock structure formed due to stator-rotor interaction was analyzed. Heat transfer and pressure at the hub and casing were also studied. Thermal segregation was observed that leads to the heat transfer patterns predicted by steady and unsteady simulations to be different.

  13. Analytical and experimental study of flow through an axial turbine stage with a nonuniform inlet radial temperature profile

    NASA Technical Reports Server (NTRS)

    Schwab, J. R.; Stabe, R. G.; Whitney, W. J.

    1983-01-01

    Results are presented for a typical nonuniform inlet radial temperature profile through an advanced single-stage axial turbine and compared with the results obtained for a uniform profile. Gas temperature rises of 40 K to 95 K are predicted at the hub and tip corners at the trailing edges of the pressure surfaces in both the stator and rotor due to convection of hot fluid from the mean by the secondary flow. The inlet temperature profile is shown to be mixed out at the rotor exit survey plane (2.3 axial chords downstream of the rotor trailing edge) in both the analysis and the experiment. The experimental rotor exit angle profile for the nonuniform inlet temperature profile indicates underturning at the tip caused by increased clearance. Severe underturning also occurs at the mean, both with and without the nonuniform inlet temperature profile. The inviscid rotational flow code used in the analysis fails to predict the underturning at the mean, which may be caused by viscous effects. Previously announced in STAR as N83-27958

  14. Analytical and Experimental Study of Flow Through an Axial Turbine Stage with a Nonuniform Inlet Radial Temperature Profile

    NASA Technical Reports Server (NTRS)

    Schwab, J. R.; Stabe, R. G.; Whitney, W. J.

    1983-01-01

    Results are presented for a typical nonuniform inlet radial temperature profile through an advanced single-stage axial turbine and compared with the results obtained for a uniform profile. Gas temperature rises of 40 K to 95 K are predicted at the hub and tip corners at the trailing edges of the pressure surfaces in both the stator and rotor due to convection of hot fluid from the mean by the secondary flow. The inlet temperature profile is shown to be mixed out at the rotor exit survey plane (2.3 axial chords downstream of the rotor trailing edge) in both the analysis and the experiment. The experimental rotor exit angle profile for the nonuniform inlet temperature profile indicates underturning at the tip caused by increased clearance. Severe underturning also occurs at the mean, both with and without the nonuniform inlet temperature profile. The inviscid rotational flow code used in the analysis fails to predict the underturning at the mean, which may be caused by viscous effects.

  15. Three-dimensional unsteady simulation of a modern high pressure turbine stage: Analysis of heat transfer and flow

    NASA Astrophysics Data System (ADS)

    Shyam, Vikram

    This is the first 3-D unsteady RANS simulation of a highly loaded transonic turbine stage and results are compared to steady calculations and experiments. A low Reynolds number k-epsilon turbulence model is employed to provide closure for the RANS system. Phase-lag is used in the tangential direction to account for stator-rotor interaction. Due to the highly loaded characteristics of the stage, inviscid effects dominate the flowfield downstream of the rotor leading edge minimizing the effect of segregation to the leading edge region of the rotor blade. Unsteadiness was observed at the tip surface that results in intermittent 'hot spots'. It is demonstrated that unsteadiness in the tip gap is governed by both inviscid and viscous effects due to shock-boundary layer interaction and is not heavily dependent on pressure ratio across the tip gap. This is contrary to published observations that have primarily dealt with subsonic tip flows. The high relative Mach numbers in the tip gap lead to a choking of the leakage flow that translates to a relative attenuation of losses at higher loading. The efficacy of a new tip geometry is discussed to minimize heat flux at the tip while maintaining choked conditions. Simulated heat flux and pressure on the blade and hub agree favorably with experiment and literature. The time-averaged simulation provides a more conservative estimate of heat flux than the steady simulation. The shock structure formed due to stator-rotor interaction is analyzed. A preprocessor has also been developed as a conduit between the unstructured multi-block grid generation software GridPro and the CFD code TURBO.

  16. 76 FR 37649 - Safety Zone; Northern California Annual Fireworks Events, July 4th Fireworks Display

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-28

    ... SECURITY Coast Guard 33 CFR Part 165 Safety Zone; Northern California Annual Fireworks Events, July 4th Fireworks Display AGENCY: Coast Guard, DHS. ACTION: Notice of enforcement of regulation. SUMMARY: The Coast Guard will enforce safety zone for the annual July 4th Fireworks Display (Tahoe City 4th of...

  17. 77 FR 39172 - Safety Zone: Skagway Harbor, Skagway, AK for 4th of July Fireworks

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-07-02

    ... SECURITY Coast Guard 33 CFR Part 165 RIN 1625-AA00 Safety Zone: Skagway Harbor, Skagway, AK for 4th of July... 4th of July Fireworks display. Persons desiring to transit within this safety zone must contact the... Inlet for the City of Skagway, Alaska, sponsored 4th of July fireworks display. A no-action...

  18. An experimental investigation of clocking effects on turbine aerodynamics using a modern 3-D one and one-half stage high pressure turbine for code verification and flow model development

    NASA Astrophysics Data System (ADS)

    Haldeman, Charles Waldo, IV

    2003-10-01

    This research uses a modern 1 and 1/2 stage high-pressure (HP) turbine operating at the proper design corrected speed, pressure ratio, and gas to metal temperature ratio to generate a detailed data set containing aerodynamic, heat-transfer and aero-performance information. The data was generated using the Ohio State University Gas Turbine Laboratory Turbine Test Facility (TTF), which is a short-duration shock tunnel facility. The research program utilizes an uncooled turbine stage for which all three airfoils are heavily instrumented at multiple spans and on the HPV and LPV endwalls and HPB platform and tips. Heat-flux and pressure data are obtained using the traditional shock-tube and blowdown facility operational modes. Detailed examination show that the aerodynamic (pressure) data obtained in the blowdown mode is the same as obtained in the shock-tube mode when the corrected conditions are matched. Various experimental conditions and configurations were performed, including LPV clocking positions, off-design corrected speed conditions, pressure ratio changes, and Reynolds number changes. The main research for this dissertation is concentrated on the LPV clocking experiments, where the LPV was clocked relative to the HPV at several different passage locations and at different Reynolds numbers. Various methods were used to evaluate the effect of clocking on both the aeroperformance (efficiency) and aerodynamics (pressure loading) on the LPV, including time-resolved measurements, time-averaged measurements and stage performance measurements. A general improvement in overall efficiency of approximately 2% is demonstrated and could be observed using a variety of independent methods. Maximum efficiency is obtained when the time-average pressures are highest on the LPV, and the time-resolved data both in the time domain and frequency domain show the least amount of variation. The gain in aeroperformance is obtained by integrating over the entire airfoil as the three

  19. PREFACE: 4th International Symposium on Functional Materials (ISFM2011)

    NASA Astrophysics Data System (ADS)

    Yin, Shu; Sekino, Tohru; Tanaka, Shun-ichiro; Sato, Tsugio; Lu, Li; Xue, Dongfeng

    2012-01-01

    The 4th International Symposium on Functional Materials (ISFM2011) was held in Sendai, Japan, on 2-6 August 2011. This Special Issue of Journal of Physics: Conference Series (JPCS) consists of partial manuscripts which were presented at ISFM2011. Advanced materials have experienced a dramatic increase in demand for research, development and applications. The aim of the International Symposium on Functional Materials (ISFM) was to provide an overview of the present status with historical background and to foresee future trends in the field of functional materials. The 4th symposium, ISFM 2011, covered a wide variety of topics within state-of-the-art advanced materials science and technology, and focused especially on four major categories including: Environmental Materials, Electronic Materials, Energy Materials and Biomedical Materials. As you know, a massive earthquake and the Tsunami that followed occurred near the Tohoku region on 11 March 2011. After the earthquake, although there were many difficulties in continuing to organize the symposium, we received warm encouragement from many researchers and societies, especially from the members of the International Advisory Committee and Organizing Committee, so that ISFM2011 could be held on schedule. We are honored that ISFM2011 was the first formal international academic conference held in the Tohoku area of Japan after the 11 March earthquake. About 140 participants from 14 countries took part in the ISFM2011 symposium, which included five plenary talks by world-leading scientists, 32 invited talks, and many oral and poster presentations. We are delighted to see that many researchers are interested in the synthesis and the properties as well as the applications of functional materials. Many fruitful and exciting research achievements were presented in the symposium. We believe that this symposium provided a good chance for scientists to communicate and exchange opinions with each other. We would also like to

  20. Managing haemophilia for life: 4th Haemophilia Global Summit.

    PubMed

    Astermark, J; Dolan, G; Hilberg, T; Jiménez-Yuste, V; Laffan, M; Lassila, R; Lobet, S; Martinoli, C; Perno, C-F

    2014-07-01

    The 4th Haemophilia Global Summit was held in Potsdam, Germany, in September 2013 and brought together an international faculty of haemophilia experts and delegates from multidisciplinary backgrounds. The programme was designed by an independent Scientific Steering Committee of haemophilia experts and explored global perspectives in haemophilia care, discussing practical approaches to the optimal management of haemophilia now and in the future. The topics outlined in this supplement were selected by the Scientific Steering Committee for their relevance and potential to influence haemophilia care globally. In this supplement from the meeting, Jan Astermark reviews current understanding of risk factors for the development of inhibitory antibodies and discusses whether this risk can be modulated and minimized. Factors key to the improvement of joint health in people with haemophilia are explored, with Carlo Martinoli and Víctor Jiménez-Yuste discussing the utility of ultrasound for the early detection of haemophilic arthropathy. Other aspects of care necessary for the prevention and management of joint disease in people with haemophilia are outlined by Thomas Hilberg and Sébastian Lobet, who highlight the therapeutic benefits of physiotherapy and sports therapy. Riitta Lassila and Carlo-Federico Perno describe current knowledge surrounding the risk of transmission of infectious agents via clotting factor concentrates. Finally, different types of extended half-life technology are evaluated by Mike Laffan, with a focus on the practicalities and challenges associated with these products. PMID:24924596

  1. European Code against Cancer 4th Edition: Diet and cancer.

    PubMed

    Norat, Teresa; Scoccianti, Chiara; Boutron-Ruault, Marie-Christine; Anderson, Annie; Berrino, Franco; Cecchini, Michele; Espina, Carolina; Key, Tim; Leitzmann, Michael; Powers, Hilary; Wiseman, Martin; Romieu, Isabelle

    2015-12-01

    Lifestyle factors, including diet, have long been recognised as potentially important determinants of cancer risk. In addition to the significant role diet plays in affecting body fatness, a risk factor for several cancers, experimental studies have indicated that diet may influence the cancer process in several ways. Prospective studies have shown that dietary patterns characterised by higher intakes of fruits, vegetables, and whole-grain foods, and lower intakes of red and processed meats and salt, are related to reduced risks of death and cancer, and that a healthy diet can improve overall survival after diagnosis of breast and colorectal cancers. There is evidence that high intakes of fruit and vegetables may reduce the risk of cancers of the aerodigestive tract, and the evidence that dietary fibre protects against colorectal cancer is convincing. Red and processed meats increase the risk of colorectal cancer. Diets rich in high-calorie foods, such as fatty and sugary foods, may lead to increased calorie intake, thereby promoting obesity and leading to an increased risk of cancer. There is some evidence that sugary drinks are related to an increased risk of pancreatic cancer. Taking this evidence into account, the 4th edition of the European Code against Cancer recommends that people have a healthy diet to reduce their risk of cancer: they should eat plenty of whole grains, pulses, vegetables and fruits; limit high-calorie foods (foods high in sugar or fat); avoid sugary drinks and processed meat; and limit red meat and foods high in salt. PMID:26164653

  2. Laser velocimeter measurements of the flow downstream of the Space Shuttle Main Engine high pressure oxidizer turbopump first-stage turbine nozzle

    NASA Technical Reports Server (NTRS)

    Ferguson, T. V.; Havskjold, G. L.; Rojas, L.

    1988-01-01

    A laser two-focus velocimeter was used in an open-loop water test facility in order to map the flowfield downstream of the SSME's high-pressure oxidizer turbopump first-stage turbine nozzle; attention was given to the effects of the upstream strut-downstream nozzle configuration on the flow at the rotor inlet, in order to estimate dynamic loads on the first-stage rotor blades. Velocity and flow angles were plotted as a function of circumferential position, and were found to clearly display the periodic behavior of the wake flow field. The influence of the upstream centerbody-supporting struts on the vane nozzle wake pattern was evident.

  3. Investigation of a 4.5-Inch-Mean-Diameter Two-Stage Axial-Flow Turbine Suitable for Auxiliary Power Drives

    NASA Technical Reports Server (NTRS)

    Wong, Robert Y.; Monroe, Daniel E.

    1959-01-01

    The design and experimental investigation of a 4.5-inch-mean-diameter two-stage turbine are presented herein and used to study the effect of size on the efficiency of turbines in the auxiliary power drive class. The results of the experimental investigation indicated that design specific work was obtained at design speed at a total-to-static efficiency of 0.639. At design pressure ratio, design static-pressure distribution through the turbine was obtained with an equivalent specific work output of 33.2 Btu per pound and an efficiency of 0.656. It was found that, in the design of turbines in the auxiliary power drive class, Reynolds number plays an important part in the selection of the design efficiency. Comparison with theoretical efficiencies based on a loss coefficient and velocity diagrams are presented. Close agreement was obtained between theory and experiment when the loss coefficient was adjusted for changes in Reynolds number to the -1/5 power.

  4. European Code against Cancer, 4th Edition: Tobacco and cancer.

    PubMed

    Leon, Maria E; Peruga, Armando; McNeill, Ann; Kralikova, Eva; Guha, Neela; Minozzi, Silvia; Espina, Carolina; Schüz, Joachim

    2015-12-01

    Tobacco use, and in particular cigarette smoking, is the single largest preventable cause of cancer in the European Union (EU). All tobacco products contain a wide range of carcinogens. The main cancer-causing agents in tobacco smoke are polycyclic aromatic hydrocarbons, tobacco-specific N-nitrosamines, aromatic amines, aldehydes, and certain volatile organic compounds. Tobacco consumers are also exposed to nicotine, leading to tobacco addiction in many users. Cigarette smoking causes cancer in multiple organs and is the main cause of lung cancer, responsible for approximately 82% of cases. In 2012, about 313,000 new cases of lung cancer and 268,000 lung cancer deaths were reported in the EU; 28% of adults in the EU smoked tobacco, and the overall prevalence of current use of smokeless tobacco products was almost 2%. Smokeless tobacco products, a heterogeneous category, are also carcinogenic but cause a lower burden of cancer deaths than tobacco smoking. One low-nitrosamine product, snus, is associated with much lower cancer risk than other smokeless tobacco products. Smoking generates second-hand smoke (SHS), an established cause of lung cancer, and inhalation of SHS by non-smokers is still common in indoor workplaces as well as indoor public places, and more so in the homes of smokers. Several interventions have proved effective for stopping smoking; the most effective intervention is the use of a combination of pharmacotherapy and behavioural support. Scientific evidence leads to the following two recommendations for individual action on tobacco in the 4th edition of the European Code Against Cancer: (1) "Do not smoke. Do not use any form of tobacco"; (2) "Make your home smoke-free. Support smoke-free policies in your workplace". PMID:26272517

  5. PREFACE: 4th International Hadron Physics Conference (TROIA'14)

    NASA Astrophysics Data System (ADS)

    Dağ, Hüseyin; Erkol, Güray; Küçükarslan, Ayşe; Özpineci, Altuğ

    2014-11-01

    The 4th International Conference on Hadron Physics, TROIA'14, was held at Canakkale, Turkey on 1-5 July 2014. Ozyegin University, Middle East Technical University, Canakkale Onsekiz Mart University, Turkish Atomic Energy Authority and HadronPhysics2 Consortium sponsored the conference. It aimed at bringing together the experts and the young scientists working on experimental and theoretical hadron physics. About 50 participants from 10 countries attended the conference. The topics covered included: . Chiral Perturbation Theory . QCD Sum Rules . Effective Field Theory . Exotic Hadrons . Hadron Properties from Lattice QCD . Experimental Results and Future Perspectives . Hadronic Distribution Amplitudes The conference presentations were organized such that the morning sessions contained invited talks and afternoon sessions were devoted to contributed talks. The speakers of the invited talks were: C. Alexandrou, A. Gal, L. Tolos, J.R. Pelaez and M. Schindler. We had also guest speakers D. A. Demir and T. Senger. The conference venue was a resort hotel around Canakkale. As a social program, a guided full-day excursion to the excavation site of the ancient Troia town and Assos was organized. We believe that this conference provided a medium for young scientists and experts in the field to effectively communicate and share ideas. We would like to express our sincere thanks to supporting agencies and to all participants for their contributions and stimulating discussions. We are also grateful to the Scientific Secretary, Bora Işıldak, and all other members of the Organizing Committee for their patience and efforts. 30.10.2014 The Editors

  6. Heat-flux measurements for the rotor of a full-stage turbine. II - Description of analysis technique and typical time-resolved measurements

    NASA Technical Reports Server (NTRS)

    Dunn, M. G.; George, W. K.; Rae, W. J.; Woodward, S. H.; Moller, J. C.

    1986-01-01

    An analytical technique for obtaining the time-resolved heat flux of a turbine blade is applied to the case of a TFE 731-2 hp full-stage rotating turbine. In order to obtain the heat flux values from the thin film gage temperature histories, a finite difference procedure is used to solve the heat equation with variable thermal properties. After setting out the data acquisition and analysis procedures, their application is illustrated for three midspan locations on the blade and operation at the design flow function. Results demonstrate that the magnitude of the heat flux fluctuation due to vane-balde interaction is large by comparison to the time-averaged heat flux at all investigated locations; FFT of a portion of the heat flux record illustrates that the dominant frequencies occur at the wake-cutting frequency and its harmonics.

  7. European Code against Cancer, 4th Edition: Cancer screening.

    PubMed

    Armaroli, Paola; Villain, Patricia; Suonio, Eero; Almonte, Maribel; Anttila, Ahti; Atkin, Wendy S; Dean, Peter B; de Koning, Harry J; Dillner, Lena; Herrero, Rolando; Kuipers, Ernst J; Lansdorp-Vogelaar, Iris; Minozzi, Silvia; Paci, Eugenio; Regula, Jaroslaw; Törnberg, Sven; Segnan, Nereo

    2015-12-01

    In order to update the previous version of the European Code against Cancer and formulate evidence-based recommendations, a systematic search of the literature was performed according to the methodology agreed by the Code Working Groups. Based on the review, the 4th edition of the European Code against Cancer recommends: "Take part in organized cancer screening programmes for: Bowel cancer (men and women); Breast cancer (women); Cervical cancer (women)." Organized screening programs are preferable because they provide better conditions to ensure that the Guidelines for Quality Assurance in Screening are followed in order to achieve the greatest benefit with the least harm. Screening is recommended only for those cancers where a demonstrated life-saving effect substantially outweighs the potential harm of examining very large numbers of people who may otherwise never have, or suffer from, these cancers, and when an adequate quality of the screening is achieved. EU citizens are recommended to participate in cancer screening each time an invitation from the national or regional screening program is received and after having read the information materials provided and carefully considered the potential benefits and harms of screening. Screening programs in the European Union vary with respect to the age groups invited and to the interval between invitations, depending on each country's cancer burden, local resources, and the type of screening test used For colorectal cancer, most programs in the EU invite men and women starting at the age of 50-60 years, and from then on every 2 years if the screening test is the guaiac-based fecal occult blood test or fecal immunochemical test, or every 10 years or more if the screening test is flexible sigmoidoscopy or total colonoscopy. Most programs continue sending invitations to screening up to the age of 70-75 years. For breast cancer, most programs in the EU invite women starting at the age of 50 years, and not before the age

  8. Urban Infrasound Observations - Examples from July 4th 2012

    NASA Astrophysics Data System (ADS)

    McComas, S.; Hayward, C.; Golden, P.; McKenna, M.; Simpson, C.

    2012-12-01

    , the Heroy Building Rooftop Array, is a two-element 30m line on a single rooftop. Large-scale fireworks displays in Dallas on 4 July 2012 provided an opportunity to identify and characterize known signals in an urban setting. The identified events were associated with one of these fireworks displays about 2 km from the arrays. Signals from these sources were used to tune processing parameters for an automatic coherent detection process, Progressive Multichannel Correlation Method (PMCC). PMCC was then used to scan the data for all possible firework sources in the urban environment and determine temporal, back azimuth, apparent velocity, and frequency information about the sources. The signal frequencies seen were 10-80 Hz and documented the details of the nearly 30 minute firework show. The resulting PMCC analysis showed potential to effectively identify other, lower frequency sources in the urban environment. These data were also is used to characterize the noise environment. Significant roof-to-roof noise differences may be related to the building configurations and mechanical equipment, as well as the interactions of the winds with the structures. During the evening of July 4th , additional ground deployed infrasound gauges provided a comparison of free surface and rooftop measurements. Permission to publish was granted by Director, Geotechnical and Structures Laboratory.

  9. 75 FR 35649 - Safety Zone; Northern California Annual Fireworks Events, July 4th Fireworks Display

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-23

    ... SECURITY Coast Guard 33 CFR Part 165 Safety Zone; Northern California Annual Fireworks Events, July 4th Fireworks Display AGENCY: Coast Guard, DHS. ACTION: Notice of enforcement of regulation. SUMMARY: The Coast Guard will enforce the Tahoe City 4th of July Fireworks Display safety zone, from 9 a.m. through 10...

  10. The Effects of Cooperative Learning Strategies on Vocabulary Skills of 4th Grade Students

    ERIC Educational Resources Information Center

    Bilen, Didem; Tavil, Zekiye Müge

    2015-01-01

    This study was carried out to investigate the effects of cooperative learning strategies on the vocabulary skills of 4th grade students. The study was also designed to ascertain the attitudes of the students in the experimental group towards cooperative learning. Out of 96 4th grade students enrolled in the private school where the study took…

  11. The school nutrition program's role in weight management of 4th grade elementary students

    Technology Transfer Automated Retrieval System (TEKTRAN)

    We are attempting to uncover the school nutrition program's role in weight management of 4th grade elementary students. Data was collected within a time frame for the food frequency questionnaire (FFQ) set at two months at the WT Cheney Elementary School and South Wood Elementary for 4th grade stud...

  12. 75 FR 34636 - Safety Zone; Jameson Beach 4th of July Fireworks Display

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-18

    ... SECURITY Coast Guard 33 CFR Part 165 RIN 1625-AA00 Safety Zone; Jameson Beach 4th of July Fireworks Display... temporary safety zone in the navigable waters of Lake Tahoe, for the Jameson Beach 4th of July Fireworks... has a substantial direct effect on State or local governments and would either preempt State law...

  13. 75 FR 34639 - Safety Zone; Reedville July 4th Celebration, Cockrell's Creek, Reedville, VA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-18

    ... Celebration, Cockrell's Creek, Reedville, VA in the Federal Register (75 FR 26157). We received no comments on... SECURITY Coast Guard 33 CFR Part 165 RIN 1625-AA00 Safety Zone; Reedville July 4th Celebration, Cockrell's... the Reedville July 4th Celebration event. This action is intended to restrict vessel traffic...

  14. 76 FR 37650 - Safety Zone; 4th of July Festival Berkeley Marina Fireworks Display Berkeley, CA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-28

    ... SECURITY Coast Guard 33 CFR Part 165 RIN 1625-AA00 Safety Zone; 4th of July Festival Berkeley Marina... Berkeley Pier, Berkeley, CA in support of the 4th of July Festival Berkeley Marina Fireworks Display... used in the fireworks display. Background and Purpose The City of Berkeley Marina will sponsor the...

  15. 75 FR 26157 - Safety Zone; Reedville July 4th Celebration, Cockrell's Creek, Reedville, VA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-11

    ... Federal Register (73 FR 3316). Public Meeting We do not now plan to hold a public meeting. But you may... SECURITY Coast Guard 33 CFR Part 165 RIN 1625-AA00 Safety Zone; Reedville July 4th Celebration, Cockrell's..., VA in support of the Reedville July 4th Celebration event. This action is intended to restrict...

  16. Science Content Courses: Workshop in Food Chemistry for 4th Grade School Teachers

    ERIC Educational Resources Information Center

    Chaiyapechara, S.; Dong, F. M.

    2004-01-01

    A science content course in food chemistry was offered as a 4-day summer workshop from 1999 to 2001 to 4th grade school teachers in the Seattle School District. The objectives of the workshop were to increase the teachers' knowledge of food science, to perform simple experiments that could be used in the 4th grade classroom, and to help the…

  17. Steam generators, turbines, and condensers. Volume six

    SciTech Connect

    Not Available

    1986-01-01

    Volume six covers steam generators (How steam is generated, steam generation in a PWR, vertical U-tube steam generators, once-through steam generators, how much steam do steam generators make.), turbines (basic turbine principles, impulse turbines, reaction turbines, turbine stages, turbine arrangements, turbine steam flow, steam admission to turbines, turbine seals and supports, turbine oil system, generators), and condensers (need for condensers, basic condenser principles, condenser arrangements, heat transfer in condensers, air removal from condensers, circulating water system, heat loss to the circulating water system, factors affecting condenser performance, condenser auxiliaries).

  18. Design considerations for a 1500 M head 300-600 MW double stage reversible pump/turbine with regulation

    NASA Astrophysics Data System (ADS)

    Chacour, S. A.; Degnan, J. R.; Fisher, R. K., Jr.

    It is noted that much attention has recently been given to the development of high-head pumped storage schemes. The special design considerations required to develop the turbine machinery for this new category of service are presented. Also included is a discussion of the advanced computer-aided design and analytical tools now available to optimize the prototype equipment. Special manufacturing considerations and model testing philosophy are introduced. It is noted that an optimized final machine design results from computer-aided mechanical design, detailed structural analysis, and a prediction of fatigue life.

  19. Experimental turbine VT-400

    NASA Astrophysics Data System (ADS)

    Zitek, Pavel; Milčák, Petr; Noga, Tomáš

    2016-03-01

    The experimental air turbine VT400 is located in hall laboratories of the Department of Power System Engineering. It is a single-stage air turbine located in the suction of the compressor. It is able to solve various problems concerning the construction solution of turbine stages. The content of the article will deal mainly with the description of measurements on this turbine. The up-to-now research on this test rig will be briefly mentioned, too, as well as the description of the ongoing reconstruction.

  20. BOOK REVIEW: Mastering Physics (4th edn) Macmillan Master Series

    NASA Astrophysics Data System (ADS)

    Sugden, Chris

    2000-01-01

    The preface to the first edition of this book, in 1982, stated the aim as `presenting ideas with a directness and simplicity that will enable students to achieve maximum comprehension in the shortest possible time'. The fourth edition remains true to this aim, whilst paying some attention to the possibility of using the book alongside classroom work as well as a revision aid. However, it is as a clear concise summary of GCSE level physics (and a little bit beyond) that this book excels. I would recommend it to students as a revision aid at the end of the course and as a reference book during it. There should certainly be a few copies in the school library. Since I see the book's main role as being for the individual use of students it seemed sensible to ask one for his impression of the book having completed GCSE Physics a few months ago, and this is appended below. Philip Britton The book is split into many small, precise subsections and so allows easy reference to the topic you want to know about. The major equations are all included and explained well. The text is quite detailed and includes helpful examples. Concepts are explained in simple stages and in a way that is easy to understand; for example, the phases of the moon and ray diagrams. Resistors, which had been a little difficult for me, are very well explained. A simple detail like putting the names of the circuit symbols beside them on diagrams helps a lot. Throughout the book there are plenty of diagrams used to assist understanding rather than just illustrate the book. Overall I think that it would be best used as a revision aid. It reads very much like a syllabus with added explanation and examples. Perhaps it would be possible for a class to read a section before a lesson so less basic explanation is required during the lesson and other work can be done. The sections are brief enough to allow even the apathetic to complete such a homework assignment.

  1. 29. VIEW OF 4TH FLOOR'S TELEPHONE RACKS WITH CABLE TRAYS ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    29. VIEW OF 4TH FLOOR'S TELEPHONE RACKS WITH CABLE TRAYS ABOVE. THESE ARE NEWER APPARATUS AND NOT ORIGINAL. - Pacific Telephone & Telegraph Company Building, 1519 Franklin Street, Oakland, Alameda County, CA

  2. 16. 4th floor roof, view west, north side of setback ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    16. 4th floor roof, view west, north side of setback to left and delivery stair bulkhead to right - Sheffield Farms Milk Plant, 1075 Webster Avenue (southwest corner of 166th Street), Bronx, Bronx County, NY

  3. TID Test Results for 4th Generation iPad(TradeMark)

    NASA Technical Reports Server (NTRS)

    Guertin, S. M.; Allen, G. R.; McClure, S. S.; LaBel, K. A.

    2013-01-01

    TID testing of 4th generation iPads is reported. Of iPad subsystems, results indicate that the charging circuitry and display drivers fail at lowest TID levels. Details of construction are investigated for additional testing of components.

  4. 18. DETAILED OFFSHORE VIEW OF 4TH TEE, LOOKING NORTHWEST, SHOWING ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    18. DETAILED OFFSHORE VIEW OF 4TH TEE, LOOKING NORTHWEST, SHOWING TRANSITION FROM WOOD BENTS TO CONCRETE BENTS - Huntington Beach Municipal Pier, Pacific Coast Highway at Main Street, Huntington Beach, Orange County, CA

  5. Thermo-fluid dynamic design study of single and double-inflow radial and single-stage axial steam turbines for open-cycle thermal energy conversion net power-producing experiment facility in Hawaii

    SciTech Connect

    Schlbeiri, T. . Dept. of Mechanical Engineering)

    1990-03-01

    The results of the study of the optimum thermo-fluid dynamic design concept are presented for turbine units operating within the open-cycle ocean thermal energy conversion (OC-OTEC) systems. The concept is applied to the first OC-OTEC net power producing experiment (NPPE) facility to be installed at Hawaii's natural energy laboratory. Detailed efficiency and performance calculations were performed for the radial turbine design concept with single and double-inflow arrangements. To complete the study, the calculation results for a single-stage axial steam turbine design are also presented. In contrast to the axial flow design with a relatively low unit efficiency, higher efficiency was achieved for single-inflow turbines. Highest efficiency was calculated for a double-inflow radial design, which opens new perspectives for energy generation from OC-OTEC systems.

  6. New technology in turbine aerodynamics.

    NASA Technical Reports Server (NTRS)

    Glassman, A. J.; Moffitt, T. P.

    1972-01-01

    Cursory review of some recent work that has been done in turbine aerodynamic research. Topics discussed include the aerodynamic effect of turbine coolant, high work-factor (ratio of stage work to square of blade speed) turbines, and computer methods for turbine design and performance prediction. Experimental cooled-turbine aerodynamics programs using two-dimensional cascades, full annular cascades, and cold rotating turbine stage tests are discussed with some typical results presented. Analytically predicted results for cooled blade performance are compared to experimental results. The problems and some of the current programs associated with the use of very high work factors for fan-drive turbines of high-bypass-ratio engines are discussed. Computer programs have been developed for turbine design-point performance, off-design performance, supersonic blade profile design, and the calculation of channel velocities for subsonic and transonic flowfields. The use of these programs for the design and analysis of axial and radial turbines is discussed.

  7. Laser-doppler-velocimetry measurements in a one and a half stage transonic test turbine with different angular stator-stator positions

    NASA Astrophysics Data System (ADS)

    Schennach, Oliver; Woisetschläger, Jakob; Marn, Andreas; Göttlich, Emil

    2007-08-01

    A one and a half stage transonic turbine was tested using a two component laser-doppler-velocimetry system. The measurements were carried out in order to record rotor phase resolved velocity, flow angle and turbulence distributions upstream and downstream of the second stator row at several different angular stator-stator positions (“clocking” positions). Altogether, the measurements downstream of the second stator were performed for ten different clocking positions and upstream of the second stator for two different clocking positions. These different clocking positions have a significant influence on the flow field upstream and downstream of the second stator. Furthermore error estimation and a discussion of the tracer particle response are discussed.

  8. Turbopumps for cryogenic upper stage engines. [fabrication and evaluation of turbine pumps for liquid hydrogen and liquid oxygen

    NASA Technical Reports Server (NTRS)

    Zachary, A. T.; Csomor, A.; Tignac, L. L.

    1973-01-01

    Small, high-performance LO2 and LH2 turbopump assembly configurations were selected, detail designs were prepared and two of each unit were fabricated with each unit consisting of pump, turbine gas generator, and appropriate controls. Following fabrication, development testing was conducted on each type to demonstrate performance, durability, transient characteristics, and heat transfer under simulated altitude conditions. Following successful completion of development effort, the two LO2 turbopump units and one LH2 turbopump unit were acceptance tested as specified. Inspection of the units following development testing revealed no deleterious effects of testing. The test results of LO2 turbopump assembly testing correlated well with predicted performance while the LH2 turbopump test results, though generally consistent with predicted values, did show lower than anticipated developed head at the design point and in the high flow range of operation.

  9. Systematically frameshifting by deletion of every 4th or 4th and 5th nucleotides during mitochondrial transcription: RNA self-hybridization regulates delRNA expression.

    PubMed

    Seligmann, Hervé

    2016-01-01

    In mitochondria, secondary structures punctuate post-transcriptional RNA processing. Recently described transcripts match the human mitogenome after systematic deletions of every 4th, respectively every 4th and 5th nucleotides, called delRNAs. Here I explore predicted stem-loop hairpin formation by delRNAs, and their associations with delRNA transcription and detected peptides matching their translation. Despite missing 25, respectively 40% of the nucleotides in the original sequence, del-transformed sequences form significantly more secondary structures than corresponding randomly shuffled sequences, indicating biological function, independently of, and in combination with, previously detected delRNA and thereof translated peptides. Self-hybridization decreases delRNA abundances, indicating downregulation. Systematic deletions of the human mitogenome reveal new, unsuspected coding and structural informations. PMID:27018206

  10. Turbine turbobrake systems

    NASA Astrophysics Data System (ADS)

    Goodisman, Michael I.

    Short duration rotating turbine facilities are a recent development in the field of turbine research. Turbine braking devices can be used to maintain the turbine at the desired test speed, resulting in a longer usable test time. The Isentropic Light Piston Cascade at the Defence Research Agency in Pyestock will perform heat transfer and aerodynamic tests on the first stage of a Rolls-Royce turbine (MT1) linked to a new type of brake, the 'axial turbo brake'. The axial turbo brake is driven by the turbine's exhaust gas and is isolated from the turbine by a choked throat. The turbo brake's power absorption must be controlled to match the power developed by the turbine stage for a constant speed run. Both the turbo brake blade shape and novel power control system were developed from tests on a 0.17 scale test rig. The turbo brake's braking is controlled through by-pass of flow over the blade tips and partial blockage of the turbo brake's exit annulus. Also described is the mechanical design, development and manufacture of the full size turbo brake, turbine disc and turbine blades, which have been successfully spun tested to their overspeed condition. Finally, a theory for self-pumping turbo brakes is developed. These devices would have additional applications because they do not require a supply of high pressure gas to drive them.

  11. 75 FR 38721 - Safety Zone; Munising 4th of July Fireworks, South Bay, Lake Superior, Munising, MI

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-06

    ... SECURITY Coast Guard 33 CFR Part 165 RIN 1625-AA00 Safety Zone; Munising 4th of July Fireworks, South Bay... is intended to restrict vessels from a portion of South Bay during the Munising 4th of July Fireworks... from hazards associated with the Munising 4th of July Fireworks display. Based on the explosive...

  12. 75 FR 34369 - Safety Zones; City of Chicago's July 4th Celebration Fireworks, Lake Michigan, Chicago, IL

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-17

    ... Chicago's July 4th Celebration Fireworks, Chicago, Illinois in the Federal Register (75 FR 22330). We... SECURITY Coast Guard 33 CFR Part 165 RIN 1625-AA00 Safety Zones; City of Chicago's July 4th Celebration... associated with the City of Chicago's July 4th Celebration Fireworks. The Captain of the Port, Sector...

  13. 75 FR 34379 - Safety Zone; Mackinac Island 4th of July Fireworks, Lake Huron, Mackinac Island, MI

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-17

    ... SECURITY Coast Guard 33 CFR Part 165 RIN 1625-AA00 Safety Zone; Mackinac Island 4th of July Fireworks, Lake... intended to restrict vessels from a portion of Lake Huron during the Mackinac Island 4th of July Fireworks... with the Mackinac Island 4th of July fireworks display. The fireworks display will occur between 9:45...

  14. 75 FR 38718 - Safety Zone; Sault Sainte Marie 4th of July Fireworks, St. Mary's River, Sault Sainte Marie, MI

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-06

    ... SECURITY Coast Guard 33 CFR Part 165 RIN 1625-AA00 Safety Zone; Sault Sainte Marie 4th of July Fireworks... the Sault Sainte Marie 4th of July Fireworks display, July ] 4, 2010. This temporary safety zone is... with the Sault Sainte Marie 4th of July Fireworks display. The fireworks display is planned to...

  15. Investigation of the Effects of Low Reynolds Number Operation on the Performance of a Single-Stage Turbine with a Downstream Stator

    NASA Technical Reports Server (NTRS)

    Forrette, Robert E.; Holeski, Donald E.; Plohr, Henry W.

    1959-01-01

    High-altitude turbojet performance is adversely affected by the effects of low air density. This performance loss is evaluated as a Reynolds number effect, which represents the increased significance of high fluid viscous forces in relation to dynamic fluid forces as the Reynolds number is decreased. An analytical and experimental investigation of the effects of low Reynolds number operation on a single-stage, high-work-output turbine with a downstream stator was carried out at Reynolds numbers of 182,500, 39,600, and 23,000, based on average rotor-design flow conditions. At low Reynolds numbers and turbulent flow conditions, increased viscous losses caused decreased effective flow area, and thus decreased weight flow, torque, and over-all efficiency at a given equivalent speed and pressure ratio. Decreasing the Reynolds number from 182,500 to 23,000 at design equivalent speed resulted in a 5.00-point loss in peak over-all turbine efficiency for both theory and experiment. The choking equivalent weight flow decreased 2.30 percent for these conditions. Limiting loading work output was reached at design equivalent speed for all three Reynolds numbers. The value of limiting loading work output at design speed decreased 4.00 percent as Reynolds number was decreased from 182,500 to 23,000. A theoretical performance-prediction method using basic boundary-layer relations gave good agreement with experimental results over most of the performance range at a given Reynolds number if the experimental and analytical design operating conditions were carefully matched at the highest Reynolds number with regard to design performance parameters. High viscous losses in the inlet stator and rotor prevented the attainment of design equivalent work output at the lowest Reynolds number of 23,000.

  16. Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Nozzles and Three Rotor-Blade Designs

    NASA Technical Reports Server (NTRS)

    Schum, Harold J.; Whitney, Warren J.

    1949-01-01

    A single-stage modification of the turbine from a Mark 25 torpedo power plant was investigated to determine the performance with two nozzles and three rotor-blade designs. The performance was evaluated in terms of brake, rotor, and blade efficiencies at pressure ratios of 8, 15 (design), and 20. The blade efficiencies with the two nozzles are compared with those obtained with four other nozzles previously investigated with the same three rotor-blade designs. Blade efficiency with the cast nozzle of rectangular cross section (J) was higher than that with the circular reamed nozzle (K) at all speeds and pressure ratios with a rotor having a 0.45-inch 17 degree-inlet-angle blades. The efficiencies for both these nozzles were generally low compared with those of the four other nozzles previously investigated in combination with this rotor. At pressure ratios of 15 and 20, the blade efficiencies with nozzle K and the two rotors with 0.40-inch blades having different inlet angles were higher than with the four other nozzles, but the efficiency with nozzle J was generally low. Increasing the blade inlet angle from 17 degrees to 20 degrees had little effect on turbine performance, whereas changing the blade length from 0.40 to 0.45 inch had a marked effect. Although a slight correlation of efficiency with nozzle size was noted for the rotor with 0.45-inch 17 degree-inlet-angle blades, no such effect was discernible ,for the two rotors with 0.40-inch blades.Losses in the supersonic air stream resulting from the complex flow path in the small air passages are probably a large percentage of the total losses, and apparently the effects of changing nozzle size and shape within the limits investigated are of secondary importance.

  17. 20. TYPICAL VIEW OF FRONT WINDOWS FROM 4TH TO 9TH ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    20. TYPICAL VIEW OF FRONT WINDOWS FROM 4TH TO 9TH FLOOR WITH WHITE GLAZED TERRA COTTA SILL AND HEADERS. MULLIONS ARE ORANGE BROWN BRICKS LIKE THE WALLS. BRICKS ARE IN FLEMISH BOND PATTERN. - Pacific Telephone & Telegraph Company Building, 1519 Franklin Street, Oakland, Alameda County, CA

  18. Using 4th order Runge-Kutta method for solving a twisted Skyrme string equation

    NASA Astrophysics Data System (ADS)

    Hadi, Miftachul; Anderson, Malcolm; Husein, Andri

    2016-03-01

    We study numerical solution, especially using 4th order Runge-Kutta method, for solving a twisted Skyrme string equation. We find numerically that the value of minimum energy per unit length of vortex solution for a twisted Skyrmion string is 20.37 × 1060 eV/m.

  19. 77 FR 39408 - Safety Zone; Buffalo July 4th Fireworks, Lake Erie, Buffalo, NY

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-07-03

    ... DHS Department of Homeland Security FR Federal Register NPRM Notice of Proposed Rulemaking A... SECURITY Coast Guard 33 CFR Part 165 RIN 1625-AA00 Safety Zone; Buffalo July 4th Fireworks, Lake Erie, Buffalo, NY AGENCY: Coast Guard, DHS. ACTION: Temporary final rule. SUMMARY: The Coast Guard...

  20. Assessment of an Engineering Technology Outreach Program for 4th-7th Grade Girls

    ERIC Educational Resources Information Center

    Dell, Elizabeth M.; Christman, Jeanne; Garrick, Robert D.

    2011-01-01

    This paper describes a workshop led by female Engineering Technology students, with support from female faculty, to provide an introduction to Engineering Technology to 4th-7th grade girls through a series of interactive laboratory experiments. This outreach program was developed to improve attitudes towards science and engineering in middle…

  1. 75 FR 33170 - Safety Zone; City of Martinez 4th of July Fireworks, Martinez, CA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-11

    ... SECURITY Coast Guard 33 CFR Part 165 RIN 1625-AA00 Safety Zone; City of Martinez 4th of July Fireworks, Martinez, CA AGENCY: Coast Guard, DHS. ACTION: Temporary final rule. SUMMARY: The Coast Guard is establishing a temporary safety zone for the launching of fireworks being sponsored by the City of...

  2. Improving Social Interaction among 4th Grade Students through Social Skills Instruction.

    ERIC Educational Resources Information Center

    Dunleavy, Shannon; Karwowski, Sandra; Shudes-Eitel, Jennifer

    This action research project implemented a program for improving social skills in order to establish positive interaction among 4th grade students at a northern Chicago suburban school. Social skills deficiency was documented through behavior checklists and referrals, teacher observations and student reflection. Teachers reported that low incomes,…

  3. Relationships between Grade Levels, Personal Factors, and Instructional Variation among 4th-12th Grade Teachers

    ERIC Educational Resources Information Center

    White, Jacquelyn M.

    2011-01-01

    The purpose of this quantitative correlational study was to investigate relationships between grade levels, personal factors of teachers, and instructional variety used by 4th-12th grade teachers in Kern County, California. The population under investigation included 2,844 teachers. 235 elementary, middle school/junior high, and secondary teachers…

  4. 77 FR 56208 - Filing Dates for the Kentucky Special Election in the 4th Congressional District

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-09-12

    ... From the Federal Register Online via the Government Publishing Office FEDERAL ELECTION COMMISSION Filing Dates for the Kentucky Special Election in the 4th Congressional District AGENCY: Federal Election Commission. ACTION: Notice of filing dates for special election. SUMMARY: Kentucky has scheduled a...

  5. Reading Development and Achievement of 4th-Grade Hmong Students

    ERIC Educational Resources Information Center

    Mahowald, Megan; Loughnane, Megan

    2016-01-01

    Researchers and practitioners alike have noted that Hmong students in the United States do not achieve as well as their monolingual peers and other bilingual students. The current mixed-methods study is designed to describe reading development and achievement of 4th-grade Hmong students in one large, urban school district. This study explores the…

  6. MAIN GATE, INTERSECTION OF 4TH AVE (200 NORTH) AND N ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    MAIN GATE, INTERSECTION OF 4TH AVE (200 NORTH) AND N STREET (895 EAST), SALT LAKE CITY, UT. VIEW LOOKING EAST THROUGH MAIN CEMETERY GATE TO CEMETERY'S MAIN STREET, REPHOTOGRAPH OF HISTORIC SHIPLER PHOTO # 18276, UTAH STATE HISTORICAL SOCIETY COLLECTION. - Salt Lake City Cemetery, 200 N Street, Salt Lake City, Salt Lake County, UT

  7. Polarimetric Microwave Emission from Snow Surface: 4th Strokes Component Analysis

    Technology Transfer Automated Retrieval System (TEKTRAN)

    The effect of ice on the polarimetric 4th Stokes component observations is investigated using WindSat data over Antarctica. The difference in the magnitude of the signal observed during (July 2003) and summer (February 2004) months is investigated using a second harmonic sine function of the azimuth...

  8. 33 CFR 165.166 - Safety Zone: Macy's July 4th Fireworks, East River, NY.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... 33 Navigation and Navigable Waters 2 2013-07-01 2013-07-01 false Safety Zone: Macy's July 4th Fireworks, East River, NY. 165.166 Section 165.166 Navigation and Navigable Waters COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) PORTS AND WATERWAYS SAFETY REGULATED NAVIGATION AREAS AND LIMITED ACCESS AREAS Specific Regulated Navigation...

  9. 33 CFR 165.166 - Safety Zone: Macy's July 4th Fireworks, East River, NY.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... CFR 165.23 apply. (2) No vessels, except the Staten Island Ferries, will be allowed to transit the... 33 Navigation and Navigable Waters 2 2010-07-01 2010-07-01 false Safety Zone: Macy's July 4th... OF HOMELAND SECURITY (CONTINUED) PORTS AND WATERWAYS SAFETY REGULATED NAVIGATION AREAS AND...

  10. 33 CFR 165.166 - Safety Zone: Macy's July 4th Fireworks, East River, NY.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... CFR 165.23 apply. (2) No vessels, except the Staten Island Ferries, will be allowed to transit the... 33 Navigation and Navigable Waters 2 2011-07-01 2011-07-01 false Safety Zone: Macy's July 4th... OF HOMELAND SECURITY (CONTINUED) PORTS AND WATERWAYS SAFETY REGULATED NAVIGATION AREAS AND...

  11. 33 CFR 165.166 - Safety Zone: Macy's July 4th Fireworks, East River, NY.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... CFR 165.23 apply. (2) No vessels, except the Staten Island Ferries, will be allowed to transit the... 33 Navigation and Navigable Waters 2 2012-07-01 2012-07-01 false Safety Zone: Macy's July 4th... OF HOMELAND SECURITY (CONTINUED) PORTS AND WATERWAYS SAFETY REGULATED NAVIGATION AREAS AND...

  12. 33 CFR 165.166 - Safety Zone: Macy's July 4th Fireworks, East River, NY.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... CFR 165.23 apply. (2) No vessels, except the Staten Island Ferries, will be allowed to transit the... 33 Navigation and Navigable Waters 2 2014-07-01 2014-07-01 false Safety Zone: Macy's July 4th... OF HOMELAND SECURITY (CONTINUED) PORTS AND WATERWAYS SAFETY REGULATED NAVIGATION AREAS AND...

  13. 11. 4TH FLOOR, HOTEL SOAP LINE No. 6 TO NORTHEAST, ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    11. 4TH FLOOR, HOTEL SOAP LINE No. 6 TO NORTHEAST, WITH WRAPPER (LEFT), PRESS (CENTER), AND CUTTER (RIGHT, BEHIND CHUTE); BUCKET CONVEYOR AT RIGHT MOVED WASTE FROM PRESS TO 5TH FLOOR FOR RE-MANUFACTURE - Colgate & Company Jersey City Plant, Building No. B-14, 54-58 Grand Street, Jersey City, Hudson County, NJ

  14. 4th level of 1945 warehouse indicating drag conveyor. From here ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    4th level of 1945 warehouse indicating drag conveyor. From here screenings were pumped from the elevator leg to this conveyor. The grains were ground, then conveyed back down to the first floor for bagging. - Stewart Company Grain Elevator, 16 West Carson Street, Pittsburgh, Allegheny County, PA

  15. 94. VIEW OF PILINGS ON SOUTHEAST SIDE, WITH 4TH TEE ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    94. VIEW OF PILINGS ON SOUTHEAST SIDE, WITH 4TH TEE IN THE BACKGROUND, FACING WEST-SOUTHWEST FROM SOUTHEAST CORNER OF THE TACKLE BOX. RAMP OF PIER EXTENSION IS VISIBLE ON RIGHT - Huntington Beach Municipal Pier, Pacific Coast Highway at Main Street, Huntington Beach, Orange County, CA

  16. Three-Dimensional Unsteady Simulation of a Modern High Pressure Turbine Stage Using Phase Lag Periodicity: Analysis of Flow and Heat Transfer

    NASA Technical Reports Server (NTRS)

    Shyam, Vikram; Ameri, Ali; Luk, Daniel F.; Chen, Jen-Ping

    2010-01-01

    Unsteady three-dimensional RANS simulations have been performed on a highly loaded transonic turbine stage and results are compared to steady calculations as well as experiment. A low Reynolds number k- turbulence model is employed to provide closure for the RANS system. A phase-lag boundary condition is used in the periodic direction. This allows the unsteady simulation to be performed by using only one blade from each of the two rows. The objective of this paper is to study the effect of unsteadiness on rotor heat transfer and to glean any insight into unsteady flow physics. The role of the stator wake passing on the pressure distribution at the leading edge is also studied. The simulated heat transfer and pressure results agreed favorably with experiment. The time-averaged heat transfer predicted by the unsteady simulation is higher than the heat transfer predicted by the steady simulation everywhere except at the leading edge. The shock structure formed due to stator-rotor interaction was analyzed. Heat transfer and pressure at the hub and casing were also studied. Thermal segregation was observed that leads to the heat transfer patterns predicted by steady and unsteady simulations to be different.

  17. Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Special Nozzles. 1; Efficiency with 0.45-inch Rotor Blades

    NASA Technical Reports Server (NTRS)

    Schum, Harold J.; Whitney, Waren J.

    1949-01-01

    An investigation was made of the first-stage turbine of a Mark 25 torpedo power plant to determine the performance of the unity with two nozzle configurations and a special rotor having 0.45-inch blades instead of the standard length of 0.40 inch. Both nozzles had smaller passages than the nozzles of similar shape that were previously investigated. The performance of the nozzle-blade combinations is evaluated in terms of brake, rotor, and blade efficiency as functions of blade-jet speed ratio for three pressure ratios. Over the range of speeds and pressure ratios investigated, the efficiency with the nozzle having rectangular passages (J) was higher than that with a nozzle having circular passages (K). The difference in blade efficiencies varied from less than 0.010 at the lower blade-jet speed ratios for the three pressure ratios investigated to 0.030 at a pressure ratio of 8 and a blade-jet speed ratio of 0.295. The efficiencies with these tow nozzles were generally lower than those obtained with nozzles previously reported in combination with the 0.45-inch blades.

  18. Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Special Nozzles. II; Efficiency with 20 Degrees-Inlet-Angle Rotor Blades

    NASA Technical Reports Server (NTRS)

    Schum, Harold J.; Whitney, Warren J.

    1949-01-01

    A single-stage modification of the turbine from a Mark 25 torpedo power plant was investigated to determine the performance with two nozzle designs in combination with special rotor blades having a 20 inlet angle. The performance is presented in terms of blade, rotor, and brake efficiency as a function of blade-jet speed ratio for pressure ratios of 8, 15 (design), and 20. The blade efficiency with the nozzle having circular pas- sages (K) was equal to or higher than that with the nozzle having rectangular passages (J) for all pressure ratios and speeds investigated. The maximum blade efficiency of 0.571 was obtained with nozzle K at a pressure ratio of 8 and a blade-jet speed ratio of 0.296. The difference in blade efficiency was negligible at a pressure ratio of 8 at the low speeds; the maxim difference was 0.040 at a pressure ratio of 20 and a blade-jet speed ratio of 0.260.

  19. Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Special Nozzles. III; Efficiency with Standard Rotor Blades

    NASA Technical Reports Server (NTRS)

    Schum, Harold J.; Whitney, Warren J.

    1949-01-01

    A Mark 25 torpedo power plant modified to operate as a single-stage turbine was investigated to determine the performance with two nozzle designs and a standard first-stage rotor having 0.40-inch blades with a 17O met-air angle. Both nozzles had smaller port cross-sectional areas than those nozzles of similar design, which were previously investigated. The performance of the two nozzles was compared on the basis of blade, rotor, and brake efficiencies as a function of blade-jet speed ratio for pressure ratios of 8, 15 (design), and 20. At pressure ratios of 15 and 20, the blade efficiency obtained with the nozzle having circular passages (K) was higher than that obtained with the nozzle having rectangular passages (J). At a pressure ratio of 8, the efficiencies obtained with the two nozzles were comparable for blade-jet speed ratios of less than 0.260. For blade-jet speed ratios exceeding this value, nozzle K yielded slightly higher efficiencies. The maximum blade efficiency of 0.569 was obtained with nozzle K at a pressure ratio of 8 and a blade-jet speed ratio of 0.295. At design speed and pressure ratio, nozzle K yielded a maximum blade efficiency of 0.534, an increase of 0.031 over that obtained with nozzle J. When the blade efficiencies of the two nozzles were compared with those of four other nozzles previously investigated, the maximum difference for the six nozzles with this rotor was 0.050. From, this comparison, no specific effect of nozzles size or shape on over-all performance was discernible.

  20. THE FIRST LASING OF 193 NM SASE, 4TH HARMONIC HGHG AND ESASE AT THE NSLS SDL.

    SciTech Connect

    WANG, X.J.; SHEN Y.; WATANABE, T.; MURPHY, J.B.; ROSE, J.; TSANG, T.

    2006-08-28

    The first lasing of three types of single-pass high-gain FELs, SASE at 193 nm, 4th harmonic HGHG at 199 nm and ESASE at the Source Development Lab (SDL) of Brookhaven National Laboratory (BNL) is reported. The saturation of 4th harmonic HGHG and ESASE FELs was observed. We also observed the spectral broadening and instability of the 4th harmonic HGHG.

  1. Ceramics for ATS industrial turbines

    SciTech Connect

    Wenglarz, R.; Ali, S.; Layne, A.

    1996-05-01

    US DOE and most US manufacturers of stationary gas turbines are participating in a major national effort to develop advanced turbine systems (ATS). The ATS program will achieve ultrahigh efficiencies, environmental superiority, and cost competitiveness compared with current combustion turbine systems. A major factor in the improved efficiencies of simple cycle ATS gas turbines will be higher operating efficiencies than curren engines. These temperatures strain the limits of metallic alloy and flow-path cooling technologies. Ceramics materials offer a potential alterative to cooled turbine alloys for ATS turbines due to higher melting points than metallics. This paper evaluates ceramics technology and plant economic issues for ATS industrial turbine systems. A program with the objective of demonstrating first-stage ceramic vanes in a commerical industrial turbine is also described.

  2. Turbinate surgery

    MedlinePlus

    Turbinectomy; Turbinoplasty; Turbinate reduction; Nasal airway surgery ... There are several types of turbinate surgery: Turbinectomy: All or part of the lower turbinate is taken out. This can be done in several different ways, but sometimes a ...

  3. 11th National Meeting of Organic Chemistry and 4th Meeting of Therapeutic Chemistry

    PubMed Central

    Sousa, Maria Emília; Araújo, Maria João; do Vale, Maria Luísa; Andrade, Paula B.; Branco, Paula; Gomes, Paula; Moreira, Rui; Pinho e Melo, Teresa M.V.D.; Freitas, Victor

    2016-01-01

    For the first time under the auspices of Sociedade Portuguesa de Química, the competences of two important fields of Chemistry are brought together into a single event, the 11st National Organic Chemistry Meeting and the the 4th National Medicinal Chemistry Meeting, to highlight complementarities and to promote new synergies. Abstracts of plenary lectures, oral communications, and posters presented during the meeting are collected in this report. PMID:27102166

  4. 11(th) National Meeting of Organic Chemistry and 4(th) Meeting of Therapeutic Chemistry.

    PubMed

    Sousa, Maria Emília; Araújo, Maria João; do Vale, Maria Luísa; Andrade, Paula B; Branco, Paula; Gomes, Paula; Moreira, Rui; Pinho E Melo, Teresa M V D; Freitas, Victor

    2016-01-01

    For the first time under the auspices of Sociedade Portuguesa de Química, the competences of two important fields of Chemistry are brought together into a single event, the 11st National Organic Chemistry Meeting and the the 4th National Medicinal Chemistry Meeting, to highlight complementarities and to promote new synergies. Abstracts of plenary lectures, oral communications, and posters presented during the meeting are collected in this report. PMID:27102166

  5. 10. 4TH FLOOR, HOTEL SOAP LINE No. 6 TO SOUTHWEST, ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    10. 4TH FLOOR, HOTEL SOAP LINE No. 6 TO SOUTHWEST, WITH AUTOMATIC CUTTER (LEFT), PRESS (CENTER), AND WRAPPER (RIGHT); LARGE CHUTE AT CENTER FROM 5TH FLOOR BINS TO 3RD FLOOR SOAP MILLS; OVERHEAD AND FLOOR (LOWER RIGHT) FINISHED GOODS CONVEYORS TO G BLOCK (HAER NO. NJ-71-NN) - Colgate & Company Jersey City Plant, Building No. B-14, 54-58 Grand Street, Jersey City, Hudson County, NJ

  6. Impact of clocking on the aero-thermodynamics of a second stator tested in a one and a half stage HP turbine

    NASA Astrophysics Data System (ADS)

    Billiard, N.; Paniagua, Guillermo; Dénos, R.

    2008-06-01

    This paper focuses on the experimental investigation of the time-averaged and time-accurate aero-thermodynamics of a second stator tested in a 1.5 stage high-pressure turbine. The effect of clocking on aerodynamic and heat transfer are investigated. Tests are performed under engine representative conditions in the VKI compression tube CT3. The test program includes four different clocking positions, i.e. relative pitch-wise positions between the first and the second stator. Probes located upstream and downstream of the second stator provide the thermodynamic conditions of the flow field. On the second stator airfoil, measurements are taken around the blade profile at 15, 50 and 85% span with pressure sensors and thin-film gauges. Both time-averaged and time-resolved aspects of the flow field are addressed. Regarding the time-averaged results, clocking effects are mainly observed within the leading edge region of the second stator, the largest effects being observed at 15% span. The surface static pressure distribution is changed locally, hence affecting the overall airfoil performance. For one clocking position, the thermal load of the airfoil is noticeably reduced. Pressure fluctuations are attributed to the passage of the upstream transonic rotor and its associated pressure gradients. The pattern of these fluctuations changes noticeably as a function of clocking. The time-resolved variations of heat flux and static pressure are analyzed together showing that the major effect is due to a potential interaction. The time-resolved pressure distribution integrated along the second stator surface yields the unsteady forces on the vane. The magnitude of the unsteady force is very dependent on the clocking position.

  7. Estimating turbine limit load

    NASA Technical Reports Server (NTRS)

    Glassman, Arthur J.

    1993-01-01

    A method for estimating turbine limit-load pressure ratio from turbine map information is presented and demonstrated. It is based on a mean line analysis at the last-rotor exit. The required map information includes choke flow rate at all speeds as well as pressure ratio and efficiency at the onset of choke at design speed. One- and two-stage turbines are analyzed to compare the results with those from a more rigorous off-design flow analysis and to show the sensitivities of the computed limit-load pressure ratios to changes in the key assumptions.

  8. Noise level evaluation for a natural gas compressor station driven by gas turbines at the planning stage after four years of operation

    SciTech Connect

    Fleischer, F.; Hiemer, H.; Mann, J.

    1987-01-01

    For a southern german gas turbine compressor station sound emission levels and noise control thereoff are evaluated based on authority specified emmission levels. Project history, planning and operating experience is shown.

  9. Can astronomy enhance UNESCO World Heritage recognition? The paradigm of 4th Dynasty Egyptian pyramids

    NASA Astrophysics Data System (ADS)

    Belmonte, Juan Antonio

    2015-08-01

    The pyramids of Egypt, notably those of the 4th Dinasty as Giza, have always be considered an unmistikable part of human world heritage as the only surviving wonders of the Ancient World. Their majesty, technical hability and innovative character have always beeen considered as representative of ancient Egyptian ingenuity. However, past and present fringe theories about the pyramids and astronomy have always polluted the role of our discipline in the design, construction and symbolism of these impressive monuments. This is indeed unfear. Fortunately, things have started to change in the last couple of decades and now astronomy is interpreted as a neccessary tool for the correct interpretation of the astral eschatology present in the 5th and 6th Dynasty Texts of the Pyramids. Although the pyramid complexes of the 4th Dynasty are mute, there is however recent research showing that a strong astral symbolism could be hidden in many aspects of the complex architecture and in the design of these exceptional monuments. This idea comes from several hints obtained not only from planning and construction, but also from epigraphy and the analysis of celestial and local landscapes. Chronology also plays a most relevant role on this. The pyramid complexes of the 4th Dynasty at Meidum, Dahshur, Giza and Abu Rowash -- all of which enjoy UNESCO World Heritage recognition -- willl be scrutinized. As a consequence, we will show how astronomy can certainly enhance the face value of these extraordinary monuments as a definitive proof of the ancient Egyptian quest for Ma'at, i.e. their perennial obsesion for Cosmic Order.

  10. miR-155 Inhibition Sensitizes CD4+ Th Cells for TREG Mediated Suppression

    PubMed Central

    Rust, Werner; Labhart, Paul; Alexiadis, Vassili; Becker, Christian; Hafner, Mathias; Weith, Andreas; Lenter, Martin C.; Jonuleit, Helmut; Schmitt, Edgar; Mennerich, Detlev

    2009-01-01

    Background In humans and mice naturally occurring CD4+CD25+ regulatory T cells (nTregs) are a thymus-derived subset of T cells, crucial for the maintenance of peripheral tolerance by controlling not only potentially autoreactive T cells but virtually all cells of the adaptive and innate immune system. Recent work using Dicer-deficient mice irrevocably demonstrated the importance of miRNAs for nTreg cell-mediated tolerance. Principal Findings DNA-Microarray analyses of human as well as murine conventional CD4+ Th cells and nTregs revealed a strong up-regulation of mature miR-155 (microRNA-155) upon activation in both populations. Studying miR-155 expression in FoxP3-deficient scurfy mice and performing FoxP3 ChIP-Seq experiments using activated human T lymphocytes, we show that the expression and maturation of miR-155 seem to be not necessarily regulated by FoxP3. In order to address the functional relevance of elevated miR-155 levels, we transfected miR-155 inhibitors or mature miR-155 RNAs into freshly-isolated human and mouse primary CD4+ Th cells and nTregs and investigated the resulting phenotype in nTreg suppression assays. Whereas miR-155 inhibition in conventional CD4+ Th cells strengthened nTreg cell-mediated suppression, overexpression of mature miR-155 rendered these cells unresponsive to nTreg cell-mediated suppression. Conclusion Investigation of FoxP3 downstream targets, certainly of bound and regulated miRNAs revealed the associated function between the master regulator FoxP3 and miRNAs as regulators itself. miR-155 is shown to be crucially involved in nTreg cell mediated tolerance by regulating the susceptibility of conventional human as well as murine CD4+ Th cells to nTreg cell-mediated suppression. PMID:19777054

  11. Proceedings of the 4th International Workshop on Tritium Effects in Plasma Facing Components

    SciTech Connect

    R. A. Causey

    1999-02-01

    The 4th International Workshop on Tritium Effects in Plasma Facing Components was held in Santa Fe, New Mexico on May 14-15, 1998. This workshop occurs every two years, and has previously been held in Livermore/California, Nagoya/Japan, and the JRC-Ispra Site in Italy. The purpose of the workshop is to gather researchers involved in the topic of tritium migration, retention, and recycling in materials used to line magnetic fusion reactor walls and provide a forum for presentation and discussions in this area. This document provides an overall summary of the workshop, the workshop agenda, a summary of the presentations, and a list of attendees.

  12. Proceedings of the 4th International Conference and Exhibition: World Congress on Superconductivity, volume 1

    NASA Technical Reports Server (NTRS)

    Krishen, Kumar (Editor); Burnham, Calvin (Editor)

    1995-01-01

    The papers presented at the 4th International Conference Exhibition: World Congress on Superconductivity held at the Marriott Orlando World Center, Orlando, Florida, are contained in this document and encompass the research, technology, applications, funding, political, and social aspects of superconductivity. Specifically, the areas covered included: high-temperature materials; thin films; C-60 based superconductors; persistent magnetic fields and shielding; fabrication methodology; space applications; physical applications; performance characterization; device applications; weak link effects and flux motion; accelerator technology; superconductivity energy; storage; future research and development directions; medical applications; granular superconductors; wire fabrication technology; computer applications; technical and commercial challenges, and power and energy applications.

  13. Multi-Dimensional Asymptotically Stable 4th Order Accurate Schemes for the Diffusion Equation

    NASA Technical Reports Server (NTRS)

    Abarbanel, Saul; Ditkowski, Adi

    1996-01-01

    An algorithm is presented which solves the multi-dimensional diffusion equation on co mplex shapes to 4th-order accuracy and is asymptotically stable in time. This bounded-error result is achieved by constructing, on a rectangular grid, a differentiation matrix whose symmetric part is negative definite. The differentiation matrix accounts for the Dirichlet boundary condition by imposing penalty like terms. Numerical examples in 2-D show that the method is effective even where standard schemes, stable by traditional definitions fail.

  14. Proceedings of the 4th International Conference and Exhibition: World Congress on Superconductivity, Volume 2

    NASA Technical Reports Server (NTRS)

    Krishen, Kumar (Editor); Burnham, Calvin (Editor)

    1995-01-01

    This document contains papers presented at the 4th International Conference Exhibition: World Congress on Superconductivity held June 27-July 1, 1994 in Orlando, Florida. These documents encompass research, technology, applications, funding, political, and social aspects of superconductivity. The areas covered included: high-temperature materials; thin films; C-60 based superconductors; persistent magnetic fields and shielding; fabrication methodology; space applications; physical applications; performance characterization; device applications; weak link effects and flux motion; accelerator technology; superconductivity energy; storage; future research and development directions; medical applications; granular superconductors; wire fabrication technology; computer applications; technical and commercial challenges; and power and energy applications.

  15. The ratio of 2nd to 4th digit length: a new predictor of disease predisposition?

    PubMed

    Manning, J T; Bundred, P E

    2000-05-01

    The ratio between the length of the 2nd and 4th digits is: (a) fixed in utero; (b) lower in men than in women; (c) negatively related to testosterone and sperm counts; and (d) positively related to oestrogen concentrations. Prenatal levels of testosterone and oestrogen have been implicated in infertility, autism, dyslexia, migraine, stammering, immune dysfunction, myocardial infarction and breast cancer. We suggest that 2D:4D ratio is predictive of these diseases and may be used in diagnosis, prognosis and in early life-style interventions which may delay the onset of disease or facilitate its early detection. PMID:10859702

  16. Aerothermal experiments in turbine rim seals

    NASA Astrophysics Data System (ADS)

    Pittman, Lionel Obadiah, Jr.

    Purge flows are necessary for ensuring that hot gasses do not penetrate the thermally sensitive rim seal and disk cavity regions of turbines. The temperature and mass flow rate of the purge air can affect the component life and aerodynamic performance of a turbine stage. Therefore it is of interest to understand the basic mechanisms that govern this complex flow problem. The present work focuses on two turbine rim seal investigations. The first focused on temperature measurements in the rim cavity region of a rotating, high-speed, low-pressure turbine as means to quantify a rim seal's effectiveness. The seal had a realistic geometry with a small axial overlap between the stationary and rotating components. The purge flow rate was varied from 0 to 1 percent of the core mass flow rate. The results will describe the temperatures as well as the seal's effectiveness as a function of the purge flow rate, and turbine operating point. The second was a study on the effect of purge flow on the aerodynamic performance of a turbine stage. Exit flow field surveys were taken in both a low pressure turbine stage and a high pressure turbine stage. Also a computational study was done on the low pressure turbine stage to add insight into the effect of purge flow on turbine stage performance. In addition, the computation results provide insight into the effect of purge flow on the low pressure turbine blade passage flow field.

  17. New technology in turbine aerodynamics

    NASA Technical Reports Server (NTRS)

    Glassman, A. J.; Moffitt, T. P.

    1972-01-01

    A cursory review is presented of some of the recent work that has been done in turbine aerodynamic research at NASA-Lewis Research Center. Topics discussed include the aerodynamic effect of turbine coolant, high work-factor (ratio of stage work to square of blade speed) turbines, and computer methods for turbine design and performance prediction. An extensive bibliography is included. Experimental cooled-turbine aerodynamics programs using two-dimensional cascades, full annular cascades, and cold rotating turbine stage tests are discussed with some typical results presented. Analytically predicted results for cooled blade performance are compared to experimental results. The problems and some of the current programs associated with the use of very high work factors for fan-drive turbines of high-bypass-ratio engines are discussed. Turbines currently being investigated make use of advanced blading concepts designed to maintain high efficiency under conditions of high aerodynamic loading. Computer programs have been developed for turbine design-point performance, off-design performance, supersonic blade profile design, and the calculation of channel velocities for subsonic and transonic flow fields. The use of these programs for the design and analysis of axial and radial turbines is discussed.

  18. Blade-to-coolant heat-transfer results and operating data from a natural-convection water-cooled single-stage turbine

    NASA Technical Reports Server (NTRS)

    Diaguila, Anthony J; Freche, John C

    1951-01-01

    Blade-to-coolant heat-transfer data and operating data were obtained with a natural-convection water-cooled turbine over range of turbine speeds and inlet-gas temperatures. The convective coefficients were correlated by the general relation for natural-convection heat transfer. The turbine data were displaced from a theoretical equation for natural convection heat transfer in the turbulent region and from natural-convection data obtained with vertical cylinders and plates; possible disruption of natural convection circulation within the blade coolant passages was thus indicated. Comparison of non dimensional temperature-ratio parameters for the blade leading edge, midchord, and trailing edge indicated that the blade cooling effectiveness is greatest at the midchord and least at the trailing edge.

  19. Design of a Nb3Sn Magnet for a 4th Generation ECR Ion Source

    SciTech Connect

    Prestemon, S,; Trillaud, F.; Caspi, S.; Ferracin, P.; Sabbi, G. L.; Lyneis, C. M.; Leitner, D.; Todd, D. S.; Hafalia, R.

    2008-08-17

    The next generation of Electron Cyclotron Resonant (ECR) ion sources are expected to operate at a heating radio frequency greater than 40 GHz. The existing 3rd generation systems, exemplified by the state of the art system VENUS, operate in the 10-28 GHz range, and use NbTi superconductors for the confinement coils. The magnetic field needed to confine the plasma scales with the rf frequency, resulting in peak fields on the magnets of the 4th generation system in excess of 10 T. High field superconductors such as Nb{sub 3}Sn must therefore be considered. The magnetic design of a 4th. generation ECR ion source operating at an rf frequency of 56 GHz is considered. The analysis considers both internal and external sextupole configurations, assuming commercially available Nb{sub 3}Sn material properties. Preliminary structural design issues are discussed based on the forces and margins associated with the coils in the different configurations, leading to quantitative data for the determination of a final magnet design.

  20. Spiritual Health Scale 2011: Defining and Measuring 4th Dimension of Health

    PubMed Central

    Dhar, Neera; Chaturvedi, SK; Nandan, Deoki

    2011-01-01

    In the midst of physical comforts provided by the unprecedented developments in all spheres of life, the humanity is at cross roads and looking at something beyond these means. Spirituality has now been identified globally as an important aspect for providing answers to many questions related to health and happiness. The World Health Organization is also keen at looking beyond physical, mental and social dimensions of the health, and the member countries are actively exploring the 4th Dimension of the health i.e. the spiritual health and its impact on the overall health and happiness of an individual. National Institute of Health and Family Welfare (NIHFW), realized this need and initiated a research study in this direction. In this study, an effort was made to define this 4th Dimension of health from a common worldly person's perspective and measure it. 3 Domains, 6 Constructs and 27 Determinants of spiritual health were identified through a scientific process. A statistically reliable and valid Spiritual Health Scale (SHS 2011) containing 114 items has been developed. Construct validity and test- retest reliability has been established for urban educated adult population. The scale is first of its kind in the world to measure the spiritual health of a common worldly person, which is devoid of religious and cultural bias. Its items have universal applicability. PMID:22279257

  1. Computational aspects of the nonlinear normal mode initialization of the GLAS 4th order GCM

    NASA Technical Reports Server (NTRS)

    Navon, I. M.; Bloom, S. C.; Takacs, L.

    1984-01-01

    Using the normal modes of the GLAS 4th Order Model, a Machenhauer nonlinear normal mode initialization (NLNMI) was carried out for the external vertical mode using the GLAS 4th Order shallow water equations model for an equivalent depth corresponding to that associated with the external vertical mode. A simple procedure was devised which was directed at identifying computational modes by following the rate of increase of BAL sub M, the partial (with respect to the zonal wavenumber m) sum of squares of the time change of the normal mode coefficients (for fixed vertical mode index) varying over the latitude index L of symmetric or antisymmetric gravity waves. A working algorithm is presented which speeds up the convergence of the iterative Machenhauer NLNMI. A 24 h integration using the NLNMI state was carried out using both Matsuno and leap-frog time-integration schemes; these runs were then compared to a 24 h integration starting from a non-initialized state. The maximal impact of the nonlinear normal mode initialization was found to occur 6-10 hours after the initial time.

  2. PREFACE: 4th International Conference on Mathematical Modeling in Physical Sciences (IC-MSquare2015)

    NASA Astrophysics Data System (ADS)

    Vlachos, Dimitrios; Vagenas, Elias C.

    2015-09-01

    The 4th International Conference on Mathematical Modeling in Physical Sciences (IC-MSQUARE) took place in Mykonos, Greece, from Friday 5th June to Monday 8th June 2015. The Conference was attended by more than 150 participants and hosted about 200 oral, poster, and virtual presentations. There were more than 600 pre-registered authors. The 4th IC-MSQUARE consisted of different and diverging workshops and thus covered various research fields where Mathematical Modeling is used, such as Theoretical/Mathematical Physics, Neutrino Physics, Non-Integrable Systems, Dynamical Systems, Computational Nanoscience, Biological Physics, Computational Biomechanics, Complex Networks, Stochastic Modeling, Fractional Statistics, DNA Dynamics, Macroeconomics etc. The scientific program was rather intense as after the Keynote and Invited Talks in the morning, three parallel oral and one poster session were running every day. However, according to all attendees, the program was excellent with a high quality of talks creating an innovative and productive scientific environment for all attendees. We would like to thank the Keynote Speaker and the Invited Speakers for their significant contribution to IC-MSQUARE. We also would like to thank the Members of the International Advisory and Scientific Committees as well as the Members of the Organizing Committee.

  3. Crime rates and sedentary behavior among 4th grade Texas school children

    PubMed Central

    Brown, H Shelton; Pérez, Adriana; Mirchandani, Gita G; Hoelscher, Deanna M; Kelder, Steven H

    2008-01-01

    Introduction Although per capita crime has generally fallen over the period which coincides with the obesity epidemic, it has not fallen uniformly across communities. It also has not fallen enough to allay fears on the part of parents. Over the past 30 years, technological changes have made the indoor alternatives to playing outside, where children are more vulnerable to criminal activity, more enjoyable (cable TV, video games, and the internet) and comfortable (the spread of air conditioning to low income neighborhoods). We determined whether indoor sedentary behavior patterns are associated with community crime statistics. 4th graders in the U.S. are typically 9 or 10 years old. Methods We used data from the 2004–2005 Texas School Physical Activity and Nutrition (SPAN) survey linked with U.S. Department of Justice, Office of Justice Programs, Bureau of Justice Statistics data for the years 2000 through 2005 and Texas State data on sexual offenders. The probability-based sample included a total of 7,907 children in grade four. Multistage probability sampling weights were used. The dependent variables included were hours of TV watching, video game playing, computer use and total indoor sedentary behavior after school. Incremental Relative Rates were computed for community crime rates including robberies, all violent crimes, murders, assaults, property crimes, rapes, burglaries, larcenies and motor vehicle thefts as well as for sexual offenders living in the neighborhood. The neighborhood refers to the areas where the students at each school live. In the case of sexual offenders, sexual offenders per capita are estimated using the per capita rate in the zip code of the school attended; all other crime statistics are estimated by the crimes per capita in the police department jurisdiction covering the school attended. After controlling for sex, age, and African-American and Hispanic, cross-sectional associations were determined using multivariate Poisson regression

  4. European Code against Cancer 4th Edition: Alcohol drinking and cancer.

    PubMed

    Scoccianti, Chiara; Cecchini, Michele; Anderson, Annie S; Berrino, Franco; Boutron-Ruault, Marie-Christine; Espina, Carolina; Key, Timothy J; Leitzmann, Michael; Norat, Teresa; Powers, Hilary; Wiseman, Martin; Romieu, Isabelle

    2015-12-01

    Alcohol consumption is the third leading risk factor for disease and mortality in Europe. The International Agency for Research on Cancer (IARC) Monographs provide strengthened evidence that the consumption of alcoholic beverages is causally associated with cancers of the oral cavity, pharynx, larynx, oesophagus, liver, colorectum and female breast, even for low and moderate alcohol intakes. The risk of cancer increases in a dose-dependent manner, and the higher the amount of alcohol consumed, the higher the risk of developing cancer. Several biological mechanisms explain the carcinogenicity of alcohol; among them, ethanol and its genotoxic metabolite acetaldehyde play a major role. Taking all this evidence into account, a recommendation of the 4th edition of the European Code against Cancer (ECAC) is: "If you drink alcohol of any type, limit your intake. Not drinking alcohol is better for cancer prevention." PMID:26115567

  5. General Chemistry Collection for Students (CD-ROM), Abstract of Special Issue 16, 4th Edition

    NASA Astrophysics Data System (ADS)

    2000-07-01

    The General Chemistry Collection contains both new and previously published JCE Software programs that are intended for use by introductory-level chemistry students. These peer-reviewed programs for Macintosh and for Windows are available on a single CD-ROM for convenient distribution to and access by students, and the CD may be adopted for students to purchase as they would a textbook. General Chemistry Collection covers a broad range of topics providing students with interesting information, tutorials, and simulations that will be useful to them as they study chemistry for the first time. There are 22 programs included in the General Chemistry Collection 4th Edition. Their titles and the general chemistry topics they cover are listed in Table 1. Features in This Edition General Chemistry Collection, 4th edition includes:

    • Lessons for Introductory Chemistry and INQUAL-S, two new programs not previously published by JCE Software (abstracts appear below)
    • Writing Electron Dot Structures (1) and Viscosity Measurement: A Virtual Experiment for Windows (2), two programs published individually by JCE Software
    • Periodic Table Live! LE, a limited edition of Periodic Table Live!, 2nd Edition (3) (this replaces Chemistry Navigator (4) and Illustrated Periodic Table (5))
    • Many of the programs from previous editions (6)1
    Hardware and Software Requirements System requirements are given in Table 2. Some programs have additional requirements. See the individual program abstracts at JCE Online, or documentation included on the CD-ROM for more specific information. Licensing and Discounts for Adoptions The General Chemistry Collection is intended for use by individual students. Institutions and faculty members may adopt General Chemistry Collection 4th Edition as they would a textbook. We can arrange for CDs to be packaged with laboratory manuals or other course materials or to be sold for direct distribution to students through the campus

  6. Quark masses and mixings in the RS1 model with a condensing 4th generation

    NASA Astrophysics Data System (ADS)

    Hernández, A. E. Cárcamo; Dib, Claudio O.; Neill, Nicolás A.; Zerwekh, Alfonso R.

    2012-02-01

    We study the hierarchy of quark masses and mixings in a model based on a 5-dimensional spacetime with constant curvature of Randall-Sundrum type with two branes, where the Electroweak Symmetry Breaking is caused dynamically by the condensation of a 4th generation of quarks, due to underlying physics from the 5D bulk and the first KK gluons. We first study the hierarchy of quark masses and mixings that can be obtained from purely adjusting the profile localizations, finding that realistic masses are not reproduced unless non trivial hierarchies of underlying 4-fermion interactions from the bulk are included. Then we study global U(1) symmetries that can be imposed in order to obtain non-symmetric modified Fritzsch-like textures in the mass matrices that reproduce reasonably well quark masses and CKM mixings.

  7. Breakthrough in cardiac arrest: reports from the 4th Paris International Conference.

    PubMed

    Kudenchuk, Peter J; Sandroni, Claudio; Drinhaus, Hendrik R; Böttiger, Bernd W; Cariou, Alain; Sunde, Kjetil; Dworschak, Martin; Taccone, Fabio Silvio; Deye, Nicolas; Friberg, Hans; Laureys, Steven; Ledoux, Didier; Oddo, Mauro; Legriel, Stéphane; Hantson, Philippe; Diehl, Jean-Luc; Laterre, Pierre-Francois

    2015-12-01

    Jean-Luc Diehl The French Intensive Care Society organized on 5th and 6th June 2014 its 4th "Paris International Conference in Intensive Care", whose principle is to bring together the best international experts on a hot topic in critical care medicine. The 2014 theme was "Breakthrough in cardiac arrest", with many high-quality updates on epidemiology, public health data, pre-hospital and in-ICU cares. The present review includes short summaries of the major presentations, classified into six main chapters: Epidemiology of CA Pre-hospital management Post-resuscitation management: targeted temperature management Post-resuscitation management: optimizing organ perfusion and metabolic parameters Neurological assessment of brain damages Public healthcare. PMID:26380990

  8. The 4th annual European League Against Rheumatism congress in Lisbon: a personal perspective

    PubMed Central

    Wollheim, Frank A

    2004-01-01

    The 4th annual European League Against Rheumatism congress, held in Lisbon, 18–21 June 2003, had a record turnout of more than 8600 delegates and the abstract submissions increased to 2600. A heat wave and a somewhat substandard venue hampered some of the activities, notably the poster sessions. The scientific program was comprehensive and of a high class, and it was organized in 10–12 parallel sessions. The European League Against Rheumatism standing committees are expanding their activities and stimulating European cooperation (e.g. by creating databases and guidelines, and by starting research programs). The standing committees presented several areas where European cooperative work is in progress. Advances in drug therapy were a prominent theme and were well presented. Commercialism remains a problem for this meeting as for other similar large meetings, where satellite symposia surround the scientific program of the congress and often duplicate this. PMID:14979931

  9. FAST DISPLACEMENT PROBABILITY PROFILE APPROXIMATION FROM HARDI USING 4TH-ORDER TENSORS.

    PubMed

    Barmpoutis, Angelos; Vemuri, Baba C; Forder, John R

    2008-05-14

    Cartesian tensor basis have been widely used to approximate spherical functions. In Medical Imaging, tensors of various orders have been used to model the diffusivity function in Diffusion-weighted MRI data sets. However, it is known that the peaks of the diffusivity do not correspond to orientations of the underlying fibers and hence the displacement probability profiles should be employed instead. In this paper, we present a novel representation of the probability profile by a 4(th) order tensor, which is a smooth spherical function that can approximate single-fibers as well as multiple-fiber structures. We also present a method for efficiently estimating the unknown tensor coefficients of the probability profile directly from a given high-angular resolution diffusion-weighted (HARDI) data set. The accuracy of our model is validated by experiments on synthetic and real HARDI datasets from a fixed rat spinal cord. PMID:20046536

  10. Report on the 4th International IUPAP Women in Physics Conference

    NASA Astrophysics Data System (ADS)

    Correa, Cynthia

    2011-10-01

    Stellenbosch, South Africa was the site of the 4^th International Union of Pure and Applied Physics (IUPAP) International Conference on Women in Physics, which took place on April 5^th-8^th. This conference brought together the diverse contributions of 250 female physicist attendees from nearly 60 countries worldwide to dissect the challenges faced by female physicists worldwide and to propose strategies to attract and retain more girls and women to the field. Having served as a member of the U.S. Delegation, I will discuss the resolutions reached and highlight the most important results of Global Survey of Physicists, where nearly 15,000 physicists shine light on how gender affects their lives and careers.

  11. Food-based Science Curriculum Increases 4(th) Graders Multidisciplinary Science Knowledge.

    PubMed

    Hovland, Jana A; Carraway-Stage, Virginia G; Cela, Artenida; Collins, Caitlin; Díaz, Sebastián R; Collins, Angelo; Duffrin, Melani W

    2013-10-01

    Health professionals and policymakers are asking educators to place more emphasis on food and nutrition education. Integrating these topics into science curricula using hand-on, food-based activities may strengthen students' understanding of science concepts. The Food, Math, and Science Teaching Enhancement Resource (FoodMASTER) Initiative is a compilation of programs aimed at using food as a tool to teach mathematics and science. Previous studies have shown that students experiencing the FoodMASTER curriculum were very excited about the activities, became increasingly interested in the subject matter of food, and were able to conduct scientific observations. The purpose of this study was to: 1) assess 4(th) graders food-related multidisciplinary science knowledge, and 2) compare gains in food-related science knowledge after implementation of an integrated, food-based curriculum. During the 2009-2010 school year, FoodMASTER researchers implemented a hands-on, food-based intermediate curriculum in eighteen 4(th) grade classrooms in Ohio (n=9) and North Carolina (n=9). Sixteen classrooms in Ohio (n=8) and North Carolina (n=8), following their standard science curricula, served as comparison classrooms. Students completed a researcher-developed science knowledge exam, consisting of 13 multiple-choice questions administered pre- and post-test. Only subjects with pre- and post-test scores were entered into the sample (Intervention n=343; Control n=237). No significant differences were observed between groups at pre-test. At post-test, the intervention group scored (9.95±2.00) significantly higher (p=.000) than the control group (8.84±2.37) on a 13-point scale. These findings suggest the FoodMASTER intermediate curriculum is more effective than a standard science curriculum in increasing students' multidisciplinary science knowledge related to food. PMID:25152539

  12. Report of the 4th World Climate Research Programme International Conference on Reanalyses

    NASA Technical Reports Server (NTRS)

    Bosilovich, Michael G.; Rixen, Michel; van Oevelen, Peter; Asrar, Ghassem; Compo, Gilbert; Onogi, Kazutoshi; Simmons, Adrian; Trenberth, Kevin; Behringer, Dave; Bhuiyan, Tanvir Hossain; Capps, Shannon; Chaudhuri, Ayan; Chen, Junye; Chen, Linling; Colasacco-Thumm, Nicole; Escobar, Maria Gabriela; Ferguson, Craig R.; Ishibashi, Toshiyuki; Liberato, Margarida L. R.; Meng, Jesse; Molod, Andrea; Poli, Paul; Roundy, Joshua; Willett, Kate; Wollen, Jack

    2012-01-01

    The 4th WCRP International Conference on Reanalyses provided an opportunity for the international community to review and discuss the observational and modelling research, as well as process studies and uncertainties associated with reanalysis of the Earth System and its components. Characterizing the uncertainty and quality of reanalyses is a task that reaches far beyond the international community of producers, and into the interdisciplinary research community, especially those using reanalysis products in their research and applications. Reanalyses have progressed greatly even in the last 5 years, and newer ideas, projects and data are coming forward. While reanalysis has typically been carried out for the individual domains of atmosphere, ocean and land, it is now moving towards coupling using Earth system models. Observations are being reprocessed and they are providing improved quality for use in reanalysis. New applications are being investigated, and the need for climate reanalyses is as strong as ever. At the heart of it all, new investigators are exploring the possibilities for reanalysis, and developing new ideas in research and applications. Given the many centres creating reanalyses products (e.g. ocean, land and cryosphere research centres as well as NWP and atmospheric centers), and the development of new ideas (e.g. families of reanalyses), the total number of reanalyses is increasing greatly, with new and innovative diagnostics and output data. The need for reanalysis data is growing steadily, and likewise, the need for open discussion and comment on the data. The 4th Conference was convened to provide a forum for constructive discussion on the objectives, strengths and weaknesses of reanalyses, indicating potential development paths for the future.

  13. European Code against Cancer 4th Edition: Medical exposures, including hormone therapy, and cancer.

    PubMed

    Friis, Søren; Kesminiene, Ausrele; Espina, Carolina; Auvinen, Anssi; Straif, Kurt; Schüz, Joachim

    2015-12-01

    The 4th edition of the European Code against Cancer recommends limiting - or avoiding when possible - the use of hormone replacement therapy (HRT) because of the increased risk of cancer, nevertheless acknowledging that prescription of HRT may be indicated under certain medical conditions. Current evidence shows that HRT, generally prescribed as menopausal hormone therapy, is associated with an increased risk of cancers of the breast, endometrium, and ovary, with the risk pattern depending on factors such as the type of therapy (oestrogen-only or combined oestrogen-progestogen), duration of treatment, and initiation according to the time of menopause. Carcinogenicity has also been established for anti-neoplastic agents used in cancer therapy, immunosuppressants, oestrogen-progestogen contraceptives, and tamoxifen. Medical use of ionising radiation, an established carcinogen, can provide major health benefits; however, prudent practices need to be in place, with procedures and techniques providing the needed diagnostic information or therapeutic gain with the lowest possible radiation exposure. For pharmaceutical drugs and medical radiation exposure with convincing evidence on their carcinogenicity, health benefits have to be balanced against the risks; potential increases in long-term cancer risk should be considered in the context of the often substantial and immediate health benefits from diagnosis and/or treatment. Thus, apart from HRT, no general recommendations on reducing cancer risk were given for carcinogenic drugs and medical radiation in the 4th edition of European Code against Cancer. It is crucial that the application of these measures relies on medical expertise and thorough benefit-risk evaluation. This also pertains to cancer-preventive drugs, and self-medication with aspirin or other potential chemopreventive drugs is strongly discouraged because of the possibility of serious, potentially lethal, adverse events. PMID:26390952

  14. Food-based Science Curriculum Increases 4th Graders Multidisciplinary Science Knowledge

    PubMed Central

    Hovland, Jana A.; Carraway-Stage, Virginia G.; Cela, Artenida; Collins, Caitlin; Díaz, Sebastián R.; Collins, Angelo; Duffrin, Melani W.

    2013-01-01

    Health professionals and policymakers are asking educators to place more emphasis on food and nutrition education. Integrating these topics into science curricula using hand-on, food-based activities may strengthen students’ understanding of science concepts. The Food, Math, and Science Teaching Enhancement Resource (FoodMASTER) Initiative is a compilation of programs aimed at using food as a tool to teach mathematics and science. Previous studies have shown that students experiencing the FoodMASTER curriculum were very excited about the activities, became increasingly interested in the subject matter of food, and were able to conduct scientific observations. The purpose of this study was to: 1) assess 4th graders food-related multidisciplinary science knowledge, and 2) compare gains in food-related science knowledge after implementation of an integrated, food-based curriculum. During the 2009–2010 school year, FoodMASTER researchers implemented a hands-on, food-based intermediate curriculum in eighteen 4th grade classrooms in Ohio (n=9) and North Carolina (n=9). Sixteen classrooms in Ohio (n=8) and North Carolina (n=8), following their standard science curricula, served as comparison classrooms. Students completed a researcher-developed science knowledge exam, consisting of 13 multiple-choice questions administered pre- and post-test. Only subjects with pre- and post-test scores were entered into the sample (Intervention n=343; Control n=237). No significant differences were observed between groups at pre-test. At post-test, the intervention group scored (9.95±2.00) significantly higher (p=.000) than the control group (8.84±2.37) on a 13-point scale. These findings suggest the FoodMASTER intermediate curriculum is more effective than a standard science curriculum in increasing students’ multidisciplinary science knowledge related to food. PMID:25152539

  15. Calculation of gas turbine characteristic

    NASA Astrophysics Data System (ADS)

    Mamaev, B. I.; Murashko, V. L.

    2016-04-01

    The reasons and regularities of vapor flow and turbine parameter variation depending on the total pressure drop rate π* and rotor rotation frequency n are studied, as exemplified by a two-stage compressor turbine of a power-generating gas turbine installation. The turbine characteristic is calculated in a wide range of mode parameters using the method in which analytical dependences provide high accuracy for the calculated flow output angle and different types of gas dynamic losses are determined with account of the influence of blade row geometry, blade surface roughness, angles, compressibility, Reynolds number, and flow turbulence. The method provides satisfactory agreement of results of calculation and turbine testing. In the design mode, the operation conditions for the blade rows are favorable, the flow output velocities are close to the optimal ones, the angles of incidence are small, and the flow "choking" modes (with respect to consumption) in the rows are absent. High performance and a nearly axial flow behind the turbine are obtained. Reduction of the rotor rotation frequency and variation of the pressure drop change the flow parameters, the parameters of the stages and the turbine, as well as the form of the characteristic. In particular, for decreased n, nonmonotonic variation of the second stage reactivity with increasing π* is observed. It is demonstrated that the turbine characteristic is mainly determined by the influence of the angles of incidence and the velocity at the output of the rows on the losses and the flow output angle. The account of the growing flow output angle due to the positive angle of incidence for decreased rotation frequencies results in a considerable change of the characteristic: poorer performance, redistribution of the pressure drop at the stages, and change of reactivities, growth of the turbine capacity, and change of the angle and flow velocity behind the turbine.

  16. Conditions for the generation of cytotoxic CD4(+) Th cells that enhance CD8(+) CTL-mediated tumor regression.

    PubMed

    Li, Kunyu; Baird, Margaret; Yang, Jianping; Jackson, Chris; Ronchese, Franca; Young, Sarah

    2016-08-01

    Adoptive cell therapies (ACTs) using tumor-reactive T cells have shown clinical benefit and potential for cancer treatment. While the majority of the current ACT are focused on using CD8(+) cytotoxic T lymphocytes (CTL), others have shown that the presence of tumor-reactive CD4(+) T helper (Th) cells can greatly enhance the anti-tumor activity of CD8(+) CTL. However, difficulties in obtaining adequate numbers of CD4(+) Th cells through in vitro expansion can limit the application of CD4 Th cells in ACT. This study aims to optimize the culture conditions for mouse CD4 T cells to provide basic information for animal studies of ACT using CD4 T cells. Taking advantage of the antigen-specificity of CD4(+) Th cells from OT-II transgenic mice, we examined different methodologies for generating antigen-specific CD4(+) Th1 cells in vitro. We found that cells grown in complete advanced-DMEM/F12 medium supplemented with low-dose IL-2 and IL-7 induced substantial cell expansion. These Th cells were Th1-like, as they expressed multiple Th1-cytokines and exhibited antigen-specific cytotoxicity. In addition co-transfer of these CD4(+) Th1-like cells with CD8(+) CTL significantly enhanced tumor regression, leading to complete cure in 80% of mice bearing established B16-OVA. These observations indicate that the CD4(+) Th1-like cells generated using the method we optimized are functionally active to eliminate their target cells, and can also assist CD8(+) CTL to enhance tumor regression. The findings of this study provide valuable data for further research into in vitro expansion of CD4(+) Th1-like cells, with potential applications to cancer treatment involving ACT. PMID:27588200

  17. Conditions for the generation of cytotoxic CD4+ Th cells that enhance CD8+ CTL-mediated tumor regression

    PubMed Central

    Li, Kunyu; Baird, Margaret; Yang, Jianping; Jackson, Chris; Ronchese, Franca; Young, Sarah

    2016-01-01

    Adoptive cell therapies (ACTs) using tumor-reactive T cells have shown clinical benefit and potential for cancer treatment. While the majority of the current ACT are focused on using CD8+ cytotoxic T lymphocytes (CTL), others have shown that the presence of tumor-reactive CD4+ T helper (Th) cells can greatly enhance the anti-tumor activity of CD8+ CTL. However, difficulties in obtaining adequate numbers of CD4+ Th cells through in vitro expansion can limit the application of CD4 Th cells in ACT. This study aims to optimize the culture conditions for mouse CD4 T cells to provide basic information for animal studies of ACT using CD4 T cells. Taking advantage of the antigen-specificity of CD4+ Th cells from OT-II transgenic mice, we examined different methodologies for generating antigen-specific CD4+ Th1 cells in vitro. We found that cells grown in complete advanced-DMEM/F12 medium supplemented with low-dose IL-2 and IL-7 induced substantial cell expansion. These Th cells were Th1-like, as they expressed multiple Th1-cytokines and exhibited antigen-specific cytotoxicity. In addition co-transfer of these CD4+ Th1-like cells with CD8+ CTL significantly enhanced tumor regression, leading to complete cure in 80% of mice bearing established B16-OVA. These observations indicate that the CD4+ Th1-like cells generated using the method we optimized are functionally active to eliminate their target cells, and can also assist CD8+ CTL to enhance tumor regression. The findings of this study provide valuable data for further research into in vitro expansion of CD4+ Th1-like cells, with potential applications to cancer treatment involving ACT. PMID:27588200

  18. PREFACE: 4th International Conference on Safe Production and Use of Nanomaterials (Nanosafe2014)

    NASA Astrophysics Data System (ADS)

    Tardif, F.; Damlencourt, J.-F.; Schuster, F.; Gaultier, V.

    2015-05-01

    This volume contains a collection of contributions presented at the 4th International Conference on Safe Production and Use of Nanomaterials (NANOSAFE 2014) held in Grenoble, France, from 18th to 20th November 2014. The issues of fast progress in the field of Nanosafety are up to the potential benefits that nanotechnology can bring to mankind. Making more efficient - more sustainable - easier to share mineral resources, increasing the yields of new energy technologies, enabling drugs that act selectively and locally are just few examples of the wide range of nanomaterial applications that currently benefit humanity. Nevertheless, the dynamic development of nanomaterials requires the adhesion from the general public who rightly demand major progresses in Nanosafety as a prerequisite. This is our exciting responsibility and challenge! Following the successful outcome of the three past international conferences on safe production and use of nanomaterials: Nanosafe 2008, 2010 and 2012, the organizing committee has the pleasure to welcoming you again to Minatec, Grenoble with some of the most famous specialists in the field. This year, two new topics have been added dealing with the "New Application of Nanomaterials" and "Nano-responsible Development" in addition to the usual issues addressed in previous Nanosafe conferences such as Expology, Detection and Characterization, Toxicology, Environmental Interactions, Nanomaterials Release, Life Cycle Analysis, Regulation and Standardization, Risk Management. The debates in 2012 proved highly successful so this formula has been kept in 2014 with 3 round tables: Nano-Responsible Development, Risks and Benefits for the Environment, Toxicology Progress. In this 4th edition, there were more than 330 registered participants from 28 different countries including 160 oral presentation covering the whole Nanosafety issues in 12 sessions, satellite workshops and round tables. This high number of participants makes this edition one of

  19. Continuum Kinetic Plasma Modeling Using a Conservative 4th-Order Method with AMR

    NASA Astrophysics Data System (ADS)

    Vogman, Genia; Colella, Phillip

    2012-10-01

    When the number of particles in a Debye sphere is large, a plasma can be accurately represented by a distribution function, which can be treated as a continuous incompressible fluid in phase space. In the most general case the evolution of such a distribution function is described by the 6D Boltzmann-Maxwell partial differential equation system. To address the challenges associated with solving a 6D hyperbolic governing equation, a simpler 3D Vlasov-Poisson system is considered. A 4th-order accurate Vlasov-Poisson model has been developed in one spatial and two velocity dimensions. The governing equation is cast in conservation law form and is solved with a finite volume representation. Adaptive mesh refinement (AMR) is used to allow for efficient use of computational resources while maintaining desired levels of resolution. The model employs a flux limiter to remedy non-physical effects such as numerical dispersion. The model is tested on the two-stream, beam-plasma, and Dory-Guest-Harris instabilities. All results are compared with linear theory.

  20. PREFACE: 4th National Conference on Processing and Characterization of Materials (NCPCM 2014)

    NASA Astrophysics Data System (ADS)

    2015-02-01

    This volume contains selected full length technical papers amongst forty oral presentations made in the 4th National Conference on Processing and Characterization of Materials (NCPCM 2014), NIT Rourkela, Rourkela, Odisha, India, December 5 - 6, 2014. The first conference of the NCPCM series was held at the same place in December 2011. Seeing the enthusiasm of the participants, it was decided to organize such conference in Rourkela every year. The basic idea was to establish a periodical national forum for multi-scale approaches in processing and characterization of materials in the eastern part of India. The conference NCPCM 2014 has successfully carried the tradition of previous conferences; more than fifty participants from twenty different organizations across India have registered. The conference was consisted of six technical sessions of about fifty contributory talks along with three keynote lectures. A metallography contest was also organized during the event. Out of these, thirty four best peer-reviewed contributions are published in this volume of IOP Conference Series: Materials Science and Engineering. We would like to thank all the contributors, members of the organizing committee, session chairs as well as colleagues and students who helped with the preparation of the conference and, particularly, with the preparation of this volume. We convey our heartiest gratitude to the sponsors and advertisers for their contribution.

  1. European Code against Cancer 4th Edition: 12 ways to reduce your cancer risk.

    PubMed

    Schüz, Joachim; Espina, Carolina; Villain, Patricia; Herrero, Rolando; Leon, Maria E; Minozzi, Silvia; Romieu, Isabelle; Segnan, Nereo; Wardle, Jane; Wiseman, Martin; Belardelli, Filippo; Bettcher, Douglas; Cavalli, Franco; Galea, Gauden; Lenoir, Gilbert; Martin-Moreno, Jose M; Nicula, Florian Alexandru; Olsen, Jørgen H; Patnick, Julietta; Primic-Zakelj, Maja; Puska, Pekka; van Leeuwen, Flora E; Wiestler, Otmar; Zatonski, Witold

    2015-12-01

    This overview describes the principles of the 4th edition of the European Code against Cancer and provides an introduction to the 12 recommendations to reduce cancer risk. Among the 504.6 million inhabitants of the member states of the European Union (EU28), there are annually 2.64 million new cancer cases and 1.28 million deaths from cancer. It is estimated that this cancer burden could be reduced by up to one half if scientific knowledge on causes of cancer could be translated into successful prevention. The Code is a preventive tool aimed to reduce the cancer burden by informing people how to avoid or reduce carcinogenic exposures, adopt behaviours to reduce the cancer risk, or to participate in organised intervention programmes. The Code should also form a base to guide national health policies in cancer prevention. The 12 recommendations are: not smoking or using other tobacco products; avoiding second-hand smoke; being a healthy body weight; encouraging physical activity; having a healthy diet; limiting alcohol consumption, with not drinking alcohol being better for cancer prevention; avoiding too much exposure to ultraviolet radiation; avoiding cancer-causing agents at the workplace; reducing exposure to high levels of radon; encouraging breastfeeding; limiting the use of hormone replacement therapy; participating in organised vaccination programmes against hepatitis B for newborns and human papillomavirus for girls; and participating in organised screening programmes for bowel cancer, breast cancer, and cervical cancer. PMID:26164654

  2. 4th-International Symposium on Ultrafast Surface Science - Final Report

    SciTech Connect

    Hrvoje Petek

    2005-01-26

    The 4-th International Symposium on Ultrafast Surface Dynamics (UDS4) was held at the Telluride Summer Research Center on June 22-27, 2003. The International Organizing Committee consisting of Hrvoje Petek (USA), Xiaoyang Zhu (USA), Pedro Echenique (Spain) and Maki Kawai (Japan) brought together a total of 51 participants 16 of whom were from Europe, 10 from Japan, and 25 from the USA. The focus of the conference was on ultrafast electron or light induced processes at well-defined surfaces. Ultrafast surface dynamics concerns the transfer of charge and energy at solid surfaces on the femtosecond time scale. These processes govern rates of fundamental steps in surface reactions, interfacial electron transfer in molecular electronics, and relaxation in spin transport. Recent developments in femtosecond laser technology make it possible to measure by a variety of nonlinear optical techniques directly in the time domain the microscopic rates underlying these interfacial processes. Parallel progress in scanning probe microscopy makes it possible at a single molecular level to perform the vibrational and electronic spectroscopy measurements, to induce reactions with tunneling electrons, and to observe their outcome. There is no doubt that successful development in the field of ultrafast surface dynamics will contribute to many important disciplines.

  3. Multiwavelength Analysis of a Moving Type-IV Radio Burst on 4th March 2012

    NASA Astrophysics Data System (ADS)

    Veluchamy, V.; Chen, Y.; Feng, S.; Du, G.; Song, H.; Kong, X.

    2015-12-01

    We performed a multiwavelength analysis of a moving Type-IV radio burst on 4th march 2012. The Type-IV radio burst is observed between 10:39 - 11:00 UT in the frequency range of 300 - 20 MHz. From the radio heliographic observation, the radio source of the type-IV burst is traced and their sky plane speed is estimated as ~ 370 km/s. A plasmoid structure is ejected during the impulsive phase of the flare, at the same time of the type-IV burst and the structure is clearly observed at SDO/AIA 131 Å channel. From this, we find that the radio source moves with the plasmoid. The high brightness temperature profile in the range of 108 - 109 K and the moderate polarization between -50 - 30 % supports the plasma emission mechanism. Further the differential emission measure (DEM) analysis will be carried out and their results will be presented to provide more evidence of the emission mechanism.

  4. European Code against Cancer 4th Edition: Ultraviolet radiation and cancer.

    PubMed

    Greinert, Rüdiger; de Vries, Esther; Erdmann, Friederike; Espina, Carolina; Auvinen, Anssi; Kesminiene, Ausrele; Schüz, Joachim

    2015-12-01

    Ultraviolet radiation (UVR) is part of the electromagnetic spectrum emitted naturally from the sun or from artificial sources such as tanning devices. Acute skin reactions induced by UVR exposure are erythema (skin reddening), or sunburn, and the acquisition of a suntan triggered by UVR-induced DNA damage. UVR exposure is the main cause of skin cancer, including cutaneous malignant melanoma, basal-cell carcinoma, and squamous-cell carcinoma. Skin cancer is the most common cancer in fair-skinned populations, and its incidence has increased steeply over recent decades. According to estimates for 2012, about 100,000 new cases of cutaneous melanoma and about 22,000 deaths from it occurred in Europe. The main mechanisms by which UVR causes cancer are well understood. Exposure during childhood appears to be particularly harmful. Exposure to UVR is a risk factor modifiable by individuals' behaviour. Excessive exposure from natural sources can be avoided by seeking shade when the sun is strongest, by wearing appropriate clothing, and by appropriately applying sunscreens if direct sunlight is unavoidable. Exposure from artificial sources can be completely avoided by not using sunbeds. Beneficial effects of sun or UVR exposure, such as for vitamin D production, can be fully achieved while still avoiding too much sun exposure and the use of sunbeds. Taking all the scientific evidence together, the recommendation of the 4th edition of the European Code Against Cancer for ultraviolet radiation is: "Avoid too much sun, especially for children. Use sun protection. Do not use sunbeds." PMID:26096748

  5. 4th annual primary care ethics conference: ethics education and lifelong learning

    PubMed Central

    Spicer, John; McKenzie-Edwards, Emma; Misselbrook, David

    2014-01-01

    Primary care ethics is a field of study that has recently found new life, with calls to establish the relevance of ethical discussion in general practice, to gather a body of literature and to carve out an intellectual space for primary care on the academic landscape of bioethics. In this report, we reflect on the key strands of the 4th primary care ethics conference held at the Royal Society of Medicine, on a theme of ethics education and lifelong learning: first, to produce insights that have relevance for policy and practice; and second, to illustrate the idea that not only is ethics relevant in primary care, but primary care is relevant in medical ethics. Core themes included the advantages and disadvantages of prescriptive ways of doing ethics in education, ethical reflection and potential risk to professional status, the need to deal with societal change and to take on board the insights gained from empirical work, whether this is about different kinds of fatherhood, or work on the causes of moral distress in healthcare workers. PMID:25949739

  6. Cutting orientations for non-complex parts in 4th axis machining

    NASA Astrophysics Data System (ADS)

    Osman Zahid, M. N.; Case, K.; Watts, D. M.

    2016-02-01

    The application of Computer Numerically Controlled (CNC) machining for Rapid Manufacturing processes (CNC-RM) exploits the innate potential of 4th axis machining. The use of an indexer allows the workpiece to be rotated to various orientations which directly increased the region accessible to the cutting tool. However, in order to avoid thin webs and preserve tool life, cutting must be executed with a minimum of three orientations even for geometrically simple parts. Recent findings have suggested the separation of cutting orientations into roughing and finishing operations. Thus, the selection of orientations in finishing processes becomes more flexible and independent. This study was conducted to identify the effects of using a minimum of two cutting orientations in finishing operations for CNC-RM applications. This method is only applicable for non-complex parts where all the features can be machined from two directions. The results of the study illustrate the positive effects of minimizing the number of orientations. Despite improvement in machining operations, the complexity in defining the cutting orientations was also reduced.

  7. European Code against Cancer 4th Edition: Ionising and non-ionising radiation and cancer.

    PubMed

    McColl, Neil; Auvinen, Anssi; Kesminiene, Ausrele; Espina, Carolina; Erdmann, Friederike; de Vries, Esther; Greinert, Rüdiger; Harrison, John; Schüz, Joachim

    2015-12-01

    Ionising radiation can transfer sufficient energy to ionise molecules, and this can lead to chemical changes, including DNA damage in cells. Key evidence for the carcinogenicity of ionising radiation comes from: follow-up studies of the survivors of the atomic bombings in Japan; other epidemiological studies of groups that have been exposed to radiation from medical, occupational or environmental sources; experimental animal studies; and studies of cellular responses to radiation. Considering exposure to environmental ionising radiation, inhalation of naturally occurring radon is the major source of radiation in the population - in doses orders of magnitude higher than those from nuclear power production or nuclear fallout. Indoor exposure to radon and its decay products is an important cause of lung cancer; radon may cause approximately one in ten lung cancers in Europe. Exposures to radon in buildings can be reduced via a three-step process of identifying those with potentially elevated radon levels, measuring radon levels, and reducing exposure by installation of remediation systems. In the 4th Edition of the European Code against Cancer it is therefore recommended to: "Find out if you are exposed to radiation from naturally high radon levels in your home. Take action to reduce high radon levels". Non-ionising types of radiation (those with insufficient energy to ionise molecules) - including extremely low-frequency electric and magnetic fields as well as radiofrequency electromagnetic fields - are not an established cause of cancer and are therefore not addressed in the recommendations to reduce cancer risk. PMID:26126928

  8. Project ASTRO: Local Coalitions for Bringing Astronomers to 4th - 9th Grade Classrooms

    NASA Astrophysics Data System (ADS)

    Fraknoi, Andrew

    1998-05-01

    We report on Project ASTRO, an NSF and NASA funded program that now links professional and amateur astronomers with local 4th through 9th grade teachers in 10 sites around the country. Each site matches and trains about 20-25 astronomer-teacher partnerships per year, focusing on hands-on, age-appropriate activities, demonstrations of the scientific method, as well as family and community outreach. Over 10,000 copies of the project's 813-page UNIVERSE AT YOUR FINGERTIPS resource and activity notebook (published by the A.S.P) are now in use in educational institututions around the world. The project's HOW-TO-MANUAL is being used as a practical guide to establishing astronomer-teacher partnerships where no formal ASTRO site exists, and a 12-minute video explaining and demonstrating the project is also available. In each of the ten sites, a coalition of educational and scientific institutions is assisting the project with in-kind donations, publicity, personnel, training, materials, etc. We are conducting an experiment (at the behest of NSF) to see to what degree the sites can become self-supporting over time. (One site, in Salt Lake City, has already received full funding from a local foundation.) We will discuss the progress of the project and will have a variety of sample materials available, including our annotated catalog of national astronomy and space science education projects (see associated URL).

  9. A Teaching Model for Scaffolding 4th Grade Students' Scientific Explanation Writing

    NASA Astrophysics Data System (ADS)

    Yang, Hsiu-Ting; Wang, Kuo-Hua

    2014-08-01

    Improving students scientific explanations is one major goal of science education. Both writing activities and concept mapping are reported as effective strategies for enhancing student learning of science. The purpose of this study was to examine the effect of a teaching model, named the DCI model, which integrates a Descriptive explanation writing activity, Concept mapping, and an Interpretive explanation writing activity, is introduced in a 4th grade science class to see if it would improve students' scientific explanations and understanding. A quasi-experimental design, including a non-randomized comparison group and a pre- and post-test design, was adopted for this study. An experimental group of 25 students were taught using the DCI teaching model, while a comparison group received a traditional lecture teaching. A rubric and content analysis was used to assess students' scientific explanations. The independent sample t test was used to measure difference in conceptual understanding between the two groups, before and after instruction. Then, the paired t test analysis was used to understand the promotion of the DCI teaching model. The results showed that students in the experimental group performed better than students in the comparison group, both in scientific concept understanding and explanation. Suggestions for using concept mapping and writing activities (the DCI teaching model) in science classes are provided in this study.

  10. Need for Specific Sugar-Sweetened Beverage Lessons for 4th and 5th Graders

    PubMed Central

    Bea, Jennifer W.; Jacobs, Laurel; Waits, Juanita; Hartz, Vern; Martinez, Stephanie H.; Standfast, Rebecca D.; Farrell, Vanessa A.; Bawden, Margine; Whitmer, Evelyn; Misner, Scottie

    2015-01-01

    Objective Consumption of sugar-sweetened beverages (SSB) is linked to obesity. We hypothesized that school-based nutrition education would decrease SSB consumption. Design Self-selected interventional cohort with random selection for pre and post measurements Setting Arizona SNAP-Ed eligible schools Participants Randomly selected (9%) 4th and 5th grade classroom students Intervention The University of Arizona Nutrition Network (UANN) provided general nutrition education training and materials to teachers, to be delivered to their students. The UANN administered behavioral questionnaires to students in both Fall and Spring. Main Outcome Measure(s) Change in SSB consumption Analyses Descriptive statistics were computed for student demographics and beverage consumption on the day prior to testing. Paired t-tests evaluated change in classroom averages. Linear regression assessed potential correlates of SSB consumption. Results Fall mean SSB consumption was 1.1 (±0.2) times; mean milk and water intake were 1.6 (±0.2) and 5.2 (±0.7) times, respectively. Beverage consumption increased (3.2%) in springtime, with increased SSBs (14.4%) accounting for the majority (p=0.006). Change in SSB consumption was negatively associated with baseline SSB and water consumption, but positively associated with baseline milk fat (p≤0.05). Conclusions and Implications The results suggest the need for beverage specific education to encourage children to consume more healthful beverages in warmer weather. PMID:25239840

  11. Steam Turbines

    NASA Technical Reports Server (NTRS)

    1981-01-01

    Turbonetics Energy, Inc.'s steam turbines are used as power generating systems in the oil and gas, chemical, pharmaceuticals, metals and mining, and pulp and paper industries. The Turbonetics line benefited from use of NASA research data on radial inflow steam turbines and from company contact with personnel of Lewis Research Center, also use of Lewis-developed computer programs to determine performance characteristics of turbines.

  12. Variable stator radial turbine

    NASA Technical Reports Server (NTRS)

    Rogo, C.; Hajek, T.; Chen, A. G.

    1984-01-01

    A radial turbine stage with a variable area nozzle was investigated. A high work capacity turbine design with a known high performance base was modified to accept a fixed vane stagger angle moveable sidewall nozzle. The nozzle area was varied by moving the forward and rearward sidewalls. Diffusing and accelerating rotor inlet ramps were evaluated in combinations with hub and shroud rotor exit rings. Performance of contoured sidewalls and the location of the sidewall split line with respect to the rotor inlet was compared to the baseline. Performance and rotor exit survey data are presented for 31 different geometries. Detail survey data at the nozzle exit are given in contour plot format for five configurations. A data base is provided for a variable geometry concept that is a viable alternative to the more common pivoted vane variable geometry radial turbine.

  13. Closed-loop air cooling system for a turbine engine

    DOEpatents

    North, William Edward

    2000-01-01

    Method and apparatus are disclosed for providing a closed-loop air cooling system for a turbine engine. The method and apparatus provide for bleeding pressurized air from a gas turbine engine compressor for use in cooling the turbine components. The compressed air is cascaded through the various stages of the turbine. At each stage a portion of the compressed air is returned to the compressor where useful work is recovered.

  14. The Ratio of 2nd to 4th Digit Length in Korean Alcohol-dependent Patients

    PubMed Central

    Han, Changwoo; Bae, Hwallip; Lee, Yu-Sang; Won, Sung-Doo; Kim, Dai Jin

    2016-01-01

    Objective The ratio of 2nd to 4th digit length (2D:4D) is a sexually dimorphic trait. Men have a relatively shorter second digit than fourth digit. This ratio is thought to be influenced by higher prenatal testosterone level or greater sensitivity to androgen. The purpose of this study is to investigate the relationship between alcohol dependence and 2D:4D in a Korean sample and whether 2D:4D can be a biologic marker in alcohol dependence. Methods In this study, we recruited 87 male patients with alcohol dependence from the alcohol center of one psychiatric hospital and 52 healthy male volunteers who were all employees in the same hospital as controls. We captured images of the right and left hands of patients and controls using a scanner and extracted data with a graphics program. We measured the 2D:4D of each hand and compared the alcohol dependence group with the control group. We analyzed these ratios using an independent-samples t-test. Results The mean 2D:4D of patients was 0.934 (right hand) and 0.942 (left hand), while the mean 2D:4D of controls was 0.956 (right hand) and 0.958 (left hand). Values for both hands were significantly lower for patients than controls (p<0.001, right hand; p=0.004, left hand). Conclusion Patients who are alcohol dependent have a significantly lower 2D:4D than controls, similar to the results of previous studies, which suggest that a higher prenatal testosterone level in the gonadal period is related to alcoholism. Furthermore, 2D:4D is a possible predictive marker of alcohol dependence. PMID:27121425

  15. PREFACE: 4th International Workshop on Statistical Physics and Mathematics for Complex Systems (SPMCS)

    NASA Astrophysics Data System (ADS)

    Wang, Alexandre; Abe, Sumiyoshi; Li, Wei

    2015-04-01

    This volume contains 24 contributed papers presented at the 4th International Workshop on Statistical Physics and Mathematics for Complex Systems (SPMCS) held during October 12-16, 2014 in Yichang, China. Each paper was peer-reviewed by at least one referee chosen from a distinguished international panel. The previous three workshops of this series were organized in 2008, 2010, and 2012, in Le Mans, France, Wuhan, China, and Kazan, Russia, respectively. The SPMCS international workshop series is destined mainly to communicate and exchange research results and information on the fundamental challenges and questions in the vanguard of statistical physics, thermodynamics and mathematics for complex systems. More specifically, the topics of interest touch, but are not limited to, the following: • Fundamental aspects in the application of statistical physics and thermodynamics to complex systems and their modeling • Finite size and non-extensive system • Fluctuation theorems and equalities, quantum thermodynamics • Variational principle for random dynamics • Fractal geometry, fractional mathematics More than 50 participants from 7 countries participated in SPMCS-2014. 35 oral contributions were presented at the workshop. We would like to take this opportunity to thank the members of the Scientific Program Committee, many of whom acted as reviewers of the papers and responded promptly. We would also like to thank the organizing committee, the session chairs, the technicians and the students for the smooth running of the whole workshop. Thanks also go to China Three Gorges University who provided generous support for the conference venue, as well as exquisite refreshments for the tea breaks. The workshop was also partially supported by Central China Normal University and the Programme of Introducing Talents of Discipline to Universities under grant NO. B08033. Special thanks are due to Ms Juy Zhu who has done excellent editing work with great effort.

  16. 4th International Conference on Energy and Environment 2013 (ICEE 2013)

    NASA Astrophysics Data System (ADS)

    Chakrabarty, Chandan Kumar; Shamsuddin, Abd Halim Bin; Ahmad, Ibrahim Bin; Desa, Mohamed Nor Bin Mohamed; Din, Norashidah Bte Md; Bte Mohd, Lariyah; Hamid, Nasri A.; See, Ong Hang; Hafiz Nagi, Farrukh; Yong, Lee Choon; Pasupuleti, Jagadeesh; Mei, Goh Su; Abdullah, Fairuz Bin; Satgunam, Meenaloshini

    2013-06-01

    The 4th International Conference on Energy & Environment 2013 (ICEE2013) was organized by the Universiti Tenaga Nasional (UNITEN) to provide a platform for creating and sharing ideas among engineers, researchers, scientists, industrialists and students in sustainable green energy and technologies. The theme 'Shaping a Sustainable Future through Advancement in Green Energy Technology' is in line with the University's vision to be a leading global energy university that shapes a sustainable future. The general scopes of the conference are renewable energy, smart grid, green technology, energy policies and economics, sustainable green energy and environment, sustainable education, international cooperation and innovation and technology transfer. Five international keynote speakers delivered their speeches in specialized areas of green energy technology and sustainability. In addition, the conference highlights several special parallel sessions by notable invited presenters in their niche areas, which are: Hybrid Energy Power Quality & Distributed Energy Smart Grid Nuclear Power & Technologies Geohazard Management Greener Environment for Sustainability Advances in Computational Fluid Dynamics The research papers presented in ICEE2013 are included in this volume of IOP Conference Series: Earth and Environmental Science (EES). EES is abstracted and indexed in SCOPUS, GeoBase, GeoRef, Compendex, Inspec, Chemical Abstracts Service, NASA Astrophysics Data System, and International Nuclear Information System (INIS). With the comprehensive programme outline, the organizing committee hopes that the ICEE2013 was a notable intellectual sharing session for the research and academic community in Malaysia and regionally. The organizing committee expresses gratitude to the ICEE2013 delegates for their great support and contributions to the event.

  17. PREFACE: 4th International Conference on: Preservation and Conservation Issues in Digital Printing and Digital Photography

    NASA Astrophysics Data System (ADS)

    Fricker, A.; Green, P.

    2010-04-01

    These conference proceedings contain the written papers of the contributions presented at the 4th International Conference on: Preservation and Conservation Issues in Digital Printing and Digital Photography. The conference was held at the Institute of Physics, London, UK on 27th-28th May 2010. Previous conferences in this series took place in 2000, 2003 and 2006. The aim of this conference series is to inform those responsible for the preservation of digitally printed materials about developments in digital photography and printing technologies. We aim to examine progress in research on inks and substrates and their significance for conservation and preservation issues and techniques. We also hope to develop links between related industries and the conservation/preservation world. Research areas explored in this conference include current developments and future trends in digital printing and photographic technologies; the effect of environmental, storage and salvage conditions on the durability of digital prints and photographs; image processing techniques; image permanence considerations and standards for fastness, permanence and the role of scanning and file formats. We would like to thank all participants for their contribution to the conference programme and these proceedings. Our thanks go to Ms C. Gu and Mr M. Sandy for chairing conference sessions. We are also grateful to Dawn Stewart and the Institute of Physics Conference Team for their invaluable support and assistance in arranging the conference and reception. Finally we would like to extend our thanks to the Society of Imaging Science and Technology (IS&T) for their sponsorship support. The Editors Acknowledgements Conference Organising Committee: Ms A Fricker and Dr. P Green (London College of Communication, University of the Arts London). Proceedings edited and compiled by Ms A Fricker and Dr. P Green.

  18. European Code against Cancer 4th Edition: Environment, occupation and cancer.

    PubMed

    Espina, Carolina; Straif, Kurt; Friis, Søren; Kogevinas, Manolis; Saracci, Rodolfo; Vainio, Harri; Schüz, Joachim

    2015-12-01

    People are exposed throughout life to a wide range of environmental and occupational pollutants from different sources at home, in the workplace or in the general environment - exposures that normally cannot be directly controlled by the individual. Several chemicals, metals, dusts, fibres, and occupations have been established to be causally associated with an increased risk of specific cancers, such as cancers of the lung, skin and urinary bladder, and mesothelioma. Significant amounts of air pollutants - mainly from road transport and industry - continue to be emitted in the European Union (EU); an increased occurrence of lung cancer has been attributed to air pollution even in areas below the EU limits for daily air pollution. Additionally, a wide range of pesticides as well as industrial and household chemicals may lead to widespread human exposure, mainly through food and water. For most environmental pollutants, the most effective measures are regulations and community actions aimed at reducing and eliminating the exposures. Thus, it is imperative to raise awareness about environmental and occupational carcinogens in order to motivate individuals to be proactive in advocating protection and supporting initiatives aimed at reducing pollution. Regulations are not homogeneous across EU countries, and protective measures in the workplace are not used consistently by all workers all the time; compliance with regulations needs to be continuously monitored and enforced. Therefore, the recommendation on Environment and Occupation of the 4th edition of the European Code against Cancer, focusing on what individuals can do to reduce their cancer risk, reads: "In the workplace, protect yourself against cancer-causing substances by following health and safety instructions." PMID:26164655

  19. Learning Natural Selection in 4th Grade with Multi-Agent-Based Computational Models

    NASA Astrophysics Data System (ADS)

    Dickes, Amanda Catherine; Sengupta, Pratim

    2013-06-01

    In this paper, we investigate how elementary school students develop multi-level explanations of population dynamics in a simple predator-prey ecosystem, through scaffolded interactions with a multi-agent-based computational model (MABM). The term "agent" in an MABM indicates individual computational objects or actors (e.g., cars), and these agents obey simple rules assigned or manipulated by the user (e.g., speeding up, slowing down, etc.). It is the interactions between these agents, based on the rules assigned by the user, that give rise to emergent, aggregate-level behavior (e.g., formation and movement of the traffic jam). Natural selection is such an emergent phenomenon, which has been shown to be challenging for novices (K16 students) to understand. Whereas prior research on learning evolutionary phenomena with MABMs has typically focused on high school students and beyond, we investigate how elementary students (4th graders) develop multi-level explanations of some introductory aspects of natural selection—species differentiation and population change—through scaffolded interactions with an MABM that simulates predator-prey dynamics in a simple birds-butterflies ecosystem. We conducted a semi-clinical interview based study with ten participants, in which we focused on the following: a) identifying the nature of learners' initial interpretations of salient events or elements of the represented phenomena, b) identifying the roles these interpretations play in the development of their multi-level explanations, and c) how attending to different levels of the relevant phenomena can make explicit different mechanisms to the learners. In addition, our analysis also shows that although there were differences between high- and low-performing students (in terms of being able to explain population-level behaviors) in the pre-test, these differences disappeared in the post-test.

  20. 77 FR 39422 - Eighth Coast Guard District Annual Safety Zones; Niceville July 4th Fireworks Show; Boggy Bayou...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-07-03

    ... SECURITY Coast Guard 33 CFR Part 165 RIN 1625-AA00 Eighth Coast Guard District Annual Safety Zones; Niceville July 4th Fireworks Show; Boggy Bayou; Niceville, FL AGENCY: Coast Guard, DHS. ACTION: Notice of enforcement of regulation. SUMMARY: The Coast Guard will enforce a Safety Zone for the Niceville July...

  1. 75 FR 34374 - Safety Zone; Stockton Ports Baseball Club/City of Stockton, 4th of July Fireworks Display...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-17

    ... SECURITY Coast Guard 33 CFR Part 165 RIN 1625-AA00 Safety Zone; Stockton Ports Baseball Club/City of... Ports Baseball Club and the City of Stockton will sponsor the Stockton Ports Baseball Club/City of... Ports Baseball Club/City of Stockton 4th of July Fireworks Display, Stockton, CA. (a) Location....

  2. 78 FR 23869 - Safety Zone; Redwood City 4th of July Fireworks Show; Port of Redwood City, Redwood City, CA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-04-23

    ..., telephone 202-366-9826. SUPPLEMENTARY INFORMATION: Table of Acronyms DHS Department of Homeland Security FR... Federal Register (73 FR 3316). 4. Public Meeting We do not plan to hold public meetings on this proposed... SECURITY Coast Guard 33 CFR Part 165 RIN 1625-AA00 Safety Zone; Redwood City 4th of July Fireworks...

  3. 78 FR 39998 - Safety Zone; Grand Haven 4th of July Fireworks; Grand River; Grand Haven, MI

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-07-03

    ...-9826. SUPPLEMENTARY INFORMATION: Table of Acronyms DHS Department of Homeland Security FR Federal... SECURITY Coast Guard 33 CFR Part 165 RIN 1625-AA00 Safety Zone; Grand Haven 4th of July Fireworks; Grand... a State, local, or tribal government, in the aggregate, or by the private sector of...

  4. Examining General and Specific Factors in the Dimensionality of Oral Language and Reading in 4th-10th Grades

    ERIC Educational Resources Information Center

    Foorman, Barbara R.; Koon, Sharon; Petscher, Yaacov; Mitchell, Alison; Truckenmiller, Adrea

    2015-01-01

    The objective of this study was to explore dimensions of oral language and reading and their influence on reading comprehension in a relatively understudied population--adolescent readers in 4th through 10th grades. The current study employed latent variable modeling of decoding fluency, vocabulary, syntax, and reading comprehension so as to…

  5. 78 FR 23866 - Safety Zone; Crescent City 4th of July Fireworks; Crescent City Harbor, Crescent City, CA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-04-23

    .... SUPPLEMENTARY INFORMATION: Table of Acronyms DHS Department of Homeland Security FR Federal Register NPRM Notice... public dockets in the January 17, 2008, issue of the Federal Register (73 FR 3316). 4. Public Meeting We... SECURITY Coast Guard 33 CFR Part 165 RIN 1625-AA00 Safety Zone; Crescent City 4th of July...

  6. 75 FR 35294 - Safety Zone; Marquette 4th of July Fireworks, Marquette Harbor, Lake Superior, Marquette, MI

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-22

    ...The Coast Guard is establishing a temporary safety zone on Marquette Harbor, Lake Superior, Marquette, MI. This zone is intended to restrict vessels from a portion of Marquette Harbor during the Marquette 4th of July Fireworks display. This temporary safety zone is necessary to protect spectators and vessels from the hazards associated with a firework...

  7. 78 FR 39606 - Safety Zone; City of Menominee 4th of July Fireworks, Green Bay, Menominee, MI

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-07-02

    ... Security FR Federal Register NPRM Notice of Proposed Rulemaking TFR Temporary Final Rule A. Regulatory... SECURITY Coast Guard 33 CFR Part 165 RIN 1625-AA00 Safety Zone; City of Menominee 4th of July Fireworks... that may result in the expenditure by a State, local, or tribal government, in the aggregate, or by...

  8. Impacts of a Discussion-Based Academic Language Program on Classroom Interactions in 4th through 7th Grades

    ERIC Educational Resources Information Center

    LaRusso, Maria; Jones, Stephanie M.; Kim, Ha Yeon; Kim, James; Donovan, Suzanne; Snow, Catherine

    2016-01-01

    This paper presents an exploratory analysis of treatment-control differences in the quality of classroom interactions in 4th through 7th grade urban classrooms. Word Generation (WG) is a research-based academic language program for middle school students designed to teach novel vocabulary and literacy through language arts, math, science, and…

  9. 76 FR 38015 - Safety Zones; July 4th Weekend Fireworks Displays Within the Captain of the Port St. Petersburg...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-29

    ... SECURITY Coast Guard 33 CFR Part 165 RIN 1625-AA00 Safety Zones; July 4th Weekend Fireworks Displays Within... under Executive Order 13132, Federalism, if it has a substantial direct effect on State or local governments and would either preempt State law or impose a substantial direct cost of compliance on them....

  10. Teacher Implementation of Reform-Based Mathematics and Implications for Algebra Readiness: A Qualitative Study of 4th Grade Classrooms

    ERIC Educational Resources Information Center

    Sher, Stephen Korb

    2011-01-01

    This study looked at 4th grade classrooms to see "how" teachers implement NCTM standards-based or reform-based mathematics instruction and then analyzed it for the capacity to improve students' "algebra readiness." The qualitative study was based on classroom observations, teacher and administrator interviews, and teacher surveys. The study took…

  11. Proceedings of the International Conference on Educational Data Mining (EDM) (4th, Eindhoven, the Netherlands, July 6-8, 2011)

    ERIC Educational Resources Information Center

    Pechenizkiy, Mykola; Calders, Toon; Conati, Cristina; Ventura, Sebastian; Romero, Cristobal; Stamper, John

    2011-01-01

    The 4th International Conference on Educational Data Mining (EDM 2011) brings together researchers from computer science, education, psychology, psychometrics, and statistics to analyze large datasets to answer educational research questions. The conference, held in Eindhoven, The Netherlands, July 6-9, 2011, follows the three previous editions…

  12. Comparing Science Learning among 4th-, 5th-, and 6th-Grade Students: STS versus Textbook-Based Instruction

    ERIC Educational Resources Information Center

    Yager, Robert E.; Choi, AeRan; Yager, Stuart O.; Akcay, Hakan

    2009-01-01

    Fifteen 4th-, 5th-, and 6th-grade teachers from five school districts each taught two sections of science--one with a Science-Technology-Society (STS) approach and the other with a more traditional textbook approach in which basic science concepts were the major organizers. Local, current, and personally relevant issues provided the context and…

  13. The Influence of Neighborhood Density and Word Frequency on Phoneme Awareness in 2nd and 4th Grades

    ERIC Educational Resources Information Center

    Hogan, Tiffany P.; Bowles, Ryan P.; Catts, Hugh W.; Storkel, Holly L.

    2011-01-01

    Purpose: The purpose of this study was to test the hypothesis that two lexical characteristics--neighborhood density and word frequency--interact to influence performance on phoneme awareness tasks. Methods: Phoneme awareness was examined in a large, longitudinal dataset of 2nd and 4th grade children. Using linear logistic test model, the relation…

  14. 4th Annual SATN Conference 2011: Curriculum Transformation at Universities of Technology: Towards Development of New Generation Universities

    ERIC Educational Resources Information Center

    Mthembu, T.

    2012-01-01

    The South African Technology Network (SATN) would like to thank the Editor of the "South African Journal of Higher Education" (SAJHE) for the opportunity to publish papers read at the 4th Annual SATN Conference that was hosted by Central University of Technology and held in Bloemfontein in November 2011. The journal makes it possible for…

  15. Communicating Science to Impact Learning? A Phenomenological Inquiry into 4th and 5th Graders' Perceptions of Science Information Sources

    ERIC Educational Resources Information Center

    Gelmez Burakgazi, Sevinc; Yildirim, Ali; Weeth Feinstein, Noah

    2016-01-01

    Rooted in science education and science communication studies, this study examines 4th and 5th grade students' perceptions of science information sources (SIS) and their use in communicating science to students. It combines situated learning theory with uses and gratifications theory in a qualitative phenomenological analysis. Data were gathered…

  16. Impact of a Health and Media Literacy Curriculum on 4th-Grade Girls: A Qualitative Study

    ERIC Educational Resources Information Center

    Fuller, Heidi A.; Damico, Amy M.; Rodgers, Shannon

    2004-01-01

    Recent research indicates that young girls are preoccupied with their body size and that the media may be a contributing factor. This study aimed to discover the impact of an interdisciplinary media literacy intervention curriculum on 4th-grade girls in an urban elementary school. The authors developed and implemented a series of lessons that…

  17. Native American Students' Understanding of Geologic Time Scale: 4th-8th Grade Ojibwe Students' Understanding of Earth's Geologic History

    ERIC Educational Resources Information Center

    Nam, Younkyeong; Karahan, Engin; Roehrig, Gillian

    2016-01-01

    Geologic time scale is a very important concept for understanding long-term earth system events such as climate change. This study examines forty-three 4th-8th grade Native American--particularly Ojibwe tribe--students' understanding of relative ordering and absolute time of Earth's significant geological and biological events. This study also…

  18. 76 FR 72957 - 4th Annual Trauma Spectrum Conference: Bridging the Gap Between Research and Clinical Practice of...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-11-28

    ... HUMAN SERVICES National Institutes of Health 4th Annual Trauma Spectrum Conference: Bridging the Gap Between Research and Clinical Practice of Psychological Health and Traumatic Brain Injury: Prevention... Psychological Health and Traumatic Brain Injury: Prevention, Diagnosis, Treatment and Recovery for the Iraq...

  19. Using Inquiry-Based Instruction to Teach Research Methods to 4th-Grade Students in an Urban Setting

    ERIC Educational Resources Information Center

    Hamm, Ellen M.; Cullen, Rebecca; Ciaravino, Melissa

    2013-01-01

    When a college professor who teaches research methods to graduate education students was approached by a local public urban elementary school to help them teach research skills to 4th-graders, it was thought that the process would be simple--take what we did at the college level and differentiate it for the childhood classroom. This article will…

  20. Characterization of HCV Specific CD4+Th17 Immunity in Recurrent Hepatitis C Induced Liver Allograft Fibrosis

    PubMed Central

    Basha, H. Ilias; Subramanian, Vijay; Seetharam, A.; Nath, D.S.; Ramachandran, S.; Anderson, C.D.; Shenoy, S.; Chapman, W.C.; Crippin, J.S.; Mohanakumar, T.

    2011-01-01

    Hepatitis C Virus (HCV) recurrence with accelerated fibrosis following orthotopic liver transplantation (OLT) is a universal phenomenon. To evaluate mechanisms contributing to HCV induced allograft fibrosis/cirrhosis, we investigated HCV specific CD4+Th17 cells and their induction in OLT recipients with recurrence utilizing 51 HCV+ OLT recipients, 15 healthy controls and 9 HCV- OLT recipients. Frequency of HCV specific CD4+ Tcells secreting IFN-γ, IL-17 and IL-10 was analyzed by ELISpot. Serum cytokines and chemokines were analyzed by LUMINEX. Recipients with recurrent HCV induced allograft inflammation and fibrosis/cirrhosis demonstrated a significant increase in frequency of HCV specific CD4+Th17 cells. Increased pro-inflammatory mediators (IL-17, IL-1β, IL-6, IL-8, MCP-1), decreased IFN-γ, and increased IL-4, IL-5 and IL-10 levels were identified. OLT recipients with allograft inflammation and fibrosis/cirrhosis demonstrated increased frequency of Foxp3+ regulatory T cells (Tregs) that inhibited HCV specific CD4+Th1 but not Th17 cells. This suggests that recurrent HCV infection in OLT recipients induces an inflammatory milieu characterized by increased IL-6, IL-1β and decreased IFN-γ which facilitates induction of HCV specific CD4+Th17 cells. These cells are resistant to suppression by Tregs and may mediate an inflammatory cascade leading to cirrhosis in OLT recipients following HCV recurrence. PMID:21446979

  1. 75 FR 38723 - Safety Zone; St. Ignace 4th of July Fireworks, East Moran Bay, Lake Huron, St. Ignace, MI

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-06

    ... SECURITY Coast Guard 33 CFR Part 165 RIN 1625-AA00 Safety Zone; St. Ignace 4th of July Fireworks, East Moran Bay, Lake Huron, St. Ignace, MI AGENCY: Coast Guard, DHS. ACTION: Temporary final rule. SUMMARY: The Coast Guard is establishing a temporary safety zone on East Moran Bay, Lake Huron, St....

  2. Turbine system

    DOEpatents

    McMahan, Kevin Weston; Dillard, Daniel Jackson

    2016-05-03

    A turbine system is disclosed. The turbine system includes a transition duct having an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The turbine system further includes a turbine section connected to the transition duct. The turbine section includes a plurality of shroud blocks at least partially defining a hot gas path, a plurality of buckets at least partially disposed in the hot gas path, and a plurality of nozzles at least partially disposed in the hot gas path. At least one of a shroud block, a bucket, or a nozzle includes means for withstanding high temperatures.

  3. FIB–SEM tomography of 4th generation PWA 1497 superalloy

    SciTech Connect

    Ziętara, Maciej Kruk, Adam Gruszczyński, Adam Czyrska-Filemonowicz, Aleksandra

    2014-01-15

    The effect of creep deformation on the microstructure of the PWA 1497 single crystal Ni-base superalloy developed for turbine blade applications was investigated. The aim of the present study was to characterize quantitatively a superalloy microstructure and subsequent development of rafted γ′ precipitates in the PWA 1497 during creep deformation at 982 °C and 248 MPa up to rupture. The PWA1497 microstructure was characterized by scanning electron microscopy and FIB–SEM electron tomography. The 3D reconstruction of the PWA1497 microstructure is presented and discussed. - Highlights: • The microstructure of PWA1497 superalloy was examined using FIB–SEM tomography. • In case of modern single crystal superalloys, measurements of A{sub A} are adequate for V{sub V}. • During creep the γ channel width increases from 65 to 193 nm for ruptured specimen. • Tomography is a useful technique for quantitative studies of material microstructure.

  4. PREFACE: 4th Global Conference on Materials Science and Engineering (CMSE 2015)

    NASA Astrophysics Data System (ADS)

    Ruda, H. E.; Khotsianovsky, A.

    2015-12-01

    IOP Conference Series: Materials Science and Engineering is publishing a volume of conference proceedings that contains a selection of papers presented at the 4th Global Conference on Materials Science and Engineering (CMSE 2015), which is an annual event that started in 2012. CMSE 2015, technically supported by the Institute of Applied Physics and Materials Engineering of University of Macau, organized by Wuhan Advance Materials Society, was successfully held at the University of Macau-new campus located on Hengqin Island from August 3rd-6th, 2015. It aims to bring together leading academic scientists, researchers and scholars to exchange and share their experience and research results on all aspects of Materials Science and Engineering, and to discuss the practical challenges encountered and the solutions adopted. Macau, one of the two special administrative regions of the People's Republic of China, where East meets West, turned out to be an ideal meeting place for domestic and overseas participants of this annual international conference. The conference program included keynote presentations, special sessions, oral and poster contributions. From several hundred submissions, 52 of the most promising and mainstream, IOP-relevant, contributions were included in this volume. The submissions present original ideas or results of general significance, supported by clear reasoning, compelling evidence and methods, theories and practices relevant to the research. The authors state clearly the problems and the significance of their research to theory and practice. Being a successful conference, this event gathered more than 200 qualified and high-level researchers and experts from over 40 countries, including 10 keynote speakers from 6 countries, which created a good platform for worldwide researchers and engineers to enjoy the academic communication. Taking advantage of this opportunity, we would like to thank all participants of this conference, and particularly the

  5. FOREWORD: 4th International Workshop on New Computational Methods for Inverse Problems (NCMIP2014)

    NASA Astrophysics Data System (ADS)

    2014-10-01

    This volume of Journal of Physics: Conference Series is dedicated to the scientific contributions presented during the 4th International Workshop on New Computational Methods for Inverse Problems, NCMIP 2014 (http://www.farman.ens-cachan.fr/NCMIP_2014.html). This workshop took place at Ecole Normale Supérieure de Cachan, on May 23, 2014. The prior editions of NCMIP also took place in Cachan, France, firstly within the scope of ValueTools Conference, in May 2011 (http://www.ncmip.org/2011/), and secondly at the initiative of Institut Farman, in May 2012 and May 2013, (http://www.farman.ens-cachan.fr/NCMIP_2012.html), (http://www.farman.ens-cachan.fr/NCMIP_2013.html). The New Computational Methods for Inverse Problems (NCMIP) Workshop focused on recent advances in the resolution of inverse problems. Indeed, inverse problems appear in numerous scientific areas such as geophysics, biological and medical imaging, material and structure characterization, electrical, mechanical and civil engineering, and finances. The resolution of inverse problems consists of estimating the parameters of the observed system or structure from data collected by an instrumental sensing or imaging device. Its success firstly requires the collection of relevant observation data. It also requires accurate models describing the physical interactions between the instrumental device and the observed system, as well as the intrinsic properties of the solution itself. Finally, it requires the design of robust, accurate and efficient inversion algorithms. Advanced sensor arrays and imaging devices provide high rate and high volume data; in this context, the efficient resolution of the inverse problem requires the joint development of new models and inversion methods, taking computational and implementation aspects into account. During this one-day workshop, researchers had the opportunity to bring to light and share new techniques and results in the field of inverse problems. The topics of the

  6. Turbine Manufacture

    NASA Technical Reports Server (NTRS)

    1979-01-01

    The machinery pictured is a set of Turbodyne steam turbines which power a sugar mill at Bell Glade, Florida. A NASA-developed computer program called NASTRAN aided development of these and other turbines manufactured by Turbodyne Corporation's Steam Turbine Division, Wellsville, New York. An acronym for NASA Structural Analysis Program, NASTRAN is a predictive tool which advises development teams how a structural design will perform under service use conditions. Turbodyne uses NASTRAN to analyze the dynamic behavior of steam turbine components, achieving substantial savings in development costs. One of the most widely used spinoffs, NASTRAN is made available to private industry through NASA's Computer Software Management Information Center (COSMIC) at the University of Georgia.

  7. PREFACE: The 4th Symposium on the Mechanics of Slender Structures (MoSS2013)

    NASA Astrophysics Data System (ADS)

    Cao, Dengqing; Kaczmarczyk, Stefan

    2013-07-01

    This volume of Journal of Physics: Conference Series contains papers presented at the 4th Symposium on the Mechanics of Slender Structures (MoSS2013) run under the auspices of the Institute of Physics Applied Mechanics Group and hosted by Harbin Institute of Technology (China) from 7-9 January 2013. The conference has been organized in collaboration with the Technical Committee on Vibration and Sound of the American Society of Mechanical Engineers and follows a one day seminar on Ropes, Cables, Belts and Chains: Theory and Applications and the MoSS2006 symposium held at the University of Northampton (UK) in 2004 and 2006, respectively, the MoSS2008 symposium held at the University of Maryland Baltimore County (USA) in 2008 and the MoSS2010 symposium hosted by Mondragon University and held in San Sebastian (Spain) in 2010. The remit of the Symposium on the Mechanics of Slender Structures series involves a broad range of scientific areas. Applications of slender structures include terrestrial, marine and space systems. Moving elastic elements such as ropes, cables, belts and tethers are pivotal components of many engineering systems. Their lengths often vary when the system is in operation. The applications include vertical transportation installations and, more recently, space tether propulsion systems. Traction drive elevator installations employ ropes and belts of variable length as a means of suspension, and also for the compensation of tensile forces over the traction sheave. In cranes and mine hoists, cables and ropes are subject to length variation in order to carry payloads. Tethers experiencing extension and retraction are important components of offshore and marine installations, as well as being proposed for a variety of different space vehicle propulsion systems based on different applications of momentum exchange and electrodynamic interactions with planetary magnetic fields. Furthermore, cables and slender rods are used extensively in civil engineering

  8. PREFACE: 4th Workshop on Theory, Modelling and Computational Methods for Semiconductors (TMCSIV)

    NASA Astrophysics Data System (ADS)

    Tomić, Stanko; Probert, Matt; Migliorato, Max; Pal, Joydeep

    2014-06-01

    These conference proceedings contain the written papers of the contributions presented at the 4th International Conference on Theory, Modelling and Computational Methods for Semiconductor materials and nanostructures. The conference was held at the MediaCityUK, University of Salford, Manchester, UK on 22-24 January 2014. The previous conferences in this series took place in 2012 at the University of Leeds, in 2010 at St William's College, York and in 2008 at the University of Manchester, UK. The development of high-performance computer architectures is finally allowing the routine use of accurate methods for calculating the structural, thermodynamic, vibrational, optical and electronic properties of semiconductors and their hetero- and nano-structures. The scope of this conference embraces modelling, theory and the use of sophisticated computational tools in semiconductor science and technology, where there is substantial potential for time-saving in R&D. Theoretical approaches represented in this meeting included: Density Functional Theory, Semi-empirical Electronic Structure Methods, Multi-scale Approaches, Modelling of PV devices, Electron Transport, and Graphene. Topics included, but were not limited to: Optical Properties of Quantum Nanostructures including Colloids and Nanotubes, Plasmonics, Magnetic Semiconductors, Photonic Structures, and Electronic Devices. This workshop ran for three days, with the objective of bringing together UK and international leading experts in the theoretical modelling of Group IV, III-V and II-VI semiconductors, as well as students, postdocs and early-career researchers. The first day focused on providing an introduction and overview of this vast field, aimed particularly at students, with several lectures given by recognized experts in various theoretical approaches. The following two days showcased some of the best theoretical research carried out in the UK in this field, with several contributions also from representatives of

  9. TURBINE COOLING FLOW AND THE RESULTING DECREASE IN TURBINE EFFICIENCY

    NASA Technical Reports Server (NTRS)

    Gauntner, J. W.

    1994-01-01

    This algorithm has been developed for calculating both the quantity of compressor bleed flow required to cool a turbine and the resulting decrease in efficiency due to cooling air injected into the gas stream. Because of the trend toward higher turbine inlet temperatures, it is important to accurately predict the required cooling flow. This program is intended for use with axial flow, air-breathing jet propulsion engines with a variety of airfoil cooling configurations. The algorithm results have compared extremely well with figures given by major engine manufacturers for given bulk metal temperatures and cooling configurations. The program calculates the required cooling flow and corresponding decrease in stage efficiency for each row of airfoils throughout the turbine. These values are combined with the thermodynamic efficiency of the uncooled turbine to predict the total bleed airflow required and the altered turbine efficiency. There are ten airfoil cooling configurations and the algorithm allows a different option for each row of cooled airfoils. Materials technology is incorporated and requires the date of the first year of service for the turbine stator vane and rotor blade. The user must specify pressure, temperatures, and gas flows into the turbine. This program is written in FORTRAN IV for batch execution and has been implemented on an IBM 3080 series computer with a central memory requirement of approximately 61K of 8 bit bytes. This program was developed in 1980.

  10. Transfer of a CD4+ Th1 cell line to nude mice effects clearance of Rhodococcus equi from the lung.

    PubMed Central

    Kanaly, S T; Hines, S A; Palmer, G H

    1996-01-01

    Rhodococcus equi, and intracellular respiratory pathogen, causes sever e granulomatous pneumonia in humans with AIDS and in young horses. Pulmonary clearance of R. equi requires functional CD4+ T cells and gamma interferon (IFN-gamma) expression from bronchial lymph node cells. The purpose of this study was to investigate whether R. equi-specific CD4+ Th1 cells could effect clearance of R. equi from the lung. Adoptive transfer of a clearance of R. equi from the lungs. In contrast, mice transfused with a R. equi-specific CD4+ Th2 cell line expressed interleukin-4 but not IFN-gamma mRNA, failed to clear pulmonary infection, and developed granulomas in the lung. Control mice, which did not receive cells, did not produce IFN-gamma or interleukin-4 and developed small pulmonary granulomas. These results clearly show that a Th1 response is sufficient to effect pulmonary clearance of R. equi. PMID:8606068

  11. A selected review of abstracts from the 4th Quadrennial Meeting of the World Federation of Neuro-Oncology.

    PubMed

    Chamberlain, Marc C

    2014-03-01

    The 4th Quadrennial Meeting of the World Federation of Neuro-Oncology (WFNO), San Francisco, CA, USA, 21-24 November 2013 The 4th Quadrennial Meeting of the World Federation of Neuro-Oncology (WFNO) was the largest neuro-oncology meeting that meets once every 4 years and brings together clinicians and scientists from all parts of the world whose focus is on new brain cancer clinical trials and research primarily pertaining to gliomas. The WFNO 2013 meeting included 1 education day, 2.5 days of presentation, 13 sunrise sessions, one town hall meeting, one mini-symposium, 130 oral presentations and 900 abstracts. This short meeting review highlights select adult clinical abstracts presented at WFNO 2013 that will only in part encompass the contents of a large and multifaceted meeting. PMID:25055016

  12. A laboratory model of post-Newtonian gravity with high power lasers and 4th generation light sources

    NASA Astrophysics Data System (ADS)

    Gregori, G.; Levy, M. C.; Wadud, M. A.; Crowley, B. J. B.; Bingham, R.

    2016-04-01

    Using the post-Newtonian formalism of gravity, we attempt to calculate the x-ray Thomson scattering cross section of electrons that are accelerated in the field of a high intensity optical laser. We show that our results are consistent with previous calculations, suggesting that the combination of high power laser and 4th generation light sources may become a powerful platform to test models exploring high order corrections to the Newtonian gravity.

  13. Gas turbine compressor unit repowering

    SciTech Connect

    Taylor, J.S.

    1996-12-31

    This paper presents how a major US gas transmission and storage company restored gas storage peaking capacity by repowering obsolete gas turbine compressor units. Consumers Power Company`s Ray Field located in Macomb County, Michigan, USA, was developed as a 44 BCF working capacity gas storage field in 1966. Due to the high deliverability, the field is operated as a peaking reservoir, handling rates as high as 500 MMCFD on injection and 1,200 MMCFD on withdrawal. Ten 2,750 horsepower gas turbine driven 4-stage centrifugal compressor units were installed in the mid to late 1960`s at the field. The compression is operated 2, 4 and 8 stage, as needed, to cover storage pressures of 450 to 1,800 psig. Each centrifugal compressor is driven by a Pratt Whitney (PW) GG-12 Gas Generator firing into a Cooper-Bessemer (CB) RT-27 Power Turbine. By 1980 parts and maintenance services for the PW GG-12 Gas Generator became very expensive to non-existent. In 1994 Consumers Power committed to a gas turbine unit repowering program as the preferred choice over unit replacement. Two refurbished Solar Centaur T4500 Gas Turbine drives were purchased and installed to repower 2 of the obsolete turbine units. This paper describes the retrofit.

  14. A general representation for axial-flow fans and turbines

    NASA Technical Reports Server (NTRS)

    Perl, W; Tucker, M

    1945-01-01

    A general representation of fan and turbine arrangements on a single classification chart is presented that is made possible by a particular definition of the stage of an axial-flow fan or turbine. Several unconventional fan and turbine arrangements are indicated and the applications of these arrangements are discussed.

  15. Dynamics of the properties of steppe paleosols of the Sarmatian time (2nd century BC-4th century AD) in relation to secular variations in climatic humidity

    NASA Astrophysics Data System (ADS)

    Demkin, V. A.; Zolotareva, B. N.; Demkina, T. S.; Khomutova, T. E.; Kashirskaya, N. N.; El'Tsov, M. V.; Udal'Tsov, S. N.

    2012-02-01

    Paleosols buried under kurgans of the Early (2nd-1st centuries BC), Middle (1st-2nd centuries AD) and Late (2nd-IV centuries AD) Sarmatian epochs were studied in dry steppes and desert steppes of the Lower Volga region (the Privolzhskaya and Ergeni Uplands and the Caspian Lowland). It was found that temporal variations in the morphological, chemical, microbiological, and magnetic properties of the paleosols in the interval of 2200-1600 BP were characterized by the cyclic pattern related to secular dynamics of climatic humidity with changes in the mean annual precipitation of ±30-50 mm. These climate changes did not transform chestnut paleosols and paleosolonetzes at the type or subtype taxonomic levels. However, they led to certain changes in the humus, carbonate, and salt profiles of the soils; in the character of solonetzic horizon B1; and in the state of microbial communities. According to these data, the Sarmatian time was characterized by alternation of micropluvial and microarid stages lasting fro about 100-200 years. In particular, the stages of humidization were observed in the 1st century BC-1st century AD and in the 4th century AD; the most arid conditions were observed in the second half of the 2nd and the first half of the 3rd century AD.

  16. Turbine design review text

    NASA Technical Reports Server (NTRS)

    1975-01-01

    Three-volume publication covers theoretical, design, and performance aspects of turbines. Volumes cover thermodynamic and fluid-dynamic concepts, velocity diagram design, turbine blade aerodynamic design, turbine energy losses, supersonic turbines, radial-inflow turbines, turbine cooling, and aerodynamic performance testing.

  17. Computed Flows In A Transonic Turbine

    NASA Technical Reports Server (NTRS)

    Rangwalla, A. A.; Madavan, N. K.; Johnson, P. D.

    1993-01-01

    Report presents computational study of flow in first stage of three alternative versions of proposed transonic turbine. Study demonstrates application of computational fluid dynamics to predict performance and analyze effects of changes in designs of these advanced machines.

  18. NASA/GE Highly-Loaded Turbine Research Program

    NASA Technical Reports Server (NTRS)

    Giel, Paul W.

    2007-01-01

    An overview of the NASA/GE Highly-Loaded Turbine Research Program at the NASA Glenn Research Center is presented. The program is sponsored by the Subsonic Fixed Wing Project of the Fundamental Aeronautics Program. The goals of the turbine research program are presented along with their relationship to the higher-level program goals. Two turbine research programs are described; the highly-loaded, single-stage high pressure turbine (HPT) and the highly loaded low pressure turbine (LPT). The HPT program is centered on an extremely high pressure ratio single-stage turbine with an engine stage pressure ratio of 5.5. It was designed with a 33% increase in stage loading. It has shown performance levels 2 points better than current engines operating at the higher work level. Some advantages of the turbine include reduced weight and parts count. Optimization of the blade shape to reduce shock losses is described. The LPT program utilizes a four-stage low pressure turbine with an integral first stage vane/transition duct strut; counter-rotation; low-solidity blading; fully optimized flowpath including vanes, blades, and endwalls; and a fluidically controlled turbine vane frame/exit guide vane. The implementation of the LPT into GE s and NASA s test facilities is described. A description of NASA's Single Spool Turbine Facility that is currently under renovation is given. Facility limits on pressures, temperatures, flow rates, rotational speeds, and power absorption are described. The current renovation status is given.

  19. Wind turbine

    DOEpatents

    Cheney, Jr., Marvin C.

    1982-01-01

    A wind turbine of the type having an airfoil blade (15) mounted on a flexible beam (20) and a pitch governor (55) which selectively, torsionally twists the flexible beam in response to wind turbine speed thereby setting blade pitch, is provided with a limiter (85) which restricts unwanted pitch change at operating speeds due to torsional creep of the flexible beam. The limiter allows twisting of the beam by the governor under excessive wind velocity conditions to orient the blades in stall pitch positions, thereby preventing overspeed operation of the turbine. In the preferred embodiment, the pitch governor comprises a pendulum (65,70) which responds to changing rotor speed by pivotal movement, the limiter comprising a resilient member (90) which engages an end of the pendulum to restrict further movement thereof, and in turn restrict beam creep and unwanted blade pitch misadjustment.

  20. Techniques for enhancing durability and equivalence ratio control in a rich-lean, three-stage ground power gas turbine combustor

    NASA Technical Reports Server (NTRS)

    Schultz, D. F.

    1982-01-01

    Rig tests of a can-type combustor were performed to demonstrate two advanced ground power engine combustor concepts: steam cooled rich-burn combustor primary zones for enhanced durability; and variable combustor geometry for three stage combustion equivalence ratio control. Both concepts proved to be highly successful in achieving their desired objectives. The steam cooling reduced peak liner temperatures to less than 800 K. This offers the potential of both long life and reduced use of strategic materials for liner fabrication. Three degrees of variable geometry were successfully implemented to control airflow distribution within the combustor. One was a variable blade angle axial flow air swirler to control primary airflow while the other two consisted of rotating bands to control secondary and tertiary or dilution air flow.

  1. The AGT 101 advanced automotive gas turbine

    NASA Technical Reports Server (NTRS)

    Rackley, R. A.; Kidwell, J. R.

    1982-01-01

    A development program is described whose goal is the accumulation of the technology base needed by the U.S. automotive industry for the production of automotive gas turbine powertrains. Such gas turbine designs must exhibit reduced fuel consumption, a multi-fuel capability, and low exhaust emissions. The AGT101 powertrain described is a 74.6 kW, regenerated single-shaft gas turbine, operating at a maximum inlet temperature of 1644 K and coupled to a split differential gearbox and automatic overdrive transmission. The engine's single stage centrifugal compressor and single stage radial inflow turbine are mounted on a common shaft, and will operate at a maximum rotor speed of 100,000 rpm. All high temperature components, including the turbine rotor, are ceramic.

  2. Caldecott 4th bore tunnel project: influence of ground water flows and inflows triggered by tectonic fault zones?

    NASA Astrophysics Data System (ADS)

    Neuhuber, G.; G. Neuhuber1, W. Klary1, A. Nitschke1, B. Thapa2, Chris Risden3, T. Crampton4, D. Zerga5

    2011-12-01

    The 4th Bore is a highway tunnel on California State Route 24 currently under construction. The 4th Bore is undertaken by the California State Department of Transportation (CALTRANS) and the Contra Costa County Transportation Commission (CCTC) to alleviate traffic congestion on SR24 connecting the cities of Oakland and Orinda in the San Francisco East Bay Area. The cost for the 4th Bore is estimated at $ 390.8 Mill. The 3,249 ft long 4th Bore tunnel will have excavated dimensions of approximately 40 ft height and 49 ft width. A total of 7 cross passages will run between the 3rd and the new 4th bore. Geology and Hydrogeology: The project is located in the Oakland Berkeley Hills of the SF Bay Area. The Caldecott Tunnels lie within the easterly assemblage of the Hayward fault zone province which consists of a sequence of sedimentary and volcanic rocks that accumulated in the interval between about 16 and 8.4 Ma (Miocene). The basal rocks of these Tertiary deposits consist of deep marine basin sediments of the Monterey Group. These rocks are overlain uncomfortably by an interbedded sequence of terrestrial sediments (Orinda Formation) and volcanic rocks (Moraga Formation). The Tertiary rocks have been folded into large amplitude, NW trending folds that are cut by N trending strike and slip faults. The SF Bay Region, which is crossed by 4 major faults (San Gregorio, San Andreas, Hayward, and Calaveras), is considered one of the more seismically active regions of the world. The active Hayward fault lies 0.9mi to the west of the Caldecott Tunnels and is the closest major fault to the project area. The tunnel is at the moment under top heading construction: West Portal (360ft) and East Portal (1,968.5ft). While major faults typically influence groundwater flow, characterization of such influences is extremely difficult because of the heterogeneity of the hydraulic systems and the different lithological parameters and influences. Four major inactive fault zones striking

  3. Production of IL-16 correlates with CD4+ Th1 inflammation and phosphorylation of axonal cytoskeleton in multiple sclerosis lesions

    PubMed Central

    Skundric, Dusanka S; Cai, Juan; Cruikshank, William W; Gveric, Djordje

    2006-01-01

    Background Multiple sclerosis (MS) is a central nervous system-specific autoimmune, demyelinating and neurodegenerative disease. Infiltration of lesions by autoaggressive, myelin-specific CD4+Th1 cells correlates with clinical manifestations of disease. The cytokine IL-16 is a CD4+ T cell-specific chemoattractant that is biased towards CD4+ Th1 cells. IL-16 precursor is constitutively expressed in lymphocytes and during CD4+ T cell activation; active caspase-3 cleaves and releases C-terminal bioactive IL-16. Previously, we used an animal model of MS to demonstrate an important role for IL-16 in regulation of autoimmune inflammation and subsequent axonal damage. This role of IL-16 in MS is largely unexplored. Here we examine the regulation of IL-16 in relation to CD4+ Th1 infiltration and inflammation-related changes of axonal cytoskeleton in MS lesions. Methods We measured relative levels of IL-16, active caspase-3, T-bet, Stat-1 (Tyr 701), and phosphorylated NF(M+H), in brain and spinal cord lesions from MS autopsies, using western blot analysis. We examined samples from 39 MS cases, which included acute, subacute and chronic lesions, as well as adjacent, normal-appearing white and grey matter. All samples were taken from patients with relapsing remitting clinical disease. We employed two-color immunostaining and confocal microscopy to identify phenotypes of IL-16-containing cells in frozen tissue sections from MS lesions. Results We found markedly increased levels of pro- and secreted IL-16 (80 kD and 22 kD, respectively) in MS lesions compared to controls. Levels of IL-16 peaked in acute, diminished in subacute, and were elevated again in chronic active lesions. Compared to lesions, lower but still appreciable IL-6 levels were measured in normal-appearing white matter adjacent to active lesions. Levels of IL-16 corresponded to increases in active-caspase-3, T-bet and phosphorylated Stat-1. In MS lesions, we readily observed IL-16 immunoreactivity confined to

  4. 4th Quarter Transportation Report FY 2014: Radioactive Waste Shipments to and from the Nevada National Security Site (NNSS)

    SciTech Connect

    Gregory, Louis

    2014-12-02

    This report satisfies the U.S. Department of Energy (DOE), National Nuclear Security Administration Nevada Field Office (NNSA/NFO) commitment to prepare a quarterly summary report of radioactive waste shipments to and from the Nevada National Security Site (NNSS) Radioactive Waste Management Complex (RWMC) at Area 5. There were no shipments sent for offsite treatment and returned to the NNSS this quarter. There was one shipment of two drums sent for offsite treatment and disposal. This report summarizes the 4th quarter of Fiscal Year (FY) 2014 low-level radioactive waste (LLW) and mixed low-level radioactive waste (MLLW) shipments. This report also includes annual summaries for FY 2014.

  5. Future perspectives in melanoma research. Meeting report from the “Melanoma Bridge. Napoli, December 2nd-4th 2012”

    PubMed Central

    2013-01-01

    Recent insights into the genetic and somatic aberrations have initiated a new era of rapidly evolving targeted and immune-based treatments for melanoma. After decades of unsuccessful attempts to finding a more effective cure in the treatment of melanoma now we have several drugs active in melanoma. The possibility to use these drugs in combination to improve responses to overcome the resistance, to potentiate the action of immune system with the new immunomodulating antibodies, and identification of biomarkers that can predict the response to a particular therapy represent new concepts and approaches in the clinical management of melanoma. The third “Melanoma Research: “A bridge from Naples to the World” meeting, shortened as “Bridge Melanoma Meeting” took place in Naples, December 2 to 4th, 2012. The four topics of discussion at this meeting were: advances in molecular profiling and novel biomarkers, combination therapies, novel concepts toward integrating biomarkers and therapies into contemporary clinical management of patients with melanoma across the entire spectrum of disease stage, and the knowledge gained from the biology of tumor microenvironment across different tumors as a bridge to impact on prognosis and response to therapy in melanoma. This international congress gathered more than 30 international faculty members who in an interactive atmosphere which stimulated discussion and exchange of their experience regarding the most recent advances in research and clinical management of melanoma patients. PMID:23731854

  6. Collaborative interactions between type 2 innate lymphoid cells and antigen-specific CD4+ Th2 cells exacerbate murine allergic airway diseases with prominent eosinophilia.

    PubMed

    Liu, Bo; Lee, Jee-Boong; Chen, Chun-Yu; Hershey, Gurjit K Khurana; Wang, Yui-Hsi

    2015-04-15

    Type-2 innate lymphoid cells (ILC2s) and the acquired CD4(+) Th2 and Th17 cells contribute to the pathogenesis of experimental asthma; however, their roles in Ag-driven exacerbation of chronic murine allergic airway diseases remain elusive. In this study, we report that repeated intranasal rechallenges with only OVA Ag were sufficient to trigger airway hyperresponsiveness, prominent eosinophilic inflammation, and significantly increased serum OVA-specific IgG1 and IgE in rested mice that previously developed murine allergic airway diseases. The recall response to repeated OVA inoculation preferentially triggered a further increase of lung OVA-specific CD4(+) Th2 cells, whereas CD4(+) Th17 and ILC2 cell numbers remained constant. Furthermore, the acquired CD4(+) Th17 cells in Stat6(-/-)/IL-17-GFP mice, or innate ILC2s in CD4(+) T cell-ablated mice, failed to mount an allergic recall response to OVA Ag. After repeated OVA rechallenge or CD4(+) T cell ablation, the increase or loss of CD4(+) Th2 cells resulted in an enhanced or reduced IL-13 production by lung ILC2s in response to IL-25 and IL-33 stimulation, respectively. In return, ILC2s enhanced Ag-mediated proliferation of cocultured CD4(+) Th2 cells and their cytokine production, and promoted eosinophilic airway inflammation and goblet cell hyperplasia driven by adoptively transferred Ag-specific CD4(+) Th2 cells. Thus, these results suggest that an allergic recall response to recurring Ag exposures preferentially triggers an increase of Ag-specific CD4(+) Th2 cells, which facilitates the collaborative interactions between acquired CD4(+) Th2 cells and innate ILC2s to drive the exacerbation of a murine allergic airway diseases with an eosinophilic phenotype. PMID:25780046

  7. Aerodynamic design of a free power turbine for a 75 KW gas turbine automotive engine

    NASA Technical Reports Server (NTRS)

    Kofskey, M. G.; Katsanis, T.; Schumann, L. F.

    1975-01-01

    A single stage axial-flow turbine having a tip diameter of 15.41 centimeters was designed. The design specifications are given and the aerodynamic design procedure is described. The design includes the transition duct and the turbine exit diffuser. The aerodynamic information includes typical results of a parametric study, velocity diagrams, blade surface and wall velocities, and blade profile and wall coordinates.

  8. Optimization of Turbine Rim Seals

    NASA Technical Reports Server (NTRS)

    Wagner, J. H.; Tew, D. E.; Stetson, G. M.; Sabnis, J. S.

    2006-01-01

    Experiments are being conducted to gain an understanding of the physics of rim scale cavity ingestion in a turbine stage with the high-work, single-stage characteristics envisioned for Advanced Subsonic Transport (AST) aircraft gas turbine engines fo the early 21st century. Initial experimental measurements to be presented include time-averaged turbine rim cavity and main gas path static pressure measurements for rim seal coolant to main gas path mass flow ratios between 0 and 0.02. The ultimate objective of this work is develop improved rim seal design concepts for use in modern high-work, single sage turbines n order to minimize the use of secondary coolant flow. Toward this objective the time averaged and unsteady data to be obtained in these experiments will be used to 1) Quantify the impact of the rim cavity cooling air on the ingestion process. 2) Quantify the film cooling benefits of the rim cavity purge flow in the main gas path. 3) Quantify the impact of the cooling air on turbine efficiency. 4) Develop/evaluate both 3D CFD and analytical models of the ingestion/cooling process.

  9. Fuel and oxidizer turbine loss analysis

    NASA Technical Reports Server (NTRS)

    Haas, J. E.

    1985-01-01

    The turbine losses for the fuel and oxidizer turbines at the FPL condition were assessed by a quasi-3D loss analysis method. This loss analysis method uses two flow codes - MERIDL and TSONIC - to calculate the flow velocities along the blade surfaces and endwalls. The velocities are then used as input to the boundary layer code - BLAYER - to calculate the friction losses due to incidence, secondary flow, and tip clearance. The loss analysis for the fuel turbine indicated an overall two-stage efficiency of about 90%. The largest loss was due to rotor tip clearance. The loss analysis for the oxidizer turbine is nearly completed. Results for the first stage of the two-stage design indicates an efficiency of about 80%, with high losses due to rotor incidence and blade and endwall friction.

  10. Properties of wind turbine wakes under various atmospheric stability conditions

    NASA Astrophysics Data System (ADS)

    Xie, Shengbai; Archer, Cristina

    2015-11-01

    Large-eddy simulations (LES) are performed to study the properties of wind turbine wakes under various atmospheric stability conditions. The Wind Turbine and Turbulence Simulator (WiTTS), a 4th-order finite-difference LES code is used for stable, neutral, and unstable conditions. The Coriolis forcing is also considered. Three cases are studied: isolated turbine, finite-size turbine array, and infinite wind farm. The results show strong correlations with stability. For the stable condition, the power extraction by an isolated turbine is highest, but the wake is also longest, thus the relative performance inside the array is lowest. In contrast, although the single-turbine power extraction is low for the unstable condition, the performance of downstream turbines is improved due to faster wake recovery. The wake shape is distorted by the stability-related wind veering. Therefore, the self-similar Gaussian wake deficit is not accurate. Here, a new wake model is proposed for correction. The infinite wind-farm case shows that the temperature near the ground is warmed by about 1 K for the stable condition, but the influence is almost negligible for the unstable and neutral conditions. For all conditions, the near-ground shear stress is reduced.

  11. Thermal stresses investigation of a gas turbine blade

    NASA Astrophysics Data System (ADS)

    Gowreesh, S.; Pravin, V. K.; Rajagopal, K.; Veena, P. H.

    2012-06-01

    The analysis of structural and thermal stress values that are produced while the turbine is operating are the key factors of study while designing the next generation gas turbines. The present study examines structural, thermal, modal analysis of the first stage rotor blade of a two stage gas turbine. The design features of the turbine segment of the gas turbine have been taken from the preliminary design of a power turbine for maximization of an existing turbojet engine with optimized dump gap of the combustion chamber, since the allowable temperature on the turbine blade dependents on the hot gas temperatures from the combustion chamber. In the present paper simplified 3-D Finite Element models are developed with governing boundary conditions and solved using the commercial FEA software ANSYS. As the temperature has a significant effect on the overall stress on the rotor blades, a detail study on mechanical and thermal stresses are estimated and evaluated with the experimental values.

  12. Theory and tests of two-phase turbines

    NASA Technical Reports Server (NTRS)

    Elliott, D. G.

    1982-01-01

    A theoretical model for two-phase turbines was developed. Apparatus was constructed for testing one- and two-stage turbines (using speed decrease from stage to stage). Turbines were tested with water and nitrogen mixtures and refrigerant 22. Nozzle efficiencies were 0.78 (measured) and 0.72 (theoretical) for water and nitrogen mixtures at a water/nitrogen mixture ratio of 68, by mass; and 0.89 (measured) and 0.84 (theoretical) for refrigerant 22 expanding from 0.02 quality to 0.28 quality. Blade efficiencies (shaft power before windage and bearing loss divided by nozzle jet power) were 0.63 (measured) and 0.71 (theoretical) for water and nitrogen mixtures and 0.62 (measured) and 0.63 (theoretical) for refrigerant 22 with a single stage turbine, and 0,70 (measured) and 0.85 (theoretical) for water and nitrogen mixtures with a two-stage turbine.

  13. Dual entry radial turbine gas generator

    SciTech Connect

    Mowill, R.J.

    1987-02-10

    This patent describes a high efficiency, single spool gas turbine gas generator comprising: (a) compressor means for providing an overall pressure ratio of greater than about 15:1, the compressor means including: (i) a first stage, double-entry centrifugal air compressor having a pair of entrances and a common exit, (ii) a second stage, centrifugal air compressor positioned adjacent to the first stage compressor, the second compressor stage having an entrance that is flow-connected to the first stage common exit and also having a second stage exit, and (iii) a shaft assembly for mechanically interconnecting the first and the second stage for rotation at the same angular speed; (b) combustor means operatively connected to the second stage exit for receiving the compressed air and combusting fuel using the compressed air to generate combustion gases; and (c) a single stage radial inflow turbine having an inlet and an outlet, the turbine being operatively connected directly to the shaft assembly drive and also being flow connected to the combustor means for receiving at the turbine inlet, and partially expanding, the combustion gases.

  14. Single Rotor Turbine

    DOEpatents

    Platts, David A.

    2004-10-26

    A rotor for use in turbine applications has a centrifugal compressor having axially disposed spaced apart fins forming passages and an axial turbine having hollow turbine blades interleaved with the fins and through which fluid from the centrifugal compressor flows.

  15. An Ecological Study of Food Desert Prevalence and 4th Grade Academic Achievement in New York State School Districts

    PubMed Central

    Frndak, Seth E.

    2014-01-01

    Background This ecological study examines the relationship between food desert prevalence and academic achievement at the school district level. Design and methods Sample included 232 suburban and urban school districts in New York State. Multiple open-source databases were merged to obtain: 4th grade science, English and math scores, school district demographic composition (NYS Report Card), regional socioeconomic indicators (American Community Survey), school district quality (US Common Core of Data), and food desert data (USDA Food Desert Atlas). Multiple regression models assessed the percentage of variation in achievement scores explained by food desert variables, after controlling for additional predictors. Results The proportion of individuals living in food deserts significantly explained 4th grade achievement scores, after accounting for additional predictors. School districts with higher proportions of individuals living in food desert regions demonstrated lower 4th grade achievement across science, English and math. Conclusions Food deserts appear to be related to academic achievement at the school district level among urban and suburban regions. Further research is needed to better understand how food access is associated with academic achievement at the individual level. Significance for public health The prevalence of food deserts in the United States is of national concern. As poor nutrition in United States children continues to spark debate, food deserts are being evaluated as potential sources of low fruit and vegetable intake and high obesity rates. Cognitive development and IQ have been linked to nutrition patterns, suggesting that children in food desert regions may have a disadvantage academically. This research evaluates if an ecological relationship between food desert prevalence and academic achievement at the school district level can be demonstrated. Results suggest that food desert prevalence may relate to poor academic performance at

  16. Successful Solutions to SSME/AT Development Turbine Blade Distress

    NASA Technical Reports Server (NTRS)

    Montgomery, Stuart K.

    1999-01-01

    As part of the High-Pressure Fuel Turbopump/Alternate Turbopump (HPFTP/AT) turbine blade development program, unique turbine blade design features were implemented to address 2nd stage turbine blade high cycle fatigue distress and improve turbine robustness. Features included the addition of platform featherseal dampers, asymmetric blade tip seal segments, gold plating of the blade attachments, and airfoil tip trailing edge modifications. Development testing shows these features have eliminated turbine blade high cycle fatigue distress and consequently these features are currently planned for incorporation to the flight configuration. Certification testing will begin in 1999. This presentation summarizes these features.

  17. International Symposium on Wind Energy Systems, 4th, Stockholm, Sweden, September 21-24, 1982, Proceedings. Volumes 1 & 2

    NASA Astrophysics Data System (ADS)

    Stephens, H. S.; Goodes, D. H.

    Progress in theoretical, meteorological, and hardware development sectors of wind energy utilization is assessed for various national programs. Wind regime characterization studies in Agentina, China, Indonesia, Norway, the U.S., Canada, Sweden, Hawaii, and offshore of the U.K. are reported. Data gained from wind turbine test sites in the U.S., Denmark, Holland, Germany, and the Netherlands are outlined. Attention is focused on the economics of wind turbine production for utility, agricultural, and third party purposes, with mention made of utilizing the resource appropriately for areas of installation of the wind powered machinery. Analyses are made of diurnal wind variations compared to diurnal demands on conventinal electricity generating power stations. Performance projections are made for wind farms featuring multi-MW machines, taking into account grid inteconnection factors, electrical control, power ramps, and environmental considerations. Mention is made of aeroelastics, dynamics, and the aerodynamics of wind turbines and rotor blades. Finally, icing, noise, fatigue failure, and blade throw problem are discussed, together with wind turbine licensing procedures in Denmark. No invidivual items are abstracted in these volumes

  18. Spin test of turbine rotor

    NASA Technical Reports Server (NTRS)

    Vavra, M. H.; Hammer, J. E.; Bell, L. E.

    1972-01-01

    Experimental data are presented for the tangential and radial stresses in the disks of the 36,000 horsepower, 4000 rpm turbine for the M-1 engine oxidizer turbopump. The two-stage Curtis turbine is a special light-weight design utilizing thin conical disks with hollow sheet metal blades attached by electron-beam welding techniques. The turbine was fabricated from Inconel 718, a nickel-chromium alloy. The stresses were obtained by strain-gage measurements using a slip-ring assembly to transmit the electrical signals. Measurements were made at different rotative speeds and different thermal loads. In addition to presenting test data, the report describes test equipment, design of associated hardware, test procedures, instrumentation, and tests for the selection and calibration of strain gages.

  19. Medical Standby: An Experience at the 4th National Youth Camping and Motivation Program Organized by Maksak Malaysia

    PubMed Central

    Zakaria, Mohd Idzwan; Isa, Ridzuan Mohd; Shah Che Hamzah, Mohd Shaharudin; Ayob, Noor Azleen

    2006-01-01

    Medical standby is the provision of emergency medical care and first aid for participants and/or spectators in a pre-planned event. This article describes the framework and the demographics of a medical standby at the 4th National Youth Camping and Motivation Program in Pasir Puteh, Kelantan from 30th July until the 3rd August 2004. The framework of the medical team is described based on the work process of any medical stand by. A medical encounter form was created for the medical standby defining the type of case seen (medical or trauma), name, age, race and diagnosis of the patient. We concluded that interagency collaboration during the initial planning and during the event itself is needed to ensure the smooth running of the medical standby. Most of the medical encounters were minor illnesses which are similar to previous studies and there was no case transferred to the hospital during that period. PMID:22589590

  20. Medical Standby: An Experience at the 4(th) National Youth Camping and Motivation Program Organized by Maksak Malaysia.

    PubMed

    Zakaria, Mohd Idzwan; Isa, Ridzuan Mohd; Shah Che Hamzah, Mohd Shaharudin; Ayob, Noor Azleen

    2006-01-01

    Medical standby is the provision of emergency medical care and first aid for participants and/or spectators in a pre-planned event. This article describes the framework and the demographics of a medical standby at the 4(th) National Youth Camping and Motivation Program in Pasir Puteh, Kelantan from 30(th) July until the 3(rd) August 2004. The framework of the medical team is described based on the work process of any medical stand by. A medical encounter form was created for the medical standby defining the type of case seen (medical or trauma), name, age, race and diagnosis of the patient. We concluded that interagency collaboration during the initial planning and during the event itself is needed to ensure the smooth running of the medical standby. Most of the medical encounters were minor illnesses which are similar to previous studies and there was no case transferred to the hospital during that period. PMID:22589590

  1. Macracanthorhynchus hirudinaceus Eggs in Canine Coprolite from the Sasanian Era in Iran (4(th)/5(th) Century CE).

    PubMed

    Mowlavi, Gholamreza; Makki, Mahsasadat; Heidari, Zahra; Rezaeian, Mostafa; Mohebali, Mehdi; Araujo, Adauto; Boenke, Nicole; Aali, Abolfazl; Stollner, Thomas; Mobedi, Iraj

    2015-01-01

    Present paper is the second publication introducing the paleoparasitological findings from animal coprolites obtained from archeological site of Chehrabad salt mine in northwestern Iran. The current archeological site is located in northwest of Iran, dated to the Sassanian Era (4(th)/5(th) century CE). In the summer 2012 the carnivore coprolite was obtained within the layers in the mine and were thoroughly analyzed for parasites using TSP rehydration technique. Eggs of 0 were successfully retrieved from the examined coprolite and were confidently identified based on reliable references. Identifying of M. hirudinaceus eggs in paleofeces with clear appearance as demonstrated herein, is much due to appropriate preservation condition has been existed in the salt mine .The present finding could be regarded as the oldest acanthocephalan infection in Iran. PMID:26246822

  2. Macracanthorhynchus hirudinaceus Eggs in Canine Coprolite from the Sasanian Era in Iran (4th/5th Century CE)

    PubMed Central

    MOWLAVI, Gholamreza; MAKKI, Mahsasadat; HEIDARI, Zahra; REZAEIAN, Mostafa; MOHEBALI, Mehdi; ARAUJO, Adauto; BOENKE, Nicole; AALI, Abolfazl; STOLLNER, Thomas; MOBEDI, Iraj

    2015-01-01

    Present paper is the second publication introducing the paleoparasitological findings from animal coprolites obtained from archeological site of Chehrabad salt mine in northwestern Iran. The current archeological site is located in northwest of Iran, dated to the Sassanian Era (4th/5th century CE). In the summer 2012 the carnivore coprolite was obtained within the layers in the mine and were thoroughly analyzed for parasites using TSP rehydration technique. Eggs of 0 were successfully retrieved from the examined coprolite and were confidently identified based on reliable references. Identifying of M. hirudinaceus eggs in paleofeces with clear appearance as demonstrated herein, is much due to appropriate preservation condition has been existed in the salt mine .The present finding could be regarded as the oldest acanthocephalan infection in Iran. PMID:26246822

  3. [Guideline for the additional test positions according to the EPQC 4th Edition for Digital Mammography Systems].

    PubMed

    Sommer, A; Lenzen, H; Blaser, D; Ehlers, S-E; Schopphoven, S; John, C

    2009-09-01

    Within the physical-technical quality assurance of the German breast cancer screening program all digital mammography systems have to perform the contrast resolution test and the determination of the average glandular dose based on the European guidelines for quality assurance in breast cancer screening and diagnosis (4th Edition). Since 1.1.2009 this applies to digital systems outside the screening program too. To accomplish uniform measurements in all federal states of Germany, the physical board of the reference centers developed together a special guideline for these test position. This Guideline describes the determination of the average glandular dose for different types of mammography systems, the CDMAM image acquisition and the CDMAM image evaluation as well. This guideline was verified by the German task group "Röntgenverordnung". PMID:19676011

  4. Neurobehavioral Evaluation System (NES): comparative performance of 2nd-, 4th-, and 8th-grade Czech children.

    PubMed

    Otto, D A; Skalik, I; House, D E; Hudnell, H K

    1996-01-01

    The Neurobehavioral Evaluation System was designed for field studies of workers, but many NES tests can be performed satisfactorily by children as young as 7 or 8 years old and a few tests, such as simple reaction time, can be performed by preschool children. However, little comparative data from children of different ages or grade levels are available. Studies of school children in the Czech Republic indicate that 2nd-grade children could perform the following NES tests satisfactorily: Finger Tapping, Visual Digit Span. Continuous Performance, Symbol-Digit Substitution, Pattern Comparison, and simpler conditions of Switching Attention. Comparative scores of boys and girls from the 2nd, 4th, and 8th grades and power analyses to estimate appropriate sample size were presented. Performance varied systematically with grade level and gender. Larger samples were needed with younger children to achieve comparable levels of statistical power. Gender comparisons indicated that boys responded faster, but made more errors than girls. PMID:8866533

  5. The influence of neighborhood density and word frequency on phoneme awareness in 2nd and 4th grades

    PubMed Central

    Hogan, Tiffany P.; Bowles, Ryan P.; Catts, Hugh W.; Storkel, Holly L.

    2010-01-01

    Purpose The purpose of this study was to test the hypothesis that two lexical characteristics – neighborhood density and word frequency – interact to influence performance on phoneme awareness tasks. Methods Phoneme awareness was examined in a large, longitudinal dataset of 2nd and 4th grade children. Using linear logistic test model, the relation between words' neighborhood density, word frequency, and phoneme awareness performance was examined across grades while covarying type and place of deletion. Results A predicted interaction was revealed: words from dense neighborhoods or those with high frequency were more likely to yield correct phoneme awareness responses across grades. Conclusions Findings support an expansion to the lexical restructuring model to include interactions between neighborhood density and word frequency to account for phoneme awareness. PMID:20691979

  6. 4th Annual Conference for African-American Researchers in the Mathematical Sciences (CAARMS4). Preliminary Program

    SciTech Connect

    Tapia, Richard

    1998-06-01

    In June, The Center for Research on Parallel Computation (CRPC), an NSF-funded Science and Technology Center, hosted the 4th Annual Conference for African-American Reserachers in the Mathematical Sciences (CAARMS4) at Rice University. The main goal of this conference was to highlight current work by African-American researchers and graduate students in mathematics. This conference strengthened the mathematical sciences by encouraging the increased participation of African-American and underrepresented groups into the field, facilitating working relationships between them and helping to cultivate their careers. In addition to the talks there was a graduate student poster session and tutorials on topics in mathematics and computer science. These talks, presentations, and discussions brought a broader perspective to the critical issues involving minority participation in mathematics.

  7. Design and numerical study of turbines operating with MDM as working fluid

    NASA Astrophysics Data System (ADS)

    Klonowicz, Piotr; Surwiło, Jan; Witanowski, Łukasz; Suchocki, Tomasz K.; Kozanecki, Zbigniew; Lampart, Piotr

    2015-12-01

    Design processes and numerical simulations have been presented for a few cases of turbines designated to work in ORC systems. The chosen working fluid isMDM. The considered design configurations include single stage centripetal reaction and centrifugal impulse turbines as well as multistage axial turbines. The power outputs vary from about 75 kW to 1 MW. The flow in single stage turbines is supersonic and requires special design of blades. The internal efficiencies of these configurations exceed 80% which is considered high for these type of machines. The efficiency of axial turbines exceed 90%. Possible turbine optimization directions have been also outlined in the work.

  8. An Analytical Method of Estimating Turbine Performance

    NASA Technical Reports Server (NTRS)

    Kochendorfer, Fred D; Nettles, J Cary

    1948-01-01

    A method is developed by which the performance of a turbine over a range of operating conditions can be analytically estimated from the blade angles and flow areas. In order to use the method, certain coefficients that determine the weight flow and friction losses must be approximated. The method is used to calculate the performance of the single-stage turbine of a commercial aircraft gas-turbine engine and the calculated performance is compared with the performance indicated by experimental data. For the turbine of the typical example, the assumed pressure losses and turning angles give a calculated performance that represents the trends of the experimental performance with reasonable accuracy. The exact agreement between analytical performance and experimental performance is contingent upon the proper selection of the blading-loss parameter. A variation of blading-loss parameter from 0.3 to 0.5 includes most of the experimental data from the turbine investigated.

  9. Analytical design of an advanced radial turbine. [automobile engines

    NASA Technical Reports Server (NTRS)

    Large, G. D.; Finger, D. G.; Linder, C. G.

    1981-01-01

    The aerodynamic and mechanical potential of a single stage ceramic radial inflow turbine was evaluated for a high temperature single stage automotive engine. The aerodynamic analysis utilizes a turbine system optimization technique to evaluate both radial and nonradial rotor blading. Selected turbine rotor configurations were evaluated mechanically with three dimensional finite element techniques. Results indicate that exceptionally high rotor tip speeds (2300 ft/sec) and performance potential are feasible with radial bladed rotors if the projected ceramic material properties are realized. Nonradial rotors reduced tip speed requirements (at constant turbine efficiency) but resulted in a lower cumulative probability of success due to higher blade and disk stresses.

  10. Plan Turbines 3 & 4, Side View Turbines ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    Plan - Turbines 3 & 4, Side View - Turbines 3 & 4, Section A-A - American Falls Water, Power & Light Company, Island Power Plant, Snake River, below American Falls Dam, American Falls, Power County, ID

  11. Advanced Hydrogen Turbine Development

    SciTech Connect

    Joesph Fadok

    2008-01-01

    Siemens has developed a roadmap to achieve the DOE goals for efficiency, cost reduction, and emissions through innovative approaches and novel technologies which build upon worldwide IGCC operational experience, platform technology, and extensive experience in G-class operating conditions. In Phase 1, the technologies and concepts necessary to achieve the program goals were identified for the gas turbine components and supporting technology areas and testing plans were developed to mitigate identified risks. Multiple studies were conducted to evaluate the impact in plant performance of different gas turbine and plant technologies. 2015 gas turbine technologies showed a significant improvement in IGCC plant efficiency, however, a severe performance penalty was calculated for high carbon capture cases. Thermodynamic calculations showed that the DOE 2010 and 2015 efficiency targets can be met with a two step approach. A risk management process was instituted in Phase 1 to identify risk and develop mitigation plans. For the risks identified, testing and development programs are in place and the risks will be revisited periodically to determine if changes to the plan are necessary. A compressor performance prediction has shown that the design of the compressor for the engine can be achieved with additional stages added to the rear of the compressor. Tip clearance effects were studied as well as a range of flow and pressure ratios to evaluate the impacts to both performance and stability. Considerable data was obtained on the four candidate combustion systems: diffusion, catalytic, premix, and distributed combustion. Based on the results of Phase 1, the premixed combustion system and the distributed combustion system were chosen as having the most potential and will be the focus of Phase 2 of the program. Significant progress was also made in obtaining combustion kinetics data for high hydrogen fuels. The Phase 1 turbine studies indicate initial feasibility of the

  12. Wind turbine

    SciTech Connect

    Traudt, R.F.

    1986-12-30

    This patent describes a wind turbine device having a main rotatable driven shaft, elongated blades operatively mounted on the main shaft for unitary rotation with the main shaft. The blade extends substantially radially away from the main shaft and is adapted to fold downwind under naturally occurring forces and simultaneously feather in direct response to the folding movement. A means associated with the blades is included for increasing the rate of fold relative to the rate of feather as the speed of rotation increases.

  13. Advanced coal-fueled gas turbine systems

    SciTech Connect

    Wenglarz, R.A.

    1994-08-01

    Several technology advances since the early coal-fueled turbine programs that address technical issues of coal as a turbine fuel have been developed in the early 1980s: Coal-water suspensions as fuel form, improved methods for removing ash and contaminants from coal, staged combustion for reducing NO{sub x} emissions from fuel-bound nitrogen, and greater understanding of deposition/erosion/corrosion and their control. Several Advanced Coal-Fueled Gas Turbine Systems programs were awarded to gas turbine manufacturers for for components development and proof of concept tests; one of these was Allison. Tests were conducted in a subscale coal combustion facility and a full-scale facility operating a coal combustor sized to the Allison Model 501-K industrial turbine. A rich-quench-lean (RQL), low nitrogen oxide combustor design incorporating hot gas cleanup was developed for coal fuels; this should also be applicable to biomass, etc. The combustor tests showed NO{sub x} and CO emissions {le} levels for turbines operating with natural gas. Water washing of vanes from the turbine removed the deposits. Systems and economic evaluations identified two possible applications for RQL turbines: Cogeneration plants based on Allison 501-K turbine (output 3.7 MW(e), 23,000 lbs/hr steam) and combined cycle power plants based on 50 MW or larger gas turbines. Coal-fueled cogeneration plant configurations were defined and evaluated for site specific factors. A coal-fueled turbine combined cycle plant design was identified which is simple, compact, and results in lower capital cost, with comparable efficiency and low emissions relative to other coal technologies (gasification, advanced PFBC).

  14. Stage 3 bucket shank bypass holes and related method

    DOEpatents

    Leone, Sal Albert; Eldrid, Sacheverel Quentin; Lupe, Douglas Arthur

    2002-01-01

    In a multi-stage turbine wherein at least one turbine wheel supports a row of buckets for rotation, and wherein the turbine wheel is located axially between first and second annular fixed arrays of nozzles, a cooling air circuit for purging a wheelspace between the turbine wheel and the second fixed annular array of nozzles comprising a flowpath through a shank portion of one or more buckets connecting a wheelspace between the turbine wheel and the first fixed annular array of nozzles with the wheelspace between the turbine wheel and the second fixed annular array of nozzles.

  15. [A development of Byzantine Christian charities during the 4(th)-7(th) centuries and the birth of the hospital].

    PubMed

    Nam, Sung Hyun

    2015-04-01

    This study aims to examine the beginning and the development of Christian Charities during the 4(th)-6(th) centuries which would eventually result in the birth of the hospital in modern sense in the first half of the 7(th) century. For this purpose, I looked carefully into various primary sources concerning the early Christian institutions for the poor and the sick. Above all, it's proper to note that the first xenodocheion where hospitality was combined with a systematic caring, is concerned with the Trinitarian debate of the 4(th) century. In 356, Eustathios, one of the leaders of homoiousios group, established xenodocheion to care for the sick and the lepers in Sebaste of Armenia, whereas his opponent Aetios, doctor and leader of the heteroousios party, was reckoned to have combined the medical treatment with his clerical activities. Then, Basil of Caesarea, disciple of Eustathios of Sebaste, also founded in 372 a magnificent benevolent complex named 'Basileias' after its founder. I scrupulously analysed several contemporary materials mentioning the charitable institution of Caesarea which was called alternatively katagogia, ptochotropheion, xenodocheion. John Chrysostome also founded several nosokomeia in Constantinople at the end of the 4(th) century and the beginning of the 5(th) century. Apparently, the contemporary sources mention that doctors existed for these Charities, but there is no sufficient proof that these 'Christian Hospitals,' Basileias or nosokomeia of Constantinople were hospitals in modern sense. Imperial constitutions began to mention ptochotropheion, xenodocheion and orphanotropheion since the second half of the 5(th) century and then some Justinian laws evoked nosokomium, brephotrophia, gerontocomia. These laws reveal that 'Christian Hospitals' were well clarified and deeply rooted in Byzantine society already in these periods. And then, new benevolent institutions emerged in the 6(th) century: nosokomeia for a specific class and

  16. Advanced radial inflow turbine rotor program: Design and dynamic testing

    NASA Technical Reports Server (NTRS)

    Rodgers, C.

    1976-01-01

    The advancement of small, cooled, radial inflow turbine technology in the area of operation at higher turbine inlet temperature is discussed. The first step was accomplished by designing, fabricating, and subjecting to limited mechanical testing an advanced gas generator rotating assembly comprising a radial inflow turbine and two-stage centrifugal compressor. The radial inflow turbine and second-stage compressor were designed as an integrally machined monorotor with turbine cooling taking place basically by conduction to the compressor. Design turbine inlet rotor gas temperature, rotational speed, and overall gas generator compressor pressure ratio were 1422 K (2560 R), 71,222 rpm, and 10/1 respectively. Mechanical testing on a fabricated rotating assembly and bearing system covered 1,000 cold start/stop cycles and three spins to 120 percent design speed (85,466 rpm).

  17. Control of Wind Turbines: Past, Present, and Future

    SciTech Connect

    Laks, J. H.; Pao, L. Y.; Wright, A. D.

    2009-01-01

    We review the objectives and techniques used in the control of horizontal axis wind turbines at the individual turbine level, where controls are applied to the turbine blade pitch and generator. The turbine system is modeled as a flexible structure operating in the presence of turbulent wind disturbances. Some overview of the various stages of turbine operation and control strategies used to maximize energy capture in below rated wind speeds is given, but emphasis is on control to alleviate loads when the turbine is operating at maximum power. After reviewing basic turbine control objectives, we provide an overview of the common basic linear control approaches and then describe more advanced control architectures and why they may provide significant advantages.

  18. Advanced IGCC/Hydrogen Gas Turbine Development

    SciTech Connect

    York, William; Hughes, Michael; Berry, Jonathan; Russell, Tamara; Lau, Y. C.; Liu, Shan; Arnett, Michael; Peck, Arthur; Tralshawala, Nilesh; Weber, Joseph; Benjamin, Marc; Iduate, Michelle; Kittleson, Jacob; Garcia-Crespo, Andres; Delvaux, John; Casanova, Fernando; Lacy, Ben; Brzek, Brian; Wolfe, Chris; Palafox, Pepe; Ding, Ben; Badding, Bruce; McDuffie, Dwayne; Zemsky, Christine

    2015-07-30

    The objective of this program was to develop the technologies required for a fuel flexible (coal derived hydrogen or syngas) gas turbine for IGCC that met DOE turbine performance goals. The overall DOE Advanced Power System goal was to conduct the research and development (R&D) necessary to produce coal-based IGCC power systems with high efficiency, near-zero emissions, and competitive capital cost. To meet this goal, the DOE Fossil Energy Turbine Program had as an interim objective of 2 to 3 percentage points improvement in combined cycle (CC) efficiency. The final goal is 3 to 5 percentage points improvement in CC efficiency above the state of the art for CC turbines in IGCC applications at the time the program started. The efficiency goals were for NOx emissions of less than 2 ppm NOx (@15 % O2). As a result of the technologies developed under this program, the DOE goals were exceeded with a projected 8 point efficiency improvement. In addition, a new combustion technology was conceived of and developed to overcome the challenges of burning hydrogen and achieving the DOE’s NOx goal. This report also covers the developments under the ARRA-funded portion of the program that include gas turbine technology advancements for improvement in the efficiency, emissions, and cost performance of gas turbines for industrial applications with carbon capture and sequestration. Example applications could be cement plants, chemical plants, refineries, steel and aluminum plants, manufacturing facilities, etc. The DOE’s goal for more than 5 percentage point improvement in efficiency was met with cycle analyses performed for representative IGCC Steel Mill and IGCC Refinery applications. Technologies were developed in this program under the following areas: combustion, larger latter stage buckets, CMC and EBC, advanced materials and coatings, advanced configurations to reduce cooling, sealing and rotor purge flows, turbine aerodynamics, advanced sensors, advancements in first

  19. Communicating Science to Impact Learning? A Phenomenological Inquiry into 4th and 5th Graders' Perceptions of Science Information Sources

    NASA Astrophysics Data System (ADS)

    Gelmez Burakgazi, Sevinc; Yildirim, Ali; Weeth Feinstein, Noah

    2016-04-01

    Rooted in science education and science communication studies, this study examines 4th and 5th grade students' perceptions of science information sources (SIS) and their use in communicating science to students. It combines situated learning theory with uses and gratifications theory in a qualitative phenomenological analysis. Data were gathered through classroom observations and interviews in four Turkish elementary schools. Focus group interviews with 47 students and individual interviews with 17 teachers and 10 parents were conducted. Participants identified a wide range of SIS, including TV, magazines, newspapers, internet, peers, teachers, families, science centers/museums, science exhibitions, textbooks, science books, and science camps. Students reported using various SIS in school-based and non-school contexts to satisfy their cognitive, affective, personal, and social integrative needs. SIS were used for science courses, homework/project assignments, examination/test preparations, and individual science-related research. Students assessed SIS in terms of the perceived accessibility of the sources, the quality of the content, and the content presentation. In particular, some sources such as teachers, families, TV, science magazines, textbooks, and science centers/museums ("directive sources") predictably led students to other sources such as teachers, families, internet, and science books ("directed sources"). A small number of sources crossed context boundaries, being useful in both school and out. Results shed light on the connection between science education and science communication in terms of promoting science learning.

  20. Identification of DRG-1 As a Melanoma-Associated Antigen Recognized by CD4+ Th1 Cells

    PubMed Central

    Kiniwa, Yukiko; Li, Jiang; Wang, Mingjun; Sun, Chuang; Lee, Jeffrey E.; Wang, Rong-Fu; Wang, Helen Y.

    2015-01-01

    Immunotherapy has emerged as a promising strategy for the treatment of metastatic melanoma. Clinical studies have demonstrated the feasibility of cancer immunotherapy using tumor antigens recognized by CD8+ T cells. However, the overall immune responses induced by these antigens are too weak and transient to induce tumor regression in the majority of patients who received immunization. A growing body of evidence suggests that CD4+ T helper (Th) cells play an important role in antitumor immunity. Therefore, the identification of MHC class II-restricted tumor antigens capable of stimulating CD4+ T cells may provide opportunities for developing effective cancer vaccines. To this end, we describe the identification of developmentally regulated GTP-binding protein 1 (DRG-1) as a melanoma-associated antigen recognized by HLA-DR11-restricted CD4+ Th1 cells. Epitope mapping analysis showed that the DRG1248-268 epitope of DRG-1 was required for T cell recognition. Reverse transcription-polymerase chain reaction revealed that DRG-1 was highly expressed in melanoma cell lines but not in normal tissues. DRG-1 knockdown by lentiviral-based shRNA suppressed melanoma cell proliferation and soft agar colony formation. Taken together, these data suggest that DRG-1 plays an important role in melanoma cell growth and transformation, indicating that DRG1 may represent a novel target for CD4+ T cell-mediated immunotherapy in melanoma. PMID:25993655

  1. A study of personality factors and interaction in 4th-year dental students and their teachers.

    PubMed

    Watts, T L; Millard, L

    1997-02-01

    No previous investigation has considered dental student and teaching staff opinions on their relationship with each other. In a day when students are increasingly asked for feedback on the quality of teaching by staff, such investigations are of particular interest. This exploratory study was designed to compare the personality characteristics of a clinical year of dental students with those of the teaching staff they most frequently encountered, and to investigate these factors for possible associations with the quality of perceived teaching-learning interaction between the 2 groups. A complete 4th year of dental students (n = 87), and those teachers whom they met regularly (n = 80), were asked to participate. Subjects completed a form of the Myers-Briggs personality questionnaire simplified for use in education, and were asked to assess their relationship with persons in the other group. All the students and 75% of the staff, after follow-up, returned usable data. There was close similarity between staff and student personality profiles, and perception of working relationships by both groups was largely independent of personality factors and temperament. There were differences in staff perception of their relationship with extrovert and introvert students. Students showed minor differences in their perception of staff relationships with respect to two other personality factors. These findings indicate a substantial similarity between staff and students, and suggest a mature and stable relationship between people in the 2 groups. PMID:9567907

  2. Meeting report: 4th ISIRV antiviral group conference: Novel antiviral therapies for influenza and other respiratory viruses.

    PubMed

    McKimm-Breschkin, Jennifer L; Fry, Alicia M

    2016-05-01

    The International Society for Influenza and other Respiratory Virus Diseases (isirv) held its 4th Antiviral Group Conference at the University of Texas on 2-4 June, 2015. With emerging resistance to the drugs currently licensed for treatment and prophylaxis of influenza viruses, primarily the neuraminidase inhibitor oseltamivir phosphate (Tamiflu) and the M2 inhibitors amantadine and rimantadine, and the lack of effective interventions against other respiratory viruses, the 3-day programme focused on the discovery and development of inhibitors of several virus targets and key host cell factors involved in virus replication or mediating the inflammatory response. Virus targets included the influenza haemagglutinin, neuraminidase and M2 proteins, and both the respiratory syncytial virus and influenza polymerases and nucleoproteins. Therapies for rhinoviruses and MERS and SARS coronaviruses were also discussed. With the emerging development of monoclonal antibodies as therapeutics, the potential implications of antibody-dependent enhancement of disease were also addressed. Topics covered all aspects from structural and molecular biology to preclinical and clinical studies. The importance of suitable clinical trial endpoints and regulatory issues were also discussed from the perspectives of both industry and government. This meeting summary provides an overview, not only for the conference participants, but also for those interested in the current status of antivirals for respiratory viruses. PMID:26872862

  3. Quality of Education Predicts Performance on the Wide Range Achievement Test-4th Edition Word Reading Subtest

    PubMed Central

    Sayegh, Philip; Arentoft, Alyssa; Thaler, Nicholas S.; Dean, Andy C.; Thames, April D.

    2014-01-01

    The current study examined whether self-rated education quality predicts Wide Range Achievement Test-4th Edition (WRAT-4) Word Reading subtest and neurocognitive performance, and aimed to establish this subtest's construct validity as an educational quality measure. In a community-based adult sample (N = 106), we tested whether education quality both increased the prediction of Word Reading scores beyond demographic variables and predicted global neurocognitive functioning after adjusting for WRAT-4. As expected, race/ethnicity and education predicted WRAT-4 reading performance. Hierarchical regression revealed that when including education quality, the amount of WRAT-4's explained variance increased significantly, with race/ethnicity and both education quality and years as significant predictors. Finally, WRAT-4 scores, but not education quality, predicted neurocognitive performance. Results support WRAT-4 Word Reading as a valid proxy measure for education quality and a key predictor of neurocognitive performance. Future research should examine these findings in larger, more diverse samples to determine their robust nature. PMID:25404004

  4. Quality of education predicts performance on the Wide Range Achievement Test-4th Edition Word Reading subtest.

    PubMed

    Sayegh, Philip; Arentoft, Alyssa; Thaler, Nicholas S; Dean, Andy C; Thames, April D

    2014-12-01

    The current study examined whether self-rated education quality predicts Wide Range Achievement Test-4th Edition (WRAT-4) Word Reading subtest and neurocognitive performance, and aimed to establish this subtest's construct validity as an educational quality measure. In a community-based adult sample (N = 106), we tested whether education quality both increased the prediction of Word Reading scores beyond demographic variables and predicted global neurocognitive functioning after adjusting for WRAT-4. As expected, race/ethnicity and education predicted WRAT-4 reading performance. Hierarchical regression revealed that when including education quality, the amount of WRAT-4's explained variance increased significantly, with race/ethnicity and both education quality and years as significant predictors. Finally, WRAT-4 scores, but not education quality, predicted neurocognitive performance. Results support WRAT-4 Word Reading as a valid proxy measure for education quality and a key predictor of neurocognitive performance. Future research should examine these findings in larger, more diverse samples to determine their robust nature. PMID:25404004

  5. Advances in Urea cycle Neuroimaging: Proceedings from the 4th International symposium on Urea cycle disorders, Barcelona, Spain, September 2013

    PubMed Central

    Pacheco-Colon, Ileana; Fricke, Stanley; VanMeter, John; Gropman, M.D.

    2014-01-01

    Our previous imaging research performed as part of a Urea Cycle Rare Disorders Consortium (UCRDC) grant, has identified specific biomarkers of neurologic injury in ornithine transcarbamylase deficiency, OTCD. While characterization of mutations can be achieved in most cases, this information does not necessarily predict the severity of the underlying neurological syndrome. The biochemical consequences of any mutation may be modified additionally by a large number of factors, including contributions of other enzymes and transport systems that mediate flux through the urea cycle, diet and other environmental factors. These factors likely vary from one patient to another, and they give rise to heterogeneity of clinical severity. Affected cognitive domains include non-verbal learning, fine motor processing, reaction time, visual memory, attention, and executive function. Deficits in these capacities may be seen in symptomatic patients, as well as asymptomatic carriers with normal IQ and correlate with variances in brain structure and function in these patients. Using neuroimaging we can identify biomarkers that reflect the downstream impact of UCDs on cognition. This manuscript is a summary of the presentation from the 4th International Consortium on Urea cycle disorders held in, Barcelona, Spain, September 2, 2014. PMID:25066103

  6. A TGF-B homologue identified from Ascaris suum 4th stage larvae (L4): Evidence for development-related transcription and incomplete gene splicing

    Technology Transfer Automated Retrieval System (TEKTRAN)

    Ascaris species represent the most prevalent parasitic worm infecting humans and swine worldwide. During the infection process, A. suum L4 establish in the jejunum and develop into adults. However, a large percentage of L4 spontaneously cure to the ileum at 14 to 21 days after inoculation (dpi), and...

  7. NASA/GE Highly-Loaded Turbine Research Program

    NASA Technical Reports Server (NTRS)

    Giel, Paul W.

    2008-01-01

    An overview of the NASA/GE Highly-Loaded Turbine Research Program at the NASA Glenn Research Center is presented. The program is sponsored by the Subsonic Fixed Wing Project of the Fundamental Aeronautics Program. The goals of the turbine research program are presented along with their relationship to the higher-level program goals. Two turbine research programs are described; the highly-loaded, single-stage high pressure turbine (HPT) and the highly loaded low pressure turbine (LPT). The HPT program is centered on an extremely high pressure ratio single-stage turbine with an engine stage pressure ratio of 5.5. It was designed with a 33% increase in stage loading. It has shown performance levels 2 points better than current engines operating at the higher work level. Some advantages of the turbine include reduced weight and parts count. Optimization of the blade shape to reduce shock losses is described. The LPT program utilizes a four-stage low pressure turbine with an integral first stage vane/transition duct strut; counterrotation; low-solidity blading; fully optimized flowpath including vanes, blades, and endwalls; and a fluidically controlled turbine vane frame/exit guide vane. The implementation of the LPT into GE s and NASA s test facilities is described. A description of NASA s Single Spool Turbine Facility that is currently under renovation is given. The new, upgraded facility is compared to its predecessor. Renovation design requirements are outlined. Facility limits on pressures, temperatures, flow rates, rotational speeds, and power absorption are described. The current renovation status is given.

  8. Hydro-flow supra-turbine engine

    SciTech Connect

    Neale, A.B.

    1981-08-04

    A turbine engine operates at high pressure and at relatively low temperatures and revolutions per minute through the use of special carburetion, compressor, combustion unit, and turbine arrangements. The system is characterized by the use of water which is vaporized and concurrently reduces the temperature of the vaporized fuel and air mixture as compression occurs, and is not physically intermixed with the combustion gases until after initial combustion takes place. The compressor includes a pair of back-to-back, four stage composite compressors to which synchronized dual carburetion or meter-flow arrangements separately supply water and gasoline or other fuel, along with air. The water absorbs heat from the compression of both of the two compressors, and the resultant vaporous product gases are routed to the jacket of a combustion chamber in which the compressed fuel and air mixture is burned. Following initial ignition and some burning of the fuel, the superheated steam and combustion products are combined, and the combination is supplied to a multistage transverse flow turbine having in the order of 17 pressure stages. The turbine includes arrangements for directing the high pressure gases back and forth through the rotor blades at different radial distances from the axis of the turbine. Exhaust gases from the turbine are applied to a ''floating'' muffler, including a rotatable inner chamber to facilitate mixing exhaust gases with the ambient air, and to disperse the high moisture content of the exhaust gases.

  9. Large-scale wind turbine structures

    NASA Technical Reports Server (NTRS)

    Spera, David A.

    1988-01-01

    The purpose of this presentation is to show how structural technology was applied in the design of modern wind turbines, which were recently brought to an advanced stage of development as sources of renewable power. Wind turbine structures present many difficult problems because they are relatively slender and flexible; subject to vibration and aeroelastic instabilities; acted upon by loads which are often nondeterministic; operated continuously with little maintenance in all weather; and dominated by life-cycle cost considerations. Progress in horizontal-axis wind turbines (HAWT) development was paced by progress in the understanding of structural loads, modeling of structural dynamic response, and designing of innovative structural response. During the past 15 years a series of large HAWTs was developed. This has culminated in the recent completion of the world's largest operating wind turbine, the 3.2 MW Mod-5B power plane installed on the island of Oahu, Hawaii. Some of the applications of structures technology to wind turbine will be illustrated by referring to the Mod-5B design. First, a video overview will be presented to provide familiarization with the Mod-5B project and the important components of the wind turbine system. Next, the structural requirements for large-scale wind turbines will be discussed, emphasizing the difficult fatigue-life requirements. Finally, the procedures used to design the structure will be presented, including the use of the fracture mechanics approach for determining allowable fatigue stresses.

  10. Large-scale wind turbine structures

    NASA Astrophysics Data System (ADS)

    Spera, David A.

    1988-05-01

    The purpose of this presentation is to show how structural technology was applied in the design of modern wind turbines, which were recently brought to an advanced stage of development as sources of renewable power. Wind turbine structures present many difficult problems because they are relatively slender and flexible; subject to vibration and aeroelastic instabilities; acted upon by loads which are often nondeterministic; operated continuously with little maintenance in all weather; and dominated by life-cycle cost considerations. Progress in horizontal-axis wind turbines (HAWT) development was paced by progress in the understanding of structural loads, modeling of structural dynamic response, and designing of innovative structural response. During the past 15 years a series of large HAWTs was developed. This has culminated in the recent completion of the world's largest operating wind turbine, the 3.2 MW Mod-5B power plane installed on the island of Oahu, Hawaii. Some of the applications of structures technology to wind turbine will be illustrated by referring to the Mod-5B design. First, a video overview will be presented to provide familiarization with the Mod-5B project and the important components of the wind turbine system. Next, the structural requirements for large-scale wind turbines will be discussed, emphasizing the difficult fatigue-life requirements. Finally, the procedures used to design the structure will be presented, including the use of the fracture mechanics approach for determining allowable fatigue stresses.

  11. Benefits of a 4th Ice Class in the Simulated Radar Reflectivities of Convective Systems Using a Bulk Microphysics Scheme

    NASA Technical Reports Server (NTRS)

    Lang, Stephen E.; Tao, Wei-Kuo; Chern, Jiun-Dar; Wu, Di; Li, Xiaowen

    2015-01-01

    Numerous cloud microphysical schemes designed for cloud and mesoscale models are currently in use, ranging from simple bulk to multi-moment, multi-class to explicit bin schemes. This study details the benefits of adding a 4th ice class (hail) to an already improved 3-class ice bulk microphysics scheme developed for the Goddard Cumulus Ensemble model based on Rutledge and Hobbs (1983,1984). Besides the addition and modification of several hail processes from Lin et al. (1983), further modifications were made to the 3-ice processes, including allowing greater ice super saturation and mitigating spurious evaporationsublimation in the saturation adjustment scheme, allowing graupelhail to become snow via vapor growth and hail to become graupel via riming, and the inclusion of a rain evaporation correction and vapor diffusivity factor. The improved 3-ice snowgraupel size-mapping schemes were adjusted to be more stable at higher mixing rations and to increase the aggregation effect for snow. A snow density mapping was also added. The new scheme was applied to an intense continental squall line and a weaker, loosely-organized continental case using three different hail intercepts. Peak simulated reflectivities agree well with radar for both the intense and weaker case and were better than earlier 3-ice versions when using a moderate and large intercept for hail, respectively. Simulated reflectivity distributions versus height were also improved versus radar in both cases compared to earlier 3-ice versions. The bin-based rain evaporation correction affected the squall line case more but did not change the overall agreement in reflectivity distributions.

  12. Breakfast patterns among low-income, ethnically-diverse 4th-6th grade children in an urban area

    PubMed Central

    2014-01-01

    Background Increasing school breakfast participation has been advocated as a method to prevent childhood obesity. However, little is known about children’s breakfast patterns outside of school (e.g., home, corner store). Policies that increase school breakfast participation without an understanding of children’s breakfast habits outside of school may result in children consuming multiple breakfasts and may undermine efforts to prevent obesity. The aim of the current study was to describe morning food and drink consumption patterns among low-income, urban children and their associations with relative weight. Methods A cross-sectional analysis was conducted of data obtained from 651 4th-6th graders (51.7% female, 61.2% African American, 10.7 years) in 2012. Students completed surveys at school that included all foods eaten and their locations that morning. Height and weight were measured by trained research staff. Results On the day surveyed, 12.4% of youth reported not eating breakfast, 49.8% reported eating one breakfast, 25.5% reported eating two breakfasts, and 12.3% reported eating three or more breakfasts. The number of breakfasts consumed and BMI percentile showed a significant curvilinear relationship, with higher mean BMI percentiles observed among children who did not consume any breakfast and those who consumed ≥ 3 breakfasts. Sixth graders were significantly less likely to have consumed breakfast compared to younger children. A greater proportion of obese youth had no breakfast (18.0%) compared to healthy weight (10.1%) and overweight youth (10.7%, p = .01). Conclusions When promoting school breakfast, policies will need to be mindful of both over- and under-consumption to effectively address childhood obesity and food insecurity. Clinical trial registration NCT01924130 from http://clinicaltrials.gov/. PMID:24928474

  13. Worn blades may have caused turbine failure

    SciTech Connect

    1994-04-01

    Detroit Edison Co.`s decision not to replace eighth-stage blades in low-pressure turbine number three may have caused the event that damaged the turbine, generator, and exciter at Fermi-2 on December 25, 1993. This finding is included in the February 7 report of the Nuclear Regulatory Commission`s Augmented Inspection Teams (AIT). GEC Turbine Generations Ltd. of England, manufacturer of the turbine, had recommended replacing the blades during the plant`s third refueling outage in September 1992. Detroit Edison chose not to do so, stating in its report, {open_quotes}This wear is of the same magnitude as that noticed in RF01 [refueling outage 1] and it is not necessary to record this wear since all blades will be changed in RF04 [refueling outage 4].{close_quotes}

  14. An analytical method of estimating turbine performance

    NASA Technical Reports Server (NTRS)

    Kochendorfer, Fred D; Nettles, J Cary

    1949-01-01

    A method is developed by which the performance of a turbine over a range of operating conditions can be analytically estimated from the blade angles and flow areas. In order to use the method, certain coefficients that determine the weight flow and the friction losses must be approximated. The method is used to calculate the performance of the single-stage turbine of a commercial aircraft gas-turbine engine and the calculated performance is compared with the performance indicated by experimental data. For the turbine of the typical example, the assumed pressure losses and the tuning angles give a calculated performance that represents the trends of the experimental performance with reasonable accuracy. The exact agreement between analytical performance and experimental performance is contingent upon the proper selection of a blading-loss parameter.

  15. Study on the turbine vane and blade for a 1500 C class industrial gas turbine

    NASA Astrophysics Data System (ADS)

    Amagasa, S.; Shimomura, K.; Kadowaki, M.; Takeishi, K.; Kawai, H.; Aoki, S.; Aoyama, K.

    1994-07-01

    This paper describes the summary of a three-year development program for the first-stage stationary vane and rotating blade for the next generation, 1500 C class, high-efficiency gas turbine. In such a high-temperature gas turbine, the first turbine vane and blade are the most important hot parts. Full-coverage film cooling (FCFC) is adopted for the cooling scheme, and directionally solidified (DS) nickel base superalloy and thermal barrier coating (TBC) will be used to prolong the creep and thermal fatigue life. The concept of the cooling configuration, fundamental cascade test results, and material test results will be presented.

  16. Autism: Proceedings of Annual Meeting of the National Society for Autistic Children (4th, June 22-24, 1972, Flint Michigan).

    ERIC Educational Resources Information Center

    National Society for Autistic Children, Syracuse, NY.

    Presented are proceedings of the 4th annual (1972) meeting of the National Society for Autistic Children including 11 papers given at the meeting. Listed are officers and board members of the society, the convention committee members, and recipients of citations and awards. The president's report notes past goals, accomplishments, and future…

  17. Examining Differentiation and Utilization of iPads across Content Areas in an Independent, PreK-4th Grade Elementary School

    ERIC Educational Resources Information Center

    Milman, Natalie B.; Carlson-Bancroft, Angela; Vanden Boogart, Amy

    2014-01-01

    This mixed methods case study examined the implementation of a 1:1 iPad initiative in a suburban, co-educational, independent, preK-4th grade elementary school in the United States. This article focuses on how teachers used iPads to differentiate instruction and across multiple content areas. Findings show the processes by which teachers employed…

  18. An Assessment of 4th, 8th, and 11th Grade Students' Knowledge Related to Marine Science and Natural Resource Issues.

    ERIC Educational Resources Information Center

    Brody, Michael J.; Koch, Helmut

    In an effort to contribute information for science teachers and curriculum developers in Maine, this study generated base line data on 4th, 8th, and 11th grade students' knowledge of marine science and natural resources principles in relation to the Gulf of Maine. Five concept maps representing 15 major content principles were developed. Two…

  19. The Relationship of Values in Elementary School 4th Grade Social Studies Textbook with the Attainments and Their Level of Being Included in Student Workbooks

    ERIC Educational Resources Information Center

    Kilic, Abdurrahman

    2012-01-01

    In this study, the relationship of values in elementary school 4th grade Social Studies textbook with the attainments and their level of being included in student workbook are tried to be determined. Case study, which is a qualitative research method, was applied for this research. To collect data, document analysis technique, which is among the…

  20. The Effect of Direct Instruction Strategy on Math Achievement of Primary 4th and 5th Grade Students with Learning Difficulties

    ERIC Educational Resources Information Center

    Al-Makahleh, Ahmad Abdulhameed Aufan

    2011-01-01

    This study seeks to verify the effect of direct instruction strategy on Math achievment of students with learning difficulties in the fourth and fifth grade levels and measure the improvement in their attitudes to Mathematics. Sample consisted of sixty (60) students with Math learning difficulties attending 4th and 5th grade level resource rooms…

  1. Color Duplex Assessment of 4th and 5th Internal Mammary Artery Perforators: The Pedicles of the Medially Based Lower Pole Breast Flaps

    PubMed Central

    Abdel-Monem, Kareem; Elshahat, Ahmed; Abou-Gamrah, Sherif; Eldin Abol-Atta, Hossam; Abd Eltawab, Reda; Massoud, Karim

    2012-01-01

    Objective: Reconstruction of a breast after mastectomy using the contralateral lower pole breast flap is an appealing procedure because it uses the tissues that were going to be excised during reduction of the sound breast to achieve symmetry. Literature mentioned that these flaps are supplied by the lower internal mammary artery perforators (IMAPs) with no further details. The aim of this study was to determine the site, size, and number of the 4th and 5th IMAPs by using preoperative color Duplex ultrasound and intraoperative exploration. Method: Twenty breasts in 10 patients who presented for reduction mammoplasty were included in this study. Preoperative color duplex was used to determine IMAPs in the 4th and 5th intercostal spaces. These perforators were localized intraoperatively. Intravenous fluorescein injection was used to determine the perfusion of the lower pole breast flap on the basis of these perforators. Results: Statistically, the 4th IMAPs diameters were significantly larger than the 5th IMAPs diameters (P < .05). The lower pole breast flap was perfused through these perforators. Conclusion: Color Duplex ultrasound is an accurate tool to preoperatively determine the 4th and 5th IMAPs. PMID:22292100

  2. The Effect of the Conceptual Change Oriented Instruction through Cooperative Learning on 4th Grade Students' Understanding of Earth and Sky Concepts

    ERIC Educational Resources Information Center

    Celikten, Oksan; Ipekcioglu, Sevgi; Ertepinar, Hamide; Geban, Omer

    2012-01-01

    The purpose of this study was to compare the effectiveness of the conceptual change oriented instruction through cooperative learning (CCICL) and traditional science instruction (TI) on 4th grade students' understanding of earth and sky concepts and their attitudes toward earth and sky concepts. In this study, 56 fourth grade students from the…

  3. Meeting Materials for the 4th NRC Meeting on the Guidance for and the Review of EPA's Toxicological Assessment of Inorganic Arsenic

    EPA Science Inventory

    On December 2-3, 2015, the National Research Council (NRC) hosted the 4th meeting of the committee formed to peer review the draft IRIS assessment of inorganic arsenic. EPA presented background and overview materials during the public session on December 2nd. This information co...

  4. U.S. Dietary and Physical Activity Guideline Knowledge and Corresponding Behaviors among 4th and 5th Grade Students: A Multi-Site Pilot Study

    ERIC Educational Resources Information Center

    Bea, Jennifer W.; Martinez, Stephanie; Armstrong-Florian, Traci; Farrell, Vanessa; Martinez, Cathy; Whitmer, Evelyn; Hartz, Vern; Blake, Samuel; Nicolini, Ariana; Misner, Scottie

    2014-01-01

    Knowledge of U.S. dietary and physical activity recommendations and corresponding behaviors were surveyed among 4th and 5th graders in five Arizona counties to determine the need for related education in SNAP-Ed eligible schools. A <70% target response rate was the criterion. Participants correctly identified recommendations for: fruit, 20%;…

  5. Nation and Language: Modern Aspects of Socio-Linguistic Development. Proceedings of the 4th International Conference (Lithuania, October 21-22, 2010)

    ERIC Educational Resources Information Center

    Online Submission, 2010

    2010-01-01

    The 4th international conference "Nation and Language: Modern Aspects of Socio-Linguistic Development" continues an eight-year old tradition. The conference is organized by Kaunas University of Technology Panevezys Institute and aims to bring scientists and researchers together for a general scientific discussion on new trends in sociolinguistic,…

  6. Theory and tests of two-phase turbines

    SciTech Connect

    Elliot, D.G.

    1982-03-15

    Two-phase turbines open the possibility of new types of power cycles operating with extremely wet mixtures of steam and water, organic fluids, or immiscible liquids and gases. Possible applications are geothermal power, waste-heat recovery, refrigerant expansion, solar conversion, transportation turbine engines, and engine bottoming cycles. A theoretical model for two-phase impulse turbines was developed. Apparatus was constructed for testing one- and two-stage turbines (using speed decrease from stage to stage). Turbines were tested with water-and-nitrogen mixtures and Refrigerant 22. Nozzle efficiencies were 0.78 (measured) and 0.72 (theoretical) for water-and-nitrogen mixtures at a water/nitrogen mixture ratio of 68, by mass; and 0.89 (measured) and 0.84 (theoretical) for Refrigerant 22 expanding from 0.02 quality to 0.28 quality. Blade efficiencies (shaft power before windage and bearing loss divided by nozzle jet power) were 0.63 (measured) and 0.71 (theoretical) for water-and-nitrogen mixtures and 0.62 (measured) and 0.63 (theoretical) for Refrigerant 22 with a single-stage turbine, and 0.70 (measured) and 0.85 (theoretical) for water-and-nitrogen mixtures with a two-stage turbine.

  7. Replaceable blade turbine and stationary specimen corrosion testing facility

    NASA Technical Reports Server (NTRS)

    Santoro, G. J.; Calfo, F. D.

    1985-01-01

    A facility was constructed to provide relatively low cost testing of hot section turbine blade and vane materials under hot corrosion conditions more akin to service environments. The facility consists of a small combustor whose pressurized gas flow can be directed to either a test section consisting of three small cascaded specimens or to a partial admittance single-stage axial flow turbine. The turbine rotor contains 28 replaceable turbine blades. The combustion gases resulting from the burning of Jet A-l fuel can be seeded with measured amounts of alkali salts. This facility is described here along with preliminary corrosion test results obtained during the final checkout of the facility.

  8. Energy efficient engine high-pressure turbine detailed design report

    NASA Technical Reports Server (NTRS)

    Thulin, R. D.; Howe, D. C.; Singer, I. D.

    1982-01-01

    The energy efficient engine high-pressure turbine is a single stage system based on technology advancements in the areas of aerodynamics, structures and materials to achieve high performance, low operating economics and durability commensurate with commercial service requirements. Low loss performance features combined with a low through-flow velocity approach results in a predicted efficiency of 88.8 for a flight propulsion system. Turbine airfoil durability goals are achieved through the use of advanced high-strength and high-temperature capability single crystal materials and effective cooling management. Overall, this design reflects a considerable extension in turbine technology that is applicable to future, energy efficient gas-turbine engines.

  9. One-dimensional analysis of choked-flow turbines

    NASA Technical Reports Server (NTRS)

    English, Robert E; Cavicchi, Richard H

    1953-01-01

    Turbines for most applications requiring high work output per stage have one or more blade rows which are choked. This analysis indicated that the area ratios and equivalent blade speed are the controlling factors in the design and operation of such turbines. Six criteria are stated that will aid in establishing from test data of multistage turbines which blade rows are choked and which are not. The variation in internal flow conditions with operating conditions for a turbine equipped with an adjustable stator is determined for one application of stator adjustment.

  10. Wind Turbines Benefit Crops

    SciTech Connect

    Takle, Gene

    2010-01-01

    Ames Laboratory associate scientist Gene Takle talks about research into the effect of wind turbines on nearby crops. Preliminary results show the turbines may have a positive effect by cooling and drying the crops and assisting with carbon dioxide uptake.

  11. Wind Turbines Benefit Crops

    ScienceCinema

    Takle, Gene

    2013-03-01

    Ames Laboratory associate scientist Gene Takle talks about research into the effect of wind turbines on nearby crops. Preliminary results show the turbines may have a positive effect by cooling and drying the crops and assisting with carbon dioxide uptake.

  12. Attenuation of upstream-generated low frequency noise by gas turbines

    NASA Technical Reports Server (NTRS)

    Doyle, V. L.; Matta, R. K.

    1977-01-01

    The acoustic transfer functions of low frequency (below 3500 Hz) noise through aircraft turbines were investigated. Model test results were compared with theoretical predictions in order to assess the validity of the theory. Component tests were conducted on both high pressure and low pressure model turbines. The influence of inlet temperature and turbine speed attenuation was evaluated, while the effects of turbine pressure ratio, blade-row choking, and additional downstream stages were determined. Preliminary identification of pertinent aeroacoustic correlating parameters was made.

  13. 76 FR 78863 - Airworthiness Directives; Rolls-Royce Corporation Turboshaft Engines

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-12-20

    ... ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will... inspection and fluorescent penetrant inspection (FPI) on certain 3rd and 4th stage turbine wheels for cracks in the turbine blades. We are proposing this AD to prevent failure of 3rd or 4th stage turbine...

  14. Sliding vane geometry turbines

    DOEpatents

    Sun, Harold Huimin; Zhang, Jizhong; Hu, Liangjun; Hanna, Dave R

    2014-12-30

    Various systems and methods are described for a variable geometry turbine. In one example, a turbine nozzle comprises a central axis and a nozzle vane. The nozzle vane includes a stationary vane and a sliding vane. The sliding vane is positioned to slide in a direction substantially tangent to an inner circumference of the turbine nozzle and in contact with the stationary vane.

  15. Large wind turbine generators

    NASA Technical Reports Server (NTRS)

    Thomas, R. L.; Donovon, R. M.

    1978-01-01

    The development associated with large wind turbine systems is briefly described. The scope of this activity includes the development of several large wind turbines ranging in size from 100 kW to several megawatt levels. A description of the wind turbine systems, their programmatic status and a summary of their potential costs is included.

  16. Results from Grimethorpe PFBC turbine cascade tests

    SciTech Connect

    Not Available

    1986-12-01

    The test program at the Grimethorpe Pressurized Fluidized-Bed Combustion (PFBC) facility included an assessment of the potential for deposition, corrosion, and erosion of gas turbine blade materials when exposed to PFBC off gases. Flue gas from the combustor was fed through three stages of cyclones before entering the cascade. The impulse foils were approximately the size and shape of the first stage blades in the GE MS-1002 gas turbine. The cascade operated through three test series, accumulating a total of 649 hours. The conditions experienced are summarized. The paper lists the alloys tested, and discusses the efficiency of the cyclones, the particle size distribution of the dusts not removed by the cyclones, and corrosion of the turbine blades. 4 references, 1 figure, 2 tables.

  17. Power dissipation of air turbine VT - 400

    NASA Astrophysics Data System (ADS)

    Noga, Tomas; Žitek, Pavel

    2016-06-01

    This article provides an overview of ongoing systematic research of a turbine stage efficiency on a model air turbine VT 400. It contains an analysis of existing mathematical relations for a rotor friction dissipation calculation, on which basis a practical procedure of a calculation of those dissipations is recommended. Friction dissipations in the turbine rotor were divided into three main tasks: disc friction dissipations, shaft friction dissipations and dissipations in bearings. A contribution of performed work lies in the fact, that there is a dependence of rotor friction losses on its speed and a stage reaction has been revealed. This knowledge is completely essential for a further research, and will lead to more precise results of experiments. For the future, we plan to adjust the measuring track by adding a moment collar. We also assume an experimental verification of calculated friction losses.

  18. Cyclic Structural Analyses of SSME Turbine Blades

    NASA Technical Reports Server (NTRS)

    Kaufman, A.; Manderscheid, J. M.

    1985-01-01

    The problems of calculating the structural response of high-temperature space propulsion components such as turbine blades for the fuel turbopump are addressed. The first high-pressure-stage fuel turbine blade (HPFTB) in the liquid-hydrogen turbopump of the space shuttle main engine (SSME) was selected for this study. In the past these blades have cracked in the blade shank region and at the airfoil leading edge adjacent to the platform. To achieve the necessary durability, these blades are currently being cast by using directional solidification. Single-crystal alloys are also being investigated for future SSME applications. The study evaluated the utility of advanced structural analysis methods in assessing the low-cycle fatigue lives of these anisotropic components. The turbine blade airfoil of the high-pressure stage of the SSME fuel turbopump was analyzed because it has a history of rapid crack initiation.

  19. A Brief Boot Camp for 4th-Year Medical Students Entering into Pediatric and Family Medicine Residencies

    PubMed Central

    Adler, Mark; Mangold, Karen; Trainor, Jennifer

    2016-01-01

    The transition from medical student to intern is a challenging process characterized by a steep learning curve. Focused courses targeting skills necessary for success as a resident have increased self-perceived preparedness, confidence, and medical knowledge. Our aim was to create a brief educational intervention for 4th-year medical students entering pediatric, family practice, and medicine/pediatric residencies to target skills necessary for an internship. The curriculum used a combination of didactic presentations, small group discussions, role-playing, facilitated debriefing, and simulation-based education. Participants completed an objective structured clinical exam requiring synthesis and application of multiple boot camp elements before and after the elective. Participants completed anonymous surveys assessing self-perceived preparedness for an internship, overall and in regards to specific skills, before the elective and after the course. Participants were asked to provide feedback about the course. Using checklists to assess performance, students showed an improvement in performing infant lumbar punctures (47.2% vs 77.0%; p < 0.01, 95% CI for the difference 0.2, 0.4%) and providing signout (2.5 vs. 3.9 (5-point scale) p < 0.01, 95% CI for the difference 0.6, 2.3). They did not show an improvement in communication with a parent. Participants demonstrated an increase in self-reported preparedness for all targeted skills, except for obtaining consults and interprofessional communication. There was no increase in reported overall preparedness. All participants agreed with the statements, “The facilitators presented the material in an effective manner,” “I took away ideas I plan to implement in internship,” and “I think all students should participate in a similar experience.” When asked to assess the usefulness of individual modules, all except order writing received a mean Likert score > 4. A focused boot camp addressing key knowledge and skills

  20. A Brief Boot Camp for 4th-Year Medical Students Entering into Pediatric and Family Medicine Residencies.

    PubMed

    Burns, Rebekah; Adler, Mark; Mangold, Karen; Trainor, Jennifer

    2016-01-01

    The transition from medical student to intern is a challenging process characterized by a steep learning curve. Focused courses targeting skills necessary for success as a resident have increased self-perceived preparedness, confidence, and medical knowledge. Our aim was to create a brief educational intervention for 4th-year medical students entering pediatric, family practice, and medicine/pediatric residencies to target skills necessary for an internship. The curriculum used a combination of didactic presentations, small group discussions, role-playing, facilitated debriefing, and simulation-based education. Participants completed an objective structured clinical exam requiring synthesis and application of multiple boot camp elements before and after the elective. Participants completed anonymous surveys assessing self-perceived preparedness for an internship, overall and in regards to specific skills, before the elective and after the course. Participants were asked to provide feedback about the course. Using checklists to assess performance, students showed an improvement in performing infant lumbar punctures (47.2% vs 77.0%; p < 0.01, 95% CI for the difference 0.2, 0.4%) and providing signout (2.5 vs. 3.9 (5-point scale) p < 0.01, 95% CI for the difference 0.6, 2.3). They did not show an improvement in communication with a parent. Participants demonstrated an increase in self-reported preparedness for all targeted skills, except for obtaining consults and interprofessional communication. There was no increase in reported overall preparedness. All participants agreed with the statements, "The facilitators presented the material in an effective manner," "I took away ideas I plan to implement in internship," and "I think all students should participate in a similar experience." When asked to assess the usefulness of individual modules, all except order writing received a mean Likert score > 4. A focused boot camp addressing key knowledge and skills required for

  1. PREFACE: 9th World Congress on Computational Mechanics and 4th Asian Pacific Congress on Computational Mechanics

    NASA Astrophysics Data System (ADS)

    Khalili, N.; Valliappan, S.; Li, Q.; Russell, A.

    2010-07-01

    The use for mathematical models of natural phenomena has underpinned science and engineering for centuries, but until the advent of modern computers and computational methods, the full utility of most of these models remained outside the reach of the engineering communities. Since World War II, advances in computational methods have transformed the way engineering and science is undertaken throughout the world. Today, theories of mechanics of solids and fluids, electromagnetism, heat transfer, plasma physics, and other scientific disciplines are implemented through computational methods in engineering analysis, design, manufacturing, and in studying broad classes of physical phenomena. The discipline concerned with the application of computational methods is now a key area of research, education, and application throughout the world. In the early 1980's, the International Association for Computational Mechanics (IACM) was founded to promote activities related to computational mechanics and has made impressive progress. The most important scientific event of IACM is the World Congress on Computational Mechanics. The first was held in Austin (USA) in 1986 and then in Stuttgart (Germany) in 1990, Chiba (Japan) in 1994, Buenos Aires (Argentina) in 1998, Vienna (Austria) in 2002, Beijing (China) in 2004, Los Angeles (USA) in 2006 and Venice, Italy; in 2008. The 9th World Congress on Computational Mechanics is held in conjunction with the 4th Asian Pacific Congress on Computational Mechanics under the auspices of Australian Association for Computational Mechanics (AACM), Asian Pacific Association for Computational Mechanics (APACM) and International Association for Computational Mechanics (IACM). The 1st Asian Pacific Congress was in Sydney (Australia) in 2001, then in Beijing (China) in 2004 and Kyoto (Japan) in 2007. The WCCM/APCOM 2010 publications consist of a printed book of abstracts given to delegates, along with 247 full length peer reviewed papers published with

  2. Multi-stage flash degaser

    DOEpatents

    Rapier, P.M.

    1980-06-26

    A multi-stage flash degaser is incorporated in an energy conversion system having a direct-contact, binary-fluid heat exchanger to remove essentially all of the noncondensable gases from geothermal brine ahead of the direct-contact binary-fluid heat exchanger in order that the heat exchanger and a turbine and condenser of the system can operate at optimal efficiency.

  3. Advanced multistage turbine blade aerodynamics, performance, cooling, and heat transfer

    SciTech Connect

    Fleeter, S.; Lawless, P.B.

    1995-10-01

    The gas turbine has the potential for power production at the highest possible efficiency. The challenge is to ensure that gas turbines operate at the optimum efficiency so as to use the least fuel and produce minimum emissions. A key component to meeting this challenge is the turbine. Turbine performance, both aerodynamics and heat transfer, is one of the barrier advanced gas turbine development technologies. This is a result of the complex, highly three-dimensional and unsteady flow phenomena in the turbine. Improved turbine aerodynamic performance has been achieved with three-dimensional highly-loaded airfoil designs, accomplished utilizing Euler or Navier-Stokes Computational Fluid Dynamics (CFD) codes. These design codes consider steady flow through isolated blade rows. Thus they do not account for unsteady flow effects. However, unsteady flow effects have a significant impact on performance. Also, CFD codes predict the complete flow field. The experimental verification of these codes has traditionally been accomplished with point data - not corresponding plane field measurements. Thus, although advanced CFD predictions of the highly complex and three-dimensional turbine flow fields are available, corresponding data are not. To improve the design capability for high temperature turbines, a detailed understanding of the highly unsteady and three-dimensional flow through multi-stage turbines is necessary. Thus, unique data are required which quantify the unsteady three-dimensional flow through multi-stage turbine blade rows, including the effect of the film coolant flow. This requires experiments in appropriate research facilities in which complete flow field data, not only point measurements, are obtained and analyzed. Also, as design CFD codes do not account for unsteady flow effects, the next logical challenge and the current thrust in CFD code development is multiple-stage analyses that account for the interactions between neighboring blade rows.

  4. Something going on in Milan: a review of the 4th International PhD Student Cancer Conference.

    PubMed

    Segré, C

    2010-01-01

    The 4th International PhD Student Cancer Conference was held at the IFOM-IEO-Campus in Milan from 19-21 May 2010 http://www.semm.it/events_researchPast.phpThe Conference covered many topics related to cancer, from basic biology to clinical aspects of the disease. All attendees presented their research, by either giving a talk or presenting a poster. This conference is an opportunity to introduce PhD students to top cancer research institutes across Europe.THE CORE PARTICIPANTING INSTITUTES INCLUDED: European School of Molecular Medicine (SEMM)-IFOM-IEO Campus, MilanBeatson Institute for Cancer Research (BICR), GlasgowCambridge Research Institute (CRI), Cambridge, UKMRC Gray Institute of Radiation Biology (GIROB), OxfordLondon Research Institute (LRI), LondonPaterson Institute for Cancer Research (PICR), ManchesterThe Netherlands Cancer Institute (NKI), Amsterdam'You organizers have crushed all my prejudices towards Italians. Congratulations, I enjoyed the conference immensely!' Even if it might have sounded like rudeness for sure this was supposed to be a genuine compliment (at least, that's how we took it), also considering that it was told by a guy who himself was the fusion of two usually antithetical concepts: fashion style and English nationality.The year 2010 has marked an important event for Italian research in the international scientific panorama: the European School of Molecular Medicine (SEMM) had the honour to host the 4th International PhD Student Cancer Conference, which was held from 19-21 May 2010 at the IFOM-IEO-Campus (http://www.semm.it/events_researchPast.php) in Milan.The conference was attended by more than one hundred students, coming from a selection of cutting edge European institutes devoted to cancer research. The rationale behind it is the promotion of cooperation among young scientists across Europe to debate about science and to exchange ideas and experiences. But that is not all, it is also designed for PhD students to get in touch

  5. Single shaft automotive gas turbine engine characterization test

    NASA Technical Reports Server (NTRS)

    Johnson, R. A.

    1979-01-01

    An automotive gas turbine incorporating a single stage centrifugal compressor and a single stage radial inflow turbine is described. Among the engine's features is the use of wide range variable geometry at the inlet guide vanes, the compressor diffuser vanes, and the turbine inlet vanes to achieve improved part load fuel economy. The engine was tested to determine its performance in both the variable geometry and equivalent fixed geometry modes. Testing was conducted without the originally designed recuperator. Test results were compared with the predicted performance of the nonrecuperative engine based on existing component rig test maps. Agreement between test results and the computer model was achieved.

  6. Turbine Imaging Technology Assessment

    SciTech Connect

    Moursund, Russell A.; Carlson, Thomas J.

    2004-12-31

    The goal of this project was to identify and evaluate imaging alternatives for observing the behavior of juvenile fish within an operating Kaplan turbine unit with a focus on methods to quantify fish injury mechanisms inside an operating turbine unit. Imaging methods are particularly needed to observe the approach and interaction of fish with turbine structural elements. This evaluation documents both the opportunities and constraints for observing juvenile fish at specific locations during turbine passage. The information may be used to acquire the scientific knowledge to make structural improvements and create opportunities for industry to modify turbines and improve fish passage conditions.

  7. HUMID AIR TURBINE CYCLE TECHNOLOGY DEVELOPMENT PROGRAM

    SciTech Connect

    Richard Tuthill

    2002-07-18

    The Humid Air Turbine (HAT) Cycle Technology Development Program focused on obtaining HAT cycle combustor technology that will be the foundation of future products. The work carried out under the auspices of the HAT Program built on the extensive low emissions stationary gas turbine work performed in the past by Pratt & Whitney (P&W). This Program is an integral part of technology base development within the Advanced Turbine Systems Program at the Department of Energy (DOE) and its experiments stretched over 5 years. The goal of the project was to fill in technological data gaps in the development of the HAT cycle and identify a combustor configuration that would efficiently burn high moisture, high-pressure gaseous fuels with low emissions. The major emphasis will be on the development of kinetic data, computer modeling, and evaluations of combustor configurations. The Program commenced during the 4th Quarter of 1996 and closed in the 4th Quarter of 2001. It teamed the National Energy Technology Laboratory (NETL) with P&W, the United Technologies Research Center (UTRC), and a subcontractor on-site at UTRC, kraftWork Systems Inc. The execution of the program started with bench-top experiments that were conducted at UTRC for extending kinetic mechanisms to HAT cycle temperature, pressure, and moisture conditions. The fundamental data generated in the bench-top experiments was incorporated into the analytical tools available at P&W to design the fuel injectors and combustors. The NETL then used the hardware to conduct combustion rig experiments to evaluate the performance of the combustion systems at elevated pressure and temperature conditions representative of the HAT cycle. The results were integrated into systems analysis done by kraftWork to verify that sufficient understanding of the technology had been achieved and that large-scale technological application and demonstration could be undertaken as follow-on activity. An optional program extended the

  8. Wind turbine rotor assembly

    SciTech Connect

    Kaiser, H. W.

    1984-11-20

    A vertical axis wind turbine having a horizontal arm member which supports an upright blade assembly. Bearing structure coupling the blade assembly to the turbine arm permits blade movement about its longitudinal axis as well as flexing motion of the blade assembly about axes perpendicular to the longitudinal axis. A latching mechanism automatically locks the blade assembly to its supporting arm during normal turbine operation and automatically unlocks same when the turbine is at rest. For overspeed prevention, a centrifugally actuated arm functions to unlatch the blade assembly permitting same to slipstream or feather into the wind. Manually actuated means are also provided for unlatching the moving blade assembly. The turbine arm additionally carries a switching mechanism in circuit with a turbine generator with said mechanism functioning to open and hence protect the generator circuit in the event of an overspeed condition of the turbine.

  9. Bilateral inferior turbinate osteoma.

    PubMed

    Sahemey, R; Warfield, A T; Ahmed, S

    2016-01-01

    Osteomas are the most common benign osteoclastic tumours of the paranasal sinuses. However, nasal cavity and turbinate osteomas are extremely rare. Only nine middle turbinate, three inferior turbinate and one inferior turbinate osteoma cases have been reported to date. The present case report describes the management and follow-up of symptomatic bilateral inferior turbinate osteoma.A 60-year-old female presented with symptoms of bilateral nasal obstruction and right-sided epiphora. Radiological investigation found hypertrophic bony changes involving both inferior turbinates. The patient was managed successfully by endoscopic inferior turbinectomies in order to achieve a patent airway, with no further recurrence of tumour after 3 months postoperatively.To the best of our knowledge, this is the first reported case of bilateral inferior turbinate osteoma. We describe a safe and minimally invasive method of tumour resection, which has a better cosmetic outcome compared with other approaches. PMID:27534890

  10. Comparison of rhodomine-WT and sodium chloride tracer transport in a 4th order arctic river

    NASA Astrophysics Data System (ADS)

    Smull, E. M.; Wlostowski, A. N.; Gooseff, M. N.; Bowden, W. B.; Wollheim, W. M.

    2012-12-01

    Conservative tracers are useful for tracking a parcel of water through a river reach and understanding tracer transport phenomena (i.e. advection, dispersion, and transient storage). Rhodomine- WT (RWT) and sodium chloride (NaCl) are two popular stream tracers. NaCl is considered to be conservative and relatively inexpensive, yet it cannot be detected at very low concentrations. On the other hand, RWT can be detected at very low concentrations (<0.1 ppb), but it is known to photo-degrade and sorb to organic materials. Previous work has compared these tracers with small-scale laboratory analyses and field experiments on small headwater streams. The limitations and advantages to each of these tracers, as applied to large river slug injections, are not clearly understood. This work seeks to answer the following questions: 1) Does RWT improve the tracer window of detection (time of tracer arrival to time of tracer non-detection), compared to NaCl? 2) Are there differences in the late-time tailing behavior of each tracer? More specifically, can we compare RWT and NaCl breakthrough curve tail shapes to understand processes contributing to late time solute transport (transient storage or sorption-desorption)? During the summer of 2012, combined slug additions of RWT and NaCl were injected into a 1.5-kilometer reach on the Kuparuk River, a 4th order tundra river underlain by continuous permafrost located on Alaska's North Slope. Fluorescence and electrical conductivity were continuously logged at the upstream and downstream ends of the reach. Preliminary results show that the window of detection is expanded when using RWT under both high and low flow conditions by 0.2 times the advective transport timescale. Tail shapes are more similar under higher discharge conditions and dissimilar under lower discharge conditions. For example, using an exponential regression model (c(t) = eat) to quantify tail shapes, at Q = 500 l/s the exponential coefficient ratio, aRWT:aNaCl, is 0

  11. Syntheses and single-crystal structures of CsTh(MoO 4) 2Cl and Na 4Th(WO 4) 4

    NASA Astrophysics Data System (ADS)

    Bang Jin, Geng; Soderholm, L.

    2011-02-01

    Colorless crystals of CsTh(MoO 4) 2Cl and Na 4Th(WO 4) 4 have been synthesized at 993 K by the solid-state reactions of ThO 2, MoO 3, CsCl, and ThCl 4 with Na 2WO 4. Both compounds have been characterized by the single-crystal X-ray diffraction. The structure of CsTh(MoO 4) 2Cl is orthorhombic, consisting of two adjacent [Th(MoO 4) 2] layers separated by an ionic CsCl sublattice. It can be considered as an insertion compound of Th(MoO 4) 2 and reformulated as Th(MoO 4) 2·CsCl. The Th atom coordinates to seven monodentate MoO 4 tetrahedra and one Cl atom in a highly distorted square antiprism. Na 4Th(WO 4) 4 adopts a scheelite superlattice structure. The three-dimensional framework of Na 4Th(WO 4) 4 is constructed from corner-sharing ThO 8 square antiprisms and WO 4 tetrahedra. The space within the channels is filled by six-coordinate Na ions. Crystal data: CsTh(MoO 4) 2Cl, monoclinic, P2 1/ c, Z=4, a=10.170(1) Å, b=10.030(1) Å, c=9.649(1) Å, β=95.671(2)°, V=979.5(2) Å 3, R( F)=2.65% for I>2 σ( I); Na 4Th(WO 4) 4, tetragonal, I4 1/ a, Z=4, a=11.437(1) Å, c=11.833(2) Å, V=1547.7(4) Å 3, R( F)=3.02% for I>2 σ( I).

  12. 2.5 Gbps clock data recovery using 1/4th-rate quadricorrelator frequency detector and skew-calibrated multi-phase clock generator

    NASA Astrophysics Data System (ADS)

    Tontisirin, S.; Tielert, R.

    2006-09-01

    A Gb/s clock and data recovery (CDR) circuit using 1/4th-rate digital quadricorrelator frequency detector and skew-calibrated multi-phase voltage-controlled oscillator is presented. With 1/4th-rate clock architecture, the coil-free oscillator can have lower operation frequency providing sufficient low-jitter operation. Moreover, it is an inherent 1-to-4 DEMUX. The skew calibration scheme is applied to reduce phase offset in multi-phase clock generator. The CDR with frequency detector can have small loop bandwidth, wide pull-in range and can operate without the need for a local reference clock. This 1/4th-rate CDR is implemented in standard 0.18 μm CMOS technology. It has an active area of 0.7 mm2 and consumes 100 mW at 1.8 V supply. The CDR has low jitter operation in a wide frequency range from 1-2.25 Gb/s. Measurement of Bit-Error Rate is less than 10-12 for 2.25 Gb/s incoming data 27-1 PRBS, jitter peak-to-peak of 0.7 unit interval (UI) modulation at 10 MHz.

  13. Coalescing Wind Turbine Wakes

    DOE PAGESBeta

    Lee, S.; Churchfield, M.; Sirnivas, S.; Moriarty, P.; Nielsen, F. G.; Skaare, B.; Byklum, E.

    2015-06-18

    A team of researchers from the National Renewable Energy Laboratory and Statoil used large-eddy simulations to numerically investigate the merging wakes from upstream offshore wind turbines. Merging wakes are typical phenomena in wind farm flows in which neighboring turbine wakes consolidate to form complex flow patterns that are as yet not well understood. In the present study, three 6-MW turbines in a row were subjected to a neutrally stable atmospheric boundary layer flow. As a result, the wake from the farthest upstream turbine conjoined the downstream wake, which significantly altered the subsequent velocity deficit structures, turbulence intensity, and the globalmore » meandering behavior. The complexity increased even more when the combined wakes from the two upstream turbines mixed with the wake generated by the last turbine, thereby forming a "triplet" structure. Although the influence of the wake generated by the first turbine decayed with downstream distance, the mutated wakes from the second turbine continued to influence the downstream wake. Two mirror-image angles of wind directions that yielded partial wakes impinging on the downstream turbines yielded asymmetric wake profiles that could be attributed to the changing flow directions in the rotor plane induced by the Coriolis force. In conclusion, the turbine wakes persisted for extended distances in the present study, which is a result of low aerodynamic surface roughness typically found in offshore conditions« less

  14. Coalescing Wind Turbine Wakes

    SciTech Connect

    Lee, S.; Churchfield, M.; Sirnivas, S.; Moriarty, P.; Nielsen, F. G.; Skaare, B.; Byklum, E.

    2015-06-18

    A team of researchers from the National Renewable Energy Laboratory and Statoil used large-eddy simulations to numerically investigate the merging wakes from upstream offshore wind turbines. Merging wakes are typical phenomena in wind farm flows in which neighboring turbine wakes consolidate to form complex flow patterns that are as yet not well understood. In the present study, three 6-MW turbines in a row were subjected to a neutrally stable atmospheric boundary layer flow. As a result, the wake from the farthest upstream turbine conjoined the downstream wake, which significantly altered the subsequent velocity deficit structures, turbulence intensity, and the global meandering behavior. The complexity increased even more when the combined wakes from the two upstream turbines mixed with the wake generated by the last turbine, thereby forming a "triplet" structure. Although the influence of the wake generated by the first turbine decayed with downstream distance, the mutated wakes from the second turbine continued to influence the downstream wake. Two mirror-image angles of wind directions that yielded partial wakes impinging on the downstream turbines yielded asymmetric wake profiles that could be attributed to the changing flow directions in the rotor plane induced by the Coriolis force. In conclusion, the turbine wakes persisted for extended distances in the present study, which is a result of low aerodynamic surface roughness typically found in offshore conditions

  15. Turbine engine interstage seal

    SciTech Connect

    Clevenger, L.L.

    1993-08-10

    A seal structure is described for a turbine engine, the turbine engine including a housing surrounding a centrifugal compressor having a rotor, and a radial inflow turbine including a turbine rotor, the compressor rotor and the turbine rotor being disposed in back-to-back relation, the turbine rotor being drivingly connected with the compressor rotor and axially spaced therefrom to define an annular gap there between, the gap radially bounded at its outer periphery by the housing and at its inner periphery by an annular surface intermediate the compressor rotor and the turbine rotor an annular sealing member disposed in the gap to control air flow from the compressor toward the turbine; the annular sealing member the first axial direction, and a third annular wall portion joining with the second annular wall portion and extending inward therefrom towards the surface intermediate the compressor rotor and the turbine rotor, and biasing means cooperating with the housing for urging the seal structure toward the turbine rotor.

  16. Coalescing Wind Turbine Wakes

    NASA Astrophysics Data System (ADS)

    Lee, S.; Churchfield, M.; Sirnivas, S.; Moriarty, P.; Nielsen, F. G.; Skaare, B.; Byklum, E.

    2015-06-01

    A team of researchers from the National Renewable Energy Laboratory and Statoil used large-eddy simulations to numerically investigate the merging wakes from upstream offshore wind turbines. Merging wakes are typical phenomena in wind farm flows in which neighboring turbine wakes consolidate to form complex flow patterns that are as yet not well understood. In the present study, three 6-MW turbines in a row were subjected to a neutrally stable atmospheric boundary layer flow. As a result, the wake from the farthest upstream turbine conjoined the downstream wake, which significantly altered the subsequent velocity deficit structures, turbulence intensity, and the global meandering behavior. The complexity increased even more when the combined wakes from the two upstream turbines mixed with the wake generated by the last turbine, thereby forming a “triplet” structure. Although the influence of the wake generated by the first turbine decayed with downstream distance, the mutated wakes from the second turbine continued to influence the downstream wake. Two mirror-image angles of wind directions that yielded partial wakes impinging on the downstream turbines yielded asymmetric wake profiles that could be attributed to the changing flow directions in the rotor plane induced by the Coriolis force. The turbine wakes persisted for extended distances in the present study, which is a result of low aerodynamic surface roughness typically found in offshore conditions.

  17. Turbine engine variable geometry device

    NASA Technical Reports Server (NTRS)

    Rogo, Casimir (Inventor); Lenz, Herman N. (Inventor)

    1985-01-01

    A variable geometry device for use with the turbine nozzle of a turbine engine of the type having a support housing and a combustion chamber contained within the support housing. A pair of spaced walls in the support housing define an annular and radially extending nozzle passageway. The outer end of the nozzle passageway is open to the combustion chamber while the inner end of the nozzle passageway is open to one or more turbine stages. A plurality of circumferentially spaced nozzle vanes are mounted to one of the spaced walls and protrude across the nozzle passageway. An annular opening is formed around the opposite spaced wall and an annular ring is axially slidably mounted within the opening. A motor is operatively connected to this ring and, upon actuation, axially displaces the ring within the nozzle passageway. In addition, the ring includes a plurality of circumferentially spaced slots which register with the nozzle vanes so that the vane geometry remains the same despite axial displacement of the ring.

  18. Numerical investigation of Marine Hydrokinetic Turbines: methodology development for single turbine and small array simulation, and application to flume and full-scale reference models

    NASA Astrophysics Data System (ADS)

    Javaherchi Mozafari, Amir Teymour

    A hierarchy of numerical models, Single Rotating Reference Frame (SRF) and Blade Element Model (BEM), were used for numerical investigation of horizontal axis Marine Hydrokinetic (MHK) Turbines. In the initial stage the SRF and BEM were used to simulate the performance and turbulent wake of a flume- and a full-scale MHK turbine reference model. A significant level of understanding and confidence was developed in the implementation of numerical models for simulation of a MHK turbine. This was achieved by simulation of the flume-scale turbine experiments and comparison between numerical and experimental results. Then the developed numerical methodology was applied to simulate the performance and wake of the full-scale MHK reference model (DOE Reference Model 1). In the second stage the BEM was used to simulate the experimental study of two different MHK turbine array configurations (i.e. two and three coaxial turbines). After developing a numerical methodology using the experimental comparison to simulate the flow field of a turbine array, this methodology was applied toward array optimization study of a full-scale model with the goal of proposing an optimized MHK turbine configuration with minimal computational cost and time. In the last stage the BEM was used to investigate one of the potential environmental effects of MHK turbine. A general methodological approach was developed and experimentally validated to investigate the effect of MHK turbine wake on the sedimentation process of suspended particles in a tidal channel.

  19. 30. VICTOR WATER TURBINE, STILWELLBIERCE CO., DAYTON, OHIO. SIMILAR TURBINE ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    30. VICTOR WATER TURBINE, STILWELL-BIERCE CO., DAYTON, OHIO. SIMILAR TURBINE TO LEFT (DOUBLE TURBINE SYSTEM), PHOTO TAKEN FROM PENSTOCK. - Prattville Manufacturing Company, Number One, 242 South Court Street, Prattville, Autauga County, AL

  20. Airfoil Heat Transfer Characteristics in Syngas and Hydrogen Turbines

    SciTech Connect

    Mazzotta, D.W.; Chyu, M.K.; Alvin, M.A.

    2007-05-01

    Hydrogen or coal-derivative syngas turbines promise increased efficiency with exceptionally low NOx emissions compared to the natural gas based turbines. To reach this goal, turbine inlet temperature (TIT) will need to be elevated to a level exceeding 1700°C [1, 2]. The thermal load induced by such a temperature increase alone will lead to immense challenges in maintaining material integrity of turbine components. In addition, as working fluid in the gas path will primarily be steam, possibly mixed with carbon oxides, the aero-thermal characteristic in a hydrogen turbine is expected to be far different from that of air/nitrogen enriched gas stream in a gas turbine. For instance, steam has distinctly higher density and specific heat in comparison to a mixture of air and combustion gases as they are expanded in a conventional gas turbine. Even if the temperature limits remain about the same, the expansion in a hydrogen turbine will have to proceed with a greater enthalpy drop and therefore requires a larger number of stages. This also implies that the flow areas may need to be expanded and blade span to be enlarged. Meanwhile, a greater number of stages and hot surfaces need to be protected. This also suggests that current cooling technology available for modern day gas turbines has to be significantly improved. The ultimate goal of the present study is to systematically investigate critical issues concerning cooling technology as it is applicable to oxy-fuel and hydrogen turbine systems, and the main scope is to develop viable means to estimate the thermal load on the turbine “gas side”, that is eventually to be removed from the “coolant side”, and to comparatively quantify the implication of external heat load and potential thermal barrier coating (TBC) degradation on the component durability and lifing. The analysis is based on two well-tested commercial codes, FLUENT and ANSYS.

  1. Rocket Engine Turbine Blade Surface Pressure Distributions Experiment and Computations

    NASA Technical Reports Server (NTRS)

    Hudson, Susan T.; Zoladz, Thomas F.; Dorney, Daniel J.; Turner, James (Technical Monitor)

    2002-01-01

    Understanding the unsteady aspects of turbine rotor flow fields is critical to successful future turbine designs. A technology program was conducted at NASA's Marshall Space Flight Center to increase the understanding of unsteady environments for rocket engine turbines. The experimental program involved instrumenting turbine rotor blades with miniature surface mounted high frequency response pressure transducers. The turbine model was then tested to measure the unsteady pressures on the rotor blades. The data obtained from the experimental program is unique in two respects. First, much more unsteady data was obtained (several minutes per set point) than has been possible in the past. Also, an extensive steady performance database existed for the turbine model. This allowed an evaluation of the effect of the on-blade instrumentation on the turbine's performance. A three-dimensional unsteady Navier-Stokes analysis was also used to blindly predict the unsteady flow field in the turbine at the design operating conditions and at +15 degrees relative incidence to the first-stage rotor. The predicted time-averaged and unsteady pressure distributions show good agreement with the experimental data. This unique data set, the lessons learned for acquiring this type of data, and the improvements made to the data analysis and prediction tools are contributing significantly to current Space Launch Initiative turbine airflow test and blade surface pressure prediction efforts.

  2. Unsteady Flow in a Supersonic Turbine with Variable Specific Heats

    NASA Technical Reports Server (NTRS)

    Dorney, Daniel J.; Griffin, Lisa W.; Huber, Frank; Sondak, Douglas L.; Turner, James (Technical Monitor)

    2001-01-01

    Modern high-work turbines can be compact, transonic, supersonic, counter-rotating, or use a dense drive gas. The vast majority of modern rocket turbine designs fall into these Categories. These turbines usually have large temperature variations across a given stage, and are characterized by large amounts of flow unsteadiness. The flow unsteadiness can have a major impact on the turbine performance and durability. For example, the Space Transportation Main Engine (STME) fuel turbine, a high work, transonic design, was found to have an unsteady inter-row shock which reduced efficiency by 2 points and increased dynamic loading by 24 percent. The Revolutionary Reusable Technology Turbopump (RRTT), which uses full flow oxygen for its drive gas, was found to shed vortices with such energy as to raise serious blade durability concerns. In both cases, the sources of the problems were uncovered (before turbopump testing) with the application of validated, unsteady computational fluid dynamics (CFD) to the designs. In the case of the RRTT and the Alternate Turbopump Development (ATD) turbines, the unsteady CFD codes have been used not just to identify problems, but to guide designs which mitigate problems due to unsteadiness. Using unsteady flow analyses as a part of the design process has led to turbine designs with higher performance (which affects temperature and mass flow rate) and fewer dynamics problems. One of the many assumptions made during the design and analysis of supersonic turbine stages is that the values of the specific heats are constant. In some analyses the value is based on an average of the expected upstream and downstream temperatures. In stages where the temperature can vary by 300 to 500 K, however, the assumption of constant fluid properties may lead to erroneous performance and durability predictions. In this study the suitability of assuming constant specific heats has been investigated by performing three-dimensional unsteady Navier

  3. Guest Editor's introduction: Selected papers from the 4th USENIX Conference on Object-Oriented Technologies and Systems

    NASA Astrophysics Data System (ADS)

    Sventek, Joe

    1998-12-01

    Hewlett-Packard Laboratories, 1501 Page Mill Road, Palo Alto, CA 94304, USA Introduction The USENIX Conference on Object-Oriented Technologies and Systems (COOTS) is held annually in the late spring. The conference evolved from a set of C++ workshops that were held under the auspices of USENIX, the first of which met in 1989. Given the growing diverse interest in object-oriented technologies, the C++ focus of the workshop eventually became too narrow, with the result that the scope was widened in 1995 to include object-oriented technologies and systems. COOTS is intended to showcase advanced R&D efforts in object-oriented technologies and software systems. The conference emphasizes experimental research and experience gained by using object-oriented techniques and languages to build complex software systems that meet real-world needs. COOTS solicits papers in the following general areas: application of, and experiences with, object-oriented technologies in particular domains (e.g. financial, medical, telecommunication); the architecture and implementation of distributed object systems (e.g. CORBA, DCOM, RMI); object-oriented programming and specification languages; object-oriented design and analysis. The 4th meeting of COOTS was held 27 - 30 April 1998 at the El Dorado Hotel, Santa Fe, New Mexico, USA. Several tutorials were given. The technical program proper consisted of a single track of six sessions, with three paper presentations per session. A keynote address and a provocative panel session rounded out the technical program. The program committee reviewed 56 papers, selecting the best 18 for presentation in the technical sessions. While we solicit papers across the spectrum of applications of object-oriented technologies, this year there was a predominance of distributed, object-oriented papers. The accepted papers reflected this asymmetry, with 15 papers on distributed objects and 3 papers on object-oriented languages. The papers in this special issue are

  4. Direct drive wind turbine

    DOEpatents

    Bywaters, Garrett Lee; Danforth, William; Bevington, Christopher; Stowell, Jesse; Costin, Daniel

    2006-09-19

    A wind turbine is provided that minimizes the size of the drive train and nacelle while maintaining the power electronics and transformer at the top of the tower. The turbine includes a direct drive generator having an integrated disk brake positioned radially inside the stator while minimizing the potential for contamination. The turbine further includes a means for mounting a transformer below the nacelle within the tower.

  5. Direct drive wind turbine

    DOEpatents

    Bywaters, Garrett; Danforth, William; Bevington, Christopher; Jesse, Stowell; Costin, Daniel

    2007-02-27

    A wind turbine is provided that minimizes the size of the drive train and nacelle while maintaining the power electronics and transformer at the top of the tower. The turbine includes a direct drive generator having an integrated disk brake positioned radially inside the stator while minimizing the potential for contamination. The turbine further includes a means for mounting a transformer below the nacelle within the tower.

  6. Direct drive wind turbine

    DOEpatents

    Bywaters, Garrett; Danforth, William; Bevington, Christopher; Stowell, Jesse; Costin, Daniel

    2006-07-11

    A wind turbine is provided that minimizes the size of the drive train and nacelle while maintaining the power electronics and transformer at the top of the tower. The turbine includes a direct drive generator having an integrated disk brake positioned radially inside the stator while minimizing the potential for contamination. The turbine further includes a means for mounting a transformer below the nacelle within the tower.

  7. Direct drive wind turbine

    DOEpatents

    Bywaters, Garrett; Danforth, William; Bevington, Christopher; Jesse, Stowell; Costin, Daniel

    2006-10-10

    A wind turbine is provided that minimizes the size of the drive train and nacelle while maintaining the power electronics and transformer at the top of the tower. The turbine includes a direct drive generator having an integrated disk brake positioned radially inside the stator while minimizing the potential for contamination. The turbine further includes a means for mounting a transformer below the nacelle within the tower.

  8. Small turbines, big unknown

    SciTech Connect

    Gipe, P.

    1995-07-01

    While financial markets focus on the wheeling and dealing of the big wind companies, the small wind turbine industry quietly keeps churning out its smaller but effective machines. Some, the micro turbines, are so small they can be carried by hand. Though worldwide sales of small wind turbines fall far short of even one large windpower plant, figures reach $8 million to $10 million annually and could be as much as twice that if batteries and engineering services are included.

  9. Vertical Axis Wind Turbine

    2002-04-01

    Blade fatigue life is an important element in determining the economic viability of the Vertical-Axis Wind Turbine (VAWT). VAWT-SAL Vertical Axis Wind Turbine- Stochastic Aerodynamic Loads Ver 3.2 numerically simulates the stochastic (random0 aerodynamic loads of the Vertical-Axis Wind Turbine (VAWT) created by the atomspheric turbulence. The program takes into account the rotor geometry, operating conditions, and assumed turbulence properties.

  10. Rampressor Turbine Design

    SciTech Connect

    Ramgen Power Systems

    2003-09-30

    The design of a unique gas turbine engine is presented. The first Rampressor Turbine engine rig will be a configuration where the Rampressor rotor is integrated into an existing industrial gas turbine engine. The Rampressor rotor compresses air which is burned in a traditional stationary combustion system in order to increase the enthalpy of the compressed air. The combustion products are then expanded through a conventional gas turbine which provides both compressor and electrical power. This in turn produces shaft torque, which drives a generator to provide electricity. The design and the associated design process of such an engine are discussed in this report.

  11. Wind Turbine Structural Dynamics

    NASA Technical Reports Server (NTRS)

    Miller, D. R. (Editor)

    1978-01-01

    A workshop on wind turbine structural dynamics was held to review and document current United States work on the dynamic behavior of large wind turbines, primarily of the horizontal-axis type, and to identify and discuss other wind turbine configurations that may have lower cost and weight. Information was exchanged on the following topics: (1) Methods for calculating dynamic loads; (2) Aeroelasticity stability (3) Wind loads, both steady and transient; (4) Critical design conditions; (5) Drive train dynamics; and (6) Behavior of operating wind turbines.

  12. Hermetic turbine generator

    DOEpatents

    Meacher, John S.; Ruscitto, David E.

    1982-01-01

    A Rankine cycle turbine drives an electric generator and a feed pump, all on a single shaft, and all enclosed within a hermetically sealed case. The shaft is vertically oriented with the turbine exhaust directed downward and the shaft is supported on hydrodynamic fluid film bearings using the process fluid as lubricant and coolant. The selection of process fluid, type of turbine, operating speed, system power rating, and cycle state points are uniquely coordinated to achieve high turbine efficiency at the temperature levels imposed by the recovery of waste heat from the more prevalent industrial processes.

  13. Combined fuel and air staged power generation system

    SciTech Connect

    Rabovitser, Iosif K; Pratapas, John M; Boulanov, Dmitri

    2014-05-27

    A method and apparatus for generation of electric power employing fuel and air staging in which a first stage gas turbine and a second stage partial oxidation gas turbine power operated in parallel. A first portion of fuel and oxidant are provided to the first stage gas turbine which generates a first portion of electric power and a hot oxidant. A second portion of fuel and oxidant are provided to the second stage partial oxidation gas turbine which generates a second portion of electric power and a hot syngas. The hot oxidant and the hot syngas are provided to a bottoming cycle employing a fuel-fired boiler by which a third portion of electric power is generated.

  14. 2D-simulation of wet steam flow in a steam turbine with spontaneous condensation

    NASA Astrophysics Data System (ADS)

    Sun, Lan-Xin; Zheng, Qun; Liu, Shun-Long

    2007-06-01

    Removal of condensates from wet steam flow in the last stages of steam turbines significantly promotes stage efficiency and prevents erosion of rotors. In this paper, homogeneous spontaneous condensation in transonic steam flow in the 2-D rotor-tip section of a stage turbine is investigated. Calculated results agree with experimental data reasonably well. On the basis of the above work, a 2-D numerical simulation of wet steam flow in adjacent root sections of a complex steam turbine stage was carried out. Computational results were analyzed and provide insights into effective removal of humidity.

  15. Preliminary Design Optimization For A Supersonic Turbine For Rocket Propulsion

    NASA Technical Reports Server (NTRS)

    Papila, Nilay; Shyy, Wei; Griffin, Lisa; Huber, Frank; Tran, Ken; McConnaughey, Helen (Technical Monitor)

    2000-01-01

    In this study, we present a method for optimizing, at the preliminary design level, a supersonic turbine for rocket propulsion system application. Single-, two- and three-stage turbines are considered with the number of design variables increasing from 6 to 11 then to 15, in accordance with the number of stages. Due to its global nature and flexibility in handling different types of information, the response surface methodology (RSM) is applied in the present study. A major goal of the present Optimization effort is to balance the desire of maximizing aerodynamic performance and minimizing weight. To ascertain required predictive capability of the RSM, a two-level domain refinement approach has been adopted. The accuracy of the predicted optimal design points based on this strategy is shown to he satisfactory. Our investigation indicates that the efficiency rises quickly from single stage to 2 stages but that the increase is much less pronounced with 3 stages. A 1-stage turbine performs poorly under the engine balance boundary condition. A portion of fluid kinetic energy is lost at the turbine discharge of the 1-stage design due to high stage pressure ratio and high-energy content, mostly hydrogen, of the working fluid. Regarding the optimization technique, issues related to the design of experiments (DOE) has also been investigated. It is demonstrated that the criteria for selecting the data base exhibit significant impact on the efficiency and effectiveness of the construction of the response surface.

  16. Research and development of ceramic gas turbine

    SciTech Connect

    Suzuki, Kazuo

    1993-12-31

    The CO{sub 2} caused by the consumption of hydrocarbon fuel is one of the main gases which affect the global climate. In order to reduce the formation of CO{sub 2}, it is necessary to conserve energy as effectively as possible. Therefore the heat energy provided by the fuel should be utilized in multi-cascades. The energy at the high temperature should be used for the generation of electric power and the energy at low temperature could be used for making the steam and the hot water. The gas turbine is preferable for this purpose. The heat energy of exhaust gas can be reused more easily. The two systems are proposed by using the gas turbine as the high temperature stage. One is the cogeneration system and the other is the combined cycle. The former generates electric power by the gas turbine and make steam or hot water in the exhaust gas. The latter employs the gas turbine as the high temperature cycle and the steam turbine as the low temperature cycle.

  17. Effect of tip clearance on performance of small axial hydraulic turbine

    NASA Technical Reports Server (NTRS)

    Boynton, J. L.; Rohlik, H. E.

    1976-01-01

    The first two stages of a six stage liquid oxygen turbine were tested in water. One and two stage performance was determined for one shrouded and two unshrouded blade end configurations over ranges of clearance and blade-jet speed ratio. First stage, two stage, and second stage efficiencies are included as well as the effect of clearance on mass flow for two stage operation.

  18. Single rotor turbine engine

    DOEpatents

    Platts, David A.

    2002-01-01

    There has been invented a turbine engine with a single rotor which cools the engine, functions as a radial compressor, pushes air through the engine to the ignition point, and acts as an axial turbine for powering the compressor. The invention engine is designed to use a simple scheme of conventional passage shapes to provide both a radial and axial flow pattern through the single rotor, thereby allowing the radial intake air flow to cool the turbine blades and turbine exhaust gases in an axial flow to be used for energy transfer. In an alternative embodiment, an electric generator is incorporated in the engine to specifically adapt the invention for power generation. Magnets are embedded in the exhaust face of the single rotor proximate to a ring of stationary magnetic cores with windings to provide for the generation of electricity. In this alternative embodiment, the turbine is a radial inflow turbine rather than an axial turbine as used in the first embodiment. Radial inflow passages of conventional design are interleaved with radial compressor passages to allow the intake air to cool the turbine blades.

  19. Turbine disc sealing assembly

    DOEpatents

    Diakunchak, Ihor S.

    2013-03-05

    A disc seal assembly for use in a turbine engine. The disc seal assembly includes a plurality of outwardly extending sealing flange members that define a plurality of fluid pockets. The sealing flange members define a labyrinth flow path therebetween to limit leakage between a hot gas path and a disc cavity in the turbine engine.

  20. Experimental study of three exit pressure distortions on turbine performance

    NASA Astrophysics Data System (ADS)

    Gaddis, Stephen W.; Boynton, James L.

    1993-06-01

    A cold flow air test of the Space Shuttle Main Engine (SSME) High Pressure Fuel Turbopump (HPFTP) turbine was conducted with a circumferential pressure distortion at the turbine exit. The effects of three circumferential exit pressure distortions on turbine efficiency and pressure ratio, are presented. Circumferential and radial total pressure, total temperature, static pressure, and flow angle distributions at the turbine exit are also presented. Efficiency and total-to-total pressure ratio are shown to have a circumferential variation as high as 13.7 percent (or points of efficiency) and 7.1 percent, respectively. A slight pressure distortion was measured downstream of the first stage nozzle and the distortion increased across subsequent blade rows to a maximum downstream of the second stage rotor for all three plates. A brief discussion of the test facility, model, instrumentation, and test plan is given for completeness.

  1. The 4th Bi-annual international African-Caribbean Cancer Consortium conference: building capacity to address cancer health disparities in populations of African descent.

    PubMed

    Blackman, Elizabeth; Campbell, Jasmine; Bowen, Carlene; Delmoor, Ernestine; Jean-Louis, Gilda; Noumbissi, Raphiatou; O'Garro, Yvonne; Richards-Waritay, Oni; Straughter, Stanley; Tolbert, Vera; Wilson, Barbara; Ragin, Camille

    2014-01-01

    This is a brief summary of the 4(th) International Meeting of the African-Caribbean Cancer Consortium (AC3), organized and sponsored by Fox Chase Cancer Center (FCCC), and held on July 21-22, 2012 at the Lincoln University Graduate Center, Lincoln Plaza, Philadelphia, Pennsylvania. AC3 investigators gathered in Philadelphia, PA to present the results of our ongoing collaborative research efforts throughout the African Diaspora. The general theme addressed cancer health disparities and presentations represented all cancer types. However, there was particular emphasis on women's cancers, related to human papillomavirus (HPV) and human immunodeficiency virus (HIV) infections. PMID:26422007

  2. 4H-Chromene-based anticancer agents towards multi-drug resistant HL60/MX2 human leukemia: SAR at the 4th and 6th positions.

    PubMed

    Puppala, Manohar; Zhao, Xinghua; Casemore, Denise; Zhou, Bo; Aridoss, Gopalakrishnan; Narayanapillai, Sreekanth; Xing, Chengguo

    2016-03-15

    4H-Chromene-based compounds, for example, CXL017, CXL035, and CXL055, have a unique anticancer potential that they selectively kill multi-drug resistant cancer cells. Reported herein is the extended structure-activity relationship (SAR) study, focusing on the ester functional group at the 4th position and the conformation at the 6th position. Sharp SARs were observed at both positions with respect to cellular cytotoxic potency and selectivity between the parental HL60 and the multi-drug resistant HL60/MX2 cells. These results provide critical guidance for future medicinal optimization. PMID:26867486

  3. Ceramic Cerami Turbine Nozzle

    DOEpatents

    Boyd, Gary L.

    1997-04-01

    A turbine nozzle vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The metallic components having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the turbine nozzle vane assembly. The turbine nozzle vane assembly includes an outer shroud and an inner shroud having a plurality of horizontally segmented vanes therebetween being positioned by a connecting member positioning segmented vanes in functional relationship one to another. The turbine nozzle vane assembly provides an economical, reliable and effective ceramic component having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the other component.

  4. Graphene in turbine blades

    NASA Astrophysics Data System (ADS)

    Das, D. K.; Swain, P. K.; Sahoo, S.

    2016-07-01

    Graphene, the two-dimensional (2D) nanomaterial, draws interest of several researchers due to its many superior properties. It has extensive applications in numerous fields. A turbine is a hydraulic machine which extracts energy from a fluid and converts it into useful work. Recently, Gudukeya and Madanhire have tried to increase the efficiency of Pelton turbine. Beucher et al. have also tried the same by reducing friction between fluid and turbine blades. In this paper, we study the advantages of using graphene as a coating on Pelton turbine blades. It is found that the efficiency of turbines increases, running and maintenance cost is reduced with more power output. By the application of graphene in pipes, cavitation will be reduced, durability of pipes will increase, operation and maintenance cost of water power plants will be less.

  5. Cascaded humidified advanced turbine

    SciTech Connect

    Nakhamkin, M.; Swenson, E.C.; Cohn, A.; Bradshaw, D.; Taylor, R.; Wilson, J.M.; Gaul, G.; Jahnke, F.; Polsky, M.

    1995-05-01

    This article describes how, by combining the best features of simple- and combined-cycle gas turbine power plants, the CHAT cycle concept offers power producers a clean, more efficient and less expensive alternative to both. The patented cascaded advanced turbine and its cascaded humidified advanced turbine (CHAT) derivative offer utilities and other power producers a practical advanced gas turbine power plant by combining commercially-available gas turbine and industrial compressor technologies in a unique way. Compared to combined-cycle plants, a CHAT power plant has lower emissions and specific capital costs-approximately 20 percent lower than what is presently available. Further, CHAT`s operating characteristics are especially well-suited to load following quick start-up scenarios and they are less susceptible to power degradation from higher ambient air temperature conditions.

  6. Ceramic turbine nozzle

    DOEpatents

    Shaffer, James E.; Norton, Paul F.

    1996-01-01

    A turbine nozzle and shroud assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The metallic components having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the turbine nozzle vane assembly. The turbine nozzle vane assembly includes a plurality of segmented vane defining a first vane segment and a second vane segment. Each of the first and second vane segments having a vertical portion. Each of the first vane segments and the second vane segments being positioned in functional relationship one to another within a recess formed within an outer shroud and an inner shroud. The turbine nozzle and shroud assembly provides an economical, reliable and effective ceramic component having a preestablished rate of thermal expansion being less than the preestablished rate of thermal expansion of the other component.

  7. Ceramic turbine nozzle

    DOEpatents

    Shaffer, J.E.; Norton, P.F.

    1996-12-17

    A turbine nozzle and shroud assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The metallic components have a preestablished rate of thermal expansion greater than the preestablished rate of thermal expansion of the turbine nozzle vane assembly. The turbine nozzle vane assembly includes a plurality of segmented vane defining a first vane segment and a second vane segment, each of the first and second vane segments having a vertical portion, and each of the first vane segments and the second vane segments being positioned in functional relationship one to another within a recess formed within an outer shroud and an inner shroud. The turbine nozzle and shroud assembly provides an economical, reliable and effective ceramic component having a preestablished rate of thermal expansion being less than the preestablished rate of thermal expansion of the other component. 4 figs.

  8. Internal coating of air cooled gas turbine blades

    NASA Technical Reports Server (NTRS)

    Ahuja, P. L.

    1979-01-01

    Six coating systems were evaluated for internal coating of decent stage (DS) eutectic high pressure turbine blades. Sequential deposition of electroless Ni by the hydrazine process, slurry Cr, and slurry Al, followed by heat treatment provided the coating composition and thickness for internal coating of DS eutectic turbine blades. Both NiCr and NiCrAl coating compositions were evaluated for strain capability and ductile to brittle transition temperature.

  9. Unsteady Blade Row Interaction in a Transonic Turbine

    NASA Technical Reports Server (NTRS)

    Dorney, Daniel J.

    1996-01-01

    Experimental data from jet-engine tests have indicated that unsteady blade row interaction effects can have a significant impact on the performance of multiple-stage turbines. The magnitude of blade row interaction is a function of both blade-count ratio and axial spacing. In the current research program, numerical simulations have been used to quantify the effects of blade count ratio on the performance of an advanced turbine geometries.

  10. Prediction of incidence and surface roughness effects on turbine performance

    NASA Technical Reports Server (NTRS)

    Boyle, R. J.

    1993-01-01

    The results of a Navier-Stokes analysis for predicting the change in turbine efficiency due to a change in either incidence or surface roughness is discussed. It was experimentally determined by Boynton, Tabibzadeh, and Hudson that polishing the SSME high pressure fuel turbine blades improved turbine efficiency by about 2 points over a wide range of operating conditions. These conditions encompassed the range of incidence seen by the turbine blading during flight. It is also necessary to be able to predict turbine performance at various operating points for future rocket turbopump applications. The code RVCQ3D, developed by Rod Chima, was used to determine the effects of changes in incidence angle on turbine blade row efficiency. The midspan Navier-Stokes results were used in conjunction with an inviscid flow analysis code to predict the efficiency of the two stage SSME over a wide range of operating conditions for smooth and rough turbine blades. The use of the Navier-Stokes analysis to predict changes in turbine efficiency due to variation in incidence angles was found to be superior to other incidence loss correlations available in the literature. The sensitivity of the Navier-Stokes results to grid parameters is discussed. The effects of the surface roughness were accounted for using the Cebeci-Chang rough wall turbulence model. This model was implemented in the code RVCQ3D. The implementation of this model for predicting the change in efficiency is also discussed.

  11. Enhanced capabilities and updated users manual for axial-flow turbine preliminary sizing code TURBAN

    NASA Technical Reports Server (NTRS)

    Glassman, Arthur J.

    1994-01-01

    Several modifications have been made to the axial-flow turbine preliminary sizing code TURBAN. Turbine cooling has been added to the analysis. New alternative input options allow direct specification of stage reaction, stage work factor, and stage work split. The Reynolds number loss dependency was modified and an internal calculation of air viscosity was added. A complete description of input and output along with sample cases are included.

  12. Automotive gas turbine fuel control

    NASA Technical Reports Server (NTRS)

    Gold, H. (Inventor)

    1978-01-01

    A fuel control system is reported for automotive-type gas turbines and particulary advanced gas turbines utilizing variable geometry components to improve mileage and reduce pollution emission. The fuel control system compensates for fuel density variations, inlet temperature variations, turbine vane actuation, acceleration, and turbine braking. These parameters are utilized to control various orifices, spool valves and pistons.

  13. PRELIMINARY DESIGN ANALYSIS OF AXIAL FLOW TURBINES

    NASA Technical Reports Server (NTRS)

    Glassman, A. J.

    1994-01-01

    A computer program has been developed for the preliminary design analysis of axial-flow turbines. Rapid approximate generalized procedures requiring minimum input are used to provide turbine overall geometry and performance adequate for screening studies. The computations are based on mean-diameter flow properties and a stage-average velocity diagram. Gas properties are assumed constant throughout the turbine. For any given turbine, all stages, except the first, are specified to have the same shape velocity diagram. The first stage differs only in the value of inlet flow angle. The velocity diagram shape depends upon the stage work factor value and the specified type of velocity diagram. Velocity diagrams can be specified as symmetrical, zero exit swirl, or impulse; or by inputting stage swirl split. Exit turning vanes can be included in the design. The 1991 update includes a generalized velocity diagram, a more flexible meanline path, a reheat model, a radial component of velocity, and a computation of free-vortex hub and tip velocity diagrams. Also, a loss-coefficient calibration was performed to provide recommended values for airbreathing engine turbines. Input design requirements include power or pressure ratio, mass flow rate, inlet temperature and pressure, and rotative speed. The design variables include inlet and exit diameters, stator angle or exit radius ratio, and number of stages. Gas properties are input as gas constant, specific heat ratio, and viscosity. The program output includes inlet and exit annulus dimensions, exit temperature and pressure, total and static efficiencies, flow angles, blading angles, and last stage absolute and relative Mach numbers. This program is written in FORTRAN 77 and can be ported to any computer with a standard FORTRAN compiler which supports NAMELIST. It was originally developed on an IBM 7000 series computer running VM and has been implemented on IBM PC computers and compatibles running MS-DOS under Lahey FORTRAN, and

  14. Energy efficient engine: Turbine intermediate case and low-pressure turbine component test hardware detailed design report

    NASA Technical Reports Server (NTRS)

    Leach, K.; Thulin, R. D.; Howe, D. C.

    1982-01-01

    A four stage, low pressure turbine component has been designed to power the fan and low pressure compressor system in the Energy Efficient Engine. Designs for a turbine intermediate case and an exit guide vane assembly also have been established. The components incorporate numerous technology features to enhance efficiency, durability, and performance retention. These designs reflect a positive step towards improving engine fuel efficiency on a component level. The aerodynamic and thermal/mechanical designs of the intermediate case and low pressure turbine components are presented and described. An overview of the predicted performance of the various component designs is given.

  15. Cooled snubber structure for turbine blades

    DOEpatents

    Mayer, Clinton A; Campbell, Christian X; Whalley, Andrew; Marra, John J

    2014-04-01

    A turbine blade assembly in a turbine engine. The turbine blade assembly includes a turbine blade and a first snubber structure. The turbine blade includes an internal cooling passage containing cooling air. The first snubber structure extends outwardly from a sidewall of the turbine blade and includes a hollow interior portion that receives cooling air from the internal cooling passage of the turbine blade.

  16. Multi-stage flash degaser

    DOEpatents

    Rapier, Pascal M.

    1982-01-01

    A multi-stage flash degaser (18) is incorporated in an energy conversion system (10) having a direct-contact, binary-fluid heat exchanger to remove essentially all of the noncondensable gases from geothermal brine ahead of the direct-contact binary-fluid heat exchanger (22) in order that the heat exchanger (22) and a turbine (48) and condenser (32) of the system (10) can operate at optimal efficiency.

  17. Humoral immunity and CD4+ Th1 cells are both necessary for a fully protective immune response upon secondary infection with Brucella melitensis.

    PubMed

    Vitry, Marie-Alice; Hanot Mambres, Delphine; De Trez, Carl; Akira, Shizuo; Ryffel, Bernhard; Letesson, Jean-Jacques; Muraille, Eric

    2014-04-15

    Brucella spp are intracellular bacteria that cause brucellosis, one of the most common zoonoses in the world. Given the serious medical consequences of this disease, a safe and effective human vaccine is urgently needed. Efforts to develop this vaccine have been hampered by our lack of understanding of what constitutes a protective memory response against Brucella. In this study, we characterize the cells and signaling pathways implicated in the generation of a protective immune memory response following priming by the injection of heat-killed or live Brucella melitensis 16M. Using a panel of gene-deficient mice, we demonstrated that during a secondary recall response, both the Brucella-specific humoral response and CD4+ Th1 cells must act together to confer protective immunity in the spleen to B. melitensis infection. Humoral protective immunity is induced by the inoculation of both heat-killed and live bacteria, and its development does not require T cells, MyD88/IL-12p35 signaling pathways, or an activation-induced deaminase-mediated isotype switch. In striking contrast, the presence of memory IFN-γ-producing CD4+ Th1 cells requires the administration of live bacteria and functional MyD88/IL-12p35 pathways. In summary, our work identifies several immune markers closely associated with protective immune memory and could help to define a rational strategy to obtain an effective human vaccine against brucellosis. PMID:24646742

  18. The Neumann system for the 4th-order eigenvalue problem and constraint flows of the coupled KdV-type equations

    NASA Astrophysics Data System (ADS)

    Zhao, Ye; Gu, Zhuquan; Liu, Yafeng

    2012-07-01

    In this paper, the Neumann system for the 4th-order eigenvalue problem Ly = (∂4+ q∂2+∂2 q+ ip∂+ i∂ p+ y = Λy) has been given. By means of the Neumann constraint condition, the perfect constraint set Γ and the relations between the potentials { q, p, r} and the eigenvector y are obtained. Then, based on the Euler-Lagrange function and Legendre transformations, a reasonable Jacobi-Ostrogradsky coordinate system has been found, which can be equal to the real Hamiltonian canonical coordinate system in R 8 N . Using Cao's method and Moser's constraint manifold, the Lax pairs of the evolution equation hierarchy with the 4th-order eigenvalue problems are nonlinearized. So a new finite-dimensional integrable Hamilton system on the constraint submanifold R 8 N-4 is generated. Moreover, the solutions of the evolution equations for the infinite-dimensional soliton systems are obtained by the involutive flow of the finite-dimensional completely integrable systems.

  19. Materials for Advanced Turbine Engines. Volume 1; Power Metallurgy Rene 95 Rotating Turbine Engine Parts

    NASA Technical Reports Server (NTRS)

    Pfouts, W. R.; Shamblen, C. E.; Mosier, J. S.; Peebles, R. E.; Gorsler, R. W.

    1979-01-01

    An attempt was made to improve methods for producing powder metallurgy aircraft gas turbine engine parts from the nickel base superalloy known as Rene 95. The parts produced were the high pressure turbine aft shaft for the CF6-50 engine and the stages 5 through 9 compressor disk forgings for the CFM56/F101 engines. A 50% cost reduction was achieved as compared to conventional cast and wrought processing practices. An integrated effort involving several powder producers and a major forging source were included.

  20. Terry turbine controls guide

    SciTech Connect

    Golas, R.S. . Steam Turbine Motor and Generator Div.); Wheeler, K.A. )

    1990-09-01

    While utility experience with Terry turbines has been positive, controls and adjustments of controls have required frequent attention. This technical guide addresses the Terry turbine controls, such as trip system, throttle valve linkage and governors. This guide will familiarize personnel who have not had prior experience with the design, organization and setup of these control systems. This document provides instructions for a broad range of utility personnel on optimum methods for the repair, maintenance, adjustment, and troubleshooting of the Terry turbine controls. The guide includes an engineering description of the operation and prevalent failure mechanisms, preventive and predictive maintenance suggestions, repair and adjustment methods, and spare parts recommendations. This guide will be a standalone updated reference manual. It will include drawings and descriptions affecting all required maintenance on the control system, and does not cover site specific appurtenances. Included are both generic and specific recommendations for utility maintenance engineers and technicians. These recommendations will help implement an effective maintenance or upgrade program for Terry turbine controls. This guide is a valuable resource for operating history and common control related problems. The preparation of this manual included the review of the applicable INPO Standby Turbine-Driven Pump Operating Experience Compilation. Individual utilities can use this guide to review their specific maintenance practices and develop improved procedures where applicable. The guide can also be used by some utilities to upgrade their Terry turbine control system. The guide is applicable to the nuclear industry and any other industry utilizing the Terry turbine models included in the document.

  1. Gas turbine combustor transition

    DOEpatents

    Coslow, Billy Joe; Whidden, Graydon Lane

    1999-01-01

    A method of converting a steam cooled transition to an air cooled transition in a gas turbine having a compressor in fluid communication with a combustor, a turbine section in fluid communication with the combustor, the transition disposed in a combustor shell and having a cooling circuit connecting a steam outlet and a steam inlet and wherein hot gas flows from the combustor through the transition and to the turbine section, includes forming an air outlet in the transition in fluid communication with the cooling circuit and providing for an air inlet in the transition in fluid communication with the cooling circuit.

  2. Gas turbine combustor transition

    DOEpatents

    Coslow, B.J.; Whidden, G.L.

    1999-05-25

    A method is described for converting a steam cooled transition to an air cooled transition in a gas turbine having a compressor in fluid communication with a combustor, a turbine section in fluid communication with the combustor, the transition disposed in a combustor shell and having a cooling circuit connecting a steam outlet and a steam inlet and wherein hot gas flows from the combustor through the transition and to the turbine section, includes forming an air outlet in the transition in fluid communication with the cooling circuit and providing for an air inlet in the transition in fluid communication with the cooling circuit. 7 figs.

  3. Aviation turbine fuels, 1980

    SciTech Connect

    Shelton, E M

    1981-03-01

    Properties of some aviation turbine fuels marketed in the United States during 1980 are presented in this report. The samples represented are typical 1980 production and were analyzed in the laboratories of 17 manufacturers of aviation turbine (jet) fuels. The data were submitted for study, calculation, and compilation under a cooperative agreement between the Department of Energy (DOE), Bartlesville Energy Technology Center (BETC), Bartlesville, Oklahoma, and the American Petroleum Institute (API). Results for the properties of 98 samples of aviation turbine fuels are included in the report for military grades JP-4 and JP-5 and commercial type Jet A.

  4. Composite turbine bucket assembly

    DOEpatents

    Liotta, Gary Charles; Garcia-Crespo, Andres

    2014-05-20

    A composite turbine blade assembly includes a ceramic blade including an airfoil portion, a shank portion and an attachment portion; and a transition assembly adapted to attach the ceramic blade to a turbine disk or rotor, the transition assembly including first and second transition components clamped together, trapping said ceramic airfoil therebetween. Interior surfaces of the first and second transition portions are formed to mate with the shank portion and the attachment portion of the ceramic blade, and exterior surfaces of said first and second transition components are formed to include an attachment feature enabling the transition assembly to be attached to the turbine rotor or disk.

  5. Wind turbine acoustics

    NASA Technical Reports Server (NTRS)

    Hubbard, Harvey H.; Shepherd, Kevin P.

    1990-01-01

    Available information on the physical characteristics of the noise generated by wind turbines is summarized, with example sound pressure time histories, narrow- and broadband frequency spectra, and noise radiation patterns. Reviewed are noise measurement standards, analysis technology, and a method of characterizing wind turbine noise. Prediction methods are given for both low-frequency rotational harmonics and broadband noise components. Also included are atmospheric propagation data showing the effects of distance and refraction by wind shear. Human perception thresholds, based on laboratory and field tests, are given. Building vibration analysis methods are summarized. The bibliography of this report lists technical publications on all aspects of wind turbine acoustics.

  6. Turbine blade vibration dampening

    DOEpatents

    Cornelius, C.C.; Pytanowski, G.P.; Vendituoli, J.S.

    1997-07-08

    The present turbine wheel assembly increases component life and turbine engine longevity. The combination of the strap and the opening combined with the preestablished area of the outer surface of the opening and the preestablished area of the outer circumferential surface of the strap and the friction between the strap and the opening increases the life and longevity of the turbine wheel assembly. Furthermore, the mass ``M`` or combined mass ``CM`` of the strap or straps and the centrifugal force assist in controlling vibrations and damping characteristics. 5 figs.

  7. Turbine blade vibration dampening

    DOEpatents

    Cornelius, Charles C.; Pytanowski, Gregory P.; Vendituoli, Jonathan S.

    1997-07-08

    The present turbine wheel assembly increases component life and turbine engine longevity. The combination of the strap and the opening combined with the preestablished area of the outer surface of the opening and the preestablished area of the outer circumferential surface of the strap and the friction between the strap and the opening increases the life and longevity of the turbine wheel assembly. Furthermore, the mass "M" or combined mass "CM" of the strap or straps and the centrifugal force assist in controlling vibrations and damping characteristics.

  8. Measured effects of coolant injection on the performance of a film cooled turbine

    NASA Technical Reports Server (NTRS)

    Mcdonel, J. D.; Eiswerth, J. E.

    1977-01-01

    Tests have been conducted on a 20-inch diameter single-stage air-cooled turbine designed to evaluate the effects of film cooling air on turbine aerodynamic performance. The present paper reports the results of five test configurations, including two different cooling designs and three combinations of cooled and solid airfoils. A comparison is made of the experimental results with a previously published analytical method of evaluating coolant injection effects on turbine performance.

  9. GAS TURBINE REHEAT USING IN SITU COMBUSTION

    SciTech Connect

    D.M. Bachovchin; T.E. Lippert; R.A. Newby P.G.A. Cizmas

    2004-05-17

    In situ reheat is an alternative to traditional gas turbine reheat design in which fuel is fed through airfoils rather than in a bulky discrete combustor separating HP and LP turbines. The goals are to achieve increased power output and/or efficiency without higher emissions. In this program the scientific basis for achieving burnout with low emissions has been explored. In Task 1, Blade Path Aerodynamics, design options were evaluated using CFD in terms of burnout, increase of power output, and possible hot streaking. It was concluded that Vane 1 injection in a conventional 4-stage turbine was preferred. Vane 2 injection after vane 1 injection was possible, but of marginal benefit. In Task 2, Combustion and Emissions, detailed chemical kinetics modeling, validated by Task 3, Sub-Scale Testing, experiments, resulted in the same conclusions, with the added conclusion that some increase in emissions was expected. In Task 4, Conceptual Design and Development Plan, Siemens Westinghouse power cycle analysis software was used to evaluate alternative in situ reheat design options. Only single stage reheat, via vane 1, was found to have merit, consistent with prior Tasks. Unifying the results of all the tasks, a conceptual design for single stage reheat utilizing 24 holes, 1.8 mm diameter, at the trailing edge of vane 1 is presented. A development plan is presented.

  10. Stage design

    DOEpatents

    Shacter, J.

    1975-12-01

    A method is described of cycling gases through a plurality of diffusion stages comprising the steps of admitting the diffused gases from a first diffusion stage into an axial compressor, simultaneously admitting the undiffused gases from a second diffusion stage into an intermediate pressure zone of said compressor corresponding in pressure to the pressure of said undiffused gases, and then admitting the resulting compressed mixture of diffused and undiffused gases into a third diffusion stage.

  11. Turbine instabilities: Case histories

    NASA Technical Reports Server (NTRS)

    Laws, C. W.

    1985-01-01

    Several possible causes of turbine rotor instability are discussed and the related design features of a wide range of turbomachinery types and sizes are considered. The instrumentation options available for detecting rotor instability and assessing its severity are also discussed.

  12. Variables in turbine erosion

    NASA Technical Reports Server (NTRS)

    Baughman, J. R.; Spies, R.

    1970-01-01

    Study of impact erosion in the operation of turbomachinery is undertaken to predict the results for particular designs. The test program investigates the effects of turbine stator blade shape, rotor blade shape, and variations in test conditions.

  13. Gas turbine engine

    DOEpatents

    Lawlor, Shawn P.; Roberts, II, William Byron

    2016-03-08

    A gas turbine engine with a compressor rotor having compressor impulse blades that delivers gas at supersonic conditions to a stator. The stator includes a one or more aerodynamic ducts that each have a converging portion and a diverging portion for deceleration of the selected gas to subsonic conditions and to deliver a high pressure oxidant containing gas to flameholders. The flameholders may be provided as trapped vortex combustors, for combustion of a fuel to produce hot pressurized combustion gases. The hot pressurized combustion gases are choked before passing out of an aerodynamic duct to a turbine. Work is recovered in a turbine by expanding the combustion gases through impulse blades. By balancing the axial loading on compressor impulse blades and turbine impulse blades, asymmetrical thrust is minimized or avoided.

  14. Radial turbine cooling

    NASA Technical Reports Server (NTRS)

    Roelke, Richard J.

    1992-01-01

    Radial turbines have been used extensively in many applications including small ground based electrical power generators, automotive engine turbochargers and aircraft auxiliary power units. In all of these applications the turbine inlet temperature is limited to a value commensurate with the material strength limitations and life requirements of uncooled metal rotors. To take advantage of all the benefits that higher temperatures offer, such as increased turbine specific power output or higher cycle thermal efficiency, requires improved high temperature materials and/or blade cooling. Extensive research is on-going to advance the material properties of high temperature superalloys as well as composite materials including ceramics. The use of ceramics with their high temperature potential and low cost is particularly appealing for radial turbines. However until these programs reach fruition the only way to make significant step increases beyond the present material temperature barriers is to cool the radial blading.

  15. Turbines in the sky

    SciTech Connect

    Boyle, R.V.; Riple, J.C.

    1987-07-01

    Gas turbines are being investigated as power sources for the proposed Star Wars weapons flatforms. The gas turbine engine offers the best opportunity for exploiting the high-temperature potential of both nuclear and chemical combustion. The use of mature gas turbine technology and existing materials would result in highly reliable PCUs capable of meeting SDI's requirements. However, operation under the temperature limits imposed by existing materials would result in a prohibitively heavy system. Cooled blades would somewhat increase temperature capability; however the turbine's mass, though reduced, would still be unacceptably large. The greatest improvements would result from the ability to operate at temperatures of up to 2000 K, pressures up to 14 MPa, and stress up to 690 MPa.

  16. Turbine nozzle positioning system

    DOEpatents

    Norton, Paul F.; Shaffer, James E.

    1996-01-30

    A nozzle guide vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The nozzle guide vane assembly includes an outer shroud having a mounting leg with an opening defined therein, a tip shoe ring having a mounting member with an opening defined therein, a nozzle support ring having a plurality of holes therein and a pin positioned in the corresponding opening in the outer shroud, opening in the tip shoe ring and the hole in the nozzle support ring. A rolling joint is provided between metallic components of the gas turbine engine and the nozzle guide vane assembly. The nozzle guide vane assembly is positioned radially about a central axis of the gas turbine engine and axially aligned with a combustor of the gas turbine engine.

  17. Turbine nozzle positioning system

    DOEpatents

    Norton, P.F.; Shaffer, J.E.

    1996-01-30

    A nozzle guide vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The nozzle guide vane assembly includes an outer shroud having a mounting leg with an opening defined therein, a tip shoe ring having a mounting member with an opening defined therein, a nozzle support ring having a plurality of holes therein and a pin positioned in the corresponding opening in the outer shroud, opening in the tip shoe ring and the hole in the nozzle support ring. A rolling joint is provided between metallic components of the gas turbine engine and the nozzle guide vane assembly. The nozzle guide vane assembly is positioned radially about a central axis of the gas turbine engine and axially aligned with a combustor of the gas turbine engine. 9 figs.

  18. Climatic changes and social transformations in the Near East and North Africa during the 'long' 4th millennium BC: A comparative study of environmental and archaeological evidence

    NASA Astrophysics Data System (ADS)

    Clarke, Joanne; Brooks, Nick; Banning, Edward B.; Bar-Matthews, Miryam; Campbell, Stuart; Clare, Lee; Cremaschi, Mauro; di Lernia, Savino; Drake, Nick; Gallinaro, Marina; Manning, Sturt; Nicoll, Kathleen; Philip, Graham; Rosen, Steve; Schoop, Ulf-Dietrich; Tafuri, Mary Anne; Weninger, Bernhard; Zerboni, Andrea

    2016-03-01

    This paper explores the possible links between rapid climate change (RCC) and social change in the Near East and surrounding regions (Anatolia, central Syria, southern Israel, Mesopotamia, Cyprus and eastern and central Sahara) during the 'long' 4th millennium (∼4500-3000) BC. Twenty terrestrial and 20 marine climate proxies are used to identify long-term trends in humidity involving transitions from humid to arid conditions and vice versa. The frequency distribution of episodes of relative aridity across these records is calculated for the period 6300-2000 BC, so that the results may be interpreted in the context of the established arid episodes associated with RCC around 6200 and 2200 BC (the 8.2 and 4.2 kyr events). We identify two distinct episodes of heightened aridity in the early-mid 4th, and late 4th millennium BC. These episodes cluster strongly at 3600-3700 and 3100-3300 BC. There is also evidence of localised aridity spikes in the 5th and 6th millennia BC. These results are used as context for the interpretation of regional and local archaeological records with a particular focus on case studies from western Syria, the middle Euphrates, southern Israel and Cyprus. Interpretation of the records involves the construction of plausible narratives of human-climate interaction informed by concepts of adaptation and resilience from the literature on contemporary (i.e. 21st century) climate change and adaptation. The results are presented alongside well-documented examples of climatically-influenced societal change in the central and eastern Sahara, where detailed geomorphological studies of ancient environments have been undertaken in tandem with archaeological research. While the narratives for the Near East and Eastern Mediterranean remain somewhat speculative, the use of resilience and adaptation frameworks allows for a more nuanced treatment of human-climate interactions and recognises the diversity and context-specificity of human responses to climatic

  19. Ceramics for the advanced automotive gas turbine engine: A look at a single shaft design

    NASA Technical Reports Server (NTRS)

    Nosek, S. M.

    1977-01-01

    The results of a preliminary analysis of a single shaft regenerative design with a single stage radial turbine are presented to show the fuel economy that can be achieved at high turbine inlet temperatures, with this particular advanced design, if the turbine tip speed and regenerator inlet temperature are not limited. The engine size was 100 hp for application to a 3500 lb auto. The fuel economy was analyzed by coupling the engine to the auto through a continuously variable speed-ratio transmission and operating the system at constant turbine inlet temperature over the Composite Driving Cycle. The fuel was gasoline and the analysis was for a 85 F day. With a turbine inlet temperature of 2500 F the fuel economy was 26.2 mpg, an improvement of 18 percent over that of 22.3 mpg with a turbine inlet temperature of 1900 F. The turbine tip speed needed for best economy with the 2500 F engine was 2530 ft/sec. The regenerator temperature was approximately 2200 F at idle. Disk stresses were estimated for one single stage radial turbine and two two-stage radial-axial turbines and compared with maximum allowable stress curves estimated for a current ceramic material. Results show a need for higher Weibull Modulus, higher strength ceramics.

  20. Radial turbine cooling

    NASA Astrophysics Data System (ADS)

    Roelke, Richard J.

    The technology of high temperature cooled radial turbines is reviewed. Aerodynamic performance considerations are described. Heat transfer and structural analysis are addressed, and in doing so the following topics are covered: cooling considerations, hot side convection, coolant side convection, and rotor mechanical analysis. Cooled rotor concepts and fabrication are described, and the following are covered in this context: internally cooled rotor, hot isostatic pressure bonded rotor, laminated rotor, split blade rotor, and the NASA radial turbine program.

  1. Radial turbine cooling

    NASA Technical Reports Server (NTRS)

    Roelke, Richard J.

    1992-01-01

    The technology of high temperature cooled radial turbines is reviewed. Aerodynamic performance considerations are described. Heat transfer and structural analysis are addressed, and in doing so the following topics are covered: cooling considerations, hot side convection, coolant side convection, and rotor mechanical analysis. Cooled rotor concepts and fabrication are described, and the following are covered in this context: internally cooled rotor, hot isostatic pressure bonded rotor, laminated rotor, split blade rotor, and the NASA radial turbine program.

  2. Cold-air performance of a 15.41-cm-tip-diameter axial-flow power turbine with variable-area stator designed for a 75-kW automotive gas turbine engine

    NASA Technical Reports Server (NTRS)

    Mclallin, K. L.; Kofskey, M. G.; Wong, R. Y.

    1982-01-01

    An experimental evaluation of the aerodynamic performance of the axial flow, variable area stator power turbine stage for the Department of Energy upgraded automotive gas turbine engine was conducted in cold air. The interstage transition duct, the variable area stator, the rotor, and the exit diffuser were included in the evaluation of the turbine stage. The measured total blading efficiency was 0.096 less than the design value of 0.85. Large radial gradients in flow conditions were found at the exit of the interstage duct that adversely affected power turbine performance. Although power turbine efficiency was less than design, the turbine operating line corresponding to the steady state road load power curve was within 0.02 of the maximum available stage efficiency at any given speed.

  3. Turbine airfoil to shround attachment

    SciTech Connect

    Campbell, Christian X; Morrison, Jay A; James, Allister W; Snider, Raymond G; Eshak, Daniel M; Marra, John J; Wessell, Brian J

    2014-05-06

    A turbine airfoil (31) with an end portion (42) that tapers (44) toward the end (43) of the airfoil. A ridge (46) extends around the end portion. It has proximal (66) and distal (67) sides. A shroud platform (50) is bi-cast onto the end portion around the ridge without bonding. Cooling shrinks the platform into compression (62) on the end portion (42) of the airfoil. Gaps between the airfoil and platform are formed using a fugitive material (56) in the bi-casting stage. These gaps are designed in combination with the taper angle (44) to accommodate differential thermal expansion while maintaining a gas seal along the contact surfaces. The taper angle (44) may vary from lesser on the pressure side (36) to greater on the suction side (38) of the airfoil. A collar portion (52) of the platform provides sufficient contact area for connection stability.

  4. Computational modes and the Machenauer N.L.N.M.I. of the GLAS 4th order model. [NonLinear Normal Mode Initialization in numerical weather forecasting

    NASA Technical Reports Server (NTRS)

    Navon, I. M.; Bloom, S.; Takacs, L. L.

    1985-01-01

    An attempt was made to use the GLAS global 4th order shallow water equations to perform a Machenhauer nonlinear normal mode initialization (NLNMI) for the external vertical mode. A new algorithm was defined for identifying and filtering out computational modes which affect the convergence of the Machenhauer iterative procedure. The computational modes and zonal waves were linearly initialized and gravitational modes were nonlinearly initialized. The Machenhauer NLNMI was insensitive to the absence of high zonal wave numbers. The effects of the Machenhauer scheme were evaluated by performing 24 hr integrations with nondissipative and dissipative explicit time integration models. The NLNMI was found to be inferior to the Rasch (1984) pseudo-secant technique for obtaining convergence when the time scales of nonlinear forcing were much smaller than the time scales expected from the natural frequency of the mode.

  5. The 4th Schizophrenia International Research Society Conference, 5-9 April 2014, Florence, Italy: a summary of topics and trends.

    PubMed

    Abayomi, Olukayode; Amato, Davide; Bailey, Candace; Bitanihirwe, Byron; Bowen, Lynneice; Burshtein, Shimon; Cullen, Alexis; Fusté, Montserrat; Herrmann, Ana P; Khodaie, Babak; Kilian, Sanja; Lang, Qortni A; Manning, Elizabeth E; Massuda, Raffael; Nurjono, Milawaty; Sadiq, Sarosh; Sanchez-Gutierrez, Teresa; Sheinbaum, Tamara; Shivakumar, Venkataram; Simon, Nicholas; Spiteri-Staines, Anneliese; Sirijit, Suttajit; Toftdahl, Nanna Gilliam; Wadehra, Sunali; Wang, Yi; Wigton, Rebekah; Wright, Susan; Yagoda, Sergey; Zaytseva, Yuliya; O'Shea, Anne; DeLisi, Lynn E

    2014-11-01

    The 4th Schizophrenia International Research Society Conference was held in Florence, Italy, April 5-9, 2014 and this year had as its emphasis, "Fostering Collaboration in Schizophrenia Research". Student travel awardees served as rapporteurs for each oral session, summarized the important contributions of each session and then each report was integrated into a final summary of data discussed at the entire conference by topic. It is hoped that by combining data from different presentations, patterns of interest will emerge and thus lead to new progress for the future. In addition, the following report provides an overview of the conference for those who were present, but could not participate in all sessions, and those who did not have the opportunity to attend, but who would be interested in an update on current investigations ongoing in the field of schizophrenia research. PMID:25306204

  6. THE 4th SCHIZOPHRENIA INTERNATIONAL RESEARCH SOCIETY CONFERENCE, 5–9 APRIL 2014, FLORENCE, ITALY: A summary of topics and trends

    PubMed Central

    Abayomi, Olukayode; Amato, Davide; Bailey, Candace; Bitanihirwe, Byron; Bowen, Lynneice; Burshtein, Shimon; Cullen, Alexis; Fusté, Montserrat; Herrmann, Ana P; Khodaie, Babak; Kilian, Sanja; Lang, Qortni A; Manning, Elizabeth E; Massuda, Raffael; Nurjono, Milawaty; Sadiq, Sarosh; Sanchez-Gutierrez, Teresa; Sheinbaum, Tamara; Shivakumar, Venkataram; Simon, Nicholas; Spiteri-Staines, Anneliese; Sirijit, Suttajit; Toftdahl, Nanna Gilliam; Wadehra, Sunali; Wang, Yi; Wigton, Rebekah; Wright, Susan; Yagoda, Sergey; Zaytseva, Yuliya; O’Shea, Anne; DeLisi, Lynn E.

    2015-01-01

    The 4th Schizophrenia International Research Society Conference was held in Florence, Italy, April 5–9, 2014.and this year had as its emphasis, “Fostering Collaboration in Schizophrenia Research”. Student travel awardees served as rapporteurs for each oral session, summarized the important contributions of each session and then each report was integrated into a final summary of data discussed at the entire conference by topic. It is hoped that by combining data from different presentations, patterns of interest will emerge and thus lead to new progress for the future. In addition, the following report provides an overview of the conference for those who were present, but could not participate in all sessions, and those who did not have the opportunity to attend, but who would be interested in an update on current investigations ongoing in the field of schizophrenia research. PMID:25306204

  7. White noise response of turbine blades subjected to heat flux and thermal gradient

    SciTech Connect

    Karadag, V.; Aba, E.; Morguel, O.K.

    1997-07-01

    Design and production of the complex mechanical structures rarely result in an optimal solution. A typical example for this is a turbine blade design. Fatigue failures of the turbine blades is one of the most vexing problems of turbo-machine manufacturers, ever since the steam turbine became the main stay for power generating equipment and the gas turbines are increasingly used in air transport. Turbine blade failures due to fatigue are predominantly vibration related. The dynamic loads on the blading can arise from many different sources such as the high rotational speed, the high operating temperatures, the asymmetric aerofil tapered form of the turbine blade etc. Therefore, vibratory analysis is one of the most important stage in the designing of the turbine blades. In this study, the random response of the turbine blade to white noise excitation has been consistently calculated, including the internal damping mechanisms of the blade. Beside the damping effects, the rotational speed and the linear thermal gradient along the turbine blade are incorporated into the analysis. Pressure difference between the two surfaces of the turbine blades are modelled as white noise excitation along all over the turbine blade. The system dynamic equation of motion are derived and solved by using the combined Finite Element-Modal Analysis Method.

  8. Extended parametric representation of compressor fans and turbines. Volume 2: Part user's manual (parametric turbine)

    NASA Technical Reports Server (NTRS)

    Coverse, G. L.

    1984-01-01

    A turbine modeling technique has been developed which will enable the user to obtain consistent and rapid off-design performance from design point input. This technique is applicable to both axial and radial flow turbine with flow sizes ranging from about one pound per second to several hundred pounds per second. The axial flow turbines may or may not include variable geometry in the first stage nozzle. A user-specified option will also permit the calculation of design point cooling flow levels and corresponding changes in efficiency for the axial flow turbines. The modeling technique has been incorporated into a time-sharing program in order to facilitate its use. Because this report contains a description of the input output data, values of typical inputs, and example cases, it is suitable as a user's manual. This report is the second of a three volume set. The titles of the three volumes are as follows: (1) Volume 1 CMGEN USER's Manual (Parametric Compressor Generator); (2) Volume 2 PART USER's Manual (Parametric Turbine); (3) Volume 3 MODFAN USER's Manual (Parametric Modulation Flow Fan).

  9. Modulated gas turbine cooling air

    SciTech Connect

    Schwarz, F.M.; Candelori, D.J.; Brooke, R.D.

    1993-07-06

    In an axial flow gas turbine engine in an aircraft, the engine having an annular flow of hot working fluid passing sequentially through a first bladed rotor stage, a vaned stator assembly having a plurality of hollow vanes, and a second bladed rotor stage; a flow resistant labyrinth seal comprised of an annular seal runner sealingly secured to the first and second rotor stages and a seal shroud surrounding and secured to the seal runner, forming a labyrinth flow passage therebetween; an upstream plenum in restricted fluid communication with the annular flow upstream of the vaned stator assembly and with the labyrinth flow passage; a downstream plenum in fluid communication with the labyrinth flow passage and in restricted flow communication with the annular flow downstream of the vaned stator assembly; a compressor; a conduit network connected to deliver a cooling airflow from the compressor to the upstream plenum, and a modulatable control valve means located in the conduit network, the method of operation comprising: measuring the temperature of gas passing through the labyrinth flow passage; sensing aircraft speed and comparing the sensed speed to a preselected air craft speed range; holding the valves open any item the sensed aircraft speed is less than the preselected aircraft speed range; and modulating he quantity of the cooling airflow in response to the measurement of the temperature of the gas passing through the labyrinth flow passage to keep the temperature at a substantially constant maximum value when the sensed aircraft speed is greater than the aircraft speed range.

  10. Wind Turbine Box - energy fluxes around a characteristic wind turbine

    NASA Astrophysics Data System (ADS)

    Calaf, Marc; Cortina, Gerard; Sharma, Varun

    2015-11-01

    This research project presents a new tool, so called ``Wind Turbine Box'', that allows for the direct comparison between the flow around a single wind turbine and the flow around a characteristic wind turbine immersed within a large wind farm. The Wind Turbine Box consists of a limited control volume defined around each wind turbine that is timely co-aligned with each corresponding turbine's yaw-angle. Hence it is possible to extract flow statistics around each wind turbine, regardless of whether the turbine is fully isolated or it is plunged within a large wind farm. The Wind Turbine Box tool has been used to compute the energy fluxes around a characteristic wind turbine of a large wind farm to better understand the wake replenishment processes throughout a complete diurnal cycle. The effective loading of the wind farm has been gradually increased, ranging from quasi-isolated wind turbines to a highly packed wind farm. For this purpose, several Large Eddy Simulations have been run, forced with a constant geostrophic wind and a time varying surface temperature extracted from a selected period of the CASES-99 field experiment. Results illustrate the differences in the flow dynamics as it evolves around a characteristic wind turbine within a large wind farm and its asymptotic transition to the fully developed wind turbine array boundary layer.

  11. Limbic system development underlies the emergence of classical fear conditioning during the 3rd and 4th weeks of life in the rat

    PubMed Central

    Deal, Alex L.; Erickson, Kristen J.; Shiers, Stephanie I.; Burman, Michael A.

    2016-01-01

    Classical fear conditioning creates an association between an aversive stimulus and a neutral stimulus. Although the requisite neural circuitry is well understood in mature organisms, the development of these circuits is less well studied. The current experiments examine the ontogeny of fear conditioning and relate it to neuronal activation assessed through immediate early gene (IEG) expression in the amygdala, hippocampus, perirhinal cortex, and hypothalamus of periweanling rats. Rat pups were fear conditioned, or not, during the 3rd or 4th weeks of life. Neuronal activation was assessed by quantifying expression of FBJ osteosarcoma oncogene (FOS) using immunohistochemistry (IHC) in Experiment 1. Fos and early growth response gene-1 (EGR1) expression was assessed using qRT-PCR in Experiment 2. Behavioral data confirm that both auditory and contextual fear continue to emerge between PD 17 and 24. The IEG expression data are highly consistent with these behavioral results. IHC results demonstrate significantly more FOS protein expression in the basal amygdala of fear conditioned PD 23 subjects compared to control subjects, but no significant difference at PD 17. qRT-PCR results suggest specific activation of the amygdala only in older subjects during auditory fear expression. A similar effect of age and conditioning status was also observed in the perirhinal cortex during both contextual and auditory fear expression. Overall, the development of fear conditioning occurring between the 3rd and 4th weeks of life appears to be at least partly attributable to changes in activation of the amygdala and perirhinal cortex during fear conditioning or expression. PMID:26820587

  12. Phase 2 clinical trial of rapamycin-resistant donor CD4+ Th2/Th1 (T-Rapa) cells after low-intensity allogeneic hematopoietic cell transplantation

    PubMed Central

    Fowler, Daniel H.; Mossoba, Miriam E.; Steinberg, Seth M.; Halverson, David C.; Stroncek, David; Khuu, Hahn M.; Hakim, Frances T.; Castiello, Luciano; Sabatino, Marianna; Leitman, Susan F.; Mariotti, Jacopo; Gea-Banacloche, Juan C.; Sportes, Claude; Hardy, Nancy M.; Hickstein, Dennis D.; Pavletic, Steven Z.; Rowley, Scott; Goy, Andre; Donato, Michele; Korngold, Robert; Pecora, Andrew; Levine, Bruce L.; June, Carl H.; Gress, Ronald E.; Bishop, Michael R.

    2013-01-01

    In experimental models, ex vivo induced T-cell rapamycin resistance occurred independent of T helper 1 (Th1)/T helper 2 (Th2) differentiation and yielded allogeneic CD4+ T cells of increased in vivo efficacy that facilitated engraftment and permitted graft-versus-tumor effects while minimizing graft-versus-host disease (GVHD). To translate these findings, we performed a phase 2 multicenter clinical trial of rapamycin-resistant donor CD4+ Th2/Th1 (T-Rapa) cells after allogeneic-matched sibling donor hematopoietic cell transplantation (HCT) for therapy of refractory hematologic malignancy. T-Rapa cell products, which expressed a balanced Th2/Th1 phenotype, were administered as a preemptive donor lymphocyte infusion at day 14 post-HCT. After T-Rapa cell infusion, mixed donor/host chimerism rapidly converted, and there was preferential immune reconstitution with donor CD4+ Th2 and Th1 cells relative to regulatory T cells and CD8+ T cells. The cumulative incidence probability of acute GVHD was 20% and 40% at days 100 and 180 post-HCT, respectively. There was no transplant-related mortality. Eighteen of 40 patients (45%) remain in sustained complete remission (range of follow-up: 42-84 months). These results demonstrate the safety of this low-intensity transplant approach and the feasibility of subsequent randomized studies to compare T-Rapa cell-based therapy with standard transplantation regimens. This trial was registered at www.cancer.gov/clinicaltrials as #NCT 00077480. PMID:23426943

  13. Turbine Design and Application, Volume 3

    NASA Technical Reports Server (NTRS)

    Glassman, A. J. (Editor)

    1975-01-01

    Turbine technology concepts for thermodynamic and fluid dynamics are presented along with velocity diagrams, losses, mechanical design, operation and performance. Designs discussed include: supersonic turbines, radial-inflow turbines, and turbine cooling.

  14. Advanced turbine design for coal-fueled engines

    SciTech Connect

    Wagner, J.H.; Johnson, B.V.

    1993-04-01

    The investigators conclude that: (1) Turbine erosion resistance was shown to be improved by a factor of 5 by varying the turbine design. Increasing the number of stages and increasing the mean radius reduces the peak predicted erosion rates for 2-D flows on the blade airfoil from values which are 6 times those of the vane to values of erosion which are comparable to those of the vane airfoils. (2) Turbine erosion was a strong function of airfoil shape depending on particle diameter. Different airfoil shapes for the same turbine operating condition resulted in a factor of 7 change in airfoil erosion for the smallest particles studied (5 micron). (3) Predicted erosion for the various turbines analyzed was a strong function of particle diameter and weaker function of particle density. (4) Three dimensional secondary flows were shown to cause increases in peak and average erosion on the vane and blade airfoils. Additionally, the interblade secondary flows and stationary outer case caused unique erosion patterns which were not obtainable with 2-D analyses. (5) Analysis of the results indicate that hot gas cleanup systems are necessary to achieve acceptable turbine life in direct-fired, coal-fueled systems. In addition, serious consequences arise when hot gas filter systems fail for even short time periods. For a complete failure of the filter system, a 0.030 in. thick corrosion-resistant protective coating on a turbine blade would be eroded at some locations within eight minutes.

  15. Advanced Turbine Technology Applications Project (ATTAP) 1993 annual report

    NASA Technical Reports Server (NTRS)

    1994-01-01

    This report summarizes work performed by AlliedSignal Engines, a unit of AlliedSignal Aerospace Company, during calendar year 1993, toward development and demonstration of structural ceramic technology for automotive gas turbine engines. This work was performed for the U.S. Department of Energy (DOE) under National Aeronautics and Space Administration (NASA) Contract DEN3-335, Advanced Turbine Technology Applications Project (ATFAP). During 1993, the test bed used to demonstrate ceramic technology was changed from the AlliedSignal Engines/Garrett Model AGT101 regenerated gas turbine engine to the Model 331-200(CT) engine. The 331-200(CT) ceramic demonstrator is a fully-developed test platform based on the existing production AlliedSignal 331-200(ER) gas turbine auxiliary power unit (APU), and is well suited to evaluating ceramic turbine blades and nozzles. In addition, commonality of the 331-200(CT) engine with existing gas turbine APU's in commercial service provides the potential for field testing of ceramic components. The 1993 ATTAP activities emphasized design modifications of the 331-200 engine test bed to accommodate ceramic first-stage turbine nozzles and blades, fabrication of the ceramic components, ceramic component proof and rig tests, operational tests of the test bed equipped with the ceramic components, and refinement of critical ceramic design technologies.

  16. Advanced Turbine Technology Applications Project (ATTAP) 1993 annual report

    NASA Astrophysics Data System (ADS)

    1994-07-01

    This report summarizes work performed by AlliedSignal Engines, a unit of AlliedSignal Aerospace Company, during calendar year 1993, toward development and demonstration of structural ceramic technology for automotive gas turbine engines. This work was performed for the U.S. Department of Energy (DOE) under National Aeronautics and Space Administration (NASA) Contract DEN3-335, Advanced Turbine Technology Applications Project (ATFAP). During 1993, the test bed used to demonstrate ceramic technology was changed from the AlliedSignal Engines/Garrett Model AGT101 regenerated gas turbine engine to the Model 331-200(CT) engine. The 331-200(CT) ceramic demonstrator is a fully-developed test platform based on the existing production AlliedSignal 331-200(ER) gas turbine auxiliary power unit (APU), and is well suited to evaluating ceramic turbine blades and nozzles. In addition, commonality of the 331-200(CT) engine with existing gas turbine APU's in commercial service provides the potential for field testing of ceramic components. The 1993 ATTAP activities emphasized design modifications of the 331-200 engine test bed to accommodate ceramic first-stage turbine nozzles and blades, fabrication of the ceramic components, ceramic component proof and rig tests, operational tests of the test bed equipped with the ceramic components, and refinement of critical ceramic design technologies.

  17. Debris trap in a turbine cooling system

    DOEpatents

    Wilson, Ian David

    2002-01-01

    In a turbine having a rotor and a plurality of stages, each stage comprising a row of buckets mounted on the rotor for rotation therewith; and wherein the buckets of at least one of the stages are cooled by steam, the improvement comprising at least one axially extending cooling steam supply conduit communicating with an at least partially annular steam supply manifold; one or more axially extending cooling steam feed tubes connected to the manifold at a location radially outwardly of the cooling steam supply conduit, the feed tubes arranged to supply cooling steam to the buckets of at least one of the plurality of stages; the manifold extending radially beyond the feed tubes to thereby create a debris trap region for collecting debris under centrifugal loading caused by rotation of the rotor.

  18. 76. TURBINE HALL, UNIT 2 SHOWING BOTH TURBINE AND CONDENSER ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    76. TURBINE HALL, UNIT 2 SHOWING BOTH TURBINE AND CONDENSER (SEE ALSO, DRAWING No. 12 OF 13) - Delaware County Electric Company, Chester Station, Delaware River at South end of Ward Street, Chester, Delaware County, PA

  19. 40. VIEW OF TURBINE HALL LOOKING SOUTHWEST AT WESTINGHOUSEPARSONS TURBINE ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    40. VIEW OF TURBINE HALL LOOKING SOUTHWEST AT WESTINGHOUSE-PARSONS TURBINE NUMBER 2. THIS UNIT WAS INSTALLED IN 1925. - New York, New Haven & Hartford Railroad, Cos Cob Power Plant, Sound Shore Drive, Greenwich, Fairfield County, CT

  20. Advanced turbine design for coal-fueled engines. Phase 1, Erosion of turbine hot gas path blading: Final report

    SciTech Connect

    Wagner, J.H.; Johnson, B.V.

    1993-04-01

    The investigators conclude that: (1) Turbine erosion resistance was shown to be improved by a factor of 5 by varying the turbine design. Increasing the number of stages and increasing the mean radius reduces the peak predicted erosion rates for 2-D flows on the blade airfoil from values which are 6 times those of the vane to values of erosion which are comparable to those of the vane airfoils. (2) Turbine erosion was a strong function of airfoil shape depending on particle diameter. Different airfoil shapes for the same turbine operating condition resulted in a factor of 7 change in airfoil erosion for the smallest particles studied (5 micron). (3) Predicted erosion for the various turbines analyzed was a strong function of particle diameter and weaker function of particle density. (4) Three dimensional secondary flows were shown to cause increases in peak and average erosion on the vane and blade airfoils. Additionally, the interblade secondary flows and stationary outer case caused unique erosion patterns which were not obtainable with 2-D analyses. (5) Analysis of the results indicate that hot gas cleanup systems are necessary to achieve acceptable turbine life in direct-fired, coal-fueled systems. In addition, serious consequences arise when hot gas filter systems fail for even short time periods. For a complete failure of the filter system, a 0.030 in. thick corrosion-resistant protective coating on a turbine blade would be eroded at some locations within eight minutes.

  1. Turbine inner shroud and turbine assembly containing such inner shroud

    DOEpatents

    Bagepalli, Bharat Sampathkumaran; Corman, Gregory Scot; Dean, Anthony John; DiMascio, Paul Stephen; Mirdamadi, Massoud

    2001-01-01

    A turbine inner shroud and a turbine assembly. The turbine assembly includes a turbine stator having a longitudinal axis and having an outer shroud block with opposing and longitudinally outward facing first and second sides having open slots. A ceramic inner shroud has longitudinally inward facing hook portions which can longitudinally and radially surround a portion of the sides of the outer shroud block. In one attachment, the hook portions are engageable with, and are positioned within, the open slots.

  2. Failure analysis report: 10 MW geothermal binary turbine, Magma Electric Company, East Mesa, California

    SciTech Connect

    Anliker, D.M.

    1981-01-01

    The cause of failure of two isobutane turbines at the East Mesa geothermal plant was investigated. One turbine lost all the vanes in all three stages, while the other turbine sustained dings and nicks in the vanes, but remained intact. The exact cause of failure could not be determined. Three possibilities were determined: (1) a single foreign object, possibly a bolt; (2) foreign substance (geothermal fluid, oil, liquid isobutane, or particulate corrosion products) entered both turbines; or (3) one or more brazed joints failed by fatigue or by a corrosive process. 5 refs., 13 figs. (ACR)

  3. Ceramic stationary gas turbine

    SciTech Connect

    Roode, M. van

    1995-10-01

    The performance of current industrial gas turbines is limited by the temperature and strength capabilities of the metallic structural materials in the engine hot section. Because of their superior high-temperature strength and durability, ceramics can be used as structural materials for hot section components (blades, nozzles, combustor liners) in innovative designs at increased turbine firing temperatures. The benefits include the ability to increase the turbine inlet temperature (TIT) to about 1200{degrees}C ({approx}2200{degrees}F) or more with uncooled ceramics. It has been projected that fully optimized stationary gas turbines would have a {approx}20 percent gain in thermal efficiency and {approx}40 percent gain in output power in simple cycle compared to all metal-engines with air-cooled components. Annual fuel savings in cogeneration in the U.S. would be on the order of 0.2 Quad by 2010. Emissions reductions to under 10 ppmv NO{sub x} are also forecast. This paper describes the progress on a three-phase, 6-year program sponsored by the U.S. Department of Energy, Office of Industrial Technologies, to achieve significant performance improvements and emissions reductions in stationary gas turbines by replacing metallic hot section components with ceramic parts. Progress is being reported for the period September 1, 1994, through September 30, 1995.

  4. Ceramic stationary gas turbine

    SciTech Connect

    Roode, M. van

    1995-12-31

    The performance of current industrial gas turbines is limited by the temperature and strength capabilities of the metallic structural materials in the engine hot section. Because of their superior high-temperature strength and durability, ceramics can be used as structural materials for hot section components (blades, nozzles, combustor liners) in innovative designs at increased turbine firing temperatures. The benefits include the ability to increase the turbine inlet temperature (TIT) to about 1200{degrees}C ({approx}2200{degrees}F) or more with uncooled ceramics. It has been projected that fully optimized stationary gas turbines would have a {approx}20 percent gain in thermal efficiency and {approx}40 percent gain in output power in simple cycle compared to all metal-engines with air-cooled components. Annual fuel savings in cogeneration in the U.S. would be on the order of 0.2 Quad by 2010. Emissions reductions to under 10 ppmv NO{sub x} are also forecast. This paper describes the progress on a three-phase, 6-year program sponsored by the U.S. Department of Energy, Office of Industrial Technologies, to achieve significant performance improvements and emissions reductions in stationary gas turbines by replacing metallic hot section components with ceramic parts. Progress is being reported for the period September 1, 1994, through September 30, 1995.

  5. Floating wind turbine system

    NASA Technical Reports Server (NTRS)

    Viterna, Larry A. (Inventor)

    2009-01-01

    A floating wind turbine system with a tower structure that includes at least one stability arm extending therefrom and that is anchored to the sea floor with a rotatable position retention device that facilitates deep water installations. Variable buoyancy for the wind turbine system is provided by buoyancy chambers that are integral to the tower itself as well as the stability arm. Pumps are included for adjusting the buoyancy as an aid in system transport, installation, repair and removal. The wind turbine rotor is located downwind of the tower structure to allow the wind turbine to follow the wind direction without an active yaw drive system. The support tower and stability arm structure is designed to balance tension in the tether with buoyancy, gravity and wind forces in such a way that the top of the support tower leans downwind, providing a large clearance between the support tower and the rotor blade tips. This large clearance facilitates the use of articulated rotor hubs to reduced damaging structural dynamic loads. Major components of the turbine can be assembled at the shore and transported to an offshore installation site.

  6. High efficiency carbonate fuel cell/turbine hybrid power cycle

    SciTech Connect

    Steinfeld, G.; Maru, H.C.; Sanderson, R.A.

    1996-07-01

    The hybrid power cycle studies were conducted to identify a high efficiency, economically competitive system. A hybrid power cycle which generates power at an LHV efficiency > 70% was identified that includes an atmospheric pressure direct carbonate fuel cell, a gas turbine, and a steam cycle. In this cycle, natural gas fuel is mixed with recycled fuel cell anode exhaust, providing water for reforming fuel. The mixed gas then flows to a direct carbonate fuel cell which generates about 70% of the power. The portion of the anode exhaust which is not recycled is burned and heat transferred through a heat exchanger (HX) to the compressed air from a gas turbine. The heated compressed air is then heated further in the gas turbine burner and expands through the turbine generating 15% of the power. Half the exhaust from the turbine provides air for the anode exhaust burner. All of the turbine exhaust eventually flows through the fuel cell cathodes providing the O2 and CO2 needed in the electrochemical reaction. Exhaust from the cathodes flows to a steam system (heat recovery steam generator, staged steam turbine generating 15% of the cycle power). Simulation of a 200 MW plant with a hybrid power cycle had an LHV efficiency of 72.6%. Power output and efficiency are insensitive to ambient temperature, compared to a gas turbine combined cycle; NOx emissions are 75% lower. Estimated cost of electricity for 200 MW is 46 mills/kWh, which is competitive with combined cycle where fuel cost is > $5.8/MMBTU. Key requirement is HX; in the 200 MW plant studies, a HX operating at 1094 C using high temperature HX technology currently under development by METC for coal gassifiers was assumed. A study of a near term (20 MW) high efficiency direct carbonate fuel cell/turbine hybrid power cycle has also been completed.

  7. Investigation on the near-wake flow structures of a utility-scale wind turbine using snowflake based flow visualization

    NASA Astrophysics Data System (ADS)

    Dasari, Teja; Toloui, Mostafa; Guala, Michele; Hong, Jiarong

    2015-11-01

    Super-large-scale particle image velocimetry and flow visualization techniques using natural snow particles have been shown as an effective tool to probe the structure of the flow around full-scale wind turbines (Hong et al. Nature Comm. 2014). Here we present a follow-up study based on the data collected during a deployment around the 2.5 MW wind turbine at EOLOS Wind Energy Research Station on April, 4th, 2014. The dataset includes the snow visualization of flow fields from different perspectives in the near wake of the turbine. The motions of the dominant coherent structures including tip, blade root, hub and tower vortices, represented by the snow voids, are examined with the objective of quantifying and correlating their behavior with the meteorological and turbine operating conditions. Some preliminary studies on flow-structure interaction are also performed by correlating the data from strain gauges, accelerometers mounted on the turbine blades, with the flow measurements. The statistical analysis of the motions of blade induced vortices shows a clear impact of atmospheric turbulence and vortex interaction on flow development in the near wake. The result further indicates a strong connection between near-wake vorticity field, turbine operation and structure deformations. The work was supported by National Science Foundation (NSF-CBET-1454259) and the research infrastructure was supported by Department of Energy.

  8. Wind turbine spoiler

    DOEpatents

    Sullivan, W.N.

    An aerodynamic spoiler system for a vertical axis wind turbine includes spoilers on the blades initially stored near the rotor axis to minimize drag. A solenoid latch adjacent the central support tower releases the spoilers and centrifugal force causes the spoilers to move up the turbine blades away from the rotor axis, thereby producing a braking effect and actual slowing of the associated wind turbine, if desired. The spoiler system can also be used as an infinitely variable power control by regulated movement of the spoilers on the blades over the range between the undeployed and fully deployed positions. This is done by the use of a suitable powered reel and cable located at the rotor tower to move the spoilers.

  9. Turbine airfoil manufacturing technology

    SciTech Connect

    Kortovich, C.

    1995-10-01

    The efficiency and effectiveness of the gas turbine engine is directly related to the turbine inlet temperatures. The ability to increase these temperatures has occurred as a result of improvements in materials, design, and processing techniques. A generic sequence indicating the relationship of these factors to temperature capability is schematically shown in Figure 1 for aircraft engine and land based engine materials. A basic contribution that is not captured by the Figure is the significant improvement in process and manufacturing capability that has accompanied each of these innovations. It is this capability that has allowed the designs and innovations to be applied on a high volume, cost effective scale in the aircraft gas turbine market.

  10. Wind Turbine Technology

    SciTech Connect

    Spera, D.A.

    1994-01-01

    This book reviews advances in aerodynamics, structural dynamics and fatigue, wind characteristics, acoustic and electromagnetic emissions, commercial wind power applications, and utility power systems that use wind power plants. The book examines the choices made by inventors, designers, and builders of turbines; absorb their practical lessons; and presents the experience of a wide range of wind-energy professionals. Included are sources of technical information, side-by-side comparisons of commercial wind turbines, technical data on wind turbines of various sizes and types, and fundamental equations for engineers designing and analyzing systems. This book would be useful to practicing engineers, designers, meteorologists, researchers, utility project managers and planners, wind power plant developers, and equipment manufacturers, as well as students and teachers.

  11. Turbine Airfoil Deposition Models

    NASA Technical Reports Server (NTRS)

    Rosner, D. E.

    1984-01-01

    Gas turbine failures associated with sea-salt ingestion and sulfur-containing fuel impurities have directed attention to alkali sulfate deposition and the associated hot corrosion of gas turbine (GT) blades under some GT operating conditions. These salt deposits form thin, molten films which undermine the protective metal oxide coating normally found on GT blades. The prediction of molten salt deposition, flow and oxide dissolution, and their effects on the lifetime of turbine blades are examined. Goals include rationalizing and helping to predict corrosion patterns on operational GT rotor blades and stators, and ultimately providing some of the tools required to design laboratory simulators and future corrosion-resistant high-performance engines. Necessary background developments are reviewed first, and then recent results and tentative conclusions are presented along with a brief account of the present research plans.

  12. Upgrading jet turbine technology

    SciTech Connect

    Valenti, M.

    1995-12-01

    This article describes a joint government/industry program that is developing a new breed of turbine components, including bearings, blades, and seals, to double the propulsion capacity of both military and commercial jet engines. Although the tensions of the Cold War have receded with the demise of the Soviet Union, the US continually seeks to improve the operational readiness of its weapon systems. The challenge facing the Pentagon today is maintaining US technological superiority in the face of post-Cold War budget cuts. A model program for doing so is the joint government/industry Integrated High Performance Turbine Engine Technology program, or IHPTET (pronounced ip-tet). The goal of the IHPTET program is to develop technologies that will double the propulsion capability of military turbine engines by the turn of the century.

  13. Gas turbine sealing apparatus

    DOEpatents

    Wiebe, David J; Wessell, Brian J; Ebert, Todd; Beeck, Alexander; Liang, George; Marussich, Walter H

    2013-02-19

    A gas turbine includes forward and aft rows of rotatable blades, a row of stationary vanes between the forward and aft rows of rotatable blades, an annular intermediate disc, and a seal housing apparatus. The forward and aft rows of rotatable blades are coupled to respective first and second portions of a disc/rotor assembly. The annular intermediate disc is coupled to the disc/rotor assembly so as to be rotatable with the disc/rotor assembly during operation of the gas turbine. The annular intermediate disc includes a forward side coupled to the first portion of the disc/rotor assembly and an aft side coupled to the second portion of the disc/rotor assembly. The seal housing apparatus is coupled to the annular intermediate disc so as to be rotatable with the annular intermediate disc and the disc/rotor assembly during operation of the gas turbine.

  14. Wind Turbine Acoustics

    NASA Technical Reports Server (NTRS)

    Hubbard, Harvey H.; Shepherd, Kevin P.

    2009-01-01

    Wind turbine generators, ranging in size from a few kilowatts to several megawatts, are producing electricity both singly and in wind power stations that encompass hundreds of machines. Many installations are in uninhabited areas far from established residences, and therefore there are no apparent environmental impacts in terms of noise. There is, however, the potential for situations in which the radiated noise can be heard by residents of adjacent neighborhoods, particularly those neighborhoods with low ambient noise levels. A widely publicized incident of this nature occurred with the operation of the experimental Mod-1 2-MW wind turbine, which is described in detail elsewhere. Pioneering studies which were conducted at the Mod-1 site on the causes and remedies of noise from wind turbines form the foundation of much of the technology described in this chapter.

  15. Wind turbine system

    SciTech Connect

    Smith, O.J.

    1982-05-18

    A wind turbine system utilizes a bicycle wheel type turbine having airfoils mounted on various spoke pairs. The vertical yaw axis lies in the horizontal projection of the airfoils to offer better control of the system; for example, automatic stowage in the case of excessive wind is provided since the superstructure of the turbine provides a torque around the vertical yaw axis which moves the wheel into a stowed position. At the same time, the wheel diameter can be made larger and thus heavier since the drive connection to the generator also helps support the weight of the wheel, since it is a rim drive. Greater electrical generation is also provided since an air scoop facing into the wind allows the effective generator capacity to be increased with air velocity. Lastly, the radial rate of change of the angle of the airfoils can be closely controlled.

  16. Turbine nozzle attachment system

    DOEpatents

    Norton, Paul F.; Shaffer, James E.

    1995-01-01

    A nozzle guide vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The nozzle guide vane assembly includes a pair of legs extending radially outwardly from an outer shroud and a pair of mounting legs extending radially inwardly from an inner shroud. Each of the pair of legs and mounting legs have a pair of holes therein. A plurality of members attached to the gas turbine engine have a plurality of bores therein which axially align with corresponding ones of the pair of holes in the legs. A plurality of pins are positioned within the corresponding holes and bores radially positioning the nozzle guide vane assembly about a central axis of the gas turbine engine.

  17. Wind turbine spoiler

    DOEpatents

    Sullivan, William N.

    1985-01-01

    An aerodynamic spoiler system for a vertical axis wind turbine includes spoilers on the blades initially stored near the rotor axis to minimize drag. A solenoid latch adjacent the central support tower releases the spoilers and centrifugal force causes the spoilers to move up the turbine blades away from the rotor axis, thereby producing a braking effect and actual slowing of the associated wind turbine, if desired. The spoiler system can also be used as an infinitely variable power control by regulated movement of the spoilers on the blades over the range between the undeployed and fully deployed positions. This is done by the use of a suitable powered reel and cable located at the rotor tower to move the spoilers.

  18. Turbine nozzle attachment system

    DOEpatents

    Norton, P.F.; Shaffer, J.E.

    1995-10-24

    A nozzle guide vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and is attached to conventional metallic components. The nozzle guide vane assembly includes a pair of legs extending radially outwardly from an outer shroud and a pair of mounting legs extending radially inwardly from an inner shroud. Each of the pair of legs and mounting legs have a pair of holes therein. A plurality of members attached to the gas turbine engine have a plurality of bores therein which axially align with corresponding ones of the pair of holes in the legs. A plurality of pins are positioned within the corresponding holes and bores radially positioning the nozzle guide vane assembly about a central axis of the gas turbine engine. 3 figs.

  19. Wind Turbine With Concentric Ducts

    NASA Technical Reports Server (NTRS)

    Muhonen, A. J.

    1983-01-01

    Wind Turbine device is relatively compact and efficient. Converging inner and outer ducts increase pressure difference across blades of wind turbine. Turbine shaft drives alternator housed inside exit cone. Suitable for installation on such existing structures as water towers, barns, houses, and commercial buildings.

  20. Predicting Noise From Wind Turbines

    NASA Technical Reports Server (NTRS)

    Grosveld, Ferdinand W.

    1990-01-01

    Computer program WINDY predicts broadband noise spectra of horizontal-axis wind-turbine generators. Enables adequate assessment of impact of broadband wind-turbine noise. Effects of turbulence, trailing-edge wakes, and bluntness taken into account. Program has practical application in design and siting of wind-turbine machines acceptable to community. Written in GW-Basic.