Sample records for turbine engine driven

  1. Gas Turbine Engine Having Fan Rotor Driven by Turbine Exhaust and with a Bypass

    NASA Technical Reports Server (NTRS)

    Suciu, Gabriel L. (Inventor); Chandler, Jesse M. (Inventor)

    2016-01-01

    A gas turbine engine has a core engine incorporating a core engine turbine. A fan rotor is driven by a fan rotor turbine. The fan rotor turbine is in the path of gases downstream from the core engine turbine. A bypass door is moveable from a closed position at which the gases from the core engine turbine pass over the fan rotor turbine, and moveable to a bypass position at which the gases are directed away from the fan rotor turbine. An aircraft is also disclosed.

  2. Performance of Blowdown Turbine driven by Exhaust Gas of Nine-Cylinder Radial Engine

    DTIC Science & Technology

    1944-12-01

    blade speed to mean jet speed FIQUBE 6.—Variation of mean turbine efficiency with ratio of blade speed to moan Jot speed. Engine speed, 2000 rpm; full...conventional turbo - supercharger axe used in series, the blowdown turbine may be geared to the engine . Aircraft engines are operated at high speed for...guide vanes in blowdown-turblno noule box. PERFORMANCE OF BLOWDOWN TURBINE DRIVEN BT EXHAUST GAS OF RADIAL ENGINE 245 (6) Diaphragm

  3. The Need and Challenges for Distributed Engine Control

    NASA Technical Reports Server (NTRS)

    Culley, Dennis E.

    2013-01-01

    The presentation describes the challenges facing the turbine engine control system. These challenges are primarily driven by a dependence on commercial electronics and an increasingly severe environment on board the turbine engine. The need for distributed control is driven by the need to overcome these system constraints and develop a new growth path for control technology and, as a result, improved turbine engine performance.

  4. 46 CFR 112.20-10 - Diesel or gas turbine driven emergency power source.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... Power Source § 112.20-10 Diesel or gas turbine driven emergency power source. Simultaneously with the operation of the transfer means under § 112.20-5, the diesel engine or gas turbine driving the final... 46 Shipping 4 2011-10-01 2011-10-01 false Diesel or gas turbine driven emergency power source. 112...

  5. 46 CFR 112.20-10 - Diesel or gas turbine driven emergency power source.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... Power Source § 112.20-10 Diesel or gas turbine driven emergency power source. Simultaneously with the operation of the transfer means under § 112.20-5, the diesel engine or gas turbine driving the final... 46 Shipping 4 2010-10-01 2010-10-01 false Diesel or gas turbine driven emergency power source. 112...

  6. Pollution reduction technology program for class T4(JT8D) engines

    NASA Technical Reports Server (NTRS)

    Roberts, R.; Fiorentino, A. J.; Diehl, L. A.

    1977-01-01

    The technology required to develop commercial gas turbine engines with reduced exhaust emissions was demonstrated. Can-annular combustor systems for the JT8D engine family (EPA class T4) were investigated. The JT8D turbofan engine is an axial-flow, dual-spool, moderate-bypass-ratio design. It has a two-stage fan, a four-stage low-pressure compressor driven by a three-stage low-pressure turbine, and a seven-stage high-pressure compressor driven by a single-stage high-pressure turbine. A cross section of the JT8D-17 showing the mechanical configuration is given. Key specifications for this engine are listed.

  7. Baseline automotive gas turbine engine development program

    NASA Technical Reports Server (NTRS)

    Wagner, C. E. (Editor); Pampreen, R. C. (Editor)

    1979-01-01

    Tests results on a baseline engine are presented to document the automotive gas turbine state-of-the-art at the start of the program. The performance characteristics of the engine and of a vehicle powered by this engine are defined. Component improvement concepts in the baseline engine were evaluated on engine dynamometer tests in the complete vehicle on a chassis dynamometer and on road tests. The concepts included advanced combustors, ceramic regenerators, an integrated control system, low cost turbine material, a continuously variable transmission, power-turbine-driven accessories, power augmentation, and linerless insulation in the engine housing.

  8. Performance of Blowdown Turbine Driven by Exhaust Gas of Nine-Cylinder Radial Engine

    NASA Technical Reports Server (NTRS)

    Turner, L Richard; Desmon, Leland G

    1944-01-01

    An investigation was made of an exhaust-gas turbine having four separate nozzle boxes each covering a 90 degree arc of the nozzle diaphragm and each connected to a pair of adjacent cylinders of a nine-cylinder radial engine. This type of turbine has been called a "blowdown" turbine because it recovers the kinetic energy developed in the exhaust stacks during the blowdown period, that is the first part of the exhaust process when the piston of the reciprocating engine is nearly stationary. The purpose of the investigation was to determine whether the blow turbine could develop appreciable power without imposing any large loss in engine power arising from restriction of the engine exhaust by the turbine.

  9. Build Up and Operation of an Axial Turbine Driven by a Rotary Detonation Engine

    DTIC Science & Technology

    2012-03-01

    RDEs) offer advantages over pulsed detonation engines ( PDEs ) due to a steadier exhaust and fewer total system losses. All previous research on...turbine integration with detonation combustors has focused on utilizing PDEs to drive axial and centrifugal turbines. The objective of this thesis was... detonation engine ............................................. 5 Figure 4. Schematic of the rotating detonation wave structure for an unwrapped view of an

  10. Efficient, Low Pressure Ratio Propulsor for Gas Turbine Engines

    NASA Technical Reports Server (NTRS)

    Gallagher, Edward J. (Inventor); Monzon, Byron R. (Inventor)

    2015-01-01

    A gas turbine engine includes a spool, a turbine coupled to drive the spool, and a propulsor that is coupled to be driven by the turbine through the spool. A gear assembly is coupled between the propulsor and the spool such that rotation of the turbine drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. The row includes no more than 20 of the propulsor blades.

  11. Efficient, Low Pressure Ratio Propulsor for Gas Turbine Engines

    NASA Technical Reports Server (NTRS)

    Monzon, Byron R. (Inventor); Gallagher, Edward J. (Inventor)

    2016-01-01

    A gas turbine engine includes a spool, a turbine coupled to drive the spool, and a propulsor that is coupled to be driven by the turbine through the spool. A gear assembly is coupled between the propulsor and the spool such that rotation of the turbine drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. The row includes no more than 20 of the propulsor blades.

  12. 46 CFR 112.20-10 - Diesel or gas turbine driven emergency power source.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 46 Shipping 4 2014-10-01 2014-10-01 false Diesel or gas turbine driven emergency power source. 112.20-10 Section 112.20-10 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Systems Having a Temporary and a Final Emergency...

  13. 46 CFR 112.20-10 - Diesel or gas turbine driven emergency power source.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 46 Shipping 4 2013-10-01 2013-10-01 false Diesel or gas turbine driven emergency power source. 112.20-10 Section 112.20-10 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Systems Having a Temporary and a Final Emergency...

  14. 46 CFR 112.20-10 - Diesel or gas turbine driven emergency power source.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... 46 Shipping 4 2012-10-01 2012-10-01 false Diesel or gas turbine driven emergency power source. 112.20-10 Section 112.20-10 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Systems Having a Temporary and a Final Emergency...

  15. Turbine Engine with Differential Gear Driven Fan and Compressor

    NASA Technical Reports Server (NTRS)

    Suciu, Gabriel L. (Inventor); Pagluica, Gino J. (Inventor); Duong, Loc Quang (Inventor); Portlock, Lawrence E. (Inventor)

    2013-01-01

    A gas turbine engine provides a differential gear system coupling the turbine to the bypass fan and the compressor. In this manner, the power/speed split between the bypass fan and the compressor can be optimized under all conditions. In the example shown, the turbine drives a sun gear, which drives a planet carrier and a ring gear in a differential manner. One of the planet carrier and the ring gear is coupled to the bypass fan, while the other is coupled to the compressor.

  16. Diesel engine catalytic combustor system. [aircraft engines

    NASA Technical Reports Server (NTRS)

    Ream, L. W. (Inventor)

    1984-01-01

    A low compression turbocharged diesel engine is provided in which the turbocharger can be operated independently of the engine to power auxiliary equipment. Fuel and air are burned in a catalytic combustor to drive the turbine wheel of turbine section which is initially caused to rotate by starter motor. By opening a flapper value, compressed air from the blower section is directed to catalytic combustor when it is heated and expanded, serving to drive the turbine wheel and also to heat the catalytic element. To start, engine valve is closed, combustion is terminated in catalytic combustor, and the valve is then opened to utilize air from the blower for the air driven motor. When the engine starts, the constituents in its exhaust gas react in the catalytic element and the heat generated provides additional energy for the turbine section.

  17. Gas turbine engine fuel control

    NASA Technical Reports Server (NTRS)

    Gold, H. S. (Inventor)

    1973-01-01

    A variable orifice system is described that is responsive to compressor inlet pressure and temperature, compressor discharge pressure and rotational speed of a gas-turbine engine. It is incorporated into a hydraulic circuit that includes a zero gradient pump driven at a speed proportional to the speed of the engine. The resulting system provides control of fuel rate for starting, steady running, acceleration and deceleration under varying altitudes and flight speeds.

  18. Investigation of the part-load performance of two 1.12 MW regenerative marine gas turbines

    NASA Astrophysics Data System (ADS)

    Korakianitis, T.; Beier, K. J.

    1994-04-01

    Regenerative and intercooled-regenerative gas turbine engines with low pressure ratio have significant efficiency advantages over traditional aero-derivative engines of higher pressure ratios, and can compete with modern diesel engines for marine propulsion. Their performance is extremely sensitive to thermodynamic-cycle parameter choices and the type of components. The performances of two 1.12 MW (1500 hp) regenerative gas turbines are predicted with computer simulations. One engine has a single-shaft configuration, and the other has a gas-generator/power-turbine combination. The latter arrangement is essential for wide off-design operating regime. The performance of each engine driving fixed-pitch and controllable-pitch propellers, or an AC electric bus (for electric-motor-driven propellers) is investigated. For commercial applications the controllable-pitch propeller may have efficiency advantages (depending on engine type and shaft arrangements). For military applications the electric drive provides better operational flexibility.

  19. Data-driven fault detection, isolation and estimation of aircraft gas turbine engine actuator and sensors

    NASA Astrophysics Data System (ADS)

    Naderi, E.; Khorasani, K.

    2018-02-01

    In this work, a data-driven fault detection, isolation, and estimation (FDI&E) methodology is proposed and developed specifically for monitoring the aircraft gas turbine engine actuator and sensors. The proposed FDI&E filters are directly constructed by using only the available system I/O data at each operating point of the engine. The healthy gas turbine engine is stimulated by a sinusoidal input containing a limited number of frequencies. First, the associated system Markov parameters are estimated by using the FFT of the input and output signals to obtain the frequency response of the gas turbine engine. These data are then used for direct design and realization of the fault detection, isolation and estimation filters. Our proposed scheme therefore does not require any a priori knowledge of the system linear model or its number of poles and zeros at each operating point. We have investigated the effects of the size of the frequency response data on the performance of our proposed schemes. We have shown through comprehensive case studies simulations that desirable fault detection, isolation and estimation performance metrics defined in terms of the confusion matrix criterion can be achieved by having access to only the frequency response of the system at only a limited number of frequencies.

  20. Advanced Gas Turbine (AGT) powertrain system development for automotive applications

    NASA Technical Reports Server (NTRS)

    1980-01-01

    Progress in the development of a gas turbine engine to improve fuel economy, reduce gaseous emissions and particulate levels, and compatible with a variety of alternate fuels is reported. The powertrain is designated AGT101 and consists of a regenerated single shaft gas turbine engine, a split differential gearbox and a Ford Automatic Overdrive production transmission. The powertrain is controlled by an electronic digital microprocessor and associated actuators, instrumentation, and sensors. Standard automotive accessories are driven by engine power provided by an accessory pad on the gearbox. Component/subsystem development progress is reported in the following areas: compressor, turbine, combustion system, regenerator, gearbox/transmission, structures, ceramic components, foil gas bearing, bearings and seals, rotor dynamics, and controls and accessories.

  1. Group 3 Unmanned Aircraft Systems Maintenance Challenges Within The Naval Aviation Enterprise

    DTIC Science & Technology

    2017-12-01

    cross winds . We again went through the mishap processes and reviewed training and maintenance records. A couple months later, there was a third crash...gas turbine engines powering aircraft with humans on board (DON, 2017). Group 3 unmanned aircraft utilize a sealed fuel system. The tank is filled...aircraft do not use gas turbine engines. They use either rotary Wankle or piston driven engines with much simpler fuel delivery systems such as carburetors

  2. Gas-heat-pump development

    NASA Astrophysics Data System (ADS)

    Creswick, F. A.

    Incentives for the development of gas heat pumps are discussed. Technical progress made on several promising technologies was reviewed. The status of development of gas-engine-driven heat pumps, the absorption cycle for the near- and long-term gas heat pump systems, the Stirling engine, the small Rankine-cycle engines, and gas-turbine-driven heat pump systems were briefly reviewed. Progress in the US, Japan, and Europe is noted.

  3. Performance and environmental impact assessment of pulse detonation based engine systems

    NASA Astrophysics Data System (ADS)

    Glaser, Aaron J.

    Experimental research was performed to investigate the feasibility of using pulse detonation based engine systems for practical aerospace applications. In order to carry out this work a new pulse detonation combustion research facility was developed at the University of Cincinnati. This research covered two broad areas of application interest. The first area is pure PDE applications where the detonation tube is used to generate an impulsive thrust directly. The second focus area is on pulse detonation based hybrid propulsion systems. Within each of these areas various studies were performed to quantify engine performance. Comparisons of the performance between detonation and conventional deflagration based engine cycles were made. Fundamental studies investigating detonation physics and flow dynamics were performed in order to gain physical insight into the observed performance trends. Experimental studies were performed on PDE-driven straight and diverging ejectors to determine the system performance. Ejector performance was quantified by thrust measurements made using a damped thrust stand. The effects of PDE operating parameters and ejector geometric parameters on thrust augmentation were investigated. For all cases tested, the maximum thrust augmentation is found to occur at a downstream ejector placement. The optimum ejector geometry was determined to have an overall length of LEJECT/DEJECT =5.61, including an intermediate-straight section length of LSTRT /DEJECT=2, and diverging exhaust section with 4 deg half-angle. A maximum thrust augmentation of 105% was observed while employing the optimized ejector geometry and operating the PDE at a fill-fraction of 0.6 and a frequency of 10 Hz. When operated at a fill-fraction of 1.0 and a frequency of 30 Hz, the thrust augmentation of the optimized PDE-driven ejector system was observed to be 71%. Static pressure was measured along the interior surface of the ejector, including the inlet and exhaust sections. The diverging ejector pressure distribution shows that the diverging section acts as a subsonic diffuser. To provide a better explanation of the observed performance trends, shadowgraph images of the detonation wave and starting vortex interacting with the ejector inlet were obtained. The acoustic signature of a pulse detonation engine was characterized in both the near-field and far-field regimes. Experimental measurements were performed in an anechoic test facility designed for jet noise testing. Both shock strength and speed were mapped as a function of radial distance and direction from the PDE exhaust plane. It was found that the PDE generated pressure field can be reasonably modeled by a theoretical point-source explosion. The effect of several exit nozzle configurations on the PDE acoustic signature was studies. These included various chevron nozzles, a perforated nozzle, and a set of proprietary noise attenuation mufflers. Experimental studies were carried out to investigate the performance of a hybrid propulsion system integrating an axial flow turbine with multiple pulse detonation combustors. The integrated system consisted of a circular array of six pulse detonation combustor (PDC) tubes exhausting through an axial flow turbine. Turbine component performance was quantified by measuring the amount of power generated by the turbine section. Direct comparisons of specific power output and turbine efficiency between a PDC-driven turbine and a turbine driven by steady-flow combustors were made. It was found that the PDC-driven turbine had comparable performance to that of a steady-burner-driven turbine across the operating map of the turbine.

  4. Variable area nozzle for gas turbine engines driven by shape memory alloy actuators

    NASA Technical Reports Server (NTRS)

    Rey, Nancy M. (Inventor); Miller, Robin M. (Inventor); Tillman, Thomas G. (Inventor); Rukus, Robert M. (Inventor); Kettle, John L. (Inventor); Dunphy, James R. (Inventor); Chaudhry, Zaffir A. (Inventor); Pearson, David D. (Inventor); Dreitlein, Kenneth C. (Inventor); Loffredo, Constantino V. (Inventor)

    2001-01-01

    A gas turbine engine includes a variable area nozzle having a plurality of flaps. The flaps are actuated by a plurality of actuating mechanisms driven by shape memory alloy (SMA) actuators to vary fan exist nozzle area. The SMA actuator has a deformed shape in its martensitic state and a parent shape in its austenitic state. The SMA actuator is heated to transform from martensitic state to austenitic state generating a force output to actuate the flaps. The variable area nozzle also includes a plurality of return mechanisms deforming the SMA actuator when the SMA actuator is in its martensitic state.

  5. Technology for National Security

    DTIC Science & Technology

    1988-10-01

    tanks, and automobiles are already driven by turbines, and more will be. Turbines must be operated at very high temperatures to compete with the...efficiency of internal combustion engines. Cheap, high-temperature turbines for automobiles and land vehicles will probably require the use of ceramic...of bytes of data. Erasable optical storage techniques are maturing and breakthroughs in reprogrammable optical storage for platform or missile

  6. Evaluation of two typical distributed energy systems

    NASA Astrophysics Data System (ADS)

    Han, Miaomiao; Tan, Xiu

    2018-03-01

    According to the two-natural gas distributed energy system driven by gas engine driven and gas turbine, in this paper, the first and second laws of thermodynamics are used to measure the distributed energy system from the two parties of “quantity” and “quality”. The calculation results show that the internal combustion engine driven distributed energy station has a higher energy efficiency, but the energy efficiency is low; the gas turbine driven distributed energy station energy efficiency is high, but the primary energy utilization rate is relatively low. When configuring the system, we should determine the applicable natural gas distributed energy system technology plan and unit configuration plan according to the actual load factors of the project and the actual factors such as the location, background and environmental requirements of the project. “quality” measure, the utilization of waste heat energy efficiency index is proposed.

  7. Practical problems relating to the hovercraft application of marine gas turbines

    NASA Astrophysics Data System (ADS)

    Jin-Zhang, Z.

    Design specifications of the marine gas turbine in a hovercraft application are discussed, in addition to the requirements for load distribution of the turbine power in this application. The effective load of the gas turbine is found to be about 57 percent higher than that of the air-cooled diesel engine, and a comparison between the two engines indicates that the effective load of the diesel-driven boat becomes advantageous only when the endurance is more than 26 hours. A multistage filter for air-water separation could reduce the salt content to less than 0.01 ppm where the pressure loss is less than 100 mm water head, and a low profile-resistance ejector without a mixing section could be developed to reduce the engine room pressure to the 45-50 C range.

  8. 46 CFR 112.50-1 - General.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... sounds on low oil pressure and high cooling water temperature. (i) If the prime mover is a gas turbine... Emergency Diesel and Gas Turbine Engine Driven Generator Sets § 112.50-1 General. (a) The prime mover of a... thermostatically-controlled electric water-jacket heater connected to the final emergency bus is permitted. (e) The...

  9. 46 CFR 112.50-1 - General.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... sounds on low oil pressure and high cooling water temperature. (i) If the prime mover is a gas turbine... Emergency Diesel and Gas Turbine Engine Driven Generator Sets § 112.50-1 General. (a) The prime mover of a... thermostatically-controlled electric water-jacket heater connected to the final emergency bus is permitted. (e) The...

  10. 46 CFR 112.50-1 - General.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... sounds on low oil pressure and high cooling water temperature. (i) If the prime mover is a gas turbine... Emergency Diesel and Gas Turbine Engine Driven Generator Sets § 112.50-1 General. (a) The prime mover of a... thermostatically-controlled electric water-jacket heater connected to the final emergency bus is permitted. (e) The...

  11. AeroDyn V15.04: Design tool for wind and MHK turbines

    DOE Data Explorer

    Murray, Robynne; Hayman, Greg; Jonkman, Jason

    2017-04-28

    AeroDyn is a time-domain wind and MHK turbine aerodynamics module that can be coupled into the FAST version 8 multi-physics engineering tool to enable aero-elastic simulation of horizontal-axis wind turbines. AeroDyn V15.04 has been updated to include a cavitation check for MHK turbines, and can be driven as a standalone code to compute wind turbine aerodynamic response uncoupled from FAST. Note that while AeroDyn has been updated to v15.04, FAST v8.16 has not yet been updated and still uses AeroDyn v15.03.

  12. 46 CFR 112.25-1 - General.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ..., DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Systems Having an Automatic Starting Diesel Engine or Gas Turbine Driven Emergency Power Source as the Sole Emergency Power Source § 112.25-1 General. This subpart contains requirements applicable to...

  13. 46 CFR 112.25-1 - General.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ..., DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Systems Having an Automatic Starting Diesel Engine or Gas Turbine Driven Emergency Power Source as the Sole Emergency Power Source § 112.25-1 General. This subpart contains requirements applicable to...

  14. 46 CFR 112.25-1 - General.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ..., DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Systems Having an Automatic Starting Diesel Engine or Gas Turbine Driven Emergency Power Source as the Sole Emergency Power Source § 112.25-1 General. This subpart contains requirements applicable to...

  15. 46 CFR 112.25-1 - General.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ..., DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Systems Having an Automatic Starting Diesel Engine or Gas Turbine Driven Emergency Power Source as the Sole Emergency Power Source § 112.25-1 General. This subpart contains requirements applicable to...

  16. 46 CFR 112.25-1 - General.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ..., DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Systems Having an Automatic Starting Diesel Engine or Gas Turbine Driven Emergency Power Source as the Sole Emergency Power Source § 112.25-1 General. This subpart contains requirements applicable to...

  17. Aircraft thrust control

    NASA Technical Reports Server (NTRS)

    Walker, Neil (Inventor); Day, Stanley G. (Inventor); Collopy, Paul D. (Inventor); Bennett, George W. (Inventor)

    1988-01-01

    An integrated control system for coaxial counterrotating aircraft propulsors driven by a common gas turbine engine. The system establishes an engine pressure ratio by control of fuel flow and uses the established pressure ratio to set propulsor speed. Propulsor speed is set by adjustment of blade pitch.

  18. Unsteady specific work and isentropic efficiency of a radial turbine driven by pulsed detonations

    NASA Astrophysics Data System (ADS)

    Rouser, Kurt P.

    There has been longstanding government and industry interest in pressure-gain combustion for use in Brayton cycle based engines. Theoretically, pressure-gain combustion allows heat addition with reduced entropy loss. The pulsed detonation combustor (PDC) is a device that can provide such pressure-gain combustion and possibly replace typical steady deflagration combustors. The PDC is inherently unsteady, however, and comparisons with conventional steady deflagration combustors must be based upon time-integrated performance variables. In this study, the radial turbine of a Garrett automotive turbocharger was coupled directly to and driven, full admission, by a PDC in experiments fueled by hydrogen or ethylene. Data included pulsed cycle time histories of turbine inlet and exit temperature, pressure, velocity, mass flow, and enthalpy. The unsteady inlet flowfield showed momentary reverse flow, and thus unsteady accumulation and expulsion of mass and enthalpy within the device. The coupled turbine-driven compressor provided a time-resolved measure of turbine power. Peak power increased with PDC fill fraction, and duty cycle increased with PDC frequency. Cycle-averaged unsteady specific work increased with fill fraction and frequency. An unsteady turbine efficiency formulation is proposed, including heat transfer effects, enthalpy flux-weighted total pressure ratio, and ensemble averaging over multiple cycles. Turbine efficiency increased with frequency but was lower than the manufacturer reported conventional steady turbine efficiency.

  19. Modernization of gas-turbine engines with high-frequency induction motors

    NASA Astrophysics Data System (ADS)

    Abramovich, B. N.; Sychev, Yu A.; Kuznetsov, P. A.

    2018-03-01

    Main tendencies of growth of electric energy consumption in general and mining industries were analyzed in the paper. A key role of electric drive in this process was designated. A review about advantages and disadvantages of unregulated gearboxes with mechanical units that are commonly used in domestically produced gas-turbine engines was made. This review allows one to propose different gas-turbine engines modernization schemes with the help of PWM-driven high-frequency induction motors. Induction motors with the double rotor winding were examined. A simulation of high-frequency induction motors with double rotor windings in Matlab-Simulink software was carried out based on equivalent circuit parameters. Obtained characteristics of new motors were compared with serially produced analogues. After the simulation, results were implemented in the real prototype.

  20. Acoustic Performance of Drive Rig Mufflers for Model Scale Engine Testing

    NASA Technical Reports Server (NTRS)

    Stephens, David, B.

    2013-01-01

    Aircraft engine component testing at the NASA Glenn Research Center (GRC) includes acoustic testing of scale model fans and propellers in the 9- by15-Foot Low Speed Wind Tunnel (LSWT). This testing utilizes air driven turbines to deliver power to the article being studied. These air turbines exhaust directly downstream of the model in the wind tunnel test section and have been found to produce significant unwanted noise that reduces the quality of the acoustic measurements of the engine model being tested. This report describes an acoustic test of a muffler designed to mitigate the extraneous turbine noise. The muffler was found to provide acoustic attenuation of at least 8 dB between 700 Hz and 20 kHz which significantly improves the quality of acoustic measurements in the facility.

  1. 46 CFR 112.35-1 - General.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... Manually Controlled Emergency Systems Having a Storage Battery or a Diesel Engine or Gas Turbine Driven Generator as the Sole Emergency Power Source § 112.35-1 General. This subpart contains requirements applicable to emergency power installations having a manually controlled storage battery, diesel engine, or...

  2. 46 CFR 112.35-1 - General.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... Manually Controlled Emergency Systems Having a Storage Battery or a Diesel Engine or Gas Turbine Driven Generator as the Sole Emergency Power Source § 112.35-1 General. This subpart contains requirements applicable to emergency power installations having a manually controlled storage battery, diesel engine, or...

  3. Fabrication and test of digital output interface devices for gas turbine electronic controls

    NASA Technical Reports Server (NTRS)

    Newirth, D. M.; Koenig, E. W.

    1978-01-01

    A program was conducted to develop an innovative digital output interface device, a digital effector with optical feedback of the fuel metering valve position, for future electronic controls for gas turbine engines. A digital effector (on-off solenoids driven directly by on-off signals from a digital electronic controller) with optical position feedback was fabricated, coupled with the fuel metering valve, and tested under simulated engine operating conditions. The testing indicated that a digital effector with optical position feedback is a suitable candidate, with proper development for future digital electronic gas turbine controls. The testing also identified several problem areas which would have to be overcome in a final production configuration.

  4. 46 CFR 112.25-3 - Normal source for emergency loads.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ....25-3 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Systems Having an Automatic Starting Diesel Engine or Gas Turbine Driven Emergency Power Source as the Sole Emergency Power Source § 112.25-3 Normal source for...

  5. 46 CFR 112.25-3 - Normal source for emergency loads.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ....25-3 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Systems Having an Automatic Starting Diesel Engine or Gas Turbine Driven Emergency Power Source as the Sole Emergency Power Source § 112.25-3 Normal source for...

  6. 46 CFR 112.35-5 - Manually started emergency systems.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ....35-5 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Manually Controlled Emergency Systems Having a Storage Battery or a Diesel Engine or Gas Turbine Driven Generator as the Sole Emergency Power Source § 112.35-5 Manually...

  7. 46 CFR 112.25-10 - Transfer of emergency loads.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Systems Having an Automatic Starting Diesel Engine or Gas Turbine Driven Emergency Power Source as the Sole Emergency Power Source § 112.25-10 Transfer of emergency loads. (a) When...

  8. 46 CFR 112.25-10 - Transfer of emergency loads.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Systems Having an Automatic Starting Diesel Engine or Gas Turbine Driven Emergency Power Source as the Sole Emergency Power Source § 112.25-10 Transfer of emergency loads. (a) When...

  9. 46 CFR 112.35-5 - Manually started emergency systems.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ....35-5 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Manually Controlled Emergency Systems Having a Storage Battery or a Diesel Engine or Gas Turbine Driven Generator as the Sole Emergency Power Source § 112.35-5 Manually...

  10. 46 CFR 112.25-10 - Transfer of emergency loads.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Systems Having an Automatic Starting Diesel Engine or Gas Turbine Driven Emergency Power Source as the Sole Emergency Power Source § 112.25-10 Transfer of emergency loads. (a) When...

  11. 46 CFR 112.25-10 - Transfer of emergency loads.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Systems Having an Automatic Starting Diesel Engine or Gas Turbine Driven Emergency Power Source as the Sole Emergency Power Source § 112.25-10 Transfer of emergency loads. (a) When...

  12. 46 CFR 112.35-5 - Manually started emergency systems.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ....35-5 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Manually Controlled Emergency Systems Having a Storage Battery or a Diesel Engine or Gas Turbine Driven Generator as the Sole Emergency Power Source § 112.35-5 Manually...

  13. 46 CFR 112.35-5 - Manually started emergency systems.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ....35-5 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Manually Controlled Emergency Systems Having a Storage Battery or a Diesel Engine or Gas Turbine Driven Generator as the Sole Emergency Power Source § 112.35-5 Manually...

  14. 46 CFR 112.50-7 - Compressed air starting.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Diesel and Gas Turbine Engine Driven Generator Sets § 112.50-7 Compressed... emergency power source. If this compressor supplies other auxiliaries, there must be a non-return valve at...

  15. 46 CFR 112.25-10 - Transfer of emergency loads.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Systems Having an Automatic Starting Diesel Engine or Gas Turbine Driven Emergency Power Source as the Sole Emergency Power Source § 112.25-10 Transfer of emergency loads. (a) When...

  16. 46 CFR 112.25-3 - Normal source for emergency loads.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ....25-3 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Systems Having an Automatic Starting Diesel Engine or Gas Turbine Driven Emergency Power Source as the Sole Emergency Power Source § 112.25-3 Normal source for...

  17. 46 CFR 112.35-5 - Manually started emergency systems.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ....35-5 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Manually Controlled Emergency Systems Having a Storage Battery or a Diesel Engine or Gas Turbine Driven Generator as the Sole Emergency Power Source § 112.35-5 Manually...

  18. 46 CFR 112.25-3 - Normal source for emergency loads.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ....25-3 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Systems Having an Automatic Starting Diesel Engine or Gas Turbine Driven Emergency Power Source as the Sole Emergency Power Source § 112.25-3 Normal source for...

  19. 46 CFR 112.25-3 - Normal source for emergency loads.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ....25-3 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Systems Having an Automatic Starting Diesel Engine or Gas Turbine Driven Emergency Power Source as the Sole Emergency Power Source § 112.25-3 Normal source for...

  20. 46 CFR 112.50-3 - Hydraulic starting.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 46 Shipping 4 2010-10-01 2010-10-01 false Hydraulic starting. 112.50-3 Section 112.50-3 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Diesel and Gas Turbine Engine Driven Generator Sets § 112.50-3 Hydraulic...

  1. 46 CFR 112.50-3 - Hydraulic starting.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 46 Shipping 4 2011-10-01 2011-10-01 false Hydraulic starting. 112.50-3 Section 112.50-3 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Diesel and Gas Turbine Engine Driven Generator Sets § 112.50-3 Hydraulic...

  2. An evaluation of a hubless inducer and a full flow hydraulic turbine driven inducer boost pump

    NASA Technical Reports Server (NTRS)

    Lindley, B. K.; Martinson, A. R.

    1971-01-01

    The purpose of the study was to compare the performance of several configurations of hubless inducers with a hydrodynamically similar conventional inducer and to demonstrate the performance of a full flow hydraulic turbine driven inducer boost pump using these inducers. A boost pump of this type consists of an inducer connected to a hydraulic turbine with a high speed rotor located in between. All the flow passes through the inducer, rotor, and hydraulic turbine, then into the main pump. The rotor, which is attached to the main pump shaft, provides the input power to drive the hydraulic turbine which, in turn, drives the inducer. The inducer, rotating at a lower speed, develops the necessary head to prevent rotor cavitation. The rotor speed is consistent with present main engine liquid hydrogen pump designs and the overall boost pump head rise is sufficient to provide adequate main pump suction head. This system would have the potential for operating at lower liquid hydrogen tank pressures.

  3. 46 CFR 112.35-3 - Normal source for emergency loads.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ....35-3 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Manually Controlled Emergency Systems Having a Storage Battery or a Diesel Engine or Gas Turbine Driven Generator as the Sole Emergency Power Source § 112.35-3 Normal source...

  4. 46 CFR 112.35-3 - Normal source for emergency loads.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ....35-3 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Manually Controlled Emergency Systems Having a Storage Battery or a Diesel Engine or Gas Turbine Driven Generator as the Sole Emergency Power Source § 112.35-3 Normal source...

  5. 46 CFR 112.35-3 - Normal source for emergency loads.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ....35-3 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Manually Controlled Emergency Systems Having a Storage Battery or a Diesel Engine or Gas Turbine Driven Generator as the Sole Emergency Power Source § 112.35-3 Normal source...

  6. 46 CFR 112.35-3 - Normal source for emergency loads.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ....35-3 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Manually Controlled Emergency Systems Having a Storage Battery or a Diesel Engine or Gas Turbine Driven Generator as the Sole Emergency Power Source § 112.35-3 Normal source...

  7. 46 CFR 112.35-3 - Normal source for emergency loads.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ....35-3 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Manually Controlled Emergency Systems Having a Storage Battery or a Diesel Engine or Gas Turbine Driven Generator as the Sole Emergency Power Source § 112.35-3 Normal source...

  8. 46 CFR 112.50-5 - Electric starting.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 46 Shipping 4 2013-10-01 2013-10-01 false Electric starting. 112.50-5 Section 112.50-5 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Diesel and Gas Turbine Engine Driven Generator Sets § 112.50-5 Electric starting...

  9. 46 CFR 112.50-5 - Electric starting.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 46 Shipping 4 2014-10-01 2014-10-01 false Electric starting. 112.50-5 Section 112.50-5 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Diesel and Gas Turbine Engine Driven Generator Sets § 112.50-5 Electric starting...

  10. 46 CFR 112.50-5 - Electric starting.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... 46 Shipping 4 2012-10-01 2012-10-01 false Electric starting. 112.50-5 Section 112.50-5 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Diesel and Gas Turbine Engine Driven Generator Sets § 112.50-5 Electric starting...

  11. 46 CFR 112.50-5 - Electric starting.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 46 Shipping 4 2011-10-01 2011-10-01 false Electric starting. 112.50-5 Section 112.50-5 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Diesel and Gas Turbine Engine Driven Generator Sets § 112.50-5 Electric starting...

  12. 46 CFR 112.50-5 - Electric starting.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 46 Shipping 4 2010-10-01 2010-10-01 false Electric starting. 112.50-5 Section 112.50-5 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING EMERGENCY LIGHTING AND POWER SYSTEMS Emergency Diesel and Gas Turbine Engine Driven Generator Sets § 112.50-5 Electric starting...

  13. 46 CFR 112.35-7 - Activating means.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... POWER SYSTEMS Manually Controlled Emergency Systems Having a Storage Battery or a Diesel Engine or Gas Turbine Driven Generator as the Sole Emergency Power Source § 112.35-7 Activating means. The activating...

  14. 46 CFR 112.35-7 - Activating means.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... POWER SYSTEMS Manually Controlled Emergency Systems Having a Storage Battery or a Diesel Engine or Gas Turbine Driven Generator as the Sole Emergency Power Source § 112.35-7 Activating means. The activating...

  15. Wingtip vortex turbine investigation for vortex energy recovery

    NASA Technical Reports Server (NTRS)

    Abeyounis, William K.; Patterson, James C., Jr.; Stough, H. P., III; Wunschel, Alfred J.; Curran, Patrick D.

    1990-01-01

    A flight test investigation has been conducted to determine the performance of wingtip vortex turbines and their effect on aircraft performance. The turbines were designed to recover part of the large energy loss (induced drag) caused by the wingtip vortex. The turbine, driven by the vortex flow, reduces the strength of the vortex, resulting in an associated induced drag reduction. A four-blade turbine was mounted on each wingtip of a single-engine, T-tail, general aviation airplane. Two sets of turbine blades were tested, one with a 15' twist (washin) and one with no twist. Th power recovered by the turbine and the installed drag increment were measured. A trade-off between turbine power and induced drag reduction was found to be a function of turbine blade incidence angle. This test has demonstrated that the wingtip vortex turbine is an attractive alternate, as well as an emergency, power source.

  16. Effect of two types of helium circulators on the performance of a subsonic nuclear powered airplane

    NASA Technical Reports Server (NTRS)

    Strack, W. C.

    1971-01-01

    Two types of helium circulators are analytically compared on the bases of their influence on airplane payload and on propulsion system variables. One type of circulator is driven by the turbofan engines with power takeoff shafting while the other, a turbocirculator, is powered by a turbine placed in the helium loop between the nuclear reactor and the helium-to-air heat exchangers inside the engines. Typical results show that the turbocirculator yields more payload for circulator efficiencies greater than 0.82. Optimum engine and heat exchanger temperatures and pressures are significantly lower in the turbocirculator case compared to the engine-driven circulator scheme.

  17. Present capabilities and future requirements for computer-aided geometric modeling in the design and manufacture of gas turbine

    NASA Technical Reports Server (NTRS)

    Caille, E.; Propen, M.; Hoffman, A.

    1984-01-01

    Gas turbine engine design requires the ability to rapidly develop complex structures which are subject to severe thermal and mechanical operating loads. As in all facets of the aerospace industry, engine designs are constantly driving towards increased performance, higher temperatures, higher speeds, and lower weight. The ability to address such requirements in a relatively short time frame has resulted in a major thrust towards integrated design/analysis/manufacturing systems. These computer driven graphics systems represent a unique challenge, with major payback opportunities if properly conceived, implemented, and applied.

  18. Engine Evaluation of Advanced Technology Control Components

    DTIC Science & Technology

    1976-08-01

    producer turbine rotor blades. This is a very desirable control feature, because protecting turbine blades from overtemperature is particularly...centrifugal boost stage operating back to back on a common drive shaft that is direct driven through the alter- nator rotor shaft. The main stage is an...computation makes this simple dynamic pumping machine possible. The pen- alty of this simple design is lower overall efficiency as com- pared to a

  19. Gas turbine cooling system

    DOEpatents

    Bancalari, Eduardo E.

    2001-01-01

    A gas turbine engine (10) having a closed-loop cooling circuit (39) for transferring heat from the hot turbine section (16) to the compressed air (24) produced by the compressor section (12). The closed-loop cooling system (39) includes a heat exchanger (40) disposed in the flow path of the compressed air (24) between the outlet of the compressor section (12) and the inlet of the combustor (14). A cooling fluid (50) may be driven by a pump (52) located outside of the engine casing (53) or a pump (54) mounted on the rotor shaft (17). The cooling circuit (39) may include an orifice (60) for causing the cooling fluid (50) to change from a liquid state to a gaseous state, thereby increasing the heat transfer capacity of the cooling circuit (39).

  20. Convective Heat Transfer with and without Film Cooling in High Temperature, Fuel Rich and Lean Environments

    NASA Astrophysics Data System (ADS)

    Greiner, Nathan J.

    Modern turbine engines require high turbine inlet temperatures and pressures to maximize thermal efficiency. Increasing the turbine inlet temperature drives higher heat loads on the turbine surfaces. In addition, increasing pressure ratio increases the turbine coolant temperature such that the ability to remove heat decreases. As a result, highly effective external film cooling is required to reduce the heat transfer to turbine surfaces. Testing of film cooling on engine hardware at engine temperatures and pressures can be exceedingly difficult and expensive. Thus, modern studies of film cooling are often performed at near ambient conditions. However, these studies are missing an important aspect in their characterization of film cooling effectiveness. Namely, they do not model effect of thermal property variations that occur within the boundary and film cooling layers at engine conditions. Also, turbine surfaces can experience significant radiative heat transfer that is not trivial to estimate analytically. The present research first computationally examines the effect of large temperature variations on a turbulent boundary layer. Subsequently, a method to model the effect of large temperature variations within a turbulent boundary layer in an environment coupled with significant radiative heat transfer is proposed and experimentally validated. Next, a method to scale turbine cooling from ambient to engine conditions via non-dimensional matching is developed computationally and the experimentally validated at combustion temperatures. Increasing engine efficiency and thrust to weight ratio demands have driven increased combustor fuel-air ratios. Increased fuel-air ratios increase the possibility of unburned fuel species entering the turbine. Alternatively, advanced ultra-compact combustor designs have been proposed to decrease combustor length, increase thrust, or generate power for directed energy weapons. However, the ultra-compact combustor design requires a film cooled vane within the combustor. In both these environments, the unburned fuel in the core flow encounters the oxidizer rich film cooling stream, combusts, and can locally heat the turbine surface rather than the intended cooling of the surface. Accordingly, a method to quantify film cooling performance in a fuel rich environment is prescribed. Finally, a method to film cool in a fuel rich environment is experimentally demonstrated.

  1. Turbine design and application volumes 1, 2, and 3

    NASA Technical Reports Server (NTRS)

    Glassman, Arthur J. (Editor)

    1994-01-01

    NASA has an interest in turbines related primarily to aeronautics and space applications. Airbreathing turbine engines provide jet and turboshaft propulsion, as well as auxiliary power for aircraft. Propellant-driven turbines provide rocket propulsion and auxiliary power for spacecraft. Closed-cycle turbine engines using inert gases, organic fluids, and metal fluids have been studied for providing long-duration electric power for spacecraft. Other applications of interest for turbine engines include land-vehicle (cars, trucks, buses, trains, etc.) propulsion power and ground-based electrical power. In view of the turbine-system interest and efforts at Lewis Research Center, a course entitled 'Turbine Design and Application' was presented during 1968-69 as part of the In-house Graduate Study Program. The course was somewhat revised and again presented in 1972-73. Various aspects of turbine technology were covered including thermodynamic and fluid-dynamic concepts, fundamental turbine concepts, velocity diagrams, losses, blade aerodynamic design, blade cooling, mechanical design, operation, and performance. The notes written and used for the course have been revised and edited for publication. Such a publication can serve as a foundation for an introductory turbine course, a means for self-study, or a reference for selected topics. Any consistent set of units will satisfy the equations presented. Two commonly used consistent sets of units and constant values are given after the symbol definitions. These are the SI units and the U.S. customary units. A single set of equations covers both sets of units by including all constants required for the U.S. customary units and defining as unity those not required for the SI units. Three volumes are compiled into one.

  2. Reverse Brayton Cycle with Bladeless Turbo Compressor for Automotive Environmental Cooling

    NASA Technical Reports Server (NTRS)

    Ganapathi, Gani B. (Inventor); Cepeda-Rizo, Juan (Inventor)

    2016-01-01

    An automotive cabin cooling system uses a bladeless turbocompressor driven by automobile engine exhaust to compress incoming ambient air. The compressed air is directed to an intercooler where it is cooled and then to another bladeless turbine used as an expander where the air cools as it expands and is directed to the cabin interior. Excess energy may be captured by an alternator couple to the expander turbine. The system employs no chemical refrigerant and may be further modified to include another intercooler on the output of the expander turbine to isolate the cooled cabin environment.

  3. Orbital transfer vehicle oxygen turbopump technology. Volume 1: Design, fabrication, and hydrostatic bearing testing

    NASA Technical Reports Server (NTRS)

    Buckmann, P. S.; Hayden, W. R.; Lorenc, S. A.; Sabiers, R. L.; Shimp, N. R.

    1990-01-01

    The design, fabrication, and initial testing of a rocket engine turbopump (TPA) for the delivery of high pressure liquid oxygen using hot oxygen for the turbine drive fluid are described. This TPA is basic to the dual expander engine which uses both oxygen and hydrogen as working fluids. Separate tasks addressed the key issue of materials for this TPA. All materials selections emphasized compatibility with hot oxygen. The OX TPA design uses a two-stage centrifugal pump driven by a single-stage axial turbine on a common shaft. The design includes ports for three shaft displacement/speed sensors, various temperature measurements, and accelerometers.

  4. High freezing point fuels used for aviation turbine engines

    NASA Technical Reports Server (NTRS)

    Friedman, R.

    1979-01-01

    Broadened-specification aviation fuels could be produced from a greater fraction of crude source material with improvements in fuel supply and price. These fuels, particularly those with increased final boiling temperatures, would have higher freezing temperatures than current aviation turbine fuels. For the small but significant fraction of commercial flights where low fuel temperatures make higher freezing-point fuel use unacceptable, adaptations to the fuel or fuel system may be made to accommodate this fuel. Several techniques are discussed. Fuel heating is the most promising concept. One simple design uses existing heat rejection from the fuel-lubricating oil cooler, another uses an engine-driven generator for electrical heating.

  5. Design and Testing of the Contra-Rotating Turbine for the Scimitar Precooled Mach 5 Cruise Engine

    NASA Astrophysics Data System (ADS)

    Varvill, R.; Paniagua, G.; Kato, H.; Thatcher, M.

    tion chamber and subsequent expansion through the main noz- zle to produce thrust. In subsonic flight it becomes the gas generator driving a high bypass ratio ducted fan through a hub turbine, the exhaust mixing with the duct flow and discharging through the bypass nozzle to produce thrust. In both modes the turbo-compressor is driven by a helium turbine which has contra rotating stages to improve its efficiency at low rotational speed and reduce the number of stages required. Due to the large speed of sound mismatch between the air compressor and the helium turbine it is possible to eliminate the turbine stators by contra rotating the spools. The compressor is divided into low pressure and high pressure spools although by normal gas turbine standards they are both low pressure ratio machines.

  6. Combined rankine and vapor compression cycles

    DOEpatents

    Radcliff, Thomas D.; Biederman, Bruce P.; Brasz, Joost J.

    2005-04-19

    An organic rankine cycle system is combined with a vapor compression cycle system with the turbine generator of the organic rankine cycle generating the power necessary to operate the motor of the refrigerant compressor. The vapor compression cycle is applied with its evaporator cooling the inlet air into a gas turbine, and the organic rankine cycle is applied to receive heat from a gas turbine exhaust to heat its boiler within one embodiment, a common condenser is used for the organic rankine cycle and the vapor compression cycle, with a common refrigerant, R-245a being circulated within both systems. In another embodiment, the turbine driven generator has a common shaft connected to the compressor to thereby eliminate the need for a separate motor to drive the compressor. In another embodiment, an organic rankine cycle system is applied to an internal combustion engine to cool the fluids thereof, and the turbo charged air is cooled first by the organic rankine cycle system and then by an air conditioner prior to passing into the intake of the engine.

  7. J-2X Upper Stage Engine: Hardware and Testing 2009

    NASA Technical Reports Server (NTRS)

    Buzzell, James C.

    2009-01-01

    Mission: Common upper stage engine for Ares I and Ares V. Challenge: Use proven technology from Saturn X-33, RS-68 to develop the highest Isp GG cycle engine in history for 2 missions in record time . Key Features: LOX/LH2 GG cycle, series turbines (2), HIP-bonded MCC, pneumatic ball-sector valves, on-board engine controller, tube-wall regen nozzle/large passively-cooled nozzle extension, TEG boost/cooling . Development Philosophy: proven hardware, aggressive schedule, early risk reduction, requirements-driven.

  8. Subsonic Swept Fan Blade

    NASA Technical Reports Server (NTRS)

    Gallagher, Edward J. (Inventor); Rogers, Thomas H. (Inventor)

    2017-01-01

    A gas turbine engine includes a spool, a turbine coupled to drive the spool, a propulsor coupled to be driven at a at a design speed by the turbine through the spool, and a gear assembly coupled between the propulsor and the spool. Rotation of the turbine drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extend from the hub. Each of the propulsor blades includes an airfoil body. The leading edge of the airfoil body has a swept profile such that, at the design speed, a component of a relative velocity vector of a working gas that is normal to the leading edge is subsonic along the entire radial span.

  9. Experimental Simulation of Turbine-Exhaust Oxygen Recovery

    NASA Technical Reports Server (NTRS)

    Clark, Jim A.; Branch, Ryan W.

    2004-01-01

    In some liquid-propellant rocket engines, the liquid-oxygen boost pump is driven by a turbine that is powered by high-pressure gaseous oxygen. Once it exits the turbine, this gaseous oxygen can be salvaged by injecting it into the subcooled liquid oxygen exiting the boost pump. If the main LOX pump is to function correctly under these circumstances, complete condensation of the gaseous oxygen must quickly follow its injection into the boost-pump discharge. The current investigation uses steam and water in a simple rig that allows the condensation process to be visualized and quantified. This paper offers dimensionless-parameter correlations of the data and trends observed.

  10. Propulsion Health Monitoring of a Turbine Engine Disk Using Spin Test Data

    NASA Technical Reports Server (NTRS)

    Abdul-Aziz, Ali; Woike, Mark R.; Oza, Nikunj; Matthews, Bryan; Baaklini, George Y.

    2010-01-01

    This paper considers data collected from an experimental study using high frequency capacitive sensor technology to capture blade tip clearance and tip timing measurements in a rotating turbine engine-like-disk-to predict the disk faults and assess its structural integrity. The experimental results collected at a range of rotational speeds from tests conducted at the NASA Glenn Research Center s Rotordynamics Laboratory are evaluated using multiple data-driven anomaly detection techniques to identify abnormalities in the disk. Further, this study presents a select evaluation of an online health monitoring scheme of a rotating disk using high caliber sensors and test the capability of the in-house spin system.

  11. Gas turbine power plant with supersonic shock compression ramps

    DOEpatents

    Lawlor, Shawn P [Bellevue, WA; Novaresi, Mark A [San Diego, CA; Cornelius, Charles C [Kirkland, WA

    2008-10-14

    A gas turbine engine. The engine is based on the use of a gas turbine driven rotor having a compression ramp traveling at a local supersonic inlet velocity (based on the combination of inlet gas velocity and tangential speed of the ramp) which compresses inlet gas against a stationary sidewall. The supersonic compressor efficiently achieves high compression ratios while utilizing a compact, stabilized gasdynamic flow path. Operated at supersonic speeds, the inlet stabilizes an oblique/normal shock system in the gasdynamic flow path formed between the rim of the rotor, the strakes, and a stationary external housing. Part load efficiency is enhanced by use of a lean pre-mix system, a pre-swirl compressor, and a bypass stream to bleed a portion of the gas after passing through the pre-swirl compressor to the combustion gas outlet. Use of a stationary low NOx combustor provides excellent emissions results.

  12. Low pressure EGR system having full range capability

    DOEpatents

    Easley, Jr., William Lanier; Milam, David Michael; Roozenboom, Stephan Donald; Bond, Michael Steven; Kapic, Amir

    2009-09-22

    An exhaust treatment system for an engine is disclosed and may have an air induction circuit, an exhaust circuit, and an exhaust recirculation circuit. The air induction circuit may be configured to direct air into the engine. The exhaust circuit may be configured to direct exhaust from the engine and include a turbine driven by the exhaust, a particulate filter disposed in series with and downstream of the turbine, and a catalytic device disposed in series with and downstream of the particulate filter. The exhaust recirculation circuit may be configured to selectively redirect at least some of the exhaust from between the particulate filter and the catalytic device to the air induction circuit. The catalytic device is selected to create backpressure within the exhaust circuit sufficient to ensure that, under normal engine operating conditions above low idle, exhaust can flow into the air induction circuit without throttling of the air.

  13. The Utility of Handheld Programmable Calculators in Aircraft Life Cycle Cost Estimation.

    DTIC Science & Technology

    1982-09-01

    are available for extended mem - ory, hardcopy printout, video interface, and special application software. Any calculator of comparable memory could...condi- tioning system. OG Total number of engine, air turbine motor (ATM) and auxiliary power unit (APU) driven generator/alternators. OHP Total number

  14. Solid Oxide Fuel Cell/Gas Turbine Hybrid Cycle Technology for Auxiliary Aerospace Power

    NASA Technical Reports Server (NTRS)

    Steffen, Christopher J., Jr.; Freeh, Joshua E.; Larosiliere, Louis M.

    2005-01-01

    A notional 440 kW auxiliary power unit has been developed for 300 passenger commercial transport aircraft in 2015AD. A hybrid engine using solid-oxide fuel cell stacks and a gas turbine bottoming cycle has been considered. Steady-state performance analysis during cruise operation has been presented. Trades between performance efficiency and system mass were conducted with system specific energy as the discriminator. Fuel cell performance was examined with an area specific resistance. The ratio of fuel cell versus turbine power was explored through variable fuel utilization. Area specific resistance, fuel utilization, and mission length had interacting effects upon system specific energy. During cruise operation, the simple cycle fuel cell/gas turbine hybrid was not able to outperform current turbine-driven generators for system specific energy, despite a significant improvement in system efficiency. This was due in part to the increased mass of the hybrid engine, and the increased water flow required for on-board fuel reformation. Two planar, anode-supported cell design concepts were considered. Designs that seek to minimize the metallic interconnect layer mass were seen to have a large effect upon the system mass estimates.

  15. 46 CFR 112.50-7 - Compressed air starting.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... AND POWER SYSTEMS Emergency Diesel and Gas Turbine Engine Driven Generator Sets § 112.50-7 Compressed... emergency generator room and a handcranked, diesel-powered air compressor for recharging the air receiver..., and energy storing devices must be in the emergency generator room, except for the main or auxiliary...

  16. 46 CFR 112.50-7 - Compressed air starting.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... AND POWER SYSTEMS Emergency Diesel and Gas Turbine Engine Driven Generator Sets § 112.50-7 Compressed... emergency generator room and a handcranked, diesel-powered air compressor for recharging the air receiver..., and energy storing devices must be in the emergency generator room, except for the main or auxiliary...

  17. Usage of Parameterized Fatigue Spectra and Physics-Based Systems Engineering Models for Wind Turbine Component Sizing: Preprint

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Parsons, Taylor; Guo, Yi; Veers, Paul

    Software models that use design-level input variables and physics-based engineering analysis for estimating the mass and geometrical properties of components in large-scale machinery can be very useful for analyzing design trade-offs in complex systems. This study uses DriveSE, an OpenMDAO-based drivetrain model that uses stress and deflection criteria to size drivetrain components within a geared, upwind wind turbine. Because a full lifetime fatigue load spectrum can only be defined using computationally-expensive simulations in programs such as FAST, a parameterized fatigue loads spectrum that depends on wind conditions, rotor diameter, and turbine design life has been implemented. The parameterized fatigue spectrummore » is only used in this paper to demonstrate the proposed fatigue analysis approach. This paper details a three-part investigation of the parameterized approach and a comparison of the DriveSE model with and without fatigue analysis on the main shaft system. It compares loads from three turbines of varying size and determines if and when fatigue governs drivetrain sizing compared to extreme load-driven design. It also investigates the model's sensitivity to shaft material parameters. The intent of this paper is to demonstrate how fatigue considerations in addition to extreme loads can be brought into a system engineering optimization.« less

  18. Experimental study of operation performance for hydrocarbon fuel pump with low specific speed

    NASA Astrophysics Data System (ADS)

    Wu, Xianyu; Yang, Jun; Jin, Xuan

    2017-10-01

    In this paper, a small flow rate hydrocarbon turbine pump was used to pressurize the fuel supply system of scramjet engine. Some experiments were carried out to investigate the characteristics of turbine pump driven by nitrogen or combustion gas under different operating conditions. A experimental database with regard to the curves of the rotational speed, mass flow rate and net head with regard to centrifugal pump were plotted. These curves were represented as functions of the pressure and temperature at turbine inlet/outlet and the throttle diameter at downstream of centrifugal pump. A sensitivity study has been carried out based on design of experiments. The experimental was employed to analyze net head of centrifugal and throttle characteristics. The research results can accumulate foundations for the close loop control system of turbine pump.

  19. Advanced space engine preliminary design

    NASA Technical Reports Server (NTRS)

    Cuffe, J. P. B.; Bradie, R. E.

    1973-01-01

    A preliminary design was completed for an O2/H2, 89 kN (20,000 lb) thrust staged combustion rocket engine that has a single-bell nozzle with an overall expansion ratio of 400:1. The engine has a best estimate vacuum specific impulse of 4623.8 N-s/kg (471.5 sec) at full thrust and mixture ratio = 6.0. The engine employs gear-driven, low pressure pumps to provide low NPSH capability while individual turbine-driven, high-speed main pumps provide the system pressures required for high-chamber pressure operation. The engine design dry weight for the fixed-nozzle configuration is 206.9 kg (456.3 lb). Engine overall length is 234 cm (92.1 in.). The extendible nozzle version has a stowed length of 141.5 cm (55.7 in.). Critical technology items in the development of the engine were defined. Development program plans and their costs for development, production, operation, and flight support of the ASE were established for minimum cost and minimum time programs.

  20. 46 CFR 112.50-3 - Hydraulic starting.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 46 Shipping 4 2013-10-01 2013-10-01 false Hydraulic starting. 112.50-3 Section 112.50-3 Shipping... POWER SYSTEMS Emergency Diesel and Gas Turbine Engine Driven Generator Sets § 112.50-3 Hydraulic starting. A hydraulic starting system must meet the following: (a) The hydraulic starting system must be a...

  1. 46 CFR 112.50-3 - Hydraulic starting.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... 46 Shipping 4 2012-10-01 2012-10-01 false Hydraulic starting. 112.50-3 Section 112.50-3 Shipping... POWER SYSTEMS Emergency Diesel and Gas Turbine Engine Driven Generator Sets § 112.50-3 Hydraulic starting. A hydraulic starting system must meet the following: (a) The hydraulic starting system must be a...

  2. 46 CFR 112.50-3 - Hydraulic starting.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 46 Shipping 4 2014-10-01 2014-10-01 false Hydraulic starting. 112.50-3 Section 112.50-3 Shipping... POWER SYSTEMS Emergency Diesel and Gas Turbine Engine Driven Generator Sets § 112.50-3 Hydraulic starting. A hydraulic starting system must meet the following: (a) The hydraulic starting system must be a...

  3. 46 CFR 112.50-1 - General.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... Emergency Diesel and Gas Turbine Engine Driven Generator Sets § 112.50-1 General. (a) The prime mover of a generator set must have: (1) All accessories necessary for operation and protection of the prime mover; and... degrees C). (c) The room that has the generator set must have intake and exhaust ducts to supply adequate...

  4. Aircraft photovoltaic power-generating system

    NASA Astrophysics Data System (ADS)

    Doellner, Oscar Leonard

    Photovoltaic cells, appropriately cooled and operating in the combustion-created high radiant-intensity environment of gas-turbine and jet engines, may replace the conventional (gearbox-driven) electrical power generators aboard jet aircraft. This study projects significant improvements not only in aircraft electrical power-generating-system performance, but also in overall aircraft performance. Jet-engine design modifications incorporating this concept not only save weight (and thus fuel), but are - in themselves - favorable to jet-engine performance. The dissertation concentrates on operational, constructional, structural, thermal, optical, radiometrical, thin-film, and solid-state theoretical aspects of the overall project.

  5. 14 CFR 29.1305 - Powerplant instruments.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... temperature indicator for each turbine engine; (12) A gas producer rotor tachometer for each turbine engine... free power turbine tachometer for each turbine engine; (16) A means, for each turbine engine, to indicate power for that engine; (17) For each turbine engine, an indicator to indicate the functioning of...

  6. 14 CFR 29.1305 - Powerplant instruments.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... temperature indicator for each turbine engine; (12) A gas producer rotor tachometer for each turbine engine... free power turbine tachometer for each turbine engine; (16) A means, for each turbine engine, to indicate power for that engine; (17) For each turbine engine, an indicator to indicate the functioning of...

  7. 14 CFR 29.1305 - Powerplant instruments.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... temperature indicator for each turbine engine; (12) A gas producer rotor tachometer for each turbine engine... free power turbine tachometer for each turbine engine; (16) A means, for each turbine engine, to indicate power for that engine; (17) For each turbine engine, an indicator to indicate the functioning of...

  8. 14 CFR 29.1305 - Powerplant instruments.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... temperature indicator for each turbine engine; (12) A gas producer rotor tachometer for each turbine engine... free power turbine tachometer for each turbine engine; (16) A means, for each turbine engine, to indicate power for that engine; (17) For each turbine engine, an indicator to indicate the functioning of...

  9. 14 CFR 29.1305 - Powerplant instruments.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... temperature indicator for each turbine engine; (12) A gas producer rotor tachometer for each turbine engine... free power turbine tachometer for each turbine engine; (16) A means, for each turbine engine, to indicate power for that engine; (17) For each turbine engine, an indicator to indicate the functioning of...

  10. Method of making an aero-derivative gas turbine engine

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Wiebe, David J.

    A method of making an aero-derivative gas turbine engine (100) is provided. A combustor outer casing (68) is removed from an existing aero gas turbine engine (60). An annular combustor (84) is removed from the existing aero gas turbine engine. A first row of turbine vanes (38) is removed from the existing aero gas turbine engine. A can annular combustor assembly (122) is installed within the existing aero gas turbine engine. The can annular combustor assembly is configured to accelerate and orient combustion gasses directly onto a first row of turbine blades of the existing aero gas turbine engine. Amore » can annular combustor assembly outer casing (108) is installed to produce the aero-derivative gas turbine engine (100). The can annular combustor assembly is installed within an axial span (85) of the existing aero gas turbine engine vacated by the annular combustor and the first row of turbine vanes.« less

  11. 14 CFR 27.939 - Turbine engine operating characteristics.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false Turbine engine operating characteristics....939 Turbine engine operating characteristics. (a) Turbine engine operating characteristics must be... limitations of the rotorcraft and of the engine. (b) The turbine engine air inlet system may not, as a result...

  12. 14 CFR 27.939 - Turbine engine operating characteristics.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 1 2013-01-01 2013-01-01 false Turbine engine operating characteristics....939 Turbine engine operating characteristics. (a) Turbine engine operating characteristics must be... limitations of the rotorcraft and of the engine. (b) The turbine engine air inlet system may not, as a result...

  13. 14 CFR 27.939 - Turbine engine operating characteristics.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false Turbine engine operating characteristics....939 Turbine engine operating characteristics. (a) Turbine engine operating characteristics must be... limitations of the rotorcraft and of the engine. (b) The turbine engine air inlet system may not, as a result...

  14. 14 CFR 29.939 - Turbine engine operating characteristics.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 1 2013-01-01 2013-01-01 false Turbine engine operating characteristics....939 Turbine engine operating characteristics. (a) Turbine engine operating characteristics must be... limitations of the rotorcraft and of the engine. (b) The turbine engine air inlet system may not, as a result...

  15. 14 CFR 29.939 - Turbine engine operating characteristics.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false Turbine engine operating characteristics....939 Turbine engine operating characteristics. (a) Turbine engine operating characteristics must be... limitations of the rotorcraft and of the engine. (b) The turbine engine air inlet system may not, as a result...

  16. 14 CFR 29.939 - Turbine engine operating characteristics.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false Turbine engine operating characteristics....939 Turbine engine operating characteristics. (a) Turbine engine operating characteristics must be... limitations of the rotorcraft and of the engine. (b) The turbine engine air inlet system may not, as a result...

  17. 14 CFR 29.939 - Turbine engine operating characteristics.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false Turbine engine operating characteristics....939 Turbine engine operating characteristics. (a) Turbine engine operating characteristics must be... limitations of the rotorcraft and of the engine. (b) The turbine engine air inlet system may not, as a result...

  18. 14 CFR 27.939 - Turbine engine operating characteristics.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false Turbine engine operating characteristics....939 Turbine engine operating characteristics. (a) Turbine engine operating characteristics must be... limitations of the rotorcraft and of the engine. (b) The turbine engine air inlet system may not, as a result...

  19. 14 CFR 27.939 - Turbine engine operating characteristics.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Turbine engine operating characteristics....939 Turbine engine operating characteristics. (a) Turbine engine operating characteristics must be... limitations of the rotorcraft and of the engine. (b) The turbine engine air inlet system may not, as a result...

  20. 14 CFR 29.939 - Turbine engine operating characteristics.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Turbine engine operating characteristics....939 Turbine engine operating characteristics. (a) Turbine engine operating characteristics must be... limitations of the rotorcraft and of the engine. (b) The turbine engine air inlet system may not, as a result...

  1. 14 CFR 29.1521 - Powerplant limitations.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... pressure (for reciprocating engines); (3) The maximum allowable turbine inlet or turbine outlet gas temperature (for turbine engines); (4) The maximum allowable power or torque for each engine, considering the... maximum allowable turbine inlet or turbine outlet gas temperature (for turbine engines); (5) The maximum...

  2. 14 CFR 29.1521 - Powerplant limitations.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... pressure (for reciprocating engines); (3) The maximum allowable turbine inlet or turbine outlet gas temperature (for turbine engines); (4) The maximum allowable power or torque for each engine, considering the... maximum allowable turbine inlet or turbine outlet gas temperature (for turbine engines); (5) The maximum...

  3. 14 CFR 29.1521 - Powerplant limitations.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... pressure (for reciprocating engines); (3) The maximum allowable turbine inlet or turbine outlet gas temperature (for turbine engines); (4) The maximum allowable power or torque for each engine, considering the... maximum allowable turbine inlet or turbine outlet gas temperature (for turbine engines); (5) The maximum...

  4. 14 CFR 29.1521 - Powerplant limitations.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... pressure (for reciprocating engines); (3) The maximum allowable turbine inlet or turbine outlet gas temperature (for turbine engines); (4) The maximum allowable power or torque for each engine, considering the... maximum allowable turbine inlet or turbine outlet gas temperature (for turbine engines); (5) The maximum...

  5. 14 CFR 29.1521 - Powerplant limitations.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... pressure (for reciprocating engines); (3) The maximum allowable turbine inlet or turbine outlet gas temperature (for turbine engines); (4) The maximum allowable power or torque for each engine, considering the... maximum allowable turbine inlet or turbine outlet gas temperature (for turbine engines); (5) The maximum...

  6. Turbine blade tip gap reduction system

    DOEpatents

    Diakunchak, Ihor S.

    2012-09-11

    A turbine blade sealing system for reducing a gap between a tip of a turbine blade and a stationary shroud of a turbine engine. The sealing system includes a plurality of flexible seal strips extending from a pressure side of a turbine blade generally orthogonal to the turbine blade. During operation of the turbine engine, the flexible seal strips flex radially outward extending towards the stationary shroud of the turbine engine, thereby reducing the leakage of air past the turbine blades and increasing the efficiency of the turbine engine.

  7. Evaluation of lightning accommodation systems for wind-driven turbine rotors

    NASA Technical Reports Server (NTRS)

    Bankaitis, H.

    1982-01-01

    Wind-driven turbine generators are being evaluated as an alternative source of electric energy. Areas of favorable location for the wind-driven turbines (high wind density) coincide with areas of high incidence of thunderstorm activity. These locations, coupled with the 30-m or larger diameter rotor blades, make the wind-driven turbine blades probable terminations for lightning strikes. Several candidate systems of lightning accommodation for composite-structural-material blades were designed and their effectiveness evaluated by submitting the systems to simulated lightning strikes. The test data were analyzed and system design were reviewed on the basis of the analysis.

  8. Combustion Sensors: Gas Turbine Applications

    NASA Technical Reports Server (NTRS)

    Human, Mel

    2002-01-01

    This report documents efforts to survey the current research directions in sensor technology for gas turbine systems. The work is driven by the current and future requirements on system performance and optimization. Accurate real time measurements of velocities, pressure, temperatures, and species concentrations will be required for objectives such as combustion instability attenuation, pollutant reduction, engine health management, exhaust profile control via active control, etc. Changing combustor conditions - engine aging, flow path slagging, or rapid maneuvering - will require adaptive responses; the effectiveness of such will be only as good as the dynamic information available for processing. All of these issues point toward the importance of continued sensor development. For adequate control of the combustion process, sensor data must include information about the above mentioned quantities along with equivalence ratios and radical concentrations, and also include both temporal and spatial velocity resolution. Ultimately these devices must transfer from the laboratory to field installations, and thus must become low weight and cost, reliable and maintainable. A primary conclusion from this study is that the optics-based sensor science will be the primary diagnostic in future gas turbine technologies.

  9. 14 CFR Appendix D to Part 147 - Powerplant Curriculum Subjects

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... a. reciprocating engines (1) 1. Inspect and repair a radial engine. (2) 2. Overhaul reciprocating.... Install, troubleshoot, and remove reciprocating engines. b. turbine engines (2) 5. Overhaul turbine engine. (3) 6. Inspect, check, service, and repair turbine engines and turbine engine installations. (3) 7...

  10. 14 CFR Appendix D to Part 147 - Powerplant Curriculum Subjects

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... a. reciprocating engines (1) 1. Inspect and repair a radial engine. (2) 2. Overhaul reciprocating.... Install, troubleshoot, and remove reciprocating engines. b. turbine engines (2) 5. Overhaul turbine engine. (3) 6. Inspect, check, service, and repair turbine engines and turbine engine installations. (3) 7...

  11. 14 CFR Appendix D to Part 147 - Powerplant Curriculum Subjects

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... a. reciprocating engines (1) 1. Inspect and repair a radial engine. (2) 2. Overhaul reciprocating.... Install, troubleshoot, and remove reciprocating engines. b. turbine engines (2) 5. Overhaul turbine engine. (3) 6. Inspect, check, service, and repair turbine engines and turbine engine installations. (3) 7...

  12. 14 CFR Appendix D to Part 147 - Powerplant Curriculum Subjects

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... a. reciprocating engines (1) 1. Inspect and repair a radial engine. (2) 2. Overhaul reciprocating.... Install, troubleshoot, and remove reciprocating engines. b. turbine engines (2) 5. Overhaul turbine engine. (3) 6. Inspect, check, service, and repair turbine engines and turbine engine installations. (3) 7...

  13. Labyrinth seal testing for lift fan engines

    NASA Technical Reports Server (NTRS)

    Dobek, L. J.

    1973-01-01

    An abradable buffered labyrinth seal for the control of turbine gas path leakage in a tip-turbine driven lift fan was designed, tested, and analyzed. The seal configuration was not designed to operate in any specific location but was sized to be evaluated in an existing test rig. The final sealing diameter selected was 28 inches. Results of testing indicate that the flow equations predicted seal air flows consistent with measured values. Excellent sealing characteristics of the abradable coating on the stator land were demonstrated when a substantial seal penetration of .030 inch into the land surface was encountered without appreciable wear on the labyrinth knife edges.

  14. Demonstration of Novel Sampling Techniques for Measurement of Turbine Engine Volatile and Non-Volatile Particulate Matter (PM) Emissions

    DTIC Science & Technology

    2016-09-01

    AFRL-RQ-WP-TR-2016-0131 DEMONSTRATION OF NOVEL SAMPLING TECHNIQUES FOR MEASUREMENT OF TURBINE ENGINE VOLATILE AND NON-VOLATILE PARTICULATE...MATTER (PM) EMISSIONS Edwin Corporan Fuels and Energy Branch Turbine Engine Division Matthew DeWitt and Chris Klingshirn University of...Energy Branch Turbine Engine Division Turbine Engine Division Aerospace Systems Directorate //Signature// CHARLES W. STEVENS Lead Engineer

  15. Feedback control of a Darrieus wind turbine and optimization of the produced energy

    NASA Astrophysics Data System (ADS)

    Maurin, T.; Henry, B.; Devos, F.; de Saint Louvent, B.; Gosselin, J.

    1984-03-01

    A microprocessor-driven control system, applied to the feedback control of a Darrieus wind turbine is presented. The use of a dc machine as a generator to recover the energy and as a motor to start the engine, allows simplified power electronics. The architecture of the control unit is built to ensure four different functions: starting, optimization of the recoverable energy, regulation of the speed, and braking. An experimental study of the system in a wind tunnel allowed optimization of the coefficients of the proportional and integral (pi) control algorithm. The electrical energy recovery was found to be much more efficient using the feedback system than without the control unit. This system allows a better characterization of the wind turbine and a regulation adapted to the wind statistics observed in one given geographical location.

  16. Shaft balancing

    DOEpatents

    Irwin, John A.

    1979-01-01

    A gas turbine engine has an internal drive shaft including one end connected to a driven load and an opposite end connected to a turbine wheel and wherein the shaft has an in situ adjustable balance system near the critical center of a bearing span for the shaft including two 360.degree. rings piloted on the outer diameter of the shaft at a point accessible through an internal engine panel; each of the rings has a small amount of material removed from its periphery whereby both of the rings are precisely unbalanced an equivalent amount; the rings are locked circumferentially together by radial serrations thereon; numbered tangs on the outside diameter of each ring identify the circumferential location of unbalance once the rings are locked together; an aft ring of the pair of rings has a spline on its inside diameter that mates with a like spline on the shaft to lock the entire assembly together.

  17. High-freezing-point fuels used for aviation turbine engines

    NASA Technical Reports Server (NTRS)

    Friedman, R.

    1979-01-01

    Broadened-specification aviation fuels could be produced from a greater fraction of crude source material with improvements in fuel supply and price. These fuels, particularly those with increased final boiling temperatures, would have higher freezing temperatures than current aviation turbine fuels. The higher-freezing-point fuels can be substituted in the majority of present commercial flights, since temperature data indicate that in-flight fuel temperatures are relatively mild. For the small but significant fraction of commercial flights where low fuel temperatures make higher freezing-point fuel use unacceptable, adaptations to the fuel or fuel system may be made to accommodate this fuel. Several techniques are discussed. Fuel heating is the most promising concept. One simple system design uses existing heat rejection from the fuel-lubricating oil cooler, another uses an engine-driven generator for electrical heating. Both systems offer advantages that outweigh the obvious penalties.

  18. A systems engineering analysis of three-point and four-point wind turbine drivetrain configurations

    DOE PAGES

    Guo, Yi; Parsons, Tyler; Dykes, Katherine; ...

    2016-08-24

    This study compares the impact of drivetrain configuration on the mass and capital cost of a series of wind turbines ranging from 1.5 MW to 5.0 MW power ratings for both land-based and offshore applications. The analysis is performed with a new physics-based drivetrain analysis and sizing tool, Drive Systems Engineering (DriveSE), which is part of the Wind-Plant Integrated System Design & Engineering Model. DriveSE uses physics-based relationships to size all major drivetrain components according to given rotor loads simulated based on International Electrotechnical Commission design load cases. The model's sensitivity to input loads that contain a high degree ofmore » variability was analyzed. Aeroelastic simulations are used to calculate the rotor forces and moments imposed on the drivetrain for each turbine design. DriveSE is then used to size all of the major drivetrain components for each turbine for both three-point and four-point configurations. The simulation results quantify the trade-offs in mass and component costs for the different configurations. On average, a 16.7% decrease in total nacelle mass can be achieved when using a three-point drivetrain configuration, resulting in a 3.5% reduction in turbine capital cost. This analysis is driven by extreme loads and does not consider fatigue. Thus, the effects of configuration choices on reliability and serviceability are not captured. Furthermore, a first order estimate of the sizing, dimensioning and costing of major drivetrain components are made which can be used in larger system studies which consider trade-offs between subsystems such as the rotor, drivetrain and tower.« less

  19. A systems engineering analysis of three-point and four-point wind turbine drivetrain configurations

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Guo, Yi; Parsons, Tyler; Dykes, Katherine

    This study compares the impact of drivetrain configuration on the mass and capital cost of a series of wind turbines ranging from 1.5 MW to 5.0 MW power ratings for both land-based and offshore applications. The analysis is performed with a new physics-based drivetrain analysis and sizing tool, Drive Systems Engineering (DriveSE), which is part of the Wind-Plant Integrated System Design & Engineering Model. DriveSE uses physics-based relationships to size all major drivetrain components according to given rotor loads simulated based on International Electrotechnical Commission design load cases. The model's sensitivity to input loads that contain a high degree ofmore » variability was analyzed. Aeroelastic simulations are used to calculate the rotor forces and moments imposed on the drivetrain for each turbine design. DriveSE is then used to size all of the major drivetrain components for each turbine for both three-point and four-point configurations. The simulation results quantify the trade-offs in mass and component costs for the different configurations. On average, a 16.7% decrease in total nacelle mass can be achieved when using a three-point drivetrain configuration, resulting in a 3.5% reduction in turbine capital cost. This analysis is driven by extreme loads and does not consider fatigue. Thus, the effects of configuration choices on reliability and serviceability are not captured. Furthermore, a first order estimate of the sizing, dimensioning and costing of major drivetrain components are made which can be used in larger system studies which consider trade-offs between subsystems such as the rotor, drivetrain and tower.« less

  20. A microscale turbine driven by diffusive mass flux.

    PubMed

    Yang, Mingcheng; Liu, Rui; Ripoll, Marisol; Chen, Ke

    2015-10-07

    An external diffusive mass flux is shown to be able to generate a mechanical torque on a microscale object based on anisotropic diffusiophoresis. In light of this finding, we propose a theoretical prototype micro-turbine driven purely by diffusive mass flux, which is in strong contrast to conventional turbines driven by convective mass flows. The rotational velocity of the proposed turbine is determined by the external concentration gradient, the geometry and the diffusiophoretic properties of the turbine. This scenario is validated by performing computer simulations. Our finding thus provides a new type of chemo-mechanical response which could be used to exploit existing chemical energies at small scales.

  1. Wind Turbine Blade CAD Models Used as Scaffolding Technique to Teach Design Engineers

    ERIC Educational Resources Information Center

    Irwin, John

    2013-01-01

    The Siemens PLM CAD software NX is commonly used for designing mechanical systems, and in complex systems such as the emerging area of wind power, the ability to have a model controlled by design parameters is a certain advantage. Formula driven expressions based on the amount of available wind in an area can drive the amount of effective surface…

  2. Advanced turbine systems program conceptual design and product development. Task 3 -- System selection; Topical report

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    White, D.J.

    1994-07-01

    Solar Turbines Incorporated has elected to pursue an intercooled and recuperated (ICR) gas turbine system to exceed the goals of the DOE Advanced Turbine Systems (ATS) program, which are to develop and commercialize an industrial gas turbine system that operates at thermal efficiencies at least 15% higher than 1991 products, and with emissions not exceeding eight ppmv NOx and 20 ppmv CO and UHC. Solar`s goal is to develop a commercially viable industrial system (3--20 MW) driven by a gas turbine engine with a thermal efficiency of 50% (ATS50), with the flexibility to meet the differing operational requirements of variousmore » markets. Dispersed power generation is currently considered to be the primary future target market for the ICR in the 5--15 MW size class. The ICR integrated system approach provides an ideal candidate for the assumed dispersed power market, with its small footprint, easy transportability, and environmental friendliness. In comparison with other systems that use water or toxic chemicals such as ammonia for NOx control, the ICR has no consumables other than fuel and air. The low pressure ratio of the gas turbine engine also is favorable in that less parasitic power is needed to pump the natural gas into the combustor than for simple-cycle machines. Solar has narrowed the ICR configuration to two basic approaches, a 1-spool, and a 2-spool version of the ATS50. The 1-spool engine will have a lower first-cost but lower part-power efficiencies. The 2-spool ATS may not only have better part-power efficiency, its efficiency will also be less sensitive to reduced turbine rotor inlet temperature levels. Thus hot-end parts life can be increased with only small sacrifices in efficiency. The flexibility of the 2-spool arrangement in meeting customer needs is its major advantage over the 1-spool. This Task 3 Topical Report is intended to present Solar`s preliminary system selection based upon the initial trade-off studies performed to date.« less

  3. Progress in the utilization of an oxide-dispersion-strengthened alloy for small engine turbine blades

    NASA Technical Reports Server (NTRS)

    Beatty, T. G.; Millan, P. P.

    1984-01-01

    The conventional means of improving gas turbine engine performance typically involves increasing the turbine inlet temperature; however, at these higher operational temperatures the high pressure turbine blades require air-cooling to maintain durability. Air-cooling imposes design, material, and economic constraints not only on the turbine blades but also on engine performance. The use of uncooled turbine blades at increased operating temperatures can offer significantly improved performance in small gas turbine engines. A program to demonstrate uncooled MA6000 high pressure turbine blades in a GTEC TFE731 turbofan engine is being conducted. The project goals include demonstration of the advantages of using uncooled MA6000 turbine blades as compared with cast directionally solidified MAR-M 247 blades.

  4. Methods of Si based ceramic components volatilization control in a gas turbine engine

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Garcia-Crespo, Andres Jose; Delvaux, John; Dion Ouellet, Noemie

    A method of controlling volatilization of silicon based components in a gas turbine engine includes measuring, estimating and/or predicting a variable related to operation of the gas turbine engine; correlating the variable to determine an amount of silicon to control volatilization of the silicon based components in the gas turbine engine; and injecting silicon into the gas turbine engine to control volatilization of the silicon based components. A gas turbine with a compressor, combustion system, turbine section and silicon injection system may be controlled by a controller that implements the control method.

  5. 14 CFR 135.379 - Large transport category airplanes: Turbine engine powered: Takeoff limitations.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... engine powered: Takeoff limitations. 135.379 Section 135.379 Aeronautics and Space FEDERAL AVIATION... category airplanes: Turbine engine powered: Takeoff limitations. (a) No person operating a turbine engine... existing at take- off. (b) No person operating a turbine engine powered large transport category airplane...

  6. 14 CFR 135.379 - Large transport category airplanes: Turbine engine powered: Takeoff limitations.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... engine powered: Takeoff limitations. 135.379 Section 135.379 Aeronautics and Space FEDERAL AVIATION... category airplanes: Turbine engine powered: Takeoff limitations. (a) No person operating a turbine engine... existing at take- off. (b) No person operating a turbine engine powered large transport category airplane...

  7. 14 CFR 25.939 - Turbine engine operating characteristics.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 1 2013-01-01 2013-01-01 false Turbine engine operating characteristics... TRANSPORTATION AIRCRAFT AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES Powerplant General § 25.939 Turbine engine operating characteristics. (a) Turbine engine operating characteristics must be investigated in...

  8. 14 CFR 25.939 - Turbine engine operating characteristics.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false Turbine engine operating characteristics... TRANSPORTATION AIRCRAFT AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES Powerplant General § 25.939 Turbine engine operating characteristics. (a) Turbine engine operating characteristics must be investigated in...

  9. 14 CFR 25.939 - Turbine engine operating characteristics.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false Turbine engine operating characteristics... TRANSPORTATION AIRCRAFT AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES Powerplant General § 25.939 Turbine engine operating characteristics. (a) Turbine engine operating characteristics must be investigated in...

  10. 14 CFR 25.939 - Turbine engine operating characteristics.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false Turbine engine operating characteristics... TRANSPORTATION AIRCRAFT AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES Powerplant General § 25.939 Turbine engine operating characteristics. (a) Turbine engine operating characteristics must be investigated in...

  11. 14 CFR 25.939 - Turbine engine operating characteristics.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Turbine engine operating characteristics... TRANSPORTATION AIRCRAFT AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES Powerplant General § 25.939 Turbine engine operating characteristics. (a) Turbine engine operating characteristics must be investigated in...

  12. Computational and Experimental Evaluation of a Complex Inlet Swirl Pattern Generation System (POSTPRINT)

    DTIC Science & Technology

    2016-08-01

    Sanders, Chase A. Nessler, William W. Copenhaver, Michael G. List, and Timothy J. Janczewski Turbomachinery Branch Turbine Engine Division AUGUST...Branch Turbine Engine Division Turbine Engine Division Aerospace Systems Directorate //Signature// ROBERT D. HANCOCK Principal Scientist Turbine ...ORGANIZATION Turbomachinery Branch Turbine Engine Division Air Force Research Laboratory, Aerospace Systems Directorate Wright-Patterson Air Force

  13. Gas Turbine Engine with Air/Fuel Heat Exchanger

    NASA Technical Reports Server (NTRS)

    Krautheim, Michael Stephen (Inventor); Chouinard, Donald G. (Inventor); Donovan, Eric Sean (Inventor); Karam, Michael Abraham (Inventor); Vetters, Daniel Kent (Inventor)

    2017-01-01

    One embodiment of the present invention is a unique aircraft propulsion gas turbine engine. Another embodiment is a unique gas turbine engine. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines with heat exchange systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

  14. System Study for Axial Vane Engine Technology

    NASA Technical Reports Server (NTRS)

    Badley, Patrick R.; Smith, Michael R.; Gould, Cedric O.

    2008-01-01

    The purpose of this engine feasibility study was to determine the benefits that can be achieved by incorporating positive displacement axial vane compression and expansion stages into high bypass turbofan engines. These positive-displacement stages would replace some or all of the conventional compressor and turbine stages in the turbine engine, but not the fan. The study considered combustion occurring internal to an axial vane component (i.e., Diesel engine replacing the standard turbine engine combustor, burner, and turbine); and external continuous flow combustion with an axial vane compressor and an axial vane turbine replacing conventional compressor and turbine systems.

  15. 14 CFR 135.381 - Large transport category airplanes: Turbine engine powered: En route limitations: One engine...

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Large transport category airplanes: Turbine... Limitations § 135.381 Large transport category airplanes: Turbine engine powered: En route limitations: One engine inoperative. (a) No person operating a turbine engine powered large transport category airplane...

  16. 14 CFR 135.381 - Large transport category airplanes: Turbine engine powered: En route limitations: One engine...

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Large transport category airplanes: Turbine... Limitations § 135.381 Large transport category airplanes: Turbine engine powered: En route limitations: One engine inoperative. (a) No person operating a turbine engine powered large transport category airplane...

  17. 14 CFR 135.381 - Large transport category airplanes: Turbine engine powered: En route limitations: One engine...

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Large transport category airplanes: Turbine... Limitations § 135.381 Large transport category airplanes: Turbine engine powered: En route limitations: One engine inoperative. (a) No person operating a turbine engine powered large transport category airplane...

  18. 14 CFR 135.381 - Large transport category airplanes: Turbine engine powered: En route limitations: One engine...

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... Limitations § 135.381 Large transport category airplanes: Turbine engine powered: En route limitations: One engine inoperative. (a) No person operating a turbine engine powered large transport category airplane... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Large transport category airplanes: Turbine...

  19. 14 CFR 135.381 - Large transport category airplanes: Turbine engine powered: En route limitations: One engine...

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... Limitations § 135.381 Large transport category airplanes: Turbine engine powered: En route limitations: One engine inoperative. (a) No person operating a turbine engine powered large transport category airplane... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Large transport category airplanes: Turbine...

  20. Turbine Engine Flowpath Averaging Techniques

    DTIC Science & Technology

    1980-10-01

    u~%x AEDC- TMR- 8 I-G 1 • R. P TURBINE ENGINE FLOWPATH AVERAGING TECHNIQUES T. W. Skiles ARO, Inc. October 1980 Final Report for Period...COVERED 00-01-1980 to 00-10-1980 4. TITLE AND SUBTITLE Turbine Engine Flowpath Averaging Techniques 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c...property for gas turbine engines were investigated. The investigation consisted of a literature review and review of turbine engine current flowpath

  1. Turbine Engine Hot Section Technology, 1985

    NASA Technical Reports Server (NTRS)

    1985-01-01

    The Turbine Engine Section Technology (HOST) Project Office of the Lewis Research Center sponsored a workshop to discuss current research pertinent to turbine engine hot section durability problems. Presentations were made concerning hot section environment and the behavior of combustion liners, turbine blades, and turbine vanes.

  2. Effects of Pulsing on Film Cooling of Gas Turbine Airfoils

    DTIC Science & Technology

    2005-05-09

    turbine engine . 15. NUMBER OF PAGES 70 14. SUBJECT TERMS: Turbine blade ; Film cooling ; Pulsed jet 16. PRICE CODE 17...with additional research, ultimately allowing for an increased efficiency in a gas turbine engine . 2 Keywords Turbine blade Film cooling Pulsed jet ... engine for aircraft propulsion…………………. 11 Figure 2: Thermodynamic cycle of a general turbine engine . ………………………..…… 11

  3. Integrated Instrumentation and Sensor Systems Enabling Condition-Based Maintenance of Aerospace Equipment

    DTIC Science & Technology

    2012-01-01

    systems . For some specific sensor requirements in the domains considered here, for example, assessing system behavior and component state in gas turbine ...Cost Objectives. In general , the implication of the suitability and life cycle cost [LCC] driven objectives for integrated instrumentation/sensor system ...section should be considered. In general , the systems engineering approach provided clear benefits in defining user significant IISS system requirements and

  4. 14 CFR 135.383 - Large transport category airplanes: Turbine engine powered: En route limitations: Two engines...

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... Limitations § 135.383 Large transport category airplanes: Turbine engine powered: En route limitations: Two...). No person may operate a turbine engine powered large transport category airplane along an intended..., 1958, but before August 30, 1959 (SR422A). No person may operate a turbine engine powered large...

  5. 14 CFR 135.383 - Large transport category airplanes: Turbine engine powered: En route limitations: Two engines...

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... Limitations § 135.383 Large transport category airplanes: Turbine engine powered: En route limitations: Two...). No person may operate a turbine engine powered large transport category airplane along an intended..., 1958, but before August 30, 1959 (SR422A). No person may operate a turbine engine powered large...

  6. Turbine Engine Mathematical Model Validation

    DTIC Science & Technology

    1976-12-01

    AEDC-TR-76-90 ~Ec i ? Z985 TURBINE ENGINE MATHEMATICAL MODEL VALIDATION ENGINE TEST FACILITY ARNOLD ENGINEERING DEVELOPMENT CENTER AIR FORCE...i f n e c e s e a ~ ~ d i den t i f y by b l ock number) YJI01-GE-100 engine turbine engines mathematical models computations mathematical...report presents and discusses the results of an investigation to develop a rationale and technique for the validation of turbine engine steady-state

  7. Mathematical modeling and characteristic analysis for over-under turbine based combined cycle engine

    NASA Astrophysics Data System (ADS)

    Ma, Jingxue; Chang, Juntao; Ma, Jicheng; Bao, Wen; Yu, Daren

    2018-07-01

    The turbine based combined cycle engine has become the most promising hypersonic airbreathing propulsion system for its superiority of ground self-starting, wide flight envelop and reusability. The simulation model of the turbine based combined cycle engine plays an important role in the research of performance analysis and control system design. In this paper, a turbine based combined cycle engine mathematical model is built on the Simulink platform, including a dual-channel air intake system, a turbojet engine and a ramjet. It should be noted that the model of the air intake system is built based on computational fluid dynamics calculation, which provides valuable raw data for modeling of the turbine based combined cycle engine. The aerodynamic characteristics of turbine based combined cycle engine in turbojet mode, ramjet mode and mode transition process are studied by the mathematical model, and the influence of dominant variables on performance and safety of the turbine based combined cycle engine is analyzed. According to the stability requirement of thrust output and the safety in the working process of turbine based combined cycle engine, a control law is proposed that could guarantee the steady output of thrust by controlling the control variables of the turbine based combined cycle engine in the whole working process.

  8. 14 CFR 23.1111 - Turbine engine bleed air system.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false Turbine engine bleed air system. 23.1111 Section 23.1111 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION... Induction System § 23.1111 Turbine engine bleed air system. For turbine engine bleed air systems, the...

  9. 14 CFR 23.1111 - Turbine engine bleed air system.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 1 2013-01-01 2013-01-01 false Turbine engine bleed air system. 23.1111 Section 23.1111 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION... Induction System § 23.1111 Turbine engine bleed air system. For turbine engine bleed air systems, the...

  10. 14 CFR 23.1111 - Turbine engine bleed air system.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false Turbine engine bleed air system. 23.1111 Section 23.1111 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION... Induction System § 23.1111 Turbine engine bleed air system. For turbine engine bleed air systems, the...

  11. 14 CFR 135.387 - Large transport category airplanes: Turbine engine powered: Landing limitations: Alternate airports.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ....387 Large transport category airplanes: Turbine engine powered: Landing limitations: Alternate... alternate airport for a turbine engine powered large transport category airplane unless (based on the... operators may select an airport as an alternate airport for a turbine engine powered large transport...

  12. 40 CFR 1042.670 - Special provisions for gas turbine engines.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... AND VESSELS Special Compliance Provisions § 1042.670 Special provisions for gas turbine engines. The provisions of this section apply for gas turbine engines. (a) Implementation schedule. The requirements of this part do not apply for gas turbine engines below 600 kW before the 2014 model year. The...

  13. 14 CFR 121.195 - Airplanes: Turbine engine powered: Landing limitations: Destination airports.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplanes: Turbine engine powered: Landing... Performance Operating Limitations § 121.195 Airplanes: Turbine engine powered: Landing limitations: Destination airports. (a) No person operating a turbine engine powered airplane may take off that airplane at...

  14. 14 CFR 91.1037 - Large transport category airplanes: Turbine engine powered; Limitations; Destination and...

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ....1037 Large transport category airplanes: Turbine engine powered; Limitations; Destination and alternate airports. (a) No program manager or any other person may permit a turbine engine powered large transport... and terrain. (c) A program manager or other person flying a turbine engine powered large transport...

  15. 14 CFR 23.1111 - Turbine engine bleed air system.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false Turbine engine bleed air system. 23.1111 Section 23.1111 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION... Induction System § 23.1111 Turbine engine bleed air system. For turbine engine bleed air systems, the...

  16. 14 CFR 23.1111 - Turbine engine bleed air system.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Turbine engine bleed air system. 23.1111 Section 23.1111 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION... Induction System § 23.1111 Turbine engine bleed air system. For turbine engine bleed air systems, the...

  17. 14 CFR 121.195 - Airplanes: Turbine engine powered: Landing limitations: Destination airports.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Airplanes: Turbine engine powered: Landing... Performance Operating Limitations § 121.195 Airplanes: Turbine engine powered: Landing limitations: Destination airports. (a) No person operating a turbine engine powered airplane may take off that airplane at...

  18. 14 CFR 135.387 - Large transport category airplanes: Turbine engine powered: Landing limitations: Alternate airports.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ....387 Large transport category airplanes: Turbine engine powered: Landing limitations: Alternate... alternate airport for a turbine engine powered large transport category airplane unless (based on the... operators may select an airport as an alternate airport for a turbine engine powered large transport...

  19. 14 CFR 135.385 - Large transport category airplanes: Turbine engine powered: Landing limitations: Destination...

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ....385 Large transport category airplanes: Turbine engine powered: Landing limitations: Destination airports. (a) No person operating a turbine engine powered large transport category airplane may take off... this section, no person operating a turbine engine powered large transport category airplane may take...

  20. 14 CFR 91.1037 - Large transport category airplanes: Turbine engine powered; Limitations; Destination and...

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ....1037 Large transport category airplanes: Turbine engine powered; Limitations; Destination and alternate airports. (a) No program manager or any other person may permit a turbine engine powered large transport... and terrain. (c) A program manager or other person flying a turbine engine powered large transport...

  1. 40 CFR 1042.670 - Special provisions for gas turbine engines.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... AND VESSELS Special Compliance Provisions § 1042.670 Special provisions for gas turbine engines. The provisions of this section apply for gas turbine engines. (a) Implementation schedule. The requirements of this part do not apply for gas turbine engines below 600 kW before the 2014 model year. The...

  2. 14 CFR 135.385 - Large transport category airplanes: Turbine engine powered: Landing limitations: Destination...

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ....385 Large transport category airplanes: Turbine engine powered: Landing limitations: Destination airports. (a) No person operating a turbine engine powered large transport category airplane may take off... this section, no person operating a turbine engine powered large transport category airplane may take...

  3. New sensors and techniques for the structural health monitoring of propulsion systems.

    PubMed

    Woike, Mark; Abdul-Aziz, Ali; Oza, Nikunj; Matthews, Bryan

    2013-01-01

    The ability to monitor the structural health of the rotating components, especially in the hot sections of turbine engines, is of major interest to aero community in improving engine safety and reliability. The use of instrumentation for these applications remains very challenging. It requires sensors and techniques that are highly accurate, are able to operate in a high temperature environment, and can detect minute changes and hidden flaws before catastrophic events occur. The National Aeronautics and Space Administration (NASA), through the Aviation Safety Program (AVSP), has taken a lead role in the development of new sensor technologies and techniques for the in situ structural health monitoring of gas turbine engines. This paper presents a summary of key results and findings obtained from three different structural health monitoring approaches that have been investigated. This includes evaluating the performance of a novel microwave blade tip clearance sensor; a vibration based crack detection technique using an externally mounted capacitive blade tip clearance sensor; and lastly the results of using data driven anomaly detection algorithms for detecting cracks in a rotating disk.

  4. New Sensors and Techniques for the Structural Health Monitoring of Propulsion Systems

    PubMed Central

    2013-01-01

    The ability to monitor the structural health of the rotating components, especially in the hot sections of turbine engines, is of major interest to aero community in improving engine safety and reliability. The use of instrumentation for these applications remains very challenging. It requires sensors and techniques that are highly accurate, are able to operate in a high temperature environment, and can detect minute changes and hidden flaws before catastrophic events occur. The National Aeronautics and Space Administration (NASA), through the Aviation Safety Program (AVSP), has taken a lead role in the development of new sensor technologies and techniques for the in situ structural health monitoring of gas turbine engines. This paper presents a summary of key results and findings obtained from three different structural health monitoring approaches that have been investigated. This includes evaluating the performance of a novel microwave blade tip clearance sensor; a vibration based crack detection technique using an externally mounted capacitive blade tip clearance sensor; and lastly the results of using data driven anomaly detection algorithms for detecting cracks in a rotating disk. PMID:23935425

  5. Reduced Noise Gas Turbine Engine System and Supersonic Exhaust Nozzle System Using Elector to Entrain Ambient Air

    NASA Technical Reports Server (NTRS)

    Sokhey, Jagdish S. (Inventor); Pierluissi, Anthony F. (Inventor)

    2017-01-01

    One embodiment of the present invention is a unique gas turbine engine system. Another embodiment is a unique exhaust nozzle system for a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engine systems and exhaust nozzle systems for gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

  6. Durability Challenges for Next Generation of Gas Turbine Engine Materials

    NASA Technical Reports Server (NTRS)

    Misra, Ajay K.

    2012-01-01

    Aggressive fuel burn and carbon dioxide emission reduction goals for future gas turbine engines will require higher overall pressure ratio, and a significant increase in turbine inlet temperature. These goals can be achieved by increasing temperature capability of turbine engine hot section materials and decreasing weight of fan section of the engine. NASA is currently developing several advanced hot section materials for increasing temperature capability of future gas turbine engines. The materials of interest include ceramic matrix composites with 1482 - 1648 C temperature capability, advanced disk alloys with 815 C capability, and low conductivity thermal barrier coatings with erosion resistance. The presentation will provide an overview of durability challenges with emphasis on the environmental factors affecting durability for the next generation of gas turbine engine materials. The environmental factors include gaseous atmosphere in gas turbine engines, molten salt and glass deposits from airborne contaminants, impact from foreign object damage, and erosion from ingestion of small particles.

  7. 14 CFR 135.383 - Large transport category airplanes: Turbine engine powered: En route limitations: Two engines...

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Large transport category airplanes: Turbine... Limitations § 135.383 Large transport category airplanes: Turbine engine powered: En route limitations: Two...). No person may operate a turbine engine powered large transport category airplane along an intended...

  8. 14 CFR 135.383 - Large transport category airplanes: Turbine engine powered: En route limitations: Two engines...

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Large transport category airplanes: Turbine... Limitations § 135.383 Large transport category airplanes: Turbine engine powered: En route limitations: Two...). No person may operate a turbine engine powered large transport category airplane along an intended...

  9. 14 CFR 135.383 - Large transport category airplanes: Turbine engine powered: En route limitations: Two engines...

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Large transport category airplanes: Turbine... Limitations § 135.383 Large transport category airplanes: Turbine engine powered: En route limitations: Two...). No person may operate a turbine engine powered large transport category airplane along an intended...

  10. 14 CFR 125.377 - Fuel supply: Turbine-engine-powered airplanes other than turbopropeller.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... AIRCRAFT Flight Release Rules § 125.377 Fuel supply: Turbine-engine-powered airplanes other than... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Fuel supply: Turbine-engine-powered... or take off a turbine-engine powered airplane (other than a turbopropeller-powered airplane) unless...

  11. 14 CFR 121.333 - Supplemental oxygen for emergency descent and for first aid; turbine engine powered airplanes...

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... and for first aid; turbine engine powered airplanes with pressurized cabins. 121.333 Section 121.333... for emergency descent and for first aid; turbine engine powered airplanes with pressurized cabins. (a) General. When operating a turbine engine powered airplane with a pressurized cabin, the certificate holder...

  12. 14 CFR 121.189 - Airplanes: Turbine engine powered: Takeoff limitations.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Airplanes: Turbine engine powered: Takeoff... Limitations § 121.189 Airplanes: Turbine engine powered: Takeoff limitations. (a) No person operating a turbine engine powered airplane may take off that airplane at a weight greater than that listed in the...

  13. 14 CFR 23.1155 - Turbine engine reverse thrust and propeller pitch settings below the flight regime.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Turbine engine reverse thrust and propeller... COMMUTER CATEGORY AIRPLANES Powerplant Powerplant Controls and Accessories § 23.1155 Turbine engine reverse thrust and propeller pitch settings below the flight regime. For turbine engine installations, each...

  14. 14 CFR 121.197 - Airplanes: Turbine engine powered: Landing limitations: Alternate airports.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Airplanes: Turbine engine powered: Landing... Performance Operating Limitations § 121.197 Airplanes: Turbine engine powered: Landing limitations: Alternate... turbine engine powered airplane unless (based on the assumptions in § 121.195 (b)) that airplane at the...

  15. 14 CFR 125.377 - Fuel supply: Turbine-engine-powered airplanes other than turbopropeller.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... AIRCRAFT Flight Release Rules § 125.377 Fuel supply: Turbine-engine-powered airplanes other than... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Fuel supply: Turbine-engine-powered... or take off a turbine-engine powered airplane (other than a turbopropeller-powered airplane) unless...

  16. 14 CFR 23.1155 - Turbine engine reverse thrust and propeller pitch settings below the flight regime.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false Turbine engine reverse thrust and propeller... COMMUTER CATEGORY AIRPLANES Powerplant Powerplant Controls and Accessories § 23.1155 Turbine engine reverse thrust and propeller pitch settings below the flight regime. For turbine engine installations, each...

  17. 14 CFR 121.189 - Airplanes: Turbine engine powered: Takeoff limitations.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplanes: Turbine engine powered: Takeoff... Limitations § 121.189 Airplanes: Turbine engine powered: Takeoff limitations. (a) No person operating a turbine engine powered airplane may take off that airplane at a weight greater than that listed in the...

  18. 14 CFR 121.197 - Airplanes: Turbine engine powered: Landing limitations: Alternate airports.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplanes: Turbine engine powered: Landing... Performance Operating Limitations § 121.197 Airplanes: Turbine engine powered: Landing limitations: Alternate... turbine engine powered airplane unless (based on the assumptions in § 121.195 (b)) that airplane at the...

  19. 14 CFR 121.333 - Supplemental oxygen for emergency descent and for first aid; turbine engine powered airplanes...

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... and for first aid; turbine engine powered airplanes with pressurized cabins. 121.333 Section 121.333... for emergency descent and for first aid; turbine engine powered airplanes with pressurized cabins. (a) General. When operating a turbine engine powered airplane with a pressurized cabin, the certificate holder...

  20. 14 CFR 23.1155 - Turbine engine reverse thrust and propeller pitch settings below the flight regime.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false Turbine engine reverse thrust and propeller... COMMUTER CATEGORY AIRPLANES Powerplant Powerplant Controls and Accessories § 23.1155 Turbine engine reverse thrust and propeller pitch settings below the flight regime. For turbine engine installations, each...

  1. 14 CFR 23.1155 - Turbine engine reverse thrust and propeller pitch settings below the flight regime.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 1 2013-01-01 2013-01-01 false Turbine engine reverse thrust and propeller... COMMUTER CATEGORY AIRPLANES Powerplant Powerplant Controls and Accessories § 23.1155 Turbine engine reverse thrust and propeller pitch settings below the flight regime. For turbine engine installations, each...

  2. 14 CFR 23.1155 - Turbine engine reverse thrust and propeller pitch settings below the flight regime.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false Turbine engine reverse thrust and propeller... COMMUTER CATEGORY AIRPLANES Powerplant Powerplant Controls and Accessories § 23.1155 Turbine engine reverse thrust and propeller pitch settings below the flight regime. For turbine engine installations, each...

  3. More diesel generation could further fossil fuel economy

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Jeffs, E.

    1976-05-01

    Following the introduction last year of their Seahorse medium-speed diesel engine, the manufacturers, Hawthorn Leslie (Engineers) Ltd., of Newcastle upon Tyne, have made an extensive analysis of the resource effectiveness of diesel-driven generating sets. Though directed towards the raising of funds to construct a demonstration power plant in the UK, the analysis is relevant elsewhere. In addition, the firm has now developed an energy recovery package for use with the basic engine to further improve the overall thermal efficiency of the system. Looked at in a British context, the basis of Hawthorn Leslie's case is this. The importance of coalmore » in electicity generation is evidence of its value as a national resource. Now that North Sea oil has emerged as a national energy resource, it must be used to the greatest effect; this means building diesel power stations to take over the mid-load cycle of utility operations. The analysis compares five prime movers: gas turbines, diesel engines, and steam turbines powered by oil- or coal-fired boilers, or thermal reactors. Capital and fixed running costs are shown. The diesel engine is the most efficient prime mover for electricity generation. With this novel energy recovery principle, greater utilization of fuel energy can be realized if direct heating is not required. (MCW)« less

  4. Aircraft Engine Systems

    NASA Technical Reports Server (NTRS)

    Veres, Joseph P.

    2003-01-01

    The objective is to develop the capability to numerically model the performance of gas turbine engines used for aircraft propulsion. This capability will provide turbine engine designers with a means of accurately predicting the performance of new engines in a system environment prior to building and testing. The 'numerical test cell' developed under this project will reduce the number of component and engine tests required during development. As a result, the project will help to reduce the design cycle time and cost of gas turbine engines. This capability will be distributed to U.S. turbine engine manufacturers and air framers. This project focuses on goals of maintaining U.S. superiority in commercial gas turbine engine development for the aeronautics industry.

  5. Flow-driven rotor simulation of vertical axis tidal turbines: A comparison of helical and straight blades

    NASA Astrophysics Data System (ADS)

    Le, Tuyen Quang; Lee, Kwang-Soo; Park, Jin-Soon; Ko, Jin Hwan

    2014-06-01

    In this study, flow-driven rotor simulations with a given load are conducted to analyze the operational characteristics of a vertical-axis Darrieus turbine, specifically its self-starting capability and fluctuations in its torque as well as the RPM. These characteristics are typically observed in experiments, though they cannot be acquired in simulations with a given tip speed ratio (TSR). First, it is shown that a flow-driven rotor simulation with a two-dimensional (2D) turbine model obtains power coefficients with curves similar to those obtained in a simulation with a given TSR. 3D flowdriven rotor simulations with an optimal geometry then show that a helical-bladed turbine has the following prominent advantages over a straight-bladed turbine of the same size: an improvement of its self-starting capabilities and reduced fluctuations in its torque and RPM curves as well as an increase in its power coefficient from 33% to 42%. Therefore, it is clear that a flow-driven rotor simulation provides more information for the design of a Darrieus turbine than a simulation with a given TSR before experiments.

  6. 14 CFR 33.84 - Engine overtorque test.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... STANDARDS: AIRCRAFT ENGINES Block Tests; Turbine Aircraft Engines § 33.84 Engine overtorque test. (a) If approval of a maximum engine overtorque is sought for an engine incorporating a free power turbine... turbine entry gas temperature equal to the maximum steady state temperature approved for use during...

  7. 14 CFR 34.61 - Turbine fuel specifications.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... be present. Specification for Fuel To Be Used in Aircraft Turbine Engine Emission Testing Property... 34.61 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT... Engine Exhaust Gaseous Emissions (Aircraft and Aircraft Gas Turbine Engines) § 34.61 Turbine fuel...

  8. 14 CFR 34.61 - Turbine fuel specifications.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... Engine Exhaust Gaseous Emissions (Aircraft and Aircraft Gas Turbine Engines) § 34.61 Turbine fuel... be present. Specification for Fuel To Be Used in Aircraft Turbine Engine Emission Testing Property... 34.61 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT...

  9. 14 CFR 34.61 - Turbine fuel specifications.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... Engine Exhaust Gaseous Emissions (Aircraft and Aircraft Gas Turbine Engines) § 34.61 Turbine fuel... be present. Specification for Fuel To Be Used in Aircraft Turbine Engine Emission Testing Property... 34.61 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT...

  10. Advanced Gas Turbine (AGT) Technology Project

    NASA Technical Reports Server (NTRS)

    1984-01-01

    Technical work on the design and effort leading to the testing of a 74.5 kW (100 hp) automotive gas turbine engine is reviewed. Development of the engine compressor, gasifier turbine, power turbine, combustor, regenerator, and secondary system is discussed. Ceramic materials development and the application of such materials in the gas turbine engine components is described.

  11. 14 CFR 33.84 - Engine overtorque test.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... STANDARDS: AIRCRAFT ENGINES Block Tests; Turbine Aircraft Engines § 33.84 Engine overtorque test. (a) If approval of a maximum engine overtorque is sought for an engine incorporating a free power turbine... at least 21/2 minutes duration. (2) A power turbine rotational speed equal to the highest speed at...

  12. 14 CFR 33.84 - Engine overtorque test.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... STANDARDS: AIRCRAFT ENGINES Block Tests; Turbine Aircraft Engines § 33.84 Engine overtorque test. (a) If approval of a maximum engine overtorque is sought for an engine incorporating a free power turbine... at least 21/2 minutes duration. (2) A power turbine rotational speed equal to the highest speed at...

  13. 14 CFR 33.84 - Engine overtorque test.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... STANDARDS: AIRCRAFT ENGINES Block Tests; Turbine Aircraft Engines § 33.84 Engine overtorque test. (a) If approval of a maximum engine overtorque is sought for an engine incorporating a free power turbine... at least 21/2 minutes duration. (2) A power turbine rotational speed equal to the highest speed at...

  14. Measurement of Turbine Engine Transient Airflow in Ground Test Facilities

    DTIC Science & Technology

    1980-08-01

    REPORT NUMBER 12 GOVT ACCESSION NO. A E D C - T R - 8 0 - 2 1 L 6. T I T L E (aqd Subl l l |e ) MEASUREMENT OF TURBINE ENGINE TRANSIENT AIRFLOW IN...21 ILLUSTRATIONS Figure !. Direct-Connect Turbine Engine Test Cell Installation...26 3. Turbine Engine Transient Airflow Simulator (TETAS) . . . . . . . . . . . . . . . . . . . . . . . . . 27 4

  15. 14 CFR 121.645 - Fuel supply: Turbine-engine powered airplanes, other than turbo propeller: Flag and supplemental...

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... specifications, no person may release for flight or takeoff a turbine-engine powered airplane (other than a turbo... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Fuel supply: Turbine-engine powered... SUPPLEMENTAL OPERATIONS Dispatching and Flight Release Rules § 121.645 Fuel supply: Turbine-engine powered...

  16. 14 CFR 121.645 - Fuel supply: Turbine-engine powered airplanes, other than turbo propeller: Flag and supplemental...

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... specifications, no person may release for flight or takeoff a turbine-engine powered airplane (other than a turbo... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Fuel supply: Turbine-engine powered... SUPPLEMENTAL OPERATIONS Dispatching and Flight Release Rules § 121.645 Fuel supply: Turbine-engine powered...

  17. Feasibility Study for a Practical High Rotor Tip Clearance Turbine.

    DTIC Science & Technology

    GAS TURBINE BLADES ), (* TURBINE BLADES , TOLERANCES(MECHANICS)), (* TURBOFAN ENGINES , GAS TURBINES , AXIAL FLOW TURBINES , AXIAL FLOW TURBINE ROTORS...AERODYNAMIC CONFIGURATIONS, LEAKAGE(FLUID), MEASUREMENT, TEST METHODS, PERFORMANCE( ENGINEERING ), MATHEMATICAL PREDICTION, REDUCTION, PRESSURE, PREDICTIONS, NOZZLE GAS FLOW, COMBUSTION CHAMBER GASES, GAS FLOW.

  18. Need for Robust Sensors for Inherently Fail-Safe Gas Turbine Engine Controls, Monitoring, and Prognostics (Postprint)

    DTIC Science & Technology

    2006-09-01

    MONITORING , AND PROGNOSTICS Alireza R. Behbahani Controls / Engine Health Management Turbine Engine Division / PRTS U.S. Air Force Research...Technical Report 2005. 8. Greitzer, Frank et al, “Gas Turbine Engine Health Monitoring and Prognostics ”, International Society of Logistics (SOLE...AFRL-PR-WP-TP-2007-217 NEED FOR ROBUST SENSORS FOR INHERENTLY FAIL-SAFE GAS TURBINE ENGINE CONTROLS, MONITORING , AND PROGNOSTICS (POSTPRINT

  19. 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.

  20. Energy extraction from a semi-passive flapping-foil turbine with active heave and passive pitch

    NASA Astrophysics Data System (ADS)

    Boudreau, Matthieu; Dumas, Guy; Gunther, Kevin; CFD Laboratory LMFN Team

    2017-11-01

    Due to the inherent complexity of the mechanisms needed to prescribe the heaving and the pitching motions of optimal flapping-foil turbines, several research groups are now investigating the potential of using unconstrained passive motions. The amplitude, the phase and the frequency of such free motions are thus the result of the interaction of the blade with the flow and its elastic supports, namely springs and dampers. In parallel with our current study on fully-passive flapping-foil turbines, we investigate in this work the possibility of using a semi-passive turbine. Unlike previous semi-passive turbines studied in the literature, we propose a turbine with a passive pitching motion and an active heaving motion constrained to be a sine wave with desired amplitude and frequency. As most of the energy extracted by flapping-foil turbines comes from the heaving motion, it is natural to connect an electric generator to this degree of freedom, thereby allowing one to constrain this motion. It is found that large-amplitude pitching motions leading to a considerable energy extraction can arise under different circumstances and mechanisms, either forced by the heaving motion or driven by an instability of the pitching motion itself. The authors gratefully acknowledge the support from the Natural Sciences and Engineering Research Council of Canada (NSERC), the Tyler Lewis Clean Energy Research Foundation, Calcul Québec and Compute Canada.

  1. Eutectic Composite Turbine Blade Development

    DTIC Science & Technology

    1976-11-01

    turbine blades for aircraft engines . An MC carbide fiber reinforced eutectic alloy, NiTaC-13...composites in turbine blades for aircraft engines . An MC carbide fiber reinforced eutectic alloy, NiTaC-13 and the low pressure turbine blade of the...identified that appeared to have potential for application to aircraft engine turbine blade hardware. The potential benefits offered by these materials

  2. 14 CFR 23.1521 - Powerplant limitations.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... reciprocating engines); (3) The maximum allowable gas temperature (for turbine engines); (4) The time limit for... maximum allowable gas temperature (for turbine engines); and (4) The maximum allowable cylinder head, oil... reciprocating engines), or fuel designation (for turbine engines), must be established so that it is not less...

  3. 14 CFR 23.1521 - Powerplant limitations.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... reciprocating engines); (3) The maximum allowable gas temperature (for turbine engines); (4) The time limit for... maximum allowable gas temperature (for turbine engines); and (4) The maximum allowable cylinder head, oil... reciprocating engines), or fuel designation (for turbine engines), must be established so that it is not less...

  4. 14 CFR 23.1521 - Powerplant limitations.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... reciprocating engines); (3) The maximum allowable gas temperature (for turbine engines); (4) The time limit for... maximum allowable gas temperature (for turbine engines); and (4) The maximum allowable cylinder head, oil... reciprocating engines), or fuel designation (for turbine engines), must be established so that it is not less...

  5. 14 CFR 23.1521 - Powerplant limitations.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... reciprocating engines); (3) The maximum allowable gas temperature (for turbine engines); (4) The time limit for... maximum allowable gas temperature (for turbine engines); and (4) The maximum allowable cylinder head, oil... reciprocating engines), or fuel designation (for turbine engines), must be established so that it is not less...

  6. 14 CFR 23.1521 - Powerplant limitations.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... reciprocating engines); (3) The maximum allowable gas temperature (for turbine engines); (4) The time limit for... maximum allowable gas temperature (for turbine engines); and (4) The maximum allowable cylinder head, oil... reciprocating engines), or fuel designation (for turbine engines), must be established so that it is not less...

  7. 40 CFR 87.61 - Turbine fuel specifications.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... (CONTINUED) CONTROL OF AIR POLLUTION FROM AIRCRAFT AND AIRCRAFT ENGINES Test Procedures for Engine Exhaust Gaseous Emissions (Aircraft and Aircraft Gas Turbine Engines) § 87.61 Turbine fuel specifications. For... 40 Protection of Environment 20 2011-07-01 2011-07-01 false Turbine fuel specifications. 87.61...

  8. 40 CFR 87.61 - Turbine fuel specifications.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... (CONTINUED) CONTROL OF AIR POLLUTION FROM AIRCRAFT AND AIRCRAFT ENGINES Test Procedures for Engine Exhaust Gaseous Emissions (Aircraft and Aircraft Gas Turbine Engines) § 87.61 Turbine fuel specifications. For... 40 Protection of Environment 20 2010-07-01 2010-07-01 false Turbine fuel specifications. 87.61...

  9. Thin-film sensors for reusable space propulsion systems

    NASA Technical Reports Server (NTRS)

    Hepp, Aloysius F.; Kim, Walter S.

    1989-01-01

    Thin-film thermocouples (TFTCs) were developed for aircraft gas turbine engines and are in use for temperature measurement on turbine blades up to 1800 F. Established aircraft engine gas turbine technology is currently being adapted to turbine engine blade materials and the environment encountered in the Space Shuttle Main Engine (SSME)-severe thermal shock from cryogenic fuel to combustion temperatures. Initial results with coupons of MAR M-246 (+Hf) and PWA 1480 were followed by fabrication of TFTC on SSME turbine blades. Current efforts are focused on preparation for testing in the Turbine Blade Tester at NASA Marshall Space Flight Center.

  10. 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 efficiency. However negative angle of attack decreases when inlet swirl is anti-clockwise and efficiency of low pressure turbine can be increased by 3% compared to inlet condition of clockwise swirl. Consequently flow simulation and analysis are able to aid in figuring out interaction mechanism of turbine system and optimizing turbine system design.

  11. 78 FR 63015 - Exhaust Emissions Standards for New Aircraft Gas Turbine Engines and Identification Plate for...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-23

    ... Turbine Engines and Identification Plate for Aircraft Engines AGENCY: Federal Aviation Administration (FAA... regulatory requirements for aircraft turbofan or turbojet engines with rated thrusts greater than 26.7... standards for certain turbine engine powered airplanes to incorporate the standards promulgated by the...

  12. 77 FR 76842 - Exhaust Emissions Standards for New Aircraft Gas Turbine Engines and Identification Plate for...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-12-31

    ... Aircraft Gas Turbine Engines and Identification Plate for Aircraft Engines AGENCY: Federal Aviation... , compliance flexibilities, and other regulatory requirements for aircraft turbofan or turbojet engines with...)(v). 6. Standards for Supersonic Aircraft Turbine Engines This final rule contains carbon monoxide...

  13. Advanced Turbine Technology Applications Project (ATTAP)

    NASA Technical Reports Server (NTRS)

    1990-01-01

    Advanced Turbine Technology Application Project (ATTAP) activities during the past year were highlighted by test-bed engine design and development activities; ceramic component design; materials and component characterization; ceramic component process development and fabrication; component rig testing; and test-bed engine fabrication and testing. Although substantial technical challenges remain, all areas exhibited progress. Test-bed engine design and development activity included engine mechanical design, power turbine flow-path design and mechanical layout, and engine system integration aimed at upgrading the AGT-5 from a 1038 C metal engine to a durable 1371 C structural ceramic component test-bed engine. ATTAP-defined ceramic and associated ceramic/metal component design activities include: the ceramic combustor body, the ceramic gasifier turbine static structure, the ceramic gasifier turbine rotor, the ceramic/metal power turbine static structure, and the ceramic power turbine rotors. The materials and component characterization efforts included the testing and evaluation of several candidate ceramic materials and components being developed for use in the ATTAP. Ceramic component process development and fabrication activities are being conducted for the gasifier turbine rotor, gasifier turbine vanes, gasifier turbine scroll, extruded regenerator disks, and thermal insulation. Component rig testing activities include the development of the necessary test procedures and conduction of rig testing of the ceramic components and assemblies. Four-hundred hours of hot gasifier rig test time were accumulated with turbine inlet temperatures exceeding 1204 C at 100 percent design gasifier speed. A total of 348.6 test hours were achieved on a single ceramic rotor without failure and a second ceramic rotor was retired in engine-ready condition at 364.9 test hours. Test-bed engine fabrication, testing, and development supported improvements in ceramic component technology that will permit the achievement of program performance and durability goals. The designated durability engine accumulated 359.3 hour of test time, 226.9 of which were on the General Motors gas turbine durability schedule.

  14. 14 CFR 135.387 - Large transport category airplanes: Turbine engine powered: Landing limitations: Alternate airports.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Large transport category airplanes: Turbine....387 Large transport category airplanes: Turbine engine powered: Landing limitations: Alternate... alternate airport for a turbine engine powered large transport category airplane unless (based on the...

  15. 14 CFR 135.385 - Large transport category airplanes: Turbine engine powered: Landing limitations: Destination...

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Large transport category airplanes: Turbine....385 Large transport category airplanes: Turbine engine powered: Landing limitations: Destination airports. (a) No person operating a turbine engine powered large transport category airplane may take off...

  16. 14 CFR 135.385 - Large transport category airplanes: Turbine engine powered: Landing limitations: Destination...

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Large transport category airplanes: Turbine....385 Large transport category airplanes: Turbine engine powered: Landing limitations: Destination airports. (a) No person operating a turbine engine powered large transport category airplane may take off...

  17. 14 CFR 135.387 - Large transport category airplanes: Turbine engine powered: Landing limitations: Alternate airports.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Large transport category airplanes: Turbine....387 Large transport category airplanes: Turbine engine powered: Landing limitations: Alternate... alternate airport for a turbine engine powered large transport category airplane unless (based on the...

  18. 14 CFR 135.387 - Large transport category airplanes: Turbine engine powered: Landing limitations: Alternate airports.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Large transport category airplanes: Turbine....387 Large transport category airplanes: Turbine engine powered: Landing limitations: Alternate... alternate airport for a turbine engine powered large transport category airplane unless (based on the...

  19. 14 CFR 135.385 - Large transport category airplanes: Turbine engine powered: Landing limitations: Destination...

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Large transport category airplanes: Turbine....385 Large transport category airplanes: Turbine engine powered: Landing limitations: Destination airports. (a) No person operating a turbine engine powered large transport category airplane may take off...

  20. 14 CFR 135.379 - Large transport category airplanes: Turbine engine powered: Takeoff limitations.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Large transport category airplanes: Turbine... PERSONS ON BOARD SUCH AIRCRAFT Airplane Performance Operating Limitations § 135.379 Large transport category airplanes: Turbine engine powered: Takeoff limitations. (a) No person operating a turbine engine...

  1. 14 CFR 135.379 - Large transport category airplanes: Turbine engine powered: Takeoff limitations.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Large transport category airplanes: Turbine... PERSONS ON BOARD SUCH AIRCRAFT Airplane Performance Operating Limitations § 135.379 Large transport category airplanes: Turbine engine powered: Takeoff limitations. (a) No person operating a turbine engine...

  2. 14 CFR 135.379 - Large transport category airplanes: Turbine engine powered: Takeoff limitations.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Large transport category airplanes: Turbine... PERSONS ON BOARD SUCH AIRCRAFT Airplane Performance Operating Limitations § 135.379 Large transport category airplanes: Turbine engine powered: Takeoff limitations. (a) No person operating a turbine engine...

  3. Exergy as a useful tool for the performance assessment of aircraft gas turbine engines: A key review

    NASA Astrophysics Data System (ADS)

    Şöhret, Yasin; Ekici, Selcuk; Altuntaş, Önder; Hepbasli, Arif; Karakoç, T. Hikmet

    2016-05-01

    It is known that aircraft gas turbine engines operate according to thermodynamic principles. Exergy is considered a very useful tool for assessing machines working on the basis of thermodynamics. In the current study, exergy-based assessment methodologies are initially explained in detail. A literature overview is then presented. According to the literature overview, turbofans may be described as the most investigated type of aircraft gas turbine engines. The combustion chamber is found to be the most irreversible component, and the gas turbine component needs less exergetic improvement compared to all other components of an aircraft gas turbine engine. Finally, the need for analyses of exergy, exergo-economic, exergo-environmental and exergo-sustainability for aircraft gas turbine engines is emphasized. A lack of agreement on exergy analysis paradigms and assumptions is noted by the authors. Exergy analyses of aircraft gas turbine engines, fed with conventional fuel as well as alternative fuel using advanced exergy analysis methodology to understand the interaction among components, are suggested to those interested in thermal engineering, aerospace engineering and environmental sciences.

  4. Staged combustion with piston engine and turbine engine supercharger

    DOEpatents

    Fischer, Larry E [Los Gatos, CA; Anderson, Brian L [Lodi, CA; O'Brien, Kevin C [San Ramon, CA

    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.

  5. Staged combustion with piston engine and turbine engine supercharger

    DOEpatents

    Fischer, Larry E [Los Gatos, CA; Anderson, Brian L [Lodi, CA; O'Brien, Kevin C [San Ramon, CA

    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.

  6. Generalization of turbojet and turbine-propeller engine performance in windmilling condition

    NASA Technical Reports Server (NTRS)

    Wallner, Ewis E; Welna, Henry J

    1951-01-01

    Windmilling characteristics of several turbojet and turbine-propeller engines were investigated individually over a wide range of flight conditions in the NACA Lewis altitude wind tunnel. A study was made of all these data and windmilling performance of gas turbine engines was generalized. Although internal-drag, air-flow, and total-pressure-drop parameters were generalized to a single curve for both the axial-flow type engines and another for the centrifugal-flow engine. The engine speed, component pressure changes, and windmilling-propeller drag were generalized to single curves for the two turbine-propeller-type engines investigated. By the use of these curves the windmilling performance can be estimated for axial-flow type gas turbine engines similar to the types investigated over a wide range of flight conditions.

  7. 76 FR 19903 - Special Conditions: Diamond Aircraft Industry Model DA-40NG; Diesel Cycle Engine

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-11

    ... DA-40NG the Austro Engine GmbH model E4 aircraft diesel engine (ADE) using turbine (jet) fuel. This... engine utilizing turbine (jet) fuel. The applicable airworthiness regulations do not contain adequate or...: Installation of the Austro Engine GmbH Model E4 ADE diesel engine utilizing turbine (jet) fuel. Discussion...

  8. Turbofan Engine Technology Evaluation System, User’s Guide.

    DTIC Science & Technology

    1984-04-01

    MOL I GROUP I SUL O. Gas Turbine Engine Parametric Computer Program 2105 2101 2103I Simulation Design & off design Turbofan Engine LComputer...show the high pressure turbine and the two cooling air ducts highlighted in the engine drawing. H$ANGE UALUE (S) HIGH PRESSURE TURBINE COOLING VANE ...ducted off to be used for high and low pressure vane and rotor cooling in the turbines before it enters the burner section of the engine at station 31

  9. 14 CFR 34.60 - Introduction.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES Test Procedures for Engine Exhaust Gaseous Emissions (Aircraft and Aircraft Gas Turbine Engines) § 34.60 Introduction. (a) Except as provided... determine the conformity of new aircraft gas turbine engines with the applicable standards set forth in this...

  10. Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors

    NASA Technical Reports Server (NTRS)

    Seda, Jorge F. (Inventor); Dunbar, Lawrence W. (Inventor); Gliebe, Philip R. (Inventor); Szucs, Peter N. (Inventor); Brauer, John C. (Inventor); Johnson, James E. (Inventor); Moniz, Thomas (Inventor); Steinmetz, Gregory T. (Inventor)

    2003-01-01

    An aircraft gas turbine engine assembly includes an inter-turbine frame axially located between high and low pressure turbines. Low pressure turbine has counter rotating low pressure inner and outer rotors with low pressure inner and outer shafts which are at least in part rotatably disposed co-axially within a high pressure rotor. Inter-turbine frame includes radially spaced apart radially outer first and inner second structural rings disposed co-axially about a centerline and connected by a plurality of circumferentially spaced apart struts. Forward and aft sump members having forward and aft central bores are fixedly joined to axially spaced apart forward and aft portions of the inter-turbine frame. Low pressure inner and outer rotors are rotatably supported by a second turbine frame bearing mounted in aft central bore of aft sump member. A mount for connecting the engine to an aircraft is located on first structural ring.

  11. A review of turbine blade tip heat transfer.

    PubMed

    Bunker, R S

    2001-05-01

    This paper presents a review of the publicly available knowledge base concerning turbine blade tip heat transfer, from the early fundamental research which laid the foundations of our knowledge, to current experimental and numerical studies utilizing engine-scaled blade cascades and turbine rigs. Focus is placed on high-pressure, high-temperature axial-turbine blade tips, which are prevalent in the majority of today's aircraft engines and power generating turbines. The state of our current understanding of turbine blade tip heat transfer is in the transitional phase between fundamentals supported by engine-based experience, and the ability to a priori correctly predict and efficiently design blade tips for engine service.

  12. 14 CFR 121.193 - Airplanes: Turbine engine powered: En route limitations: Two engines inoperative.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplanes: Turbine engine powered: En route limitations: Two engines inoperative. 121.193 Section 121.193 Aeronautics and Space FEDERAL AVIATION... Performance Operating Limitations § 121.193 Airplanes: Turbine engine powered: En route limitations: Two...

  13. 14 CFR 121.191 - Airplanes: Turbine engine powered: En route limitations: One engine inoperative.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Airplanes: Turbine engine powered: En route limitations: One engine inoperative. 121.191 Section 121.191 Aeronautics and Space FEDERAL AVIATION... Performance Operating Limitations § 121.191 Airplanes: Turbine engine powered: En route limitations: One...

  14. 14 CFR 121.191 - Airplanes: Turbine engine powered: En route limitations: One engine inoperative.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplanes: Turbine engine powered: En route limitations: One engine inoperative. 121.191 Section 121.191 Aeronautics and Space FEDERAL AVIATION... Performance Operating Limitations § 121.191 Airplanes: Turbine engine powered: En route limitations: One...

  15. 14 CFR 121.193 - Airplanes: Turbine engine powered: En route limitations: Two engines inoperative.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Airplanes: Turbine engine powered: En route limitations: Two engines inoperative. 121.193 Section 121.193 Aeronautics and Space FEDERAL AVIATION... Performance Operating Limitations § 121.193 Airplanes: Turbine engine powered: En route limitations: Two...

  16. 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.

  17. 14 CFR 91.1037 - Large transport category airplanes: Turbine engine powered; Limitations; Destination and...

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Large transport category airplanes: Turbine....1037 Large transport category airplanes: Turbine engine powered; Limitations; Destination and alternate airports. (a) No program manager or any other person may permit a turbine engine powered large transport...

  18. 14 CFR 91.1037 - Large transport category airplanes: Turbine engine powered; Limitations; Destination and...

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Large transport category airplanes: Turbine....1037 Large transport category airplanes: Turbine engine powered; Limitations; Destination and alternate airports. (a) No program manager or any other person may permit a turbine engine powered large transport...

  19. 14 CFR 91.1037 - Large transport category airplanes: Turbine engine powered; Limitations; Destination and...

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Large transport category airplanes: Turbine....1037 Large transport category airplanes: Turbine engine powered; Limitations; Destination and alternate airports. (a) No program manager or any other person may permit a turbine engine powered large transport...

  20. 14 CFR 33.88 - Engine overtemperature test.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... AIRWORTHINESS STANDARDS: AIRCRAFT ENGINES Block Tests; Turbine Aircraft Engines § 33.88 Engine overtemperature... this run, the turbine assembly must be within serviceable limits. (b) In addition to the test... this run, the turbine assembly may exhibit distress beyond the limits for an overtemperature condition...

  1. 14 CFR 33.88 - Engine overtemperature test.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... AIRWORTHINESS STANDARDS: AIRCRAFT ENGINES Block Tests; Turbine Aircraft Engines § 33.88 Engine overtemperature... this run, the turbine assembly must be within serviceable limits. (b) In addition to the test... this run, the turbine assembly may exhibit distress beyond the limits for an overtemperature condition...

  2. 14 CFR 33.88 - Engine overtemperature test.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... AIRWORTHINESS STANDARDS: AIRCRAFT ENGINES Block Tests; Turbine Aircraft Engines § 33.88 Engine overtemperature... this run, the turbine assembly must be within serviceable limits. (b) In addition to the test... this run, the turbine assembly may exhibit distress beyond the limits for an overtemperature condition...

  3. Teaching Risk Analysis in an Aircraft Gas Turbine Engine Design Capstone Course

    DTIC Science & Technology

    2016-01-01

    American Institute of Aeronautics and Astronautics 1 Teaching Risk Analysis in an Aircraft Gas Turbine Engine Design Capstone Course...development costs, engine production costs, and scheduling (Byerley A. R., 2013) as well as the linkage between turbine inlet temperature, blade cooling...analysis SE majors have studied and how this is linked to the specific issues they must face in aircraft gas turbine engine design. Aeronautical and

  4. Sensing Challenges for Controls and PHM in the Hostile Operating Conditions of Modern Turbine Engine (Postprint)

    DTIC Science & Technology

    2008-07-01

    SUBJECT TERMS Gas turbine, sensors, Hostile Operating Conditions, FADEC , High Temperature Regimes for Sensors, Sensor Needs, Turbine Engine...Authority Digital Engine Control ( FADEC ). The frequency and bandwidth capability of sensors for engine control are drastically different for each sensor...metering valve assembly is responsive to electrical signals generated by the FADEC in response to sensors that measure turbine speed, pressure

  5. Test Rig for Active Turbine Blade Tip Clearance Control Concepts: An Update

    NASA Technical Reports Server (NTRS)

    Taylor, Shawn; Steinetz, Bruce; Oswald, Jay; DeCastro, Jonathan; Melcher, Kevin

    2006-01-01

    The objective is to develop and demonstrate a fast-acting active clearance control system to improve turbine engine performance, reduce emissions, and increase service life. System studies have shown the benefits of reducing blade tip clearances in modern turbine engines. Minimizing blade tip clearances throughout the engine will contribute materially to meeting NASA's Ultra-Efficient Engine Technology (UEET) turbine engine project goals. NASA GRC is examining two candidate approaches including rub-avoidance and regeneration which are explained in subsequent slides.

  6. Integrated Turbine Tip Clearance and Gas Turbine Engine Simulation

    NASA Technical Reports Server (NTRS)

    Chapman, Jeffryes W.; Kratz, Jonathan; Guo, Ten-Huei; Litt, Jonathan

    2016-01-01

    Gas turbine compressor and turbine blade tip clearance (i.e., the radial distance between the blade tip of an axial compressor or turbine and the containment structure) is a major contributing factor to gas path sealing, and can significantly affect engine efficiency and operational temperature. This paper details the creation of a generic but realistic high pressure turbine tip clearance model that may be used to facilitate active tip clearance control system research. This model uses a first principles approach to approximate thermal and mechanical deformations of the turbine system, taking into account the rotor, shroud, and blade tip components. Validation of the tip clearance model shows that the results are realistic and reflect values found in literature. In addition, this model has been integrated with a gas turbine engine simulation, creating a platform to explore engine performance as tip clearance is adjusted. Results from the integrated model explore the effects of tip clearance on engine operation and highlight advantages of tip clearance management.

  7. 14 CFR 34.80 - Introduction.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES Test Procedures for Engine Smoke Emissions (Aircraft Gas Turbine Engines) § 34.80 Introduction. Except as provided under § 34.5, the... of new and in-use gas turbine engines with the applicable standards set forth in this part. The test...

  8. 14 CFR 121.329 - Supplemental oxygen for sustenance: Turbine engine powered airplanes.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... engine powered airplanes. 121.329 Section 121.329 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Equipment Requirements § 121.329 Supplemental oxygen for sustenance: Turbine engine powered airplanes. (a) General. When operating a turbine engine powered airplane, each certificate holder shall equip the...

  9. 14 CFR 121.329 - Supplemental oxygen for sustenance: Turbine engine powered airplanes.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... engine powered airplanes. 121.329 Section 121.329 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Equipment Requirements § 121.329 Supplemental oxygen for sustenance: Turbine engine powered airplanes. (a) General. When operating a turbine engine powered airplane, each certificate holder shall equip the...

  10. Helical piles: an innovative foundation design option for offshore wind turbines.

    PubMed

    Byrne, B W; Houlsby, G T

    2015-02-28

    Offshore wind turbines play a key part in the renewable energy strategy in the UK and Europe as well as in other parts of the world (for example, China). The majority of current developments, certainly in UK waters, have taken place in relatively shallow water and close to shore. This limits the scale of the engineering to relatively simple structures, such as those using monopile foundations, and these have been the most common design to date, in UK waters. However, as larger turbines are designed, or they are placed in deeper water, it will be necessary to use multi-footing structures such as tripods or jackets. For these designs, the tension on the upwind footing becomes the critical design condition. Driven pile foundations could be used, as could suction-installed foundations. However, in this paper, we present another concept-the use of helical pile foundations. These foundations are routinely applied onshore where large tension capacities are required. However, for use offshore, a significant upscaling of the technology will be needed, particularly of the equipment required for installation of the piles. A clear understanding of the relevant geotechnical engineering will be needed if this upscaling is to be successful. © 2015 The Author(s) Published by the Royal Society. All rights reserved.

  11. Perspective on thermal barrier coatings for industrial gas turbine applications

    NASA Technical Reports Server (NTRS)

    Mutasim, Z. Z.; Hsu, L. L.; Brentnall, W. D.

    1995-01-01

    Thermal Barrier Coatings (TBC's) have been used in high thrust aircraft engines for many years, and have proved to be very effective in allowing higher turbine inlet temperatures. TBC life requirements for aircraft engines are typically less than those required in industrial gas turbines. The use of TBC's for industrial gas turbines can increase if durability and longer service life can be successfully demonstrated. This paper will describe current and future applications of TBC's in industrial gas turbine engines. Early testing and applications of TBC's will also be reviewed. This paper focuses on the key factors that are expected to influence utilization of TBC's in advanced industrial gas turbine engines. It is anticipated that reliable, durable and high effective coating systems will be produced that will ultimately improve engine efficiency and performance.

  12. Aeronautical Engineering. A Continuing Bibliography with Indexes

    DTIC Science & Technology

    1987-09-01

    engines 482 01 AERONAUTICS (GENERAL) i-10 aircraft equipped with turbine engine ...rate adaptive control with applications to lateral Statistics on aircraft gas turbine engine rotor failures Unified model for the calculation of blade ...PUMPS p 527 A87-35669 to test data for a composite prop-tan model Gas turbine combustor and engine augmentor tube GENERAL AVIATION AIRCRAFT

  13. NACA Conference on Turbojet Engines for Supersonic Propulsion. A Compilation of Technical Material Presented

    DTIC Science & Technology

    1953-10-01

    turbojet Pngine with a turbine cooled by compressor air involves several design pruilems that do not e~ist in an uncooled turbo - jet engine . Careful...facilitate testing the sheet-metal blades in the turbojet engine , bases were formed by removing the solid airfoil portion from the standard turbine blade ...OF TURBINE BLADES by J. C. Freche 6. APPLICATION AND OPERATION OF AIR-COOLED TURBINES IN TURBOJET ENGINES

  14. An Extended Combustion Model for the Aircraft Turbojet Engine

    NASA Astrophysics Data System (ADS)

    Rotaru, Constantin; Andres-Mihăilă, Mihai; Matei, Pericle Gabriel

    2014-08-01

    The paper consists in modelling and simulation of the combustion in a turbojet engine in order to find optimal characteristics of the burning process and the optimal shape of combustion chambers. The main focus of this paper is to find a new configuration of the aircraft engine combustion chambers, namely an engine with two main combustion chambers, one on the same position like in classical configuration, between compressor and turbine and the other, placed behind the turbine but not performing the role of the afterburning. This constructive solution could allow a lower engine rotational speed, a lower temperature in front of the first stage of the turbine and the possibility to increase the turbine pressure ratio by extracting the flow stream after turbine in the inner nozzle. Also, a higher thermodynamic cycle efficiency and thrust in comparison to traditional constant-pressure combustion gas turbine engines could be obtained.

  15. 14 CFR 34.10 - Applicability.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES Engine Fuel Venting Emissions (New and In-Use Aircraft Gas Turbine Engines) § 34.10 Applicability. (a) The provisions of this subpart are applicable to all new aircraft gas turbine engines of classes T3, T8, TSS, and TF equal to or greater than 36...

  16. 14 CFR 34.10 - Applicability.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES Engine Fuel Venting Emissions (New and In-Use Aircraft Gas Turbine Engines) § 34.10 Applicability. (a) The provisions of this subpart are applicable to all new aircraft gas turbine engines of classes T3, T8, TSS, and TF equal to or greater than 36...

  17. 14 CFR 34.10 - Applicability.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES Engine Fuel Venting Emissions (New and In-Use Aircraft Gas Turbine Engines) § 34.10 Applicability. (a) The provisions of this subpart are applicable to all new aircraft gas turbine engines of classes T3, T8, TSS, and TF equal to or greater than 36...

  18. 14 CFR 121.191 - Airplanes: Turbine engine powered: En route limitations: One engine inoperative.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Airplanes: Turbine engine powered: En route...: CERTIFICATION AND OPERATIONS OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Airplane Performance Operating Limitations § 121.191 Airplanes: Turbine engine powered: En route limitations: One...

  19. 14 CFR 121.193 - Airplanes: Turbine engine powered: En route limitations: Two engines inoperative.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Airplanes: Turbine engine powered: En route...: CERTIFICATION AND OPERATIONS OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Airplane Performance Operating Limitations § 121.193 Airplanes: Turbine engine powered: En route limitations: Two...

  20. 14 CFR 121.193 - Airplanes: Turbine engine powered: En route limitations: Two engines inoperative.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Airplanes: Turbine engine powered: En route...: CERTIFICATION AND OPERATIONS OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Airplane Performance Operating Limitations § 121.193 Airplanes: Turbine engine powered: En route limitations: Two...

  1. 14 CFR 121.191 - Airplanes: Turbine engine powered: En route limitations: One engine inoperative.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Airplanes: Turbine engine powered: En route...: CERTIFICATION AND OPERATIONS OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Airplane Performance Operating Limitations § 121.191 Airplanes: Turbine engine powered: En route limitations: One...

  2. 14 CFR 121.193 - Airplanes: Turbine engine powered: En route limitations: Two engines inoperative.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Airplanes: Turbine engine powered: En route...: CERTIFICATION AND OPERATIONS OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Airplane Performance Operating Limitations § 121.193 Airplanes: Turbine engine powered: En route limitations: Two...

  3. 14 CFR 121.191 - Airplanes: Turbine engine powered: En route limitations: One engine inoperative.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Airplanes: Turbine engine powered: En route...: CERTIFICATION AND OPERATIONS OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Airplane Performance Operating Limitations § 121.191 Airplanes: Turbine engine powered: En route limitations: One...

  4. 78 FR 63017 - Exhaust Emissions Standards for New Aircraft Gas Turbine Engines and Identification Plate for...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-23

    ... Aircraft Gas Turbine Engines and Identification Plate for Aircraft Engines AGENCY: Federal Aviation... (NO X ), compliance flexibilities, and other regulatory requirements for aircraft turbofan or turbojet... adopting the gas turbine engine test procedures of the International Civil Aviation Organization (ICAO...

  5. Feasibility of water injection into the turbine coolant to permit gas turbine contingency power for helicopter application

    NASA Technical Reports Server (NTRS)

    Vanfossen, G. J.

    1983-01-01

    A system which would allow a substantially increased output from a turboshaft engine for brief periods in emergency situations with little or no loss of turbine stress rupture life is proposed and studied analytically. The increased engine output is obtained by overtemperaturing the turbine; however, the temperature of the compressor bleed air used for hot section cooling is lowered by injecting and evaporating water. This decrease in cooling air temperature can offset the effect of increased gas temperature and increased shaft speed and thus keep turbine blade stress rupture life constant. The analysis utilized the NASA-Navy-Engine-Program or NNEP computer code to model the turboshaft engine in both design and off-design modes. This report is concerned with the effect of the proposed method of power augmentation on the engine cycle and turbine components. A simple cycle turboshaft engine with a 16:1 pressure ratio and a 1533 K (2760 R) turbine inlet temperature operating at sea level static conditions was studied to determine the possible power increase and the effect on turbine stress rupture life that could be expected using the proposed emergency cooling scheme. The analysis showed a 54 percent increse in output power can be achieved with no loss in gas generator turbine stress rupture life. A 231 K (415 F) rise in turbine inlet temperature is required for this level of augmentation. The required water flow rate was found to be .0109 kg water per kg of engine air flow.

  6. Method for Making Measurements of the Post-Combustion Residence Time in a Gas Turbine Engine

    NASA Technical Reports Server (NTRS)

    Miles, Jeffrey H (Inventor)

    2015-01-01

    A system and method of measuring a residence time in a gas-turbine engine is provided, whereby the method includes placing pressure sensors at a combustor entrance and at a turbine exit of the gas-turbine engine and measuring a combustor pressure at the combustor entrance and a turbine exit pressure at the turbine exit. The method further includes computing cross-spectrum functions between a combustor pressure sensor signal from the measured combustor pressure and a turbine exit pressure sensor signal from the measured turbine exit pressure, applying a linear curve fit to the cross-spectrum functions, and computing a post-combustion residence time from the linear curve fit.

  7. Advanced Turbine Technology Applications Project (ATTAP)

    NASA Technical Reports Server (NTRS)

    1989-01-01

    ATTAP activities during the past year were highlighted by an extensive materials assessment, execution of a reference powertrain design, test-bed engine design and development, ceramic component design, materials and component characterization, ceramic component process development and fabrication, component rig design and fabrication, test-bed engine fabrication, and hot gasifier rig and engine testing. Materials assessment activities entailed engine environment evaluation of domestically supplied radial gasifier turbine rotors that were available at the conclusion of the Advanced Gas Turbine (AGT) Technology Development Project as well as an extensive survey of both domestic and foreign ceramic suppliers and Government laboratories performing ceramic materials research applicable to advanced heat engines. A reference powertrain design was executed to reflect the selection of the AGT-5 as the ceramic component test-bed engine for the ATTAP. Test-bed engine development activity focused on upgrading the AGT-5 from a 1038 C (1900 F) metal engine to a durable 1371 C (2500 F) structural ceramic component test-bed engine. Ceramic component design activities included the combustor, gasifier turbine static structure, and gasifier turbine rotor. The materials and component characterization efforts have included the testing and evaluation of several candidate ceramic materials and components being developed for use in the ATTAP. Ceramic component process development and fabrication activities were initiated for the gasifier turbine rotor, gasifier turbine vanes, gasifier turbine scroll, extruded regenerator disks, and thermal insulation. Component rig development activities included combustor, hot gasifier, and regenerator rigs. Test-bed engine fabrication activities consisted of the fabrication of an all-new AGT-5 durability test-bed engine and support of all engine test activities through instrumentation/build/repair. Hot gasifier rig and test-bed engine testing activities were performed.

  8. Cooling system for high speed aircraft

    NASA Technical Reports Server (NTRS)

    Lawing, P. L.; Pagel, L. L. (Inventor)

    1981-01-01

    The system eliminates the necessity of shielding an aircraft airframe constructed of material such as aluminum. Cooling is accomplished by passing a coolant through the aircraft airframe, the coolant acting as a carrier to remove heat from the airframe. The coolant is circulated through a heat pump and a heat exchanger which together extract essentially all of the added heat from the coolant. The heat is transferred to the aircraft fuel system via the heat exchanger and the heat pump. The heat extracted from the coolant is utilized to power the heat pump. The heat pump has associated therewith power turbine mechanism which is also driven by the extracted heat. The power turbines are utilized to drive various aircraft subsystems, the compressor of the heat pump, and provide engine cooling.

  9. Rub tolerance evaluation of two sintered NiCrAl gas path seal materials. [wear tests of gas turbine engine seals

    NASA Technical Reports Server (NTRS)

    Bill, R. C.

    1978-01-01

    Two strength level variations of sintered NiCrAl (about 40 percent dense), candidate high pressure turbine seal materials, were subject to rub tolerance testing against AM 355 steel blade tips. The high strength material (17 N/sq mm tensile strength) showed frictional and radial loads that were 20 to 50 percent higher than those measured for the low strength material (15.5 N/ sq mm tensile strength). Measured wear to the AM 355 blade tips was not significantly different for the two sintered NiCrAl seal materials. Wear of the sintered NiCrAl was characterized by material removal to a depth greater than the depth to which blade tips were driven into the seal, indicating self-erosion effects.

  10. Economic aspects of advanced coal-fired gas turbine locomotives

    NASA Technical Reports Server (NTRS)

    Liddle, S. G.; Bonzo, B. B.; Houser, B. C.

    1983-01-01

    Increases in the price of such conventional fuels as Diesel No. 2, as well as advancements in turbine technology, have prompted the present economic assessment of coal-fired gas turbine locomotive engines. A regenerative open cycle internal combustion gas turbine engine may be used, given the development of ceramic hot section components. Otherwise, an external combustion gas turbine engine appears attractive, since although its thermal efficiency is lower than that of a Diesel engine, its fuel is far less expensive. Attention is given to such a powerplant which will use a fluidized bed coal combustor. A life cycle cost analysis yields figures that are approximately half those typical of present locomotive engines.

  11. 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.

  12. Altitude Investigation of Performance of Turbine-propeller Engine and Its Components

    NASA Technical Reports Server (NTRS)

    Wallner, Lewis E; Saari, Martin J

    1950-01-01

    An investigation was conducted on a turbine-propeller engine in the NACA Lewis altitude wind tunnel at altitudes from 5000 to 35,000 feet. The applicability of generalized parameters to turbine-propeller engine data, analyses of the compressor, the combustion chambers, and the turbine, and a study of the over-all engine performance are reported. Engine performance data obtained at sea-level static conditions could be used to predict static performance at altitudes up to 35,000 feet by use of the standard generalized parameters.

  13. 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.

  14. Ceramic regenerator systems development program. [for automobile gas turbine engines

    NASA Technical Reports Server (NTRS)

    Cook, J. A.; Fucinari, C. A.; Lingscheit, J. N.; Rahnke, C. J.

    1977-01-01

    Ceramic regenerator cores are considered that can be used in passenger car gas turbine engines, Stirling engines, and industrial/truck gas turbine engines. Improved materials and design concepts aimed at reducing or eliminating chemical attack were placed on durability test in Ford 707 industrial gas turbine engines. The results of 19,600 hours of turbine engine durability testing are described. Two materials, aluminum silicate and magnesium aluminum silicate, continue to show promise toward achieving the durability objectives of this program. A regenerator core made from aluminum silicate showed minimal evidence of chemical attack damage after 6935 hours of engine test at 800 C and another showed little distress after 3510 hours at 982 C. Results obtained in ceramic material screening tests, aerothermodynamic performance tests, stress analysis, cost studies, and material specifications are also included.

  15. Systems Engineering Models and Tools | Wind | NREL

    Science.gov Websites

    (tm)) that provides wind turbine and plant engineering and cost models for holistic system analysis turbine/component models and wind plant analysis models that the systems engineering team produces. If you integrated modeling of wind turbines and plants. It provides guidance for overall wind turbine and plant

  16. Optimization of a Low Heat Load Turbine Nozzle Guide Vane

    DTIC Science & Technology

    2006-03-01

    HEAT LOAD TURBINE NOZZLE GUIDE VANE THESIS Presented to the Faculty Department of Aeronautical and Astronautical Engineering ...a function of turbine inlet temperature. .................... 2 Figure 2 Traditional turbofan engine and stator vane location (from Ref [1...the non-rotating stator vanes within a cross-section of a classical two-spool turbofan engine which has an inlet, 4 compressor, combustor, turbine

  17. Thermal Barrier Coatings (les Revetements anti-mur de chaleur)

    DTIC Science & Technology

    1998-04-01

    blades and vanes of advanced aircraft engines », 1992, Yokohama International Gas Turbine Congress... turbine blade and nozzle guide vane aerofoils for the aerogas turbine engine . Figure 9 Scanning electron micrograph of the surface of a plasma...2. Liebert C. H. et al, "Durability of zirconia thermal barrier coatings on air cooled turbine blades in cyclic jet engine operation", NASA

  18. 14 CFR 29.1093 - Induction system icing protection.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... prevent icing has a preheater that can provide a heat rise of 100 °F. (b) Turbine engines. (1) It must be shown that each turbine engine and its air inlet system can operate throughout the flight power range of... engine operation, within the limitations established for the rotorcraft. (2) Each turbine engine must...

  19. 14 CFR 29.1093 - Induction system icing protection.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... prevent icing has a preheater that can provide a heat rise of 100 °F. (b) Turbine engines. (1) It must be shown that each turbine engine and its air inlet system can operate throughout the flight power range of... engine operation, within the limitations established for the rotorcraft. (2) Each turbine engine must...

  20. 14 CFR 29.1093 - Induction system icing protection.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... prevent icing has a preheater that can provide a heat rise of 100 °F. (b) Turbine engines. (1) It must be shown that each turbine engine and its air inlet system can operate throughout the flight power range of... engine operation, within the limitations established for the rotorcraft. (2) Each turbine engine must...

  1. 14 CFR 29.1093 - Induction system icing protection.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... prevent icing has a preheater that can provide a heat rise of 100 °F. (b) Turbine engines. (1) It must be shown that each turbine engine and its air inlet system can operate throughout the flight power range of... engine operation, within the limitations established for the rotorcraft. (2) Each turbine engine must...

  2. 14 CFR 33.62 - Stress analysis.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS STANDARDS: AIRCRAFT ENGINES Design and Construction; Turbine Aircraft Engines § 33.62 Stress analysis. A stress analysis must be performed on each turbine engine showing the design safety margin of each turbine...

  3. 14 CFR 33.62 - Stress analysis.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS STANDARDS: AIRCRAFT ENGINES Design and Construction; Turbine Aircraft Engines § 33.62 Stress analysis. A stress analysis must be performed on each turbine engine showing the design safety margin of each turbine...

  4. Advanced Turbine Technology Applications Project (ATTAP)

    NASA Technical Reports Server (NTRS)

    1992-01-01

    ATTAP activities during the past year included test-bed engine design and development, ceramic component design, materials and component characterization, ceramic component process development and fabrication, ceramic component rig testing, and test-bed engine fabrication and testing. Significant technical challenges remain, but all areas exhibited progress. Test-bed engine design and development included engine mechanical design, combustion system design, alternate aerodynamic designs of gasifier scrolls, and engine system integration aimed at upgrading the AGT-5 from a 1038 C (1900 F) metal engine to a durable 1372 C (2500 F) structural ceramic component test-bed engine. ATTAP-defined ceramic and associated ceramic/metal component design activities completed include the ceramic gasifier turbine static structure, the ceramic gasifier turbine rotor, ceramic combustors, the ceramic regenerator disk, the ceramic power turbine rotors, and the ceramic/metal power turbine static structure. The material and component characterization efforts included the testing and evaluation of seven candidate materials and three development components. Ceramic component process development and fabrication proceeded for the gasifier turbine rotor, gasifier turbine scroll, gasifier turbine vanes and vane platform, extruded regenerator disks, and thermal insulation. Component rig activities included the development of both rigs and the necessary test procedures, and conduct of rig testing of the ceramic components and assemblies. Test-bed engine fabrication, testing, and development supported improvements in ceramic component technology that permit the achievement of both program performance and durability goals. Total test time in 1991 amounted to 847 hours, of which 128 hours were engine testing, and 719 were hot rig testing.

  5. Advanced Turbine Technology Applications Project (ATTAP)

    NASA Technical Reports Server (NTRS)

    1993-01-01

    The Advanced Turbine Technologies Application Project (ATTAP) is in the fifth year of a multiyear development program to bring the automotive gas turbine engine to a state at which industry can make commercialization decisions. Activities during the past year included reference powertrain design updates, test-bed engine design and development, ceramic component design, materials and component characterization, ceramic component process development and fabrication, ceramic component rig testing, and test-bed engine fabrication and testing. Engine design and development included mechanical design, combustion system development, alternate aerodynamic flow testing, and controls development. Design activities included development of the ceramic gasifier turbine static structure, the ceramic gasifier rotor, and the ceramic power turbine rotor. Material characterization efforts included the testing and evaluation of five candidate high temperature ceramic materials. Ceramic component process development and fabrication, with the objective of approaching automotive volumes and costs, continued for the gasifier turbine rotor, gasifier turbine scroll, extruded regenerator disks, and thermal insulation. Engine and rig fabrication, testing, and development supported improvements in ceramic component technology. Total test time in 1992 amounted to 599 hours, of which 147 hours were engine testing and 452 were hot rig testing.

  6. Stationary Engineers Apprenticeship. Related Training Modules. 15.1-15.5 Turbines.

    ERIC Educational Resources Information Center

    Lane Community Coll., Eugene, OR.

    This learning module, one in a series of 20 related training modules for apprentice stationary engineers, deals with turbines. addressed in the individual instructional packages included in the module are the following topics: types and components of steam turbines, steam turbine auxiliaries, operation and maintenance of steam turbines, and gas…

  7. Ceramic Composite Development for Gas Turbine Engine Hot Section Components

    NASA Technical Reports Server (NTRS)

    DiCarlo, James A.; VANrOODE, mARK

    2006-01-01

    The development of ceramic materials for incorporation into the hot section of gas turbine engines has been ongoing for about fifty years. Researchers have designed, developed, and tested ceramic gas turbine components in rigs and engines for automotive, aero-propulsion, industrial, and utility power applications. Today, primarily because of materials limitations and/or economic factors, major challenges still remain for the implementation of ceramic components in gas turbines. For example, because of low fracture toughness, monolithic ceramics continue to suffer from the risk of failure due to unknown extrinsic damage events during engine service. On the other hand, ceramic matrix composites (CMC) with their ability to display much higher damage tolerance appear to be the materials of choice for current and future engine components. The objective of this paper is to briefly review the design and property status of CMC materials for implementation within the combustor and turbine sections for gas turbine engine applications. It is shown that although CMC systems have advanced significantly in thermo-structural performance within recent years, certain challenges still exist in terms of producibility, design, and affordability for commercial CMC turbine components. Nevertheless, there exist some recent successful efforts for prototype CMC components within different engine types.

  8. Exhaust turbine and jet propulsion systems

    NASA Technical Reports Server (NTRS)

    Leist, Karl; Knornschild, Eugen

    1951-01-01

    DVL experimental and analytical work on the cooling of turbine blades by using ram air as the working fluid over a sector or sectors of the turbine annulus area is summarized. The subsonic performance of ram-jet, turbo-jet, and turbine-propeller engines with both constant pressure and pulsating-flow combustion is investigated. Comparison is made with the performance of a reciprocating engine and the advantages of the gas turbine and jet-propulsion engines are analyzed. Nacelle installation methods and power-level control are discussed.

  9. Preliminary Results of an Altitude-Wind-Tunnel Investigation of an Axial-Flow Gas Turbine-Propeller Engine. 4; Compressor and Turbine Performance Characteristics

    NASA Technical Reports Server (NTRS)

    Wallner, Lewis E.; Saari, Martin J.

    1948-01-01

    As part of an investigation of the performance and operational characteristics of the axial-flow gas turbine-propeller engine, conducted in the Cleveland altitude wind tunnel, the performance characteristics of the compressor and the turbine were obtained. The data presented were obtained at a compressor-inlet ram-pressure ratio of 1.00 for altitudes from 5000 to 35,000 feet, engine speeds from 8000 to 13,000 rpm, and turbine-inlet temperatures from 1400 to 2100 R. The highest compressor pressure ratio obtained was 6.15 at a corrected air flow of 23.7 pounds per second and a corrected turbine-inlet temperature of 2475 R. Peak adiabatic compressor efficiencies of about 77 percent were obtained near the value of corrected air flow corresponding to a corrected engine speed of 13,000 rpm. This maximum efficiency may be somewhat low, however, because of dirt accumulations on the compressor blades. A maximum adiabatic turbine efficiency of 81.5 percent was obtained at rated engine speed for all altitudes and turbine-inlet temperatures investigated.

  10. Preliminary Results of an Altitude-Wind-Tunnel Investigation of a TG-100A Gas Turbine-Propeller Engine. 4; Compressor and Turbine Performance Characteristics

    NASA Technical Reports Server (NTRS)

    Wallner, Lewis E.; Saari, Martin J.

    1947-01-01

    As part of an investigation of the performance and operational characteristics of the TG-100A gas turbine-propeller engine, conducted in the Cleveland altitude wind tunnel, the performance characteristics of the compressor and the turbine were obtained. The data presented were obtained at a compressor-inlet ram-pressure ratio of 1.00 for altitudes from 5000 to 35,000 feet, engine speeds from 8000 to 13,000 rpm, and turbine-inlet temperatures from 1400 to 2100R. The highest compressor pressure ratio was 6.15 at a corrected air flow of 23.7 pounds per second and a corrected turbine-inlet temperature of 2475R. Peak adiabatic compressor efficiencies of about 77 percent were obtained near the value of corrected air flow corresponding to a corrected engine speed of 13,000 rpm. This maximum efficiency may be somewhat low, however, because of dirt accumulations on the compressor blades. A maximum adiabatic turbine efficiency of 81.5 percent was obtained at rated engine speed for all altitudes and turbine-inlet temperatures investigated.

  11. 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.

  12. 14 CFR 34.30 - Applicability.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES Exhaust Emissions (In-use Aircraft Gas Turbine Engines) § 34.30 Applicability. The provisions of this subpart are applicable to all in-use aircraft gas turbine engines certificated for operation within the United States of the classes specified...

  13. 14 CFR 34.30 - Applicability.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES Exhaust Emissions (In-use Aircraft Gas Turbine Engines) § 34.30 Applicability. The provisions of this subpart are applicable to all in-use aircraft gas turbine engines certificated for operation within the United States of the classes specified...

  14. 14 CFR 34.30 - Applicability.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES Exhaust Emissions (In-use Aircraft Gas Turbine Engines) § 34.30 Applicability. The provisions of this subpart are applicable to all in-use aircraft gas turbine engines certificated for operation within the United States of the classes specified...

  15. 14 CFR 34.20 - Applicability.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES Exhaust Emissions (New Aircraft Gas Turbine Engines) § 34.20 Applicability. The provisions of this subpart are applicable to all aircraft gas turbine engines of the classes specified beginning on the dates specified in § 34.21. ...

  16. 14 CFR 34.20 - Applicability.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES Exhaust Emissions (New Aircraft Gas Turbine Engines) § 34.20 Applicability. The provisions of this subpart are applicable to all aircraft gas turbine engines of the classes specified beginning on the dates specified in § 34.21. ...

  17. 14 CFR 34.20 - Applicability.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES Exhaust Emissions (New Aircraft Gas Turbine Engines) § 34.20 Applicability. The provisions of this subpart are applicable to all aircraft gas turbine engines of the classes specified beginning on the dates specified in § 34.21. ...

  18. An Analysis of the Influence of some External Disturbances on the Aerodynamic Stability of Turbine Engine Axial Flow Fans and Compressors

    DTIC Science & Technology

    1977-08-01

    237 265 X A E DC-T R-77-80 CHAPTER I INTRODUCTION Stable aerodynamic operation of the compression system of an aircraft gas turbine engine is...of an aircraft gas turbine engine consists of one or more compressors arranged in configurations such as those illustrated in Fig. 1 (Appendix A). 1...difficulties in the operation of several aircraft gas turbine engines which have been experienced because of compressor stability problems. Montgomery’s

  19. Core Engine Noise Program. Volume III. Prediction Methods -- Supplement I. - Extension of Prediction Methods

    DTIC Science & Technology

    1976-03-01

    frequency noise transmission through turbine blade rows and addition of engine and component data to the prediction method for core noise. " Phase VI...lower turbine blade row attenuation for this low bypass engine . When the blade row attenuation is accounted for by means of a turbine work extrac...component and engine data. Currently, an in-depth program to investigate turbine blade row attenuation is underway (NAS3-19435 and DOT-FA75WA-3688). The

  20. Some Problems of Exploitation of Jet Turbine Aircraft Engines of Lot Polish Air Lines,

    DTIC Science & Technology

    1977-04-26

    CI ‘AD~AOII6 221 FOREIGN TECHNOLOGY DIV WR IGHT—PATTERSON AFB OHIO F/I 21/5SOME PROBLEMS OF EXPLOITATION OF JET TURBINE AIRCRAFT ENGINES O—CTC(U...EXPLOITATION OF JET TURBINE AIRCRAFT ENGINES OF LOT POLISH AIR LINE S By: Andrzej Slodownik English pages: 1~ Source: Technika Lotnicza I Astronautyczna...SOME PROBLEMS OF EXPLOITATION OF JET TURBINE AIRCRAFT ENGINES OF LOT POLISH AIR LINES Andrzej Slodownik , M. Eng . FTD— ID ( RS) I— 0 1475 — 77 I

  1. Full hoop casing for midframe of industrial gas turbine engine

    DOEpatents

    Myers, Gerald A.; Charron, Richard C.

    2015-12-01

    A can annular industrial gas turbine engine, including: a single-piece rotor shaft spanning a compressor section (82), a combustion section (84), a turbine section (86); and a combustion section casing (10) having a section (28) configured as a full hoop. When the combustion section casing is detached from the engine and moved to a maintenance position to allow access to an interior of the engine, a positioning jig (98) is used to support the compressor section casing (83) and turbine section casing (87).

  2. Field Evaluation of Six Protective Coatings Applied to T56 Turbines after 1500 Hours Engine Use

    DTIC Science & Technology

    1991-06-01

    Six Coating Systems On First-stage Gas Turbine Blades In The Engines of a Long-Range Maritime Patrol Aircraft ", Surface and Coating Technology, 36...based coatings. They were applied to the first-stage turbine blades in the engines of two long range maritime patrol aircraft operated by the Royal...incorrect. These differently coated turbine - blades have in fact seen 1500 hours service in a T56 engine . The title and further reference in the text should

  3. Abradable compressor and turbine seals, volume 1. [for turbofan engines

    NASA Technical Reports Server (NTRS)

    Sundberg, D. V.; Dennis, R. E.; Hurst, L. G.

    1979-01-01

    The application and advantages of abradable coatings as gas-path seals in a general aviation turbine engine were evaluated for use on the high-pressure compressor, the high-pressure turbine, and the low-pressure turbine shrouds. Topics covered include: (1) the initial selection of candidate materials for interim full-scale engine testing; (2) interim engine testing of the initially selected materials and additional candidate materials; (3) the design of the component required to adapt the hardware to permit full-scale engine testing of the most promising materials; (4) finalization of the fabrication methods used in the manufacture of engine test hardware; and (5) the manufacture of the hardware necessary to support the final full-scale engine tests.

  4. Supersonic Transport Noise Reduction Technology Program - Phase 2. Volume 1

    DTIC Science & Technology

    1975-09-01

    transport aircraft . In addition, PNL and EPNL con- tributions made by each major engine component ( jet , turbine , combustor and compressor) were... Turbine noise was studied using a J85 engine with massive Inlet suppressor and open nozzle to unmask the turbine . Second-stage turbine blade /nozzle...17. Kty Words (Suggnted by Author(tl) Jet Noise, High Velocity Suppression, Aircraft Engine Suppression, Turbomachlnery Noise, Hybrid Inlet

  5. Compressor airfoil tip clearance optimization system

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Little, David A.; Pu, Zhengxiang

    2015-08-18

    A compressor airfoil tip clearance optimization system for reducing a gap between a tip of a compressor airfoil and a radially adjacent component of a turbine engine is disclosed. The turbine engine may include ID and OD flowpath boundaries configured to minimize compressor airfoil tip clearances during turbine engine operation in cooperation with one or more clearance reduction systems that are configured to move the rotor assembly axially to reduce tip clearance. The configurations of the ID and OD flowpath boundaries enhance the effectiveness of the axial movement of the rotor assembly, which includes movement of the ID flowpath boundary.more » During operation of the turbine engine, the rotor assembly may be moved axially to increase the efficiency of the turbine engine.« less

  6. Demonstration and evaluation of gas turbine transit buses

    NASA Technical Reports Server (NTRS)

    1983-01-01

    The Gas Turbine Transit Bus Demonstration Program was designed to demonstrate and evaluate the operation of gas turbine engines in transit coaches in revenue service compared with diesel powered coaches. The main objective of the program was to accelerate development and commercialization of automotive gas turbines. The benefits from the installation of this engine in a transit coach were expected to be reduced weight, cleaner exhaust emissions, lower noise levels, reduced engine vibration and maintenance requirements, improved reliability and vehicle performance, greater engine braking capability, and superior cold weather starting. Four RTS-II advanced design transit coaches were converted to gas turbine power using engines and transmissions. Development, acceptance, performance and systems tests were performed on the coaches prior to the revenue service demonstration.

  7. A method to estimate weight and dimensions of small aircraft propulsion gas turbine engines: User's guide

    NASA Technical Reports Server (NTRS)

    Hale, P. L.

    1982-01-01

    The weight and major envelope dimensions of small aircraft propulsion gas turbine engines are estimated. The computerized method, called WATE-S (Weight Analysis of Turbine Engines-Small) is a derivative of the WATE-2 computer code. WATE-S determines the weight of each major component in the engine including compressors, burners, turbines, heat exchangers, nozzles, propellers, and accessories. A preliminary design approach is used where the stress levels, maximum pressures and temperatures, material properties, geometry, stage loading, hub/tip radius ratio, and mechanical overspeed are used to determine the component weights and dimensions. The accuracy of the method is generally better than + or - 10 percent as verified by analysis of four small aircraft propulsion gas turbine engines.

  8. 40 CFR 87.21 - Exhaust emission standards for Tier 4 and earlier engines.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... Emissions (New Aircraft Gas Turbine Engines) § 87.21 Exhaust emission standards for Tier 4 and earlier... standards. (a) Exhaust emissions of smoke from each new aircraft gas turbine engine of class T8 manufactured... from each new aircraft gas turbine engine of class TF and of rated output of 129 kilonewtons thrust or...

  9. 40 CFR 87.21 - Exhaust emission standards for Tier 4 and earlier engines.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... Emissions (New Aircraft Gas Turbine Engines) § 87.21 Exhaust emission standards for Tier 4 and earlier... standards. (a) Exhaust emissions of smoke from each new aircraft gas turbine engine of class T8 manufactured... from each new aircraft gas turbine engine of class TF and of rated output of 129 kilonewtons thrust or...

  10. 46 CFR 11.522 - Service requirements for national endorsement as assistant engineer (limited) of steam, motor...

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... assistant engineer (limited) of steam, motor, and/or gas turbine-propelled vessels. 11.522 Section 11.522... requirements for national endorsement as assistant engineer (limited) of steam, motor, and/or gas turbine... engineer (limited) of steam, motor, and/or gas turbine-propelled vessels is 3 years of service in the...

  11. Cost Effective Repair Techniques for Turbine Airfoils. Volume 2

    DTIC Science & Technology

    1979-04-01

    BLADES , *GUIDE VANES , *REPAIR, TURBOFAN ENGINES , DIFFUSION BONDING, COST EFFECTIVENESS Identifiers: (U) * Turbine vanes , TF-39 engines , Activated...REPAIR TECHNIQUES FOR TURBINE AIRFOILS J. A. WEIN W. R. YOUNG GENERAL ELECTRIC COMPANY AIRCRAFT ENGINE GROUP CINCINNATI, OHIO 45215 APRIL 1979...Author: GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP Unclassified Title: (U) Cost Effective Repair Techniques for

  12. Computational thermo-fluid dynamics contributions to advanced gas turbine engine design

    NASA Technical Reports Server (NTRS)

    Graham, R. W.; Adamczyk, J. J.; Rohlik, H. E.

    1984-01-01

    The design practices for the gas turbine are traced throughout history with particular emphasis on the calculational or analytical methods. Three principal components of the gas turbine engine will be considered: namely, the compressor, the combustor and the turbine.

  13. 14 CFR 121.197 - Airplanes: Turbine engine powered: Landing limitations: Alternate airports.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Airplanes: Turbine engine powered: Landing... AND OPERATIONS OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Airplane Performance Operating Limitations § 121.197 Airplanes: Turbine engine powered: Landing limitations: Alternate...

  14. 14 CFR 121.189 - Airplanes: Turbine engine powered: Takeoff limitations.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Airplanes: Turbine engine powered: Takeoff... OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Airplane Performance Operating Limitations § 121.189 Airplanes: Turbine engine powered: Takeoff limitations. (a) No person operating a...

  15. 14 CFR 121.189 - Airplanes: Turbine engine powered: Takeoff limitations.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Airplanes: Turbine engine powered: Takeoff... OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Airplane Performance Operating Limitations § 121.189 Airplanes: Turbine engine powered: Takeoff limitations. (a) No person operating a...

  16. 14 CFR 121.189 - Airplanes: Turbine engine powered: Takeoff limitations.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Airplanes: Turbine engine powered: Takeoff... OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Airplane Performance Operating Limitations § 121.189 Airplanes: Turbine engine powered: Takeoff limitations. (a) No person operating a...

  17. 14 CFR 121.195 - Airplanes: Turbine engine powered: Landing limitations: Destination airports.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Airplanes: Turbine engine powered: Landing...: CERTIFICATION AND OPERATIONS OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Airplane Performance Operating Limitations § 121.195 Airplanes: Turbine engine powered: Landing limitations...

  18. 14 CFR 121.197 - Airplanes: Turbine engine powered: Landing limitations: Alternate airports.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Airplanes: Turbine engine powered: Landing... AND OPERATIONS OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Airplane Performance Operating Limitations § 121.197 Airplanes: Turbine engine powered: Landing limitations: Alternate...

  19. 14 CFR 121.195 - Airplanes: Turbine engine powered: Landing limitations: Destination airports.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Airplanes: Turbine engine powered: Landing...: CERTIFICATION AND OPERATIONS OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Airplane Performance Operating Limitations § 121.195 Airplanes: Turbine engine powered: Landing limitations...

  20. 14 CFR 121.195 - Airplanes: Turbine engine powered: Landing limitations: Destination airports.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Airplanes: Turbine engine powered: Landing...: CERTIFICATION AND OPERATIONS OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Airplane Performance Operating Limitations § 121.195 Airplanes: Turbine engine powered: Landing limitations...

  1. 14 CFR 121.197 - Airplanes: Turbine engine powered: Landing limitations: Alternate airports.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Airplanes: Turbine engine powered: Landing... AND OPERATIONS OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Airplane Performance Operating Limitations § 121.197 Airplanes: Turbine engine powered: Landing limitations: Alternate...

  2. A summary of computational experience at GE Aircraft Engines for complex turbulent flows in gas turbines

    NASA Astrophysics Data System (ADS)

    Zerkle, Ronald D.; Prakash, Chander

    1995-03-01

    This viewgraph presentation summarizes some CFD experience at GE Aircraft Engines for flows in the primary gaspath of a gas turbine engine and in turbine blade cooling passages. It is concluded that application of the standard k-epsilon turbulence model with wall functions is not adequate for accurate CFD simulation of aerodynamic performance and heat transfer in the primary gas path of a gas turbine engine. New models are required in the near-wall region which include more physics than wall functions. The two-layer modeling approach appears attractive because of its computational complexity. In addition, improved CFD simulation of film cooling and turbine blade internal cooling passages will require anisotropic turbulence models. New turbulence models must be practical in order to have a significant impact on the engine design process. A coordinated turbulence modeling effort between NASA centers would be beneficial to the gas turbine industry.

  3. A summary of computational experience at GE Aircraft Engines for complex turbulent flows in gas turbines

    NASA Technical Reports Server (NTRS)

    Zerkle, Ronald D.; Prakash, Chander

    1995-01-01

    This viewgraph presentation summarizes some CFD experience at GE Aircraft Engines for flows in the primary gaspath of a gas turbine engine and in turbine blade cooling passages. It is concluded that application of the standard k-epsilon turbulence model with wall functions is not adequate for accurate CFD simulation of aerodynamic performance and heat transfer in the primary gas path of a gas turbine engine. New models are required in the near-wall region which include more physics than wall functions. The two-layer modeling approach appears attractive because of its computational complexity. In addition, improved CFD simulation of film cooling and turbine blade internal cooling passages will require anisotropic turbulence models. New turbulence models must be practical in order to have a significant impact on the engine design process. A coordinated turbulence modeling effort between NASA centers would be beneficial to the gas turbine industry.

  4. Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8, and 19XB-1 Jet-Propulsion Engines. II - Analysis of Turbine Performance of the 19B-8 Engine

    NASA Technical Reports Server (NTRS)

    Krebs, Richard P.; Suozzi, Frank L.

    1947-01-01

    Performance characteristics of the turbine in the 19B-8 jet propulsion engine were determined from an investigation of the complete engine in the Cleveland altitude wind tunnel. The investigation covered a range of simulated altitudes from 5000 to 30,000 feet and flight Mach numbers from 0.05 to 0.46 for various tail-cone positions over the entire operable range of engine speeds. The characteristics of the turbine are presented as functions of the total-pressure ratio across the turbine and the turbine speed and the gas flow corrected to NACA standard atmospheric conditions at sea level. The effect of changes in altitude, flight Mach number, and tail-cone position on turbine performance is discussed. The turbine efficiency with the tail cone in varied from a maximum of 80.5 percent to minimum of 75 percent over a range of engine speeds from 7500 to 17,500 rpm at a flight Mach number of 0.055. Turbine efficiency was unaffected by changes in altitude up to 15,000 feet but was a function of tail-cone position and flight Mach number. Decreasing the tail-pipe-nozzle outlet area 21 percent reduced the turbine efficiency between 2 and 4.5 percent. The turbine efficiency increased between 1.5 and 3 percent as the flight Mach number changed from 0.055 to 0.297.

  5. Cost Effective Repair Techniques for Turbine Airfoils. Volume I

    DTIC Science & Technology

    1978-11-01

    Turbine blades and vanes in current engines are subjected to the most hostile environment...payoff potential in turbine vanes / blades . The criteria used included: • Incidence of damage - Scrapped or damaged turbine airfoils at the ALC centers...Corporate Author: GENERAL ELECTRIC CO CINCINNATI OHIO AIRCRAFT ENGINE GROUP Unclassified Title: (U) Cost Effective Repair Techniques for Turbine

  6. Exhaust gas recirculation system for an internal combustion engine

    DOEpatents

    Wu, Ko-Jen

    2013-05-21

    An exhaust gas recirculation system for an internal combustion engine comprises an exhaust driven turbocharger having a low pressure turbine outlet in fluid communication with an exhaust gas conduit. The turbocharger also includes a low pressure compressor intake and a high pressure compressor outlet in communication with an intake air conduit. An exhaust gas recirculation conduit fluidly communicates with the exhaust gas conduit to divert a portion of exhaust gas to a low pressure exhaust gas recirculation branch extending between the exhaust gas recirculation conduit and an engine intake system for delivery of exhaust gas thereto. A high pressure exhaust gas recirculation branch extends between the exhaust gas recirculation conduit and the compressor intake and delivers exhaust gas to the compressor for mixing with a compressed intake charge for delivery to the intake system.

  7. Thermal barrier coatings for aircraft engines: History and directions

    NASA Technical Reports Server (NTRS)

    Miller, R. A.

    1995-01-01

    Thin thermal barrier coatings for protecting aircraft turbine section airfoils are examined. The discussion focuses on those advances that led first to their use for component life extension and more recently as an integral part of airfoil design. It is noted that development has been driven by laboratory rig and furnace testing corroborated by engine testing and engine field experience. The technology has also been supported by performance modeling to demonstrate benefits and life modeling for mission analysis. Factors which have led to the selection of the current state-of-the-art plasma sprayed and physical vapor deposited zirconia-yttria/MCrAlY TBC's is emphasized in addition to observations fundamentally related to their behavior. Current directions in research into thermal barrier coatings and recent progress at NASA is also noted.

  8. Low-Cost, Net-Shape Ceramic Radial Turbine Program

    DTIC Science & Technology

    1985-05-01

    PROGRAM ELEMENT. PROJECT. TASK Garrett Turbine Engine Company AE OKUI UBR 111 South 34th Street, P.O. Box 2517 Phoenix, Arizona 85010 %I. CONTROLLING...processing iterations. Program management and materials characterization were conducted at Garrett Turbine Engine Company (GTEC), test bar and rotor...automotive gas turbine engine rotor development efforts at ACC. xvii PREFACE This is the final technical report of the Low-Cost, Net- Shape Ceramic

  9. 14 CFR 34.3 - General requirements.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... powered by aircraft gas turbine engines of the classes specified herein and that have U.S. standard...), this FAR applies to civil airplanes that are powered by aircraft gas turbine engines of the classes... EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES General Provisions § 34.3 General...

  10. 14 CFR 34.3 - General requirements.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... powered by aircraft gas turbine engines of the classes specified herein and that have U.S. standard...), this FAR applies to civil airplanes that are powered by aircraft gas turbine engines of the classes... EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES General Provisions § 34.3 General...

  11. 14 CFR 34.3 - General requirements.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES General Provisions § 34.3 General... powered by aircraft gas turbine engines of the classes specified herein and that have U.S. standard...), this FAR applies to civil airplanes that are powered by aircraft gas turbine engines of the classes...

  12. Performance of J33 turbojet engine with shaft-power extraction III : turbine performance

    NASA Technical Reports Server (NTRS)

    Huppert, M C; Nettles, J C

    1949-01-01

    The performance of the turbine component of a J33 turbojet engine was determined over a range of turbine speeds from 8000 to 11,500 rpm.Turbine-inlet temperature was varied from the minimum required to drive the compressor to a maximum of approximately 2000 degrees R at each of several intermediate turbine speeds. Data are presented that show the horsepower developed by the turbine per pound of gas flow. The relation between turbine-inlet stagnation pressure, turbine-outlet stagnation pressure, and turbine-outlet static pressure was established. The turbine-weight-flow parameter varied from 39.2 to 43.6. The maximum turbine efficiency measured was 0.86 at a pressure ratio of 3.5 and a ratio of blade speed to theoretical nozzle velocity of 0.39. A generalized performance map of the turbine-horsepower parameter plotted against the turbine-speed parameter indicated that the best turbine efficiency is obtained when the turbine power is 10 percent greater than the compressor horsepower. The variation of efficiency with the ratio of blade speed to nozzle velocity indicated that the turbine operates at a speed above that for maximum efficiency when the engine is operated normally with the 19-inch-diameter jet nozzle.

  13. ISGV Self-rectifying Turbine Design For Thermoacoustic Application

    NASA Astrophysics Data System (ADS)

    Sammak, Shervin; Asghary, Maryam; Ghorbanian, Kaveh

    2014-11-01

    Thermoacoustic engines produce the acoustic power from wasted heat and then electricity can be generated from acoustic power. Utilizing self-rectifying turbine after a thermoacoustic engine allows for deploying standard generators with high enough rotational speed that remarkably reduce abrasion, size and cost and significantly increase efficiency and controllability in comparison with linear alternators. In this paper, by evaluating all different type of self-rectifying turbine, impulse turbine with self-piched controlled (ISGV) is chosen as the most appropriate type for this application. This kind of turbine is designed in detail for a popular engine, thermoacoustic stirling heat engine (TASHE). In order to validate the design, a full scale size of designed turbine is modeled in ANSYS CFX. As a result, optimum power and efficiency gained based on numerical data.

  14. Contingency power for small turboshaft engines using water injection into turbine cooling air

    NASA Technical Reports Server (NTRS)

    Biesiadny, Thomas J.; Klann, Gary A.; Clark, David A.; Berger, Brett

    1987-01-01

    Because of one engine inoperative requirements, together with hot-gas reingestion and hot day, high altitude takeoff situations, power augmentation for multiengine rotorcraft has always been of critical interest. However, power augmentation using overtemperature at the turbine inlet will shorten turbine life unless a method of limiting thermal and mechanical stresses is found. A possible solution involves allowing the turbine inlet temperature to rise to augment power while injecting water into the turbine cooling air to limit hot-section metal temperatures. An experimental water injection device was installed in an engine and successfully tested. Although concern for unprotected subcomponents in the engine hot section prevented demonstration of the technique's maximum potential, it was still possible to demonstrate increases in power while maintaining nearly constant turbine rotor blade temperature.

  15. High Temperature Investigations into an Active Turbine Blade Tip Clearance Control Concept

    NASA Technical Reports Server (NTRS)

    Taylor, Shawn; Steinetz, Bruce M.; Oswald, Jay J.

    2007-01-01

    System studies have shown the benefits of reducing blade tip clearances in modern turbine engines. Minimizing blade tip clearances throughout the engine will contribute materially to meeting NASA s Ultra-Efficient Engine Technology (UEET) turbine engine project goals. NASA GRC is examining two candidate approaches including rub-avoidance and regeneration which are explained in subsequent slides.

  16. 46 CFR 11.514 - Service requirements for national endorsement as second assistant engineer of steam, motor, and...

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... assistant engineer of steam, motor, and/or gas turbine-propelled vessels. 11.514 Section 11.514 Shipping... requirements for national endorsement as second assistant engineer of steam, motor, and/or gas turbine... assistant engineer of steam, motor, and/or gas turbine-propelled vessels is— (1) One year of service as an...

  17. 46 CFR 11.512 - Service requirements for national endorsement as first assistant engineer of steam, motor, and/or...

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... assistant engineer of steam, motor, and/or gas turbine-propelled vessels. 11.512 Section 11.512 Shipping... requirements for national endorsement as first assistant engineer of steam, motor, and/or gas turbine-propelled... engineer of steam, motor, and/or gas turbine-propelled vessels is— (1) One year of service as an assistant...

  18. 46 CFR 11.510 - Service requirements for national endorsement as chief engineer of steam, motor, and/or gas...

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... engineer of steam, motor, and/or gas turbine-propelled vessels. 11.510 Section 11.510 Shipping COAST GUARD... endorsement as chief engineer of steam, motor, and/or gas turbine-propelled vessels. (a) The minimum service required to qualify an applicant for endorsement as chief engineer of steam, motor, and/or gas turbine...

  19. High Temperature Investigations into an Active Turbine Blade Tip Clearance Control Concept

    NASA Technical Reports Server (NTRS)

    Taylor, Shawn C.; Steinetz, Bruce; Oswald, Jay J.

    2008-01-01

    System studies have shown the benefits of reducing blade tip clearances in modern turbine engines. Minimizing blade tip clearances throughout the engine will contribute materially to meeting NASA s Ultra-Efficient Engine Technology (UEET) turbine engine project goals. NASA GRC is examining two candidate approaches including rub-avoidance and regeneration which are explained in subsequent slides.

  20. 14 CFR 25.1093 - Induction system icing protection.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... percent of maximum continuous power. (b) Turbine engines. (1) Each turbine engine must operate throughout... turbine engine must idle for 30 minutes on the ground, with the air bleed available for engine icing... between 15° and 30 °F (between −9° and −1 °C) and has a liquid water content not less than 0.3 grams per...

  1. 14 CFR 25.1093 - Induction system icing protection.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... percent of maximum continuous power. (b) Turbine engines. (1) Each turbine engine must operate throughout... turbine engine must idle for 30 minutes on the ground, with the air bleed available for engine icing... between 15° and 30 °F (between −9° and −1 °C) and has a liquid water content not less than 0.3 grams per...

  2. 14 CFR 25.1093 - Induction system icing protection.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... percent of maximum continuous power. (b) Turbine engines. (1) Each turbine engine must operate throughout... turbine engine must idle for 30 minutes on the ground, with the air bleed available for engine icing... between 15° and 30 °F (between −9° and −1 °C) and has a liquid water content not less than 0.3 grams per...

  3. 14 CFR 25.1093 - Induction system icing protection.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... percent of maximum continuous power. (b) Turbine engines. (1) Each turbine engine must operate throughout... turbine engine must idle for 30 minutes on the ground, with the air bleed available for engine icing... between 15° and 30 °F (between −9° and −1 °C) and has a liquid water content not less than 0.3 grams per...

  4. PVD TBC experience on GE aircraft engines

    NASA Technical Reports Server (NTRS)

    Bartz, A.; Mariocchi, A.; Wortman, D. J.

    1995-01-01

    The higher performance levels of modern gas turbine engines present significant challenges in the reliability of materials in the turbine. The increased engine temperatures required to achieve the higher performance levels reduce the strength of the materials used in the turbine sections of the engine. Various forms of Thermal Barrier Coatings (TBC's) have been used for many years to increase the reliability of gas turbine engine components. Recent experience with the Physical Vapor Deposition (PVD) process using ceramic material has demonstrated success in extending the service life of turbine blades and nozzles. Engine test results of turbine components with a 125 micrometer (0.005 in) PVD TBC have demonstrated component operating temperatures of 56-83 C (100-150 F) lower than uncoated components. Engine testing has also revealed the TBC is susceptible to high angle particle impact damage. Sand particles and other engine debris impact the TBC surface at the leading edge of airfoils and fracture the PVD columns. As the impacting continues the TBC erodes away in local areas. Analysis of the eroded areas has shown a slight increase in temperature over a fully coated area, however, a significant temperature reduction was realized over an airfoil without any TBC.

  5. PVD TBC experience on GE aircraft engines

    NASA Technical Reports Server (NTRS)

    Maricocchi, Antonio; Bartz, Andi; Wortman, David

    1995-01-01

    The higher performance levels of modern gas turbine engines present significant challenges in the reliability of materials in the turbine. The increased engine temperatures required to achieve the higher performance levels reduce the strength of the materials used in the turbine sections of the engine. Various forms of thermal barrier coatings (TBC's) have been used for many years to increase the reliability of gas turbine engine components. Recent experience with the physical vapor deposition (PVD) process using ceramic material has demonstrated success in extending the service life of turbine blades and nozzles. Engine test results of turbine components with a 125 micron (0.005 in) PVD TBC have demonstrated component operating temperatures of 56-83 C (100-150 F) lower than non-PVD TBC components. Engine testing has also revealed the TBC is susceptible to high angle particle impact damage. Sand particles and other engine debris impact the TBC surface at the leading edge of airfoils and fracture the PVD columns. As the impacting continues, the TBC erodes away in local areas. Analysis of the eroded areas has shown a slight increase in temperature over a fully coated area, however a significant temperature reduction was realized over an airfoil without TBC.

  6. PVD TBC experience on GE aircraft engines

    NASA Astrophysics Data System (ADS)

    Maricocchi, A.; Bartz, A.; Wortman, D.

    1997-06-01

    The higher performance levels of modern gas turbine engines present significant challenges in the reli-ability of materials in the turbine. The increased engine temperatures required to achieve the higher per-formance levels reduce the strength of the materials used in the turbine sections of the engine. Various forms of thermal barrier coatings have been used for many years to increase the reliability of gas turbine engine components. Recent experience with the physical vapor deposition process using ceramic material has demonstrated success in extending the service life of turbine blades and nozzles. Engine test results of turbine components with a 125 μm (0.005 in.) PVD TBC have demonstrated component operating tem-peratures of 56 to 83 °C (100 to 150 °F) lower than non-PVD TBC components. Engine testing has also revealed that TBCs are susceptible to high angle particle impact damage. Sand particles and other engine debris impact the TBC surface at the leading edge of airfoils and fracture the PVD columns. As the impacting continues, the TBC erodes in local areas. Analysis of the eroded areas has shown a slight increase in temperature over a fully coated area ; however, a significant temperature reduc-tion was realized over an airfoil without TBC.

  7. Effects of Gas Turbine Component Performance on Engine and Rotary Wing Vehicle Size and Performance

    NASA Technical Reports Server (NTRS)

    Snyder, Christopher A.; Thurman, Douglas R.

    2010-01-01

    In support of the Fundamental Aeronautics Program, Subsonic Rotary Wing Project, further gas turbine engine studies have been performed to quantify the effects of advanced gas turbine technologies on engine weight and fuel efficiency and the subsequent effects on a civilian rotary wing vehicle size and mission fuel. The Large Civil Tiltrotor (LCTR) vehicle and mission and a previous gas turbine engine study will be discussed as a starting point for this effort. Methodology used to assess effects of different compressor and turbine component performance on engine size, weight and fuel efficiency will be presented. A process to relate engine performance to overall LCTR vehicle size and fuel use will also be given. Technology assumptions and levels of performance used in this analysis for the compressor and turbine components performances will be discussed. Optimum cycles (in terms of power specific fuel consumption) will be determined with subsequent engine weight analysis. The combination of engine weight and specific fuel consumption will be used to estimate their effect on the overall LCTR vehicle size and mission fuel usage. All results will be summarized to help suggest which component performance areas have the most effect on the overall mission.

  8. Turbine Engine Hot Section Technology 1986

    NASA Technical Reports Server (NTRS)

    1986-01-01

    The Turbine Engine Hot Section Technology (HOST) Project of the NASA Lewis Research Center sponsored a workshop to discuss current research pertinent to turbine engine durability problems. Presentations were made concerning the hot section environment and the behavior of combustion liners, turbine blades, and turbine vanes. The presentations were divided into six sessions: Instrumentation, Combustion, Turbine Heat Transfer, Structural Analysis, Fatigue and Fracture, and Surface Protection. Topics discussed included modeling of thermal and fluid-flow phenomena, structural analysis, fatigue and fracture, surface protective coatings, constitutive behavior of materials, stress-strain response, and life-prediction methods. Researchers from industry, academia, and government presented results of their work sponsored by the HOST project.

  9. Update on the NASA Glenn Propulsion Systems Lab Ice Crystal Cloud Characterization (2015, 2016)

    NASA Technical Reports Server (NTRS)

    Van Zante, Judith; Bencic, Timothy; Ratvasky, Thomas

    2016-01-01

    NASA Glenn's Propulsion Systems Lab, an altitude engine test facility, was outfitted with a spray system to generate ice crystals in 2011. Turbine engines and driven rigs can experience ice crystal icing at flight altitudes, temperatures and Mach numbers. To support these tests, four ice crystal characterizations have been conducted in two different facility configurations. In addition, super-cooled liquid and mixed phase clouds have also been generated. This paper represents a work in progress. It will describe some of the 11-parameter calibration space, and how those parameters interact with each other, the instrumentation used to characterize the cloud and present a sample of the cloud characterization results.

  10. Altitude Investigation of Gas Temperature Distribution at Turbine of Three Similar Axial-Flow Turbojet Engines

    NASA Technical Reports Server (NTRS)

    Prince, W.R.; Schulze, F.W.

    1952-01-01

    An investigation of the effect of inlet pressure, corrected engine speed, and turbine temperature level on turbine-inlet gas temperature distributions was conducted on a J40-WE-6, interim J40-WE-6, and prototype J40-WE-8 turbojet engine in the altitude wind tunnel at the NAC.4 Lewis laboratory. The engines were investigated over a range of simulated pressure altitudes from 15,000 to 55,000 feet, flight Mach numbers from 0.12 to 0.64, and corrected engine speeds from 7198 to 8026 rpm, The gas temperature distribution at the turbine of the three engines over the range of operating conditions investigated was considered satisfactory from the standpoint of desired temperature distribution with one exception - the distribution for the J40-WE-6 engine indicated a trend with decreasing engine-inlet pressure for the temperature to exceed the desired in the region of the blade hub. Installation of a compressor-outlet mixer vane assembly remedied this undesirable temperature distribution, The experimental data have shown that turbine-inlet temperature distributions are influenced in the expected manner by changes in compressor-outlet pressure or mass-flow distribution and by changes in combustor hole-area distribution. The similarity between turbine-inlet and turbine-outlet temperature distribution indicated only a small shift in temperature distribution imposed by the turbine rotors. The attainable jet thrusts of the three engines were influenced in different degrees and directions by changes in temperature distributions with change in engine-inlet pressure. Inability to match the desired temperature distribution resulted, for the J40-WE-6 engine, in an 11-percent thrust loss based on an average turbine-inlet temperature of 1500 F at an engine-inlet pressure of 500 pounds per square foot absolute. Departure from the desired temperature distribution in the Slade tip region results, for the prototype J40-WE-8 engine, in an attainable thrust increase of 3 to 4 percent as compared with that obtained if tip-region temperature limitations were observed.

  11. Perspective on thermal barrier coatings for industrial gas turbine applications

    NASA Technical Reports Server (NTRS)

    Mutasim, Zaher; Brentnall, William

    1995-01-01

    Thermal barrier coatings (TBC's) have been used in high thrust aircraft engines for many years, and have proved to be very effective in providing thermal protection and increasing engine efficiencies. TBC life requirements for aircraft engines are typically less than those required for industrial gas turbines. This paper describes current and future applications of TBC's in industrial gas turbine engines. Early testing and applications of TBC's is reviewed. Areas of concern from the engine designer's and materials engineer's perspective are identified and evaluated. This paper focuses on the key factors that are expected to influence utilization of TBC's in advanced industrial gas turbine engines. It is anticipated that reliable, durable and highly effective coating systems will be produced that will ultimately improve engine efficiency and performance.

  12. 14 CFR 34.31 - Standards for exhaust emissions.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES Exhaust Emissions (In-use Aircraft Gas Turbine Engines) § 34.31 Standards for exhaust emissions. (a) Exhaust emissions of smoke from each in-use aircraft gas turbine engine of Class T8, beginning February 1, 1974, shall...

  13. 14 CFR 34.21 - Standards for exhaust emissions.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES Exhaust Emissions (New Aircraft Gas Turbine Engines) § 34.21 Standards for exhaust emissions. (a) Exhaust emissions of smoke from each new aircraft gas turbine engine of class T8 manufactured on or after February 1, 1974...

  14. 14 CFR 34.31 - Standards for exhaust emissions.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES Exhaust Emissions (In-use Aircraft Gas Turbine Engines) § 34.31 Standards for exhaust emissions. (a) Exhaust emissions of smoke from each in-use aircraft gas turbine engine of Class T8, beginning February 1, 1974, shall...

  15. 14 CFR 34.31 - Standards for exhaust emissions.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... FUEL VENTING AND EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES Exhaust Emissions (In-use Aircraft Gas Turbine Engines) § 34.31 Standards for exhaust emissions. (a) Exhaust emissions of smoke from each in-use aircraft gas turbine engine of Class T8, beginning February 1, 1974, shall...

  16. 14 CFR 33.62 - Stress analysis.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false Stress analysis. 33.62 Section 33.62... STANDARDS: AIRCRAFT ENGINES Design and Construction; Turbine Aircraft Engines § 33.62 Stress analysis. A stress analysis must be performed on each turbine engine showing the design safety margin of each turbine...

  17. 14 CFR 33.62 - Stress analysis.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false Stress analysis. 33.62 Section 33.62... STANDARDS: AIRCRAFT ENGINES Design and Construction; Turbine Aircraft Engines § 33.62 Stress analysis. A stress analysis must be performed on each turbine engine showing the design safety margin of each turbine...

  18. 14 CFR 33.62 - Stress analysis.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 1 2013-01-01 2013-01-01 false Stress analysis. 33.62 Section 33.62... STANDARDS: AIRCRAFT ENGINES Design and Construction; Turbine Aircraft Engines § 33.62 Stress analysis. A stress analysis must be performed on each turbine engine showing the design safety margin of each turbine...

  19. 78 FR 42758 - 36(b)(1) Arms Sales Notification

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-07-17

    ... aircraft, to include: Inlet/Fan Modules, Core Engine Modules, Rear Compressor Drive Turbines, Fan Drive...-PW-229 engines for the Hellenic Air Force F-16 aircraft, to include: Inlet/Fan Modules, Core Engine Modules, Rear Compressor Drive Turbines, Fan Drive Turbine Modules, Augmentor Duct and Nozzle Modules, and...

  20. 14 CFR 23.1045 - Cooling test procedures for turbine engine powered airplanes.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false Cooling test procedures for turbine engine powered airplanes. 23.1045 Section 23.1045 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... CATEGORY AIRPLANES Powerplant Cooling § 23.1045 Cooling test procedures for turbine engine powered...

  1. 14 CFR 23.1045 - Cooling test procedures for turbine engine powered airplanes.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Cooling test procedures for turbine engine powered airplanes. 23.1045 Section 23.1045 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... CATEGORY AIRPLANES Powerplant Cooling § 23.1045 Cooling test procedures for turbine engine powered...

  2. 14 CFR 34.1 - Definitions.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES General Provisions § 34.1 Definitions... in, or which is manufactured for installation in, an aircraft. Aircraft gas turbine engine means a.... Class T3 means all aircraft gas turbine engines of the JT3D model family. Class T8 means all aircraft...

  3. Gas turbine engines with particle traps

    DOEpatents

    Boyd, Gary L.; Sumner, D. Warren; Sheoran, Yogendra; Judd, Z. Daniel

    1992-01-01

    A gas turbine engine (10) incorporates a particle trap (46) that forms an entrapment region (73) in a plenum (24) which extends from within the combustor (18) to the inlet (32) of a radial-inflow turbine (52, 54). The engine (10) is thereby adapted to entrap particles that originate downstream from the compressor (14) and are otherwise propelled by combustion gas (22) into the turbine (52, 54). Carbonaceous particles that are dislodged from the inner wall (50) of the combustor (18) are incinerated within the entrapment region (73) during operation of the engine (10).

  4. Gas flow path for a gas turbine engine

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Montgomery, Matthew D.; Charron, Richard C.; Snyder, Gary D.

    A duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades A gas flow path is formed by the duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades The duct arrangement includes at least one straight section having a centerline thatmore » is misaligned with a centerline of the combustor.« less

  5. Gasoline-Engine Assembler (engine & turbine) 806.781; Internal-Combustion-Engine-Assembler (engine & turbine) 806.781; Outboard-Motor Assembler (engine & turbine) 806.781--Technical Report on Development of USTES Aptitude Test Battery.

    ERIC Educational Resources Information Center

    Manpower Administration (DOL), Washington, DC. U.S. Training and Employment Service.

    The United States Training and Employment Service General Aptitude Test Battery (GATB), first published in 1947, has been included in a continuing program of research to validate the tests against success in many different occupations. The GATB consists of 12 tests which measure nine aptitudes: General Learning Ability; Verbal Aptitude; Numerical…

  6. Demonstration of Novel Sampling Techniques for Measurement of Turbine Engine Volatile and Non-Volatile Particulate Matter (PM) Emissions

    DTIC Science & Technology

    2015-12-30

    FINAL REPORT Demonstration of Novel Sampling Techniques for Measurement of Turbine Engine Volatile and Non-Volatile Particulate Matter (PM...Novel Sampling Techniques for Measurement of Turbine Engine Volatile and Non-Volatile Particulate Matter (PM) Emissions 6. AUTHOR(S) E. Corporan, M...report contains color. 14. ABSTRACT This project consists of demonstrating the performance and viability of two devices to condition aircraft turbine

  7. Parametric tests of a traction drive retrofitted to an automotive gas turbine

    NASA Technical Reports Server (NTRS)

    Rohn, D. A.; Lowenthal, S. H.; Anderson, N. E.

    1980-01-01

    The results of a test program to retrofit a high performance fixed ratio Nasvytis Multiroller Traction Drive in place of a helical gear set to a gas turbine engine are presented. Parametric tests up to a maximum engine power turbine speed of 45,500 rpm and to a power level of 11 kW were conducted. Comparisons were made to similar drives that were parametrically tested on a back-to-back test stand. The drive showed good compatibility with the gas turbine engine. Specific fuel consumption of the engine with the traction drive speed reducer installed was comparable to the original helical gearset equipped engine.

  8. 78 FR 47581 - Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-08-06

    ... turbine disc. We are proposing this AD to prevent disc cracking, uncontained 2nd-stage turbine blade..., possibly resulting in uncontained second stage turbine blade release with consequent damage to, and reduced...-stage turbine blade release, damage to the engine, and damage to the helicopter. (e) Actions and...

  9. 14 CFR 33.61 - Applicability.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... STANDARDS: AIRCRAFT ENGINES Design and Construction; Turbine Aircraft Engines § 33.61 Applicability. This subpart prescribes additional design and construction requirements for turbine aircraft engines. ...

  10. 14 CFR 33.61 - Applicability.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... STANDARDS: AIRCRAFT ENGINES Design and Construction; Turbine Aircraft Engines § 33.61 Applicability. This subpart prescribes additional design and construction requirements for turbine aircraft engines. ...

  11. 14 CFR 33.61 - Applicability.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... STANDARDS: AIRCRAFT ENGINES Design and Construction; Turbine Aircraft Engines § 33.61 Applicability. This subpart prescribes additional design and construction requirements for turbine aircraft engines. ...

  12. Cost/benefit studies of advanced materials technologies for future aircraft turbine engines: Materials for advanced turbine engines

    NASA Technical Reports Server (NTRS)

    Stearns, M.; Wilbers, L.

    1982-01-01

    Cost benefit studies were conducted on six advanced materials and processes technologies applicable to commercial engines planned for production in the 1985 to 1990 time frame. These technologies consisted of thermal barrier coatings for combustor and high pressure turbine airfoils, directionally solidified eutectic high pressure turbine blades, (both cast and fabricated), and mixers, tail cones, and piping made of titanium-aluminum alloys. A fabricated titanium fan blisk, an advanced turbine disk alloy with improved low cycle fatigue life, and a long-life high pressure turbine blade abrasive tip and ceramic shroud system were also analyzed. Technologies showing considerable promise as to benefits, low development costs, and high probability of success were thermal barrier coating, directionally solidified eutectic turbine blades, and abrasive-tip blades/ceramic-shroud turbine systems.

  13. Inspection system for a turbine blade region of a turbine engine

    DOEpatents

    Smed, Jan P [Winter Springs, FL; Lemieux, Dennis H [Casselberry, FL; Williams, James P [Orlando, FL

    2007-06-19

    An inspection system formed at least from a viewing tube for inspecting aspects of a turbine engine during operation of the turbine engine. An outer housing of the viewing tube may be positioned within a turbine engine using at least one bearing configured to fit into an indentation of a support housing to form a ball and socket joint enabling the viewing tube to move during operation as a result of vibrations and other movements. The viewing tube may also include one or more lenses positioned within the viewing tube for viewing the turbine components. The lenses may be kept free of contamination by maintaining a higher pressure in the viewing tube than a pressure outside of the viewing tube and enabling gases to pass through an aperture in a cap at a viewing end of the viewing tube.

  14. Contingency power for a small turboshaft engine by using water injection into turbine cooling air

    NASA Technical Reports Server (NTRS)

    Biesiadny, Thomas J.; Klann, Gary A.

    1992-01-01

    Because of one-engine-inoperative (OEI) requirements, together with hot-gas reingestion and hot-day, high-altitude take-off situations, power augmentation for multiengine rotorcraft has always been of critical interest. However, power augmentation by using overtemperature at the turbine inlet will shorten turbine life unless a method of limiting thermal and mechanical stress is found. A possible solution involves allowing the turbine inlet temperature to rise to augment power while injecting water into the turbine cooling air to limit hot-section metal temperatures. An experimental water injection device was installed in an engine and successfully tested. Although concern for unprotected subcomponents in the engine hot section prevented demonstration of the technique's maximum potential, it was still possible to demonstrate increases in power while maintaining nearly constant turbine rotor blade temperature.

  15. Space Shuttle Main Engine structural analysis and data reduction/evaluation. Volume 2: High pressure oxidizer turbo-pump turbine end bearing analysis

    NASA Technical Reports Server (NTRS)

    Sisk, Gregory A.

    1989-01-01

    The high-pressure oxidizer turbopump (HPOTP) consists of two centrifugal pumps, on a common shaft, that are directly driven by a hot-gas turbine. Pump shaft axial thrust is balanced in that the double-entry main inducer/impeller is inherently balanced and the thrusts of the preburner pump and turbine are nearly equal but opposite. Residual shaft thrust is controlled by a self-compensating, non-rubbing, balance piston. Shaft hang-up must be avoided if the balance piston is to perform properly. One potential cause of shaft hang-up is contact between the Phase 2 bearing support and axial spring cartridge of the HPOTP main pump housing. The status of the bearing support/axial spring cartridge interface is investigated under current loading conditions. An ANSYS version 4.3, three-dimensional, finite element model was generated on Lockheed's VAX 11/785 computer. A nonlinear thermal analysis was then executed on the Marshall Space Flight Center Engineering Analysis Data System (EADS). These thermal results were then applied along with the interference fit and bolt preloads to the model as load conditions for a static analysis to determine the gap status of the bearing support/axial spring cartridge interface. For possible further analysis of the local regions of HPOTP main pump housing assembly, detailed ANSYS submodels were generated using I-DEAS Geomod and Supertab (Appendix A).

  16. Study of an advanced General Aviation Turbine Engine (GATE)

    NASA Technical Reports Server (NTRS)

    Gill, J. C.; Short, F. R.; Staton, D. V.; Zolezzi, B. A.; Curry, C. E.; Orelup, M. J.; Vaught, J. M.; Humphrey, J. M.

    1979-01-01

    The best technology program for a small, economically viable gas turbine engine applicable to the general aviation helicopter and aircraft market for 1985-1990 was studied. Turboshaft and turboprop engines in the 112 to 746 kW (150 to 1000 hp) range and turbofan engines up to 6672 N (1500 lbf) thrust were considered. A good market for new turbine engines was predicted for 1988 providing aircraft are designed to capitalize on the advantages of the turbine engine. Parametric engine families were defined in terms of design and off-design performance, mass, and cost. These were evaluated in aircraft design missions selected to represent important market segments for fixed and rotary-wing applications. Payoff parameters influenced by engine cycle and configuration changes were aircraft gross mass, acquisition cost, total cost of ownership, and cash flow. Significant advantage over a current technology, small gas turbine engines was found especially in cost of ownership and fuel economy for airframes incorporating an air-cooled high-pressure ratio engine. A power class of 373 kW (500 hp) was recommended as the next frontier for technology advance where large improvements in fuel economy and engine mass appear possible through component research and development.

  17. Analysis of the Challenges and Opportunities of Hydrokinetic Turbine Development Affecting the US Army Corps of Engineers

    DTIC Science & Technology

    2014-08-01

    Hydrokinetic Turbine Development Affecting the US Army Corps of Engineers by David L. Smith, John M. Nestler, Richard Styles, and Brian Tetreault BACKGROUND...attendant environmental impacts. One family of renewable energy technologies experiencing increased national interest is hydrokinetic turbines ...Hydrokinetic turbines include systems that convert waves, tides, and river flow (without impoundment) into electric energy. River hydrokinetic turbines

  18. An overview of aerospace gas turbine technology of relevance to the development of the automotive gas turbine engine

    NASA Technical Reports Server (NTRS)

    Evans, D. G.; Miller, T. J.

    1978-01-01

    Technology areas related to gas turbine propulsion systems with potential for application to the automotive gas turbine engine are discussed. Areas included are: system steady-state and transient performance prediction techniques, compressor and turbine design and performance prediction programs and effects of geometry, combustor technology and advanced concepts, and ceramic coatings and materials technology.

  19. 77 FR 40479 - Airworthiness Directives; Rolls-Royce Corporation Turboshaft Engines

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-07-10

    ... inspection (FPI) on certain 3rd and 4th stage turbine wheels for cracks in the turbine blades. We are issuing this AD to prevent failure of 3rd or 4th stage turbine wheel blades which could cause engine failure... certain 3rd and 4th stage turbine wheels for cracks in the turbine blades. Comments We gave the public the...

  20. Turbulent Coolant Dispersion in the Wake of a Turbine Vane Trailing Edge

    DTIC Science & Technology

    2015-01-01

    turbine vane from a gas turbine engine. The understanding and prediction of the highly three-dimensional flow and heat transfer in a modern gas turbine ...engine is a problem that has not been solved over many years of turbomachinery research. Turbine blades and vanes are both internally and...Approved for public release; distribution is unlimited. Turbulent Coolant Dispersion in the Wake of a Turbine Vane Trailing Edge The views, opinions and/or

  1. Wind-driven roof turbines: a novel way to improve ventilation for TB infection control in health facilities.

    PubMed

    Cox, Helen; Escombe, Rod; McDermid, Cheryl; Mtshemla, Yolanda; Spelman, Tim; Azevedo, Virginia; London, Leslie

    2012-01-01

    Tuberculosis transmission in healthcare facilities contributes significantly to the TB epidemic, particularly in high HIV settings. Although improving ventilation may reduce transmission, there is a lack of evidence to support low-cost practical interventions. We assessed the efficacy of wind-driven roof turbines to achieve recommended ventilation rates, compared to current recommended practices for natural ventilation (opening windows), in primary care clinic rooms in Khayelitsha, South Africa. Room ventilation was assessed (CO₂ gas tracer technique) in 4 rooms where roof turbines and air-intake grates were installed, across three scenarios: turbine, grate and window closed, only window open, and only turbine and grate open, with concurrent wind speed measurement. 332 measurements were conducted over 24 months. For all 4 rooms combined, median air changes per hour (ACH) increased with wind speed quartiles across all scenarios. Higher median ACH were recorded with open roof turbines and grates, compared to open windows across all wind speed quartiles. Ventilation with open turbine and grate exceeded WHO-recommended levels (60 Litres/second/patient) for 95% or more of measurements in 3 of the 4 rooms; 47% in the remaining room, where wind speeds were lower and a smaller diameter turbine was installed. High room ventilation rates, meeting recommended thresholds, may be achieved using wind-driven roof turbines and grates, even at low wind speeds. Roof turbines and air-intake grates are not easily closed by staff, allowing continued ventilation through colder periods. This simple, low-cost technology represents an important addition to our tools for TB infection control.

  2. Wind-Driven Roof Turbines: A Novel Way to Improve Ventilation for TB Infection Control in Health Facilities

    PubMed Central

    Cox, Helen; Escombe, Rod; McDermid, Cheryl; Mtshemla, Yolanda; Spelman, Tim; Azevedo, Virginia; London, Leslie

    2012-01-01

    Objective Tuberculosis transmission in healthcare facilities contributes significantly to the TB epidemic, particularly in high HIV settings. Although improving ventilation may reduce transmission, there is a lack of evidence to support low-cost practical interventions. We assessed the efficacy of wind-driven roof turbines to achieve recommended ventilation rates, compared to current recommended practices for natural ventilation (opening windows), in primary care clinic rooms in Khayelitsha, South Africa. Methods Room ventilation was assessed (CO2 gas tracer technique) in 4 rooms where roof turbines and air-intake grates were installed, across three scenarios: turbine, grate and window closed, only window open, and only turbine and grate open, with concurrent wind speed measurement. 332 measurements were conducted over 24 months. Findings For all 4 rooms combined, median air changes per hour (ACH) increased with wind speed quartiles across all scenarios. Higher median ACH were recorded with open roof turbines and grates, compared to open windows across all wind speed quartiles. Ventilation with open turbine and grate exceeded WHO-recommended levels (60 Litres/second/patient) for 95% or more of measurements in 3 of the 4 rooms; 47% in the remaining room, where wind speeds were lower and a smaller diameter turbine was installed. Conclusion High room ventilation rates, meeting recommended thresholds, may be achieved using wind-driven roof turbines and grates, even at low wind speeds. Roof turbines and air-intake grates are not easily closed by staff, allowing continued ventilation through colder periods. This simple, low-cost technology represents an important addition to our tools for TB infection control. PMID:22253742

  3. 40 CFR 87.31 - Standards for exhaust emissions.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... Gas Turbine Engines) § 87.31 Standards for exhaust emissions. (a) Exhaust emissions of smoke from each in-use aircraft gas turbine engine of Class T8, beginning February 1, 1974, shall not exceed: Smoke number of 30. (b) Exhaust emissions of smoke from each in-use aircraft gas turbine engine of class TF and...

  4. 40 CFR 87.31 - Standards for exhaust emissions.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... Gas Turbine Engines) § 87.31 Standards for exhaust emissions. (a) Exhaust emissions of smoke from each in-use aircraft gas turbine engine of Class T8, beginning February 1, 1974, shall not exceed: Smoke number of 30. (b) Exhaust emissions of smoke from each in-use aircraft gas turbine engine of class TF and...

  5. 40 CFR 87.31 - Standards for exhaust emissions.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... Gas Turbine Engines) § 87.31 Standards for exhaust emissions. (a) Exhaust emissions of smoke from each in-use aircraft gas turbine engine of Class T8, beginning February 1, 1974, shall not exceed: Smoke number of 30. (b) Exhaust emissions of smoke from each in-use aircraft gas turbine engine of class TF and...

  6. 40 CFR 87.31 - Standards for exhaust emissions.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... Gas Turbine Engines) § 87.31 Standards for exhaust emissions. (a) Exhaust emissions of smoke from each in-use aircraft gas turbine engine of Class T8, beginning February 1, 1974, shall not exceed: Smoke number of 30. (b) Exhaust emissions of smoke from each in-use aircraft gas turbine engine of class TF and...

  7. 40 CFR 87.21 - Standards for exhaust emissions.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... (CONTINUED) Definitions. Exhaust Emissions (New Aircraft Gas Turbine Engines) § 87.21 Standards for exhaust... each new aircraft gas turbine engine of class T8 manufactured on or after February 1, 1974, shall not exceed: Smoke number of 30. (b) Exhaust emissions of smoke from each new aircraft gas turbine engine of...

  8. 40 CFR 87.31 - Standards for exhaust emissions.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... (CONTINUED) Definitions. Exhaust Emissions (In-Use Aircraft Gas Turbine Engines) § 87.31 Standards for exhaust emissions. (a) Exhaust emissions of smoke from each in-use aircraft gas turbine engine of Class T8... in-use aircraft gas turbine engine of class TF and of rated output of 129 kilonewtons thrust or...

  9. 14 CFR 34.10 - Applicability.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... In-Use Aircraft Gas Turbine Engines) § 34.10 Applicability. (a) The provisions of this subpart are applicable to all new aircraft gas turbine engines of classes T3, T8, TSS, and TF equal to or greater than 36... applicable to all new aircraft gas turbine engines of class TF less than 36 kilonewtons (8090 pounds) rated...

  10. 14 CFR 34.21 - Standards for exhaust emissions.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... (New Aircraft Gas Turbine Engines) § 34.21 Standards for exhaust emissions. (a) Exhaust emissions of smoke from each new aircraft gas turbine engine of class T8 manufactured on or after February 1, 1974...) Exhaust emission of smoke from each new aircraft gas turbine engine of class T3 manufactured on or after...

  11. 14 CFR 34.21 - Standards for exhaust emissions.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... (New Aircraft Gas Turbine Engines) § 34.21 Standards for exhaust emissions. (a) Exhaust emissions of smoke from each new aircraft gas turbine engine of class T8 manufactured on or after February 1, 1974...) Exhaust emission of smoke from each new aircraft gas turbine engine of class T3 manufactured on or after...

  12. 14 CFR 34.10 - Applicability.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... In-Use Aircraft Gas Turbine Engines) § 34.10 Applicability. (a) The provisions of this subpart are applicable to all new aircraft gas turbine engines of classes T3, T8, TSS, and TF equal to or greater than 36... applicable to all new aircraft gas turbine engines of class TF less than 36 kilonewtons (8090 pounds) rated...

  13. 14 CFR 25.1127 - Exhaust driven turbo-superchargers.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... flexibility between exhaust conduits and the turbine. (b) There must be provisions for lubricating the turbine and for cooling turbine parts where temperatures are critical. (c) If the normal turbo-supercharger control system malfunctions, the turbine speed may not exceed its maximum allowable value. Except for the...

  14. 14 CFR 25.1127 - Exhaust driven turbo-superchargers.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... flexibility between exhaust conduits and the turbine. (b) There must be provisions for lubricating the turbine and for cooling turbine parts where temperatures are critical. (c) If the normal turbo-supercharger control system malfunctions, the turbine speed may not exceed its maximum allowable value. Except for the...

  15. 14 CFR 25.1127 - Exhaust driven turbo-superchargers.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... flexibility between exhaust conduits and the turbine. (b) There must be provisions for lubricating the turbine and for cooling turbine parts where temperatures are critical. (c) If the normal turbo-supercharger control system malfunctions, the turbine speed may not exceed its maximum allowable value. Except for the...

  16. Advanced technology payoffs for future rotorcraft, commuter aircraft, cruise missile, and APU propulsion systems

    NASA Technical Reports Server (NTRS)

    Turk, M. A.; Zeiner, P. K.

    1986-01-01

    In connection with the significant advances made regarding the performance of larger gas turbines, challenges arise concerning the improvement of small gas turbine engines in the 250 to 1000 horsepower range. In response to these challenges, the NASA/Army-sponsored Small Engine Component Technology (SECT) study was undertaken with the objective to identify the engine cycle, configuration, and component technology requirements for the substantial performance improvements desired in year-2000 small gas turbine engines. In the context of this objective, an American turbine engine company evaluated engines for four year-2000 applications, including a rotorcraft, a commuter aircraft, a supersonic cruise missile, and an auxiliary power unit (APU). Attention is given to reference missions, reference engines, reference aircraft, year-2000 technology projections, cycle studies, advanced engine selections, and a technology evaluation.

  17. Substitution of ceramics for high temperature alloys. [advantages of using silicon carbides and silicon nitrides in gas turbine engines

    NASA Technical Reports Server (NTRS)

    Probst, H. B.

    1978-01-01

    The high temperature capability of ceramics such as silicon nitride and silicon carbide can result in turbine engines of improved efficiency. Other advantages when compared to the nickel and cobalt alloys in current use are raw material availability, lower weight, erosion/corrosion resistance, and potentially lower cost. The use of ceramics in three different sizes of gas turbine is considered; these are the large utility turbines, advanced aircraft turbines, and small automotive turbines. Special consideration, unique to each of these applications, arise when one considers substituting ceramics for high temperature alloys. The effects of material substitutions are reviewed in terms of engine performance, operating economy, and secondary effects.

  18. Thermal barrier coatings for gas turbine and diesel engines

    NASA Technical Reports Server (NTRS)

    Miller, Robert A.; Brindley, William J.; Bailey, M. Murray

    1989-01-01

    The present state of development of thin thermal barrier coatings for aircraft gas turbine engines and thick thermal barrier coatings for truck diesel engines is assessed. Although current thermal barrier coatings are flying in certain gas turbine engines, additional advances will be needed for future engines. Thick thermal barrier coatings for truck diesel engines have advanced to the point where they are being seriously considered for the next generation of engine. Since coatings for truck engines is a young field of inquiry, continued research and development efforts will be required to help bring this technology to commercialization.

  19. Self-balancing air riding seal for a turbine

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Mills, Jacob A.

    A turbine of a gas turbine engine has an air riding seal that forms a seal between a rotor and a stator of the turbine, the air riding seal including an annular piston movable in an axial direction under the influence of a pressure on one side with a pressure acting on an opposite side that self-balances the air riding seal during the steady state condition of the engine and lifts off the seal during engine transients.

  20. Surface Modification Concepts for Enhancement of the High-Temperature Corrosion Resistance of Gas Turbine Superalloys,

    DTIC Science & Technology

    1980-12-01

    now developed to the point where they could be considered as true engineering materials. ** Nickel-based alloys are used for turbine blading and...Introduction Implicit in the design of modern gas turbine engines is the premise that their aerofoil components, made of nickel- and cobalt-based...the deposit. Hot corrosion is a principal process of degradation of aerofoil surface integrity in gas turbine engines . 2.2 Mechanisms of Hot Corrosion

  1. Ceramic applications in turbine engines

    NASA Technical Reports Server (NTRS)

    Helms, H. E.; Heitman, P. W.; Lindgren, L. C.; Thrasher, S. R.

    1984-01-01

    The application of ceramic components to demonstrate improved cycle efficiency by raising the operating temperature of the existing Allison IGI 404 vehicular gas turbine engine is discussed. This effort was called the Ceramic Applications in Turbine Engines (CATE) program and has successfully demonstrated ceramic components. Among these components are two design configurations featuring stationary and rotating caramic components in the IGT 404 engine. A complete discussion of all phases of the program, design, materials development, fabrication of ceramic components, and testing-including rig, engine, and vehicle demonstation test are presented. During the CATE program, a ceramic technology base was established that is now being applied to automotive and other gas turbine engine programs. This technology base is outlined and also provides a description of the CATE program accomplishments.

  2. Adaptation of a Turbine Test Facility to High-Temperature Research (Adaptation d’un banc de Turbine aux Recherches pour les Hautes Temperatures,

    DTIC Science & Technology

    1980-12-19

    Des hautes temperatures devant turbine sur turborgacteur et turbines A gaz. (High turbine inlet temperatures in turbo - jet engines and gas turbines ... turbo - jet engines .) Revue Gn(rale de Thermique, No. 166, October 1975 15 D. Arnal Etude exprimentale et thgorique de la transition de la couche J.C...r AD-AIOl 374 ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUBH (ENGLAND) F/B 10/1 ADAPTATION OF A TURBINE TEST FACILITY TO HIGH-TEMPERATURE RESEA--ETC(U) DEC

  3. A Study on Aircraft Structure and Jet Engine

    NASA Astrophysics Data System (ADS)

    Park, Gil Moon; Park, Hwan Kyu; Kim, Jong Il; Kim, Jin Won; Kim, Jin Heung; Lee, Moo Seok; Chung, Nak Kyu

    1985-12-01

    The one of critical factor in gas turbine engine performance is high turbine inlet gas temperature. Therefore, the turbine rotor has so many problems which must be considered such as the turbine blade cooling, thermal stress of turbine disk due to severe temperature gradient, turbine rotor tip clearance, under the high operation temperature. The purpose of this study is to provide the temperature distribution and heat flux in turbine disk which is required to considered premensioned problem by the Finite Difference Method and the Finite Element Methods on the steady state condition.

  4. Proactive monitoring of an onshore wind farm through lidar measurements, SCADA data and a data-driven RANS solver

    NASA Astrophysics Data System (ADS)

    Iungo, Giacomo Valerio; Camarri, Simone; Ciri, Umberto; El-Asha, Said; Leonardi, Stefano; Rotea, Mario A.; Santhanagopalan, Vignesh; Viola, Francesco; Zhan, Lu

    2016-11-01

    Site conditions, such as topography and local climate, as well as wind farm layout strongly affect performance of a wind power plant. Therefore, predictions of wake interactions and their effects on power production still remain a great challenge in wind energy. For this study, an onshore wind turbine array was monitored through lidar measurements, SCADA and met-tower data. Power losses due to wake interactions were estimated to be approximately 4% and 2% of the total power production under stable and convective conditions, respectively. This dataset was then leveraged for the calibration of a data driven RANS (DDRANS) solver, which is a compelling tool for prediction of wind turbine wakes and power production. DDRANS is characterized by a computational cost as low as that for engineering wake models, and adequate accuracy achieved through data-driven tuning of the turbulence closure model. DDRANS is based on a parabolic formulation, axisymmetry and boundary layer approximations, which allow achieving low computational costs. The turbulence closure model consists in a mixing length model, which is optimally calibrated with the experimental dataset. Assessment of DDRANS is then performed through lidar and SCADA data for different atmospheric conditions. This material is based upon work supported by the National Science Foundation under the I/UCRC WindSTAR, NSF Award IIP 1362033.

  5. 14 CFR 33.84 - Engine overtorque test.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Engine overtorque test. 33.84 Section 33.84... STANDARDS: AIRCRAFT ENGINES Block Tests; Turbine Aircraft Engines § 33.84 Engine overtorque test. (a) If approval of a maximum engine overtorque is sought for an engine incorporating a free power turbine...

  6. Nonintrusive transceiver and method for characterizing temperature and velocity fields in a gas turbine combustor

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    DeSilva, Upul P.; Claussen, Heiko

    An acoustic transceiver is implemented for measuring acoustic properties of a gas in a turbine engine combustor. The transceiver housing defines a measurement chamber and has an opening adapted for attachment to a turbine engine combustor wall. The opening permits propagation of acoustic signals between the gas in the turbine engine combustor and gas in the measurement chamber. An acoustic sensor mounted to the housing receives acoustic signals propagating in the measurement chamber, and an acoustic transmitter mounted to the housing creates acoustic signals within the measurement chamber. An acoustic measurement system includes at least two such transceivers attached tomore » a turbine engine combustor wall and connected to a controller.« less

  7. Gas Turbine Characteristics for a Large Civil Tilt-Rotor (LCTR)

    NASA Technical Reports Server (NTRS)

    Snyder, Christopher A.; Thurman, Douglas R.

    2010-01-01

    In support of the Fundamental Aeronautics Program, Subsonic Rotary Wing Project; an engine system study has been undertaken to help define and understand some of the major gas turbine engine parameters required to meet performance and weight requirements as defined by earlier vehicle system studies. These previous vehicle studies will be reviewed to help define gas turbine performance goals. Assumptions and analysis methods used will be described. Performance and weight estimates for a few conceptual gas turbine engines meeting these requirements will be given and discussed. Estimated performance for these conceptual engines over a wide speed variation (down to 50 percent power turbine rpm at high torque) will be presented. Finally, areas needing further effort will be suggested and discussed.

  8. Investigations of thermal barrier coatings of turbine parts using gas flame heating

    NASA Astrophysics Data System (ADS)

    Lepeshkin, A. R.; Bichkov, N. G.; Ilinskaja, O. I.; Nazarov, V. V.

    2017-09-01

    The development of methods for the calculated and experimental investigations thermal barrier coatings and thermal state of gas-turbine engine parts with a thermal barrier coatings is actual work. The gas flame heating was demonstrated to be effectively used during investigations of a thermal ceramic barrier coatings and thermal state of such gas-turbine engine parts with a TBC as the cooled turbine blades and vanes and combustion liner components. The gas-flame heating is considered to be preferable when investigating the gas-turbine engine parts with a TBC in the special cases when both the convective and radiant components of thermal flow are of great importance. The small-size rig with gas-flame flow made it possible to conduct the comparison investigations with the purpose of evaluating the efficiency of thermal protection of the ceramic deposited thermal barrier coatings on APS and EB techniques. The developed design-experiment method was introduced in bench tests of turbine blades and combustion liner components of gas turbine engines.

  9. High temperature turbine engine structure

    DOEpatents

    Carruthers, William D.; Boyd, Gary L.

    1994-01-01

    A high temperature ceramic/metallic turbine engine includes a metallic housing which journals a rotor member of the turbine engine. A ceramic disk-like shroud portion of the engine is supported on the metallic housing portion and maintains a close running clearance with the rotor member. A ceramic spacer assembly maintains the close running clearance of the shroud portion and rotor member despite differential thermal movements between the shroud portion and metallic housing portion.

  10. High temperature turbine engine structure

    DOEpatents

    Carruthers, William D.; Boyd, Gary L.

    1992-01-01

    A high temperature ceramic/metallic turbine engine includes a metallic housing which journals a rotor member of the turbine engine. A ceramic disk-like shroud portion of the engine is supported on the metallic housing portion and maintains a close running clearance with the rotor member. A ceramic spacer assembly maintains the close running clearance of the shroud portion and rotor member despite differential thermal movements between the shroud portion and metallic housing portion.

  11. High temperature turbine engine structure

    DOEpatents

    Carruthers, William D.; Boyd, Gary L.

    1993-01-01

    A high temperature ceramic/metallic turbine engine includes a metallic housing which journals a rotor member of the turbine engine. A ceramic disk-like shroud portion of the engine is supported on the metallic housing portion and maintains a close running clearance with the rotor member. A ceramic spacer assembly maintains the close running clearance of the shroud portion and rotor member despite differential thermal movements between the shroud portion and metallic housing portion.

  12. A Fully Non-Metallic Gas Turbine Engine Enabled by Additive Manufacturing

    NASA Technical Reports Server (NTRS)

    Grady, Joseph E.; Halbig, Michael C.; Singh, Mrityunjay

    2015-01-01

    In a NASA Aeronautics Research Institute (NARI) sponsored program entitled "A Fully Non-Metallic Gas Turbine Engine Enabled by Additive Manufacturing," evaluation of emerging materials and additive manufacturing technologies was carried out. These technologies may enable fully non-metallic gas turbine engines in the future. This paper highlights the results of engine system trade studies which were carried out to estimate reduction in engine emissions and fuel burn enabled due to advanced materials and manufacturing processes. A number of key engine components were identified in which advanced materials and additive manufacturing processes would provide the most significant benefits to engine operation. In addition, feasibility of using additive manufacturing technologies to fabricate gas turbine engine components from polymer and ceramic matrix composite were demonstrated. A wide variety of prototype components (inlet guide vanes (IGV), acoustic liners, engine access door, were additively manufactured using high temperature polymer materials. Ceramic matrix composite components included first stage nozzle segments and high pressure turbine nozzle segments for a cooled doublet vane. In addition, IGVs and acoustic liners were tested in simulated engine conditions in test rigs. The test results are reported and discussed in detail.

  13. A Fully Non-Metallic Gas Turbine Engine Enabled by Additive Manufacturing

    NASA Technical Reports Server (NTRS)

    Grady, Joseph E.; Halbig, Michael C.; Singh, Mrityunjay

    2015-01-01

    In a NASA Aeronautics Research Institute (NARI) sponsored program entitled "A Fully Non-Metallic Gas Turbine Engine Enabled by Additive Manufacturing", evaluation of emerging materials and additive manufacturing technologies was carried out. These technologies may enable fully non-metallic gas turbine engines in the future. This paper highlights the results of engine system trade studies which were carried out to estimate reduction in engine emissions and fuel burn enabled due to advanced materials and manufacturing processes. A number of key engine components were identified in which advanced materials and additive manufacturing processes would provide the most significant benefits to engine operation. In addition, feasibility of using additive manufacturing technologies to fabricate gas turbine engine components from polymer and ceramic matrix composite were demonstrated. A wide variety of prototype components (inlet guide vanes (IGV), acoustic liners, engine access door) were additively manufactured using high temperature polymer materials. Ceramic matrix composite components included first stage nozzle segments and high pressure turbine nozzle segments for a cooled doublet vane. In addition, IGVs and acoustic liners were tested in simulated engine conditions in test rigs. The test results are reported and discussed in detail.

  14. 40 CFR 87.1 - Definitions.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... engines. Class TF means all turbofan or turbojet aircraft engines or aircraft engines designed for... turbine engines employed for propulsion of aircraft designed to operate at supersonic flight speeds... Model means all commercial aircraft turbine engines which are of the same general series, displacement...

  15. 40 CFR 87.1 - Definitions.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... engines. Class TF means all turbofan or turbojet aircraft engines or aircraft engines designed for... turbine engines employed for propulsion of aircraft designed to operate at supersonic flight speeds... Model means all commercial aircraft turbine engines which are of the same general series, displacement...

  16. 40 CFR 87.1 - Definitions.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... engines. Class TF means all turbofan or turbojet aircraft engines or aircraft engines designed for... turbine engines employed for propulsion of aircraft designed to operate at supersonic flight speeds... Model means all commercial aircraft turbine engines which are of the same general series, displacement...

  17. Cost/benefit analysis of advanced material technologies for small aircraft turbine engines

    NASA Technical Reports Server (NTRS)

    Comey, D. H.

    1977-01-01

    Cost/benefit studies were conducted on ten advanced material technologies applicable to small aircraft gas turbine engines to be produced in the 1985 time frame. The cost/benefit studies were applied to a two engine, business-type jet aircraft in the 6800- to 9100-Kg (15,000- to 20,000-lb) gross weight class. The new material technologies are intended to provide improvements in the areas of high-pressure turbine rotor components, high-pressure turbine rotor components, high-pressure turbine stator airfoils, and static structural components. The cost/benefit of each technology is presented in terms of relative value, which is defined as a change in life cycle cost times probability of success divided by development cost. Technologies showing the most promising cost/benefits based on relative value are uncooled single crystal MAR-M 247 turbine blades, cooled DS MAR-M 247 turbine blades, and cooled ODS 'M'CrAl laminate turbine stator vanes.

  18. Cold flow testing of the Space Shuttle Main Engine high pressure fuel turbine model

    NASA Technical Reports Server (NTRS)

    Hudson, Susan T.; Gaddis, Stephen W.; Johnson, P. D.; Boynton, James L.

    1991-01-01

    In order to experimentally determine the performance of the Space Shuttle Main Engine (SSME) High Pressure Fuel Turbopump (HPFTP) turbine, a 'cold' air flow turbine test program was established at NASA's Marshall Space Flight Center. As part of this test program, a baseline test of Rocketdyne's HPFTP turbine has been completed. The turbine performance and turbine diagnostics such as airfoil surface static pressure distributions, static pressure drops through the turbine, and exit swirl angles were investigated at the turbine design point, over its operating range, and at extreme off-design points. The data was compared to pretest predictions with good results. The test data has been used to improve meanline prediction codes and is now being used to validate various three-dimensional codes. The data will also be scaled to engine conditions and used to improve the SSME steady-state performance model.

  19. Cold-air performance of the compressor-drive turbine of the Department of Energy baseline automobile gas-turbine engine

    NASA Technical Reports Server (NTRS)

    Roelke, R. J.; Mclallin, K. L.

    1978-01-01

    The aerodynamic performance of the compressor-drive turbine of the DOE baseline gas-turbine engine was determined over a range of pressure ratios and speeds. In addition, static pressures were measured in the diffusing transition duct located immediately downstream of the turbine. Results are presented in terms of mass flow, torque, specific work, and efficiency for the turbine and in terms of pressure recovery and effectiveness for the transition duct.

  20. CF6 Jet Engine Performance Improvement Program: High Pressure Turbine Aerodynamic Performance Improvement

    NASA Technical Reports Server (NTRS)

    Fasching, W. A.

    1980-01-01

    The improved single shank high pressure turbine design was evaluated in component tests consisting of performance, heat transfer and mechanical tests, and in core engine tests. The instrumented core engine test verified the thermal, mechanical, and aeromechanical characteristics of the improved turbine design. An endurance test subjected the improved single shank turbine to 1000 simulated flight cycles, the equivalent of approximately 3000 hours of typical airline service. Initial back-to-back engine tests demonstrated an improvement in cruise sfc of 1.3% and a reduction in exhaust gas temperature of 10 C. An additional improvement of 0.3% in cruise sfc and 6 C in EGT is projected for long service engines.

  1. Progress toward determining the potential of ODS alloys for gas turbine applications

    NASA Technical Reports Server (NTRS)

    Dreshfield, R. L.; Hoppin, G., III; Sheffler, K.

    1983-01-01

    The Materials for Advanced Turbine Engine (MATE) Program managed by the NASA Lewis Research Center is supporting two projects to evaluate the potential of oxide dispersion strengthened (ODS) alloys for aircraft gas turbine applications. One project involves the evaluation of Incoloy (TM) MA-956 for application as a combustor liner material. An assessment of advanced engine potential will be conducted by means of a test in a P&WA 2037 turbofan engine. The other project involves the evaluation of Inconel (TM) MA 6000 for application as a high pressure turbine blade material and includes a test in a Garrett TFE 731 turbofan engine. Both projects are progressing toward these engine tests in 1984.

  2. Electrospark Deposition for Depot- and Field-Level Component Repair and Replacement of Hard Chromium Plating

    DTIC Science & Technology

    2006-09-07

    aircraft repairs, including: 1. Single crystal turbine blade for two gas turbine engines ( FAA approved repair) 2. Second stage gas turbine blade ...gas turbine engine components. These include (a) application of corrosion resistant coatings to turbine blade tips where protective diffusion...base materials on many functional components (e.g., Ni-base superalloys, stainless steels, Monel, titanium alloys), thus allowing for self-repair

  3. Low Cost Process for Manufacture of Oxide Dispersion Strengthened (ODS) Turbine Nozzle Components.

    DTIC Science & Technology

    1979-12-01

    SWTTPROCESS FORJIANUFACTURE OF9OXIDE)ISPERSIONSTRENGTHENED (ODS) O0 TURBINE !IJOZZLE COMPONENTS, -- , General Electric Company Aircraft Engine Group...machining processes for low pressure turbine (LPT) vanes , high pressure turbine (HPT) vanes , and HPT band segments for the F101 engine . The primary intent...for aircraft turbine nozzle components. These processes were shown capable of maintaining required microstructures and properties for the vane and

  4. Effects of Front-Loading and Stagger Angle on Endwall Losses of High Lift Low Pressure Turbine Vanes

    DTIC Science & Technology

    2012-09-01

    TURBINE VANES DISSERTATION Presented to the Faculty Department of Aeronautical and Astronautical... Engineering and Management iv AFIT/DS/ENY/12-05 Abstract Past efforts to reduce the airfoil count in low pressure turbines have produced high lift...LOSSES OF HIGH LIFT LOW PRESSURE TURBINE VANES 1. Introduction The low pressure turbine (LPT) in modern high bypass ratio aero- engines is

  5. 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.

  6. A thermoacoustic Stirling heat engine

    NASA Astrophysics Data System (ADS)

    Backhaus, S.; Swift, G. W.

    1999-05-01

    Electrical and mechanical power, together with other forms of useful work, are generated worldwide at a rate of about 1012 watts, mostly using heat engines. The efficiency of such engines is limited by the laws of thermodynamics and by practical considerations such as the cost of building and operating them. Engines with high efficiency help to conserve fossil fuels and other natural resources, reducing global-warming emissions and pollutants. In practice, the highest efficiencies are obtained only in the most expensive, sophisticated engines, such as the turbines in central utility electrical plants. Here we demonstrate an inexpensive thermoacoustic engine that employs the inherently efficient Stirling cycle. The design is based on a simple acoustic apparatus with no moving parts. Our first small laboratory prototype, constructed using inexpensive hardware (steel pipes), achieves an efficiency of 0.30, which exceeds the values of 0.10-0.25 attained in other heat engines, with no moving parts. Moreover, the efficiency of our prototype is comparable to that of the common internal combustion engine (0.25-0.40) and piston-driven Stirling engines, (0.20-0.38).

  7. 14 CFR 34.81 - Fuel specifications.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES Test Procedures for Engine Smoke Emissions (Aircraft Gas Turbine Engines) § 34.81 Fuel specifications. Fuel having specifications as provided...

  8. 14 CFR 34.60 - Introduction.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... EXHAUST EMISSION REQUIREMENTS FOR TURBINE ENGINE POWERED AIRPLANES Test Procedures for Engine Exhaust Gaseous Emissions (Aircraft and Aircraft Gas Turbine Engines) § 34.60 Introduction. (a) Use the equipment...

  9. Erosion-Resistant Nanocoatings for Improved Energy Efficiency in Gas Turbine Engines

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    None

    2009-06-01

    This factsheet describes a research project whose goal is to test and substantiate erosion-resistant (ER) nanocoatings for application on compressor airfoils for gas turbine engines in both industrial gas turbines and commercial aviation.

  10. Simulation of the Effects of Cooling Techniques on Turbine Blade Heat Transfer

    NASA Astrophysics Data System (ADS)

    Shaw, Vince; Fatuzzo, Marco

    Increases in the performance demands of turbo machinery has stimulated the development many new technologies over the last half century. With applications that spread beyond marine, aviation, and power generation, improvements in gas turbine technologies provide a vast impact. High temperatures within the combustion chamber of the gas turbine engine are known to cause an increase in thermal efficiency and power produced by the engine. However, since operating temperatures of these engines reach above 1000 K within the turbine section, the need for advances in material science and cooling techniques to produce functioning engines under these high thermal and dynamic stresses is crucial. As with all research and development, costs related to the production of prototypes can be reduced through the use of computational simulations. By making use of Ansys Simulation Software, the effects of turbine cooling techniques were analyzed. Simulation of the Effects of Cooling Techniques on Turbine Blade Heat Transfer.

  11. Internal combustion engine system having a power turbine with a broad efficiency range

    DOEpatents

    Whiting, Todd Mathew; Vuk, Carl Thomas

    2010-04-13

    An engine system incorporating an air breathing, reciprocating internal combustion engine having an inlet for air and an exhaust for products of combustion. A centripetal turbine receives products of the combustion and has a housing in which a turbine wheel is rotatable. The housing has first and second passages leading from the inlet to discrete, approximately 180.degree., portions of the circumference of the turbine wheel. The passages have fixed vanes adjacent the periphery of the turbine wheel and the angle of the vanes in one of the passages is different than those in the other so as to accommodate different power levels providing optimum approach angles between the gases passing the vanes and the blades of the turbine wheel. Flow through the passages is controlled by a flapper valve to direct it to one or the other or both passages depending upon the load factor for the engine.

  12. Thin-film sensors for space propulsion technology: Fabrication and preparation for testing

    NASA Technical Reports Server (NTRS)

    Kim, Walter S.; Hepp, Aloysius F.

    1989-01-01

    The goal of this work is to develop and test thin-film thermocouples for Space Shuttle Main Engine (SSME) components. Thin-film thermocouples have been developed for aircraft gas turbine engines and are in use for temperature measurement on turbine blades up to 1800 F. Established aircraft engine gas turbine technology is currently being adapted to turbine engine blade materials and the environment encountered in the SSME, especially severe thermal shock from cryogenic fuel to combustion temperatures. Initial results using coupons of MAR M-246 (+Hf) and PWA 1480 have been followed by fabrication of thin-film thermocouples on SSME turbine blades. Current efforts are focused on preparing for testing in the Turbine Blade Tester at the NASA Marshall Space Flight Center (MSFC). Future work will include testing of thin-film thermocouples on SSME blades of single crystal PWA 1480 at MSFC.

  13. Advanced Seal Development for Large Industrial Gas Turbines

    NASA Technical Reports Server (NTRS)

    Chupp, Raymond E.

    2006-01-01

    Efforts are in progress to develop advanced sealing for large utility industrial gas turbine engines (combustion turbines). Such seals have been under developed for some time for aero gas turbines. It is desired to transition this technology to combustion turbines. Brush seals, film riding face and circumferential seals, and other dynamic and static sealing approaches are being incorporated into gas turbines for aero applications by several engine manufacturers. These seals replace labyrinth or other seals with significantly reduced leakage rates. For utility industrial gas turbines, leakage reduction with advanced sealing can be even greater with the enormous size of the components. Challenges to transitioning technology include: extremely long operating times between overhauls; infrequent but large radial and axial excursions; difficulty in coating larger components; and maintenance, installation, and durability requirements. Advanced sealing is part of the Advanced Turbine Systems (ATS) engine development being done under a cooperative agreement between Westinghouse and the US Department of Energy, Office of Fossil Energy. Seal development focuses on various types of seals in the 501ATS engine both at dynamic and static locations. Each development includes rig testing of candidate designs and subsequent engine validation testing of prototype seals. This presentation gives an update of the ongoing ATS sealing efforts with special emphasis on brush seals.

  14. 40 CFR 87.21 - Standards for exhaust emissions.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... aircraft gas turbine engine of class T8 manufactured on or after February 1, 1974, shall not exceed: Smoke number of 30. (b) Exhaust emissions of smoke from each new aircraft gas turbine engine of class TF and of... gas turbine engine of class T3 manufactured on or after January 1, 1978, shall not exceed: Smoke...

  15. 40 CFR 87.21 - Standards for exhaust emissions.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... aircraft gas turbine engine of class T8 manufactured on or after February 1, 1974, shall not exceed: Smoke number of 30. (b) Exhaust emissions of smoke from each new aircraft gas turbine engine of class TF and of... gas turbine engine of class T3 manufactured on or after January 1, 1978, shall not exceed: Smoke...

  16. 46 CFR 11.524 - Service requirements for national endorsement as designated duty engineer (DDE) of steam, motor...

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... designated duty engineer (DDE) of steam, motor, and/or gas turbine-propelled vessels. 11.524 Section 11.524... requirements for national endorsement as designated duty engineer (DDE) of steam, motor, and/or gas turbine... steam, motor, and/or gas turbine-propelled vessels of unlimited propulsion power, the applicant must...

  17. 40 CFR 87.10 - Applicability.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    .... Engine Fuel Venting Emissions (New and In-Use Aircraft Gas Turbine Engines) § 87.10 Applicability. (a) The provisions of this subpart are applicable to all new aircraft gas turbines of classes T3, T8, TSS..., and to all in-use aircraft gas turbine engines of classes T3, T8, TSS and TF equal to or greater than...

  18. CF6 jet engine performance improvement program. Task 1: Feasibility analysis

    NASA Technical Reports Server (NTRS)

    Fasching, W. A.

    1979-01-01

    Technical and economic engine improvement concepts selected for subsequent development include: (1) fan improvement; (2) short core exhaust; (3) HP turbine aerodynamic improvement; (4) HP turbine roundness control; (5) HP turbine active clearance control; and (6) cabin air recirculation. The fuel savings for the selected engine modification concepts for the CF6 fleet are estimated.

  19. 36th International Symposium on Combustion (ISOC2016)

    DTIC Science & Technology

    2016-12-01

    GREENHOUSE GASES / IC ENGINE COMBUSTION I GAS TURBINE COMBUSTION I NOVEL COMBUSTION CONCEPTS, TECHNOLOGIES AND SYSTEMS 15. SUBJECT TERMS Reaction...pollutants and greenhouse gases; IC engine combustion; Gas turbine combustion; Novel combustion concepts, technologies and systems 16. SECURITY...PLENARY LECTURE TRANSFER (15 min) am Turbulent Flames IC Engines Laminar Flames Reaction Kinetics Gas Turbines Soot Solid Fuels/Pollutants

  20. 76 FR 25300 - Foreign-Trade Zone 141-Rochester, NY; Application for Manufacturing Authority, Firth Rixson, Inc...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-04

    ... County (see Docket 29-2011). The facility is used to produce aircraft turbine engine components of forged... aircraft turbine engines for the U.S. market and export. The manufacturing process under FTZ procedures... procedures that applies to aircraft turbine engine components and forged rings of titanium (duty rates--free...

  1. 14 CFR 121.645 - Fuel supply: Turbine-engine powered airplanes, other than turbo propeller: Flag and supplemental...

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Fuel supply: Turbine-engine powered airplanes, other than turbo propeller: Flag and supplemental operations. 121.645 Section 121.645 Aeronautics... SUPPLEMENTAL OPERATIONS Dispatching and Flight Release Rules § 121.645 Fuel supply: Turbine-engine powered...

  2. 14 CFR 121.645 - Fuel supply: Turbine-engine powered airplanes, other than turbo propeller: Flag and supplemental...

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Fuel supply: Turbine-engine powered airplanes, other than turbo propeller: Flag and supplemental operations. 121.645 Section 121.645 Aeronautics... SUPPLEMENTAL OPERATIONS Dispatching and Flight Release Rules § 121.645 Fuel supply: Turbine-engine powered...

  3. 14 CFR 121.645 - Fuel supply: Turbine-engine powered airplanes, other than turbo propeller: Flag and supplemental...

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Fuel supply: Turbine-engine powered airplanes, other than turbo propeller: Flag and supplemental operations. 121.645 Section 121.645 Aeronautics... SUPPLEMENTAL OPERATIONS Dispatching and Flight Release Rules § 121.645 Fuel supply: Turbine-engine powered...

  4. 76 FR 78863 - Airworthiness Directives; Rolls-Royce Corporation Turboshaft Engines

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-12-20

    ... engines. This proposed AD was prompted by seven cases reported of released turbine blades and shrouds... wheels for cracks in the turbine blades. We are proposing this AD to prevent failure of 3rd or 4th stage turbine wheel blades which could cause engine failure and damage to the airplane. DATES: We must receive...

  5. 14 CFR 27.1093 - Induction system icing protection.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ...— (i) 100 degrees F.; or (ii) If a fluid deicing system is used, at least 40 degrees F. (b) Turbine engine. (1) It must be shown that each turbine engine and its air inlet system can operate throughout the.... (2) Each turbine engine must idle for 30 minutes on the ground, with the air bleed available for...

  6. 14 CFR 23.1093 - Induction system icing protection.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 75 percent of its maximum continuous power. (b) Turbine engines. (1) Each turbine engine and its air... established for the airplane for such operation. (2) Each turbine engine must idle for 30 minutes on the...) and has a liquid water content not less than 0.3 grams per cubic meter in the form of drops having a...

  7. 14 CFR 23.1093 - Induction system icing protection.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 75 percent of its maximum continuous power. (b) Turbine engines. (1) Each turbine engine and its air... established for the airplane for such operation. (2) Each turbine engine must idle for 30 minutes on the...) and has a liquid water content not less than 0.3 grams per cubic meter in the form of drops having a...

  8. 14 CFR 27.1093 - Induction system icing protection.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ...— (i) 100 degrees F.; or (ii) If a fluid deicing system is used, at least 40 degrees F. (b) Turbine engine. (1) It must be shown that each turbine engine and its air inlet system can operate throughout the.... (2) Each turbine engine must idle for 30 minutes on the ground, with the air bleed available for...

  9. 14 CFR 23.1093 - Induction system icing protection.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 75 percent of its maximum continuous power. (b) Turbine engines. (1) Each turbine engine and its air... established for the airplane for such operation. (2) Each turbine engine must idle for 30 minutes on the...) and has a liquid water content not less than 0.3 grams per cubic meter in the form of drops having a...

  10. 14 CFR 27.1093 - Induction system icing protection.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ...— (i) 100 degrees F.; or (ii) If a fluid deicing system is used, at least 40 degrees F. (b) Turbine engine. (1) It must be shown that each turbine engine and its air inlet system can operate throughout the.... (2) Each turbine engine must idle for 30 minutes on the ground, with the air bleed available for...

  11. 14 CFR 27.1093 - Induction system icing protection.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ...— (i) 100 degrees F.; or (ii) If a fluid deicing system is used, at least 40 degrees F. (b) Turbine engine. (1) It must be shown that each turbine engine and its air inlet system can operate throughout the.... (2) Each turbine engine must idle for 30 minutes on the ground, with the air bleed available for...

  12. 14 CFR 23.1093 - Induction system icing protection.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 75 percent of its maximum continuous power. (b) Turbine engines. (1) Each turbine engine and its air... established for the airplane for such operation. (2) Each turbine engine must idle for 30 minutes on the...) and has a liquid water content not less than 0.3 grams per cubic meter in the form of drops having a...

  13. 14 CFR 27.1093 - Induction system icing protection.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ...— (i) 100 degrees F.; or (ii) If a fluid deicing system is used, at least 40 degrees F. (b) Turbine engine. (1) It must be shown that each turbine engine and its air inlet system can operate throughout the.... (2) Each turbine engine must idle for 30 minutes on the ground, with the air bleed available for...

  14. 14 CFR 23.1093 - Induction system icing protection.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 75 percent of its maximum continuous power. (b) Turbine engines. (1) Each turbine engine and its air... established for the airplane for such operation. (2) Each turbine engine must idle for 30 minutes on the...) and has a liquid water content not less than 0.3 grams per cubic meter in the form of drops having a...

  15. Reviewing sulfidation corrosion—Yesterday and today

    NASA Astrophysics Data System (ADS)

    Bornstein, Norman S.

    1996-11-01

    At one time, sulfidation corrosion threatened to severely limit the use of gas turbines in marine applications, markedly reduce the life of industrial gas turbines, and affect the performance of aircraft engines. Today, gas turbine engines drive U.S. naval ships, produce electricity, and power aircraft. However, the problem of sulfidation corrosion has not disappeared. The rapid rate of degradation of airfoil materials in the presence of condensed sulfates is still a concern for gas turbine engines that operate in industrial and marine environments.

  16. Thermal Response Turbine Shroud.

    DTIC Science & Technology

    1979-11-01

    AD-AO82 754. GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE GROUP F/G 21/5 THERMAL RESPONSE TURBINE SHROUO.(UI NOV 79 C N GAY F33615-7B-C-2071...SUPPLEMENTARY NOTES IS. IEV WORDS (C..tIam. ON guinea 80410 Itf08M 8". 1~0 &VU~ b lma n-M-) Clearance Shroud Clearance Control Turbine Shroud engine / aircrafte ...compressor Active Clearance Control Systems (ACC) de-signed for aircraft gas turbine engine applications. The study vas conducted by personnel of the

  17. Supersonic Transport Noise Reduction Technology Program - Phase 2, Volume 2

    DTIC Science & Technology

    1975-09-01

    a J85 is shown on Figure 350. The J85 turbojet engine has an eight-stage compressor (with an air bleed system) and a two-stage turbine . Blade ...investigated in this program using a YJ85 engine . Both turbine second-stage spacing ( blade - vane ) and exhaust duct treatment were determined to be...using a J85 engine with massive Inlet suppressor and open nozzle to unmask the turbine . Second-stag« turbine blade /nozzle spacing and exhaust

  18. A simulation study of turbofan engine deterioration estimation using Kalman filtering techniques

    NASA Technical Reports Server (NTRS)

    Lambert, Heather H.

    1991-01-01

    Deterioration of engine components may cause off-normal engine operation. The result is an unecessary loss of performance, because the fixed schedules are designed to accommodate a wide range of engine health. These fixed control schedules may not be optimal for a deteriorated engine. This problem may be solved by including a measure of deterioration in determining the control variables. These engine deterioration parameters usually cannot be measured directly but can be estimated. A Kalman filter design is presented for estimating two performance parameters that account for engine deterioration: high and low pressure turbine delta efficiencies. The delta efficiency parameters model variations of the high and low pressure turbine efficiencies from nominal values. The filter has a design condition of Mach 0.90, 30,000 ft altitude, and 47 deg power level angle (PLA). It was evaluated using a nonlinear simulation of the F100 engine model derivative (EMD) engine, at the design Mach number and altitude over a PLA range of 43 to 55 deg. It was found that known high pressure turbine delta efficiencies of -2.5 percent and low pressure turbine delta efficiencies of -1.0 percent can be estimated with an accuracy of + or - 0.25 percent efficiency with a Kalman filter. If both the high and low pressure turbine are deteriorated, the delta efficiencies of -2.5 percent to both turbines can be estimated with the same accuracy.

  19. Brayton cycle solarized advanced gas turbine

    NASA Technical Reports Server (NTRS)

    1986-01-01

    Described is the development of a Brayton Engine/Generator Set for solar thermal to electrical power conversion, authorized under DOE/NASA Contract DEN3-181. The objective was to design, fabricate, assemble, and test a small, hybrid, 20-kW Brayton-engine-powered generator set. The latter, called a power conversion assembly (PCA), is designed to operate with solar energy obtained from a parobolic dish concentrator, 11 meters in diameter, or with fossil energy supplied by burning fuels in a combustor, or by a combination of both (hybrid model). The CPA consists of the Brayton cycle engine, a solar collector, a belt-driven 20-kW generator, and the necessary control systems for automatic operation in solar-only, fuel-only, and hybrid modes to supply electrical power to a utility grid. The original configuration of the generator set used the GTEC Model GTP36-51 gas turbine engine for the PCA prime mover. However, subsequent development of the GTEC Model AGT101 led to its selection as the powersource for the PCA. Performance characteristics of the latter, thermally coupled to a solar collector for operation in the solar mode, are presented. The PCA was successfully demonstrated in the fuel-only mode at the GTEC Phoenix, Arizona, facilities prior to its shipment to Sandia National Laboratory in Albuquerque, New Mexico, for installation and testing on a test bed concentractor (parabolic dish). Considerations relative to Brayton-engine development using the all-ceramic AGT101 when it becomes available, which would satisfy the DOE heat engine efficiency goal of 35 to 41 percent, are also discussed in the report.

  20. High density fuel qualification for a gas turbine engine

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Macleod, J.D.; Orbanski, B.; Hastings, P.R.

    1992-01-01

    A program for the evaluation of gas turbine engine performance, carried out in the Engine Laboratory of the National Research Council of Canada, is described. Problems under consideration include performance alteration between JP-4 fuel and a high energy density fuel, called strategic military fuel (SMF); performance deterioration during the accelerated endurance test; and emission analysis. The T56 fuel control system is found to be capable of operation on the higher energy density fuel with no detrimental effects regarding control of the engine's normal operating regime. The deterioration of the engine performance during 150-hour endurance tests on SMF was very high,more » which was caused by an increase in turbine nozzle effective flow area and turbine blade untwist. The most significant performance losses during the endurance tests were on corrected output power, fuel flow, specific fuel consumption and compressor and turbine presure ratio. 9 refs.« less

  1. Application of single crystal superalloys for Earth-to-orbit propulsion systems

    NASA Technical Reports Server (NTRS)

    Dreshfield, R. L.; Parr, R. A.

    1987-01-01

    Single crystal superalloys were first identified as potentially useful engineering materials for aircraft gas turbine engines in the mid-1960's. Although they were not introduced into service as turbine blades in commercial aircraft engines until the early 1980's, they have subsequently accumulated tens of millions of flight hours in revenue producing service. The space shuttle main engine (SSME) and potential advanced earth-to-orbit propulsion systems impose severe conditions on turbopump turbine blades which for some potential failure modes are more severe than in aircraft gas turbines. Research activities which are directed at evaluating the potential for single crystal superalloys for application as turbopump turbine blades in the SSME and advanced rocket engines are discussed. The mechanical properties of these alloys are summarized and the effects of hydrogen are noted. The use of high gradient directional solidification and hot isostatic pressing to improve fatigue properties is also addressed.

  2. Aeronautical Engineering: A Continuing Bibliography with Indexes (Supplement 218)

    DTIC Science & Technology

    1987-10-01

    reviews the current situation and the history of development of cast turbine blades of Chinese aircraft engines for nearly three decades since 1956... aviation oils - Causes gas turbine engine p 592 N87-23577 MIDAIR COLLISIONS and consequences p 604 A87-40925 Aircraft Dynamic Response to Damaged and...numerical solution of the Navier-Stokes equations Numerical optimization design of transonic airfoils compressors of aircraft gas turbine engines p 553 A87

  3. General Aviation Turbine Engine (GATE) study

    NASA Technical Reports Server (NTRS)

    Baerst, C. F.; Furst, D. G.

    1979-01-01

    The feasibility of turbine engines for the smaller general aviation aircraft was investigated and a technology program for developing the necessary technology was identified. Major results included the definition of the 1988 general aviation market, the identification of turboprop and turboshaft engines that meet the requirements of the aircraft studies, a benefit analysis showing the superiority of gas turbine engines for portions of the market studied, and detailed plans for the development of the necessary technology.

  4. Aircraft Photovoltaic Power-Generating System.

    NASA Astrophysics Data System (ADS)

    Doellner, Oscar Leonard

    Photovoltaic cells, appropriately cooled and operating in the combustion-created high radiant-intensity environment of gas-turbine and jet engines, may replace the conventional (gearbox-driven) electrical power generators aboard jet aircraft. This study projects significant improvements not only in aircraft electrical power-generating-system performance, but also in overall aircraft performance. Jet -engine design modifications incorporating this concept not only save weight (and thus fuel), but are--in themselves --favorable to jet-engine performance. The dissertation concentrates on operational, constructional, structural, thermal, optical, radiometrical, thin-film, and solid-state theoretical aspects of the overall project. This new electrical power-generating system offers solid-state reliability with electrical power-output capability comparable to that of existing aircraft electromechanical power-generating systems (alternators and generators). In addition to improvements in aircraft performance, significant aircraft fuel- and weight-saving advantages are projected.

  5. Microstructure Based Material-Sand Particulate Interactions and Assessment of Coatings for High Temperature Turbine Blades

    NASA Technical Reports Server (NTRS)

    Murugan, Muthuvel; Ghoshal, Anindya; Walock, Michael; Nieto, Andy; Bravo, Luis; Barnett, Blake; Pepi, Marc; Swab, Jeffrey; Pegg, Robert Tyler; Rowe, Chris; hide

    2017-01-01

    Gas turbine engines for military/commercial fixed-wing and rotary wing aircraft use thermal barrier coatings in the high-temperature sections of the engine for improved efficiency and power. The desire to further make improvements in gas turbine engine efficiency and high power-density is driving the research and development of thermal barrier coatings and the effort of improving their tolerance to fine foreign particulates that may be contained in the intake air. Both commercial and military aircraft engines often are required to operate over sandy regions such as in the Middle-East nations, as well as over volcanic zones. For rotorcraft gas turbine engines, the sand ingestion is adverse during take-off, hovering near ground, and landing conditions. Although, most of the rotorcraft gas turbine engines are fitted with inlet particle separators, they are not 100 percent efficient in filtering fine sand particles of size 75 microns or below. The presence of these fine solid particles in the working fluid medium has an adverse effect on the durability of turbine blade thermal barrier coatings and overall performance of the engine. Typical turbine blade damages include blade coating wear, sand glazing, Calcia-Magnesia-Alumina-Silicate (CMAS) attack, oxidation, plugged cooling holes, all of which can cause rapid performance deterioration including loss of aircraft. The objective of this research is to understand the fine particle interactions with typical ceramic coatings of turbine blades at the microstructure level. A finite-element based microstructure modeling and analysis has been performed to investigate particle-surface interactions, and restitution characteristics. Experimentally, a set of tailored thermal barrier coatings and surface treatments were down-selected through hot burner rig tests and then applied to first stage nozzle vanes of the Gas Generator Turbine of a typical rotorcraft gas turbine engine. Laser Doppler velocity measurements were performed during hot burner rig testing to determine sand particle incoming velocities and their rebound characteristics upon impact on coated material targets. Further, engine sand ingestion tests were carried out to test the CMAS tolerance of the coated nozzle vanes. The findings from this on-going collaborative research to develop the next-gen sand tolerant coatings for turbine blades are presented in this paper.

  6. Certification of alternative aviation fuels and blend components

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Wilson III, George R.; Edwards, Tim; Corporan, Edwin

    2013-01-15

    Aviation turbine engine fuel specifications are governed by ASTM International, formerly known as the American Society for Testing and Materials (ASTM) International, and the British Ministry of Defence (MOD). ASTM D1655 Standard Specification for Aviation Turbine Fuels and MOD Defence Standard 91-91 are the guiding specifications for this fuel throughout most of the world. Both of these documents rely heavily on the vast amount of experience in production and use of turbine engine fuels from conventional sources, such as crude oil, natural gas condensates, heavy oil, shale oil, and oil sands. Turbine engine fuel derived from these resources and meetingmore » the above specifications has properties that are generally considered acceptable for fuels to be used in turbine engines. Alternative and synthetic fuel components are approved for use to blend with conventional turbine engine fuels after considerable testing. ASTM has established a specification for fuels containing synthesized hydrocarbons under D7566, and the MOD has included additional requirements for fuels containing synthetic components under Annex D of DS91-91. New turbine engine fuel additives and blend components need to be evaluated using ASTM D4054, Standard Practice for Qualification and Approval of New Aviation Turbine Fuels and Fuel Additives. This paper discusses these specifications and testing requirements in light of recent literature claiming that some biomass-derived blend components, which have been used to blend in conventional aviation fuel, meet the requirements for aviation turbine fuels as specified by ASTM and the MOD. The 'Table 1' requirements listed in both D1655 and DS91-91 are predicated on the assumption that the feedstocks used to make fuels meeting these requirements are from approved sources. Recent papers have implied that commercial jet fuel can be blended with renewable components that are not hydrocarbons (such as fatty acid methyl esters). These are not allowed blend components for turbine engine fuels as discussed in this paper.« less

  7. 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.

  8. 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.

  9. AGT (Advanced Gas Turbine) technology project

    NASA Technical Reports Server (NTRS)

    1988-01-01

    An overall summary documentation is provided for the Advanced Gas Turbine Technology Project conducted by the Allison Gas Turbine Division of General Motors. This advanced, high risk work was initiated in October 1979 under charter from the U.S. Congress to promote an engine for transportation that would provide an alternate to reciprocating spark ignition (SI) engines for the U.S. automotive industry and simultaneously establish the feasibility of advanced ceramic materials for hot section components to be used in an automotive gas turbine. As this program evolved, dictates of available funding, Government charter, and technical developments caused program emphases to focus on the development and demonstration of the ceramic turbine hot section and away from the development of engine and powertrain technologies and subsequent vehicular demonstrations. Program technical performance concluded in June 1987. The AGT 100 program successfully achieved project objectives with significant technology advances. Specific AGT 100 program achievements are: (1) Ceramic component feasibility for use in gas turbine engines has been demonstrated; (2) A new, 100 hp engine was designed, fabricated, and tested for 572 hour at operating temperatures to 2200 F, uncooled; (3) Statistical design methodology has been applied and correlated to experimental data acquired from over 5500 hour of rig and engine testing; (4) Ceramic component processing capability has progressed from a rudimentary level able to fabricate simple parts to a sophisticated level able to provide complex geometries such as rotors and scrolls; (5) Required improvements for monolithic and composite ceramic gas turbine components to meet automotive reliability, performance, and cost goals have been identified; (6) The combustor design demonstrated lower emissions than 1986 Federal Standards on methanol, JP-5, and diesel fuel. Thus, the potential for meeting emission standards and multifuel capability has been initiated; (7) Small turbine engine aerodynamic and mechanical design capability has been initiated; and (8) An infrastructure of manpower, facilities, materials, and fabrication capabilities has been established which is available for continued development of ceramic component technology in gas turbine and other heat engines.

  10. 14 CFR 33.81 - Applicability.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... STANDARDS: AIRCRAFT ENGINES Block Tests; Turbine Aircraft Engines § 33.81 Applicability. This subpart prescribes the block tests and inspections for turbine engines. [Doc. 3025, 29 FR 7453, June 10, 1964, as...

  11. 14 CFR 33.81 - Applicability.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... STANDARDS: AIRCRAFT ENGINES Block Tests; Turbine Aircraft Engines § 33.81 Applicability. This subpart prescribes the block tests and inspections for turbine engines. [Doc. 3025, 29 FR 7453, June 10, 1964, as...

  12. 14 CFR 33.81 - Applicability.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... STANDARDS: AIRCRAFT ENGINES Block Tests; Turbine Aircraft Engines § 33.81 Applicability. This subpart prescribes the block tests and inspections for turbine engines. [Doc. 3025, 29 FR 7453, June 10, 1964, as...

  13. 46 CFR 11.518 - Service requirements for national endorsement as chief engineer (limited) of steam, motor, and/or...

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... engineer (limited) of steam, motor, and/or gas turbine-propelled vessels. 11.518 Section 11.518 Shipping... requirements for national endorsement as chief engineer (limited) of steam, motor, and/or gas turbine-propelled... (limited) of steam, motor, and/or gas turbine-propelled vessels is 5 years of total service in the...

  14. Environmental Degradation of Nickel-Based Superalloys Due to Gypsiferous Desert Dusts

    DTIC Science & Technology

    2015-09-17

    twenty-five years of continuous operation in the dusty environments of Southwest Asia have shown that degradation of gas turbine engine components...proven to initiate hot corrosion at temperatures associated with modern gas turbine engine operation, which are beyond the range at which sodium sulfate...Relevant Research into Failure Due to Molten Deposits . . . . . . . . . 13 2.1 The Gas Turbine Engine

  15. Topology optimization of a gas-turbine engine part

    NASA Astrophysics Data System (ADS)

    Faskhutdinov, R. N.; Dubrovskaya, A. S.; Dongauzer, K. A.; Maksimov, P. V.; Trufanov, N. A.

    2017-02-01

    One of the key goals of aerospace industry is a reduction of the gas turbine engine weight. The solution of this task consists in the design of gas turbine engine components with reduced weight retaining their functional capabilities. Topology optimization of the part geometry leads to an efficient weight reduction. A complex geometry can be achieved in a single operation with the Selective Laser Melting technology. It should be noted that the complexity of structural features design does not affect the product cost in this case. Let us consider a step-by-step procedure of topology optimization by an example of a gas turbine engine part.

  16. 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.

  17. 40 CFR 87.20 - Applicability.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... POLLUTION FROM AIRCRAFT AND AIRCRAFT ENGINES Exhaust Emissions (New Aircraft Gas Turbine Engines) § 87.20 Applicability. The provisions of this subpart are applicable to all aircraft gas turbine engines of the classes...

  18. 40 CFR 87.30 - Applicability.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... POLLUTION FROM AIRCRAFT AND AIRCRAFT ENGINES Exhaust Emissions (In-Use Aircraft Gas Turbine Engines) § 87.30 Applicability. The provisions of this subpart are applicable to all in-use aircraft gas turbine engines...

  19. 40 CFR 87.20 - Applicability.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... POLLUTION FROM AIRCRAFT AND AIRCRAFT ENGINES Exhaust Emissions (New Aircraft Gas Turbine Engines) § 87.20 Applicability. The provisions of this subpart are applicable to all aircraft gas turbine engines of the classes...

  20. 40 CFR 87.30 - Applicability.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... POLLUTION FROM AIRCRAFT AND AIRCRAFT ENGINES Exhaust Emissions (In-Use Aircraft Gas Turbine Engines) § 87.30 Applicability. The provisions of this subpart are applicable to all in-use aircraft gas turbine engines...

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