Caterpillar C7 and GEP 6.5L (T) Fuel System Durability Using 25% ATJ Fuel Blend

DTIC Science & Technology

2015-02-01

loss. Its most likely that this degradation was caused by some sort of engine controller or sensor issue that existed on the engine being evaluated...Some investigation was conducted into the engine controller/harness/ sensors , but ultimately it was determined that the time and cost to fully...Abs./cm) E168 FTNG 0.0 5.0 13.7 18.4 31.6 59.5 100.7 Nitration (Abs./cm) E168 FTNG 0.0 10.3 16.7 19.5 31.5 45.3 48.6 Soot Soot 0.2

A Systems Engineering Approach to Aircraft Kinetic Kill Countermeasures Technology: Development of an Active Aircraft Defense System for the C/KC-135 Aircraft. Volume 1

DTIC Science & Technology

1995-12-01

comparison among all candidate systems , the reliability of each aircraft defense would evenly affect the evaluation of each system , and would have the...more reliable data. Obviously the more reliable and accurate the data evaluated though the hierarchy chart, the better the results. 29 IV. System ...1.3.5 System Evaluation ................................................................ 6 1.3.6 Decision M aking

Waste Heat Recovery from a High Temperature Diesel Engine

NASA Astrophysics Data System (ADS)

Adler, Jonas E.

Government-mandated improvements in fuel economy and emissions from internal combustion engines (ICEs) are driving innovation in engine efficiency. Though incremental efficiency gains have been achieved, most combustion engines are still only 30-40% efficient at best, with most of the remaining fuel energy being rejected to the environment as waste heat through engine coolant and exhaust gases. Attempts have been made to harness this waste heat and use it to drive a Rankine cycle and produce additional work to improve efficiency. Research on waste heat recovery (WHR) demonstrates that it is possible to improve overall efficiency by converting wasted heat into usable work, but relative gains in overall efficiency are typically minimal ( 5-8%) and often do not justify the cost and space requirements of a WHR system. The primary limitation of the current state-of-the-art in WHR is the low temperature of the engine coolant ( 90 °C), which minimizes the WHR from a heat source that represents between 20% and 30% of the fuel energy. The current research proposes increasing the engine coolant temperature to improve the utilization of coolant waste heat as one possible path to achieving greater WHR system effectiveness. An experiment was performed to evaluate the effects of running a diesel engine at elevated coolant temperatures and to estimate the efficiency benefits. An energy balance was performed on a modified 3-cylinder diesel engine at six different coolant temperatures (90 °C, 100 °C, 125 °C, 150 °C, 175 °C, and 200 °C) to determine the change in quantity and quality of waste heat as the coolant temperature increased. The waste heat was measured using the flow rates and temperature differences of the coolant, engine oil, and exhaust flow streams into and out of the engine. Custom cooling and engine oil systems were fabricated to provide adequate adjustment to achieve target coolant and oil temperatures and large enough temperature differences across the engine to reduce uncertainty. Changes to exhaust emissions were recorded using a 5-gas analyzer. The engine condition was also monitored throughout the tests by engine compression testing, oil analysis, and a complete teardown and inspection after testing was completed. The integrity of the head gasket seal proved to be a significant problem and leakage of engine coolant into the combustion chamber was detected when testing ended. The post-test teardown revealed problems with oil breakdown at locations where temperatures were highest, with accompanying component wear. The results from the experiment were then used as inputs for a WHR system model using ethanol as the working fluid, which provided estimates of system output and improvement in efficiency. Thermodynamic models were created for eight different WHR systems with coolant temperatures of 90 °C, 150 °C, 175 °C, and 200 °C and condenser temperatures of 60 °C and 90 °C at a single operating point of 3100 rpm and 24 N-m of torque. The models estimated that WHR output for both condenser temperatures would increase by over 100% when the coolant temperature was increased from 90 °C to 200 °C. This increased WHR output translated to relative efficiency gains as high as 31.0% for the 60 °C condenser temperature and 24.2% for the 90 °C condenser temperature over the baseline engine efficiency at 90 °C. Individual heat exchanger models were created to estimate the footprint for a WHR system for each of the eight systems. When the coolant temperature increased from 90 °C to 200 °C, the total heat exchanger volume increased from 16.6 x 103 cm3 to 17.1 x 10 3 cm3 with a 60 °C condenser temperature, but decreased from 15.1 x 103 cm3 to 14.2 x 10 3 cm3 with a 90 °C condenser temperature. For all cases, increasing the coolant temperature resulted in an improvement in the efficiency gain for each cubic meter of heat exchanger volume required. Additionally, the engine oil coolers represented a significant portion of the required heat exchanger volume due to abnormally low engine oil temperatures during the experiment ( 80 °C). Future studies should focus on allowing the engine oil to reach higher operating temperatures which would decrease the heat rejected to the engine oil and reduce the heat duty for the oil coolers resulting in reduced oil cooler volume.

USAF Propellant Handbooks. Nitric Acid/Nitrogen Tetroxide Oxidizers. Volume II.

DTIC Science & Technology

1977-02-01

Report . MCR -64-88, Martin Marietta Corpora 32. Lukens, S.C.: Sterilizable Liquid PropulSion tion, Denver, Colorado. November 1964. System, Part I1...the Air Force Project Engineer. Mr. A. C. Wright was the Martin Marietta Program Manager. This report has been reviewed by the Information Office/DOZ...lated from test data reported by the Martin Marietta 2C2 H6 + 3NO2----- 2C6 H5 NO 2 + NO + H2 0 Company (11), Test values were obtained at four

A Demonstration of an Intelligent Control System for a Reusable Rocket Engine

DTIC Science & Technology

1992-06-01

Research Center Cleveland, Ohio 44135 ABSTRACT DTIC QUALrI’ ’illE ,;TED 3 An Intelligent Control System for reusable rocket engines is under development at...through the ring seal may be written as rh,i,,g - 0.685 It Co d c~iiPexi g ( 3 )VRTIprt( where d. and cri6t now correspond to the shaft diameter and the ring...discharge coefficient of 0.9 for both seals and disk and shaft diameters of 6.0 and 2.0 inches respectively, equations I and 3 may be equated and the

Ames Lab 101: C6: Virtual Engineering

ScienceCinema

McCorkle, Doug

2018-01-01

Ames Laboratory scientist Doug McCorkle explains the importance of virtual engineering and talks about the C6. The C6 is a three-dimensional, fully-immersive synthetic environment residing in the center atrium of Iowa State University's Howe Hall.

The Department of the Navy Systems Engineering Career Competency Model (SECCM)

DTIC Science & Technology

2015-05-13

Respond 71% Value 18% Organize 3% Characterize 4% Affective Domain Total KSAs : 869 ENG Career Field Competency Model 10 1.0 Mission Level...The Department of the Navy Systems Engineering Career Competency Model (SECCM) 2015 Acquisition Symposium Naval Postgraduate School Monterey...Career Competency Model (SECCM) 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e. TASK NUMBER

Systems Engineering Technical Leadership Development Program

DTIC Science & Technology

2012-08-30

technology-based competitive advantage can be part of firm’s business strategy.  Review the Porter Model . Return to Syllabus UNCLASSIFIED 66...Program 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR( S ) 5d. PROJECT NUMBER 5e. TASK NUMBER 5f. WORK UNIT NUMBER 7...PERFORMING ORGANIZATION NAME( S ) AND ADDRESS(ES) Stevens Institute of Technology,Systems Engineering Research Center,Castle Point on the Hudson,Hoboken,NJ

The Subchronic Inhalation Toxicity of DF2 (Diesel Fuel) Used in Vehicle Engine Exhaust Smoke Systems (VEESS).

DTIC Science & Technology

1986-03-01

4-I +4 .- -+ + _C tL+ + + +i + T + +- + - -) 4. c_ --- - * - 4A _ __ _ -- 0 0 ICx" C ) 4j cliou 0 N4cr(\\lc’ + + ++ ++ + + +1 -4++111+ = 0 m x...Charles L. Crouse SP6 David C . Burnett Garnet E. Affleck Dale H. Heitkamp Edmund G. Cummings, Ph.D. Carlyle Lilly Richard L. Farrand, Ph.D. Joseph J...Feeney, Ph.D. Robert W. Dorsey Michael Rausa SP6 Mohammed S. Ghumman Ernest H. Kandel Robert D. Armstrong Jeffrey D. Bergmann William C . Stark. John

Data Integration Framework Data Management Plan Remote Sensing Dataset

DTIC Science & Technology

2016-07-01

performed by the Coastal Observations and Analysis Branch (CEERD-HFA) of the Flood and Storm Protection Division (CEERD-HF), U.S. Army Engineer Research... Protection Division, Coastal Observations and Analysis Branch CESAM U.S. Army Corps of Engineers, Mobile District CESAM-OP-J U.S. Army Corps of Engineers...ER D C/ CH L SR -1 6- 2 Coastal Ocean Data Systems Program Data Integration Framework Data Management Plan Remote Sensing Dataset Co

On the thermodynamics of waste heat recovery from internal combustion engine exhaust gas

NASA Astrophysics Data System (ADS)

Meisner, G. P.

2013-03-01

The ideal internal combustion (IC) engine (Otto Cycle) efficiency ηIC = 1-(1/r)(γ - 1) is only a function of engine compression ratio r =Vmax/Vmin and exhaust gas specific heat ratio γ = cP/cV. Typically r = 8, γ = 1.4, and ηIC = 56%. Unlike the Carnot Cycle where ηCarnot = 1-(TC/TH) for a heat engine operating between hot and cold heat reservoirs at TH and TC, respectively, ηIC is not a function of the exhaust gas temperature. Instead, the exhaust gas temperature depends only on the intake gas temperature (ambient), r, γ, cV, and the combustion energy. The ejected exhaust gas heat is thermally decoupled from the IC engine and conveyed via the exhaust system (manifold, pipe, muffler, etc.) to ambient, and the exhaust system is simply a heat engine that does no useful work. The maximum fraction of fuel energy that can be extracted from the exhaust gas stream as useful work is (1-ηIC) × ηCarnot = 32% for TH = 850 K (exhaust) and TC = 370 K (coolant). This waste heat can be recovered using a heat engine such as a thermoelectric generator (TEG) with ηTEG> 0 in the exhaust system. A combined IC engine and TEG system can generate net useful work from the exhaust gas waste heat with efficiency ηWH = (1-ηIC) × ηCarnot ×ηTEG , and this will increase the overall fuel efficiency of the total system. Recent improvements in TEGs yield ηTEG values approaching 15% giving a potential total waste heat conversion efficiency of ηWH = 4.6%, which translates into a fuel economy improvement approaching 5%. This work is supported by the US DOE under DE-EE0005432.

48 CFR 209.571-6 - Identification of organizational conflicts of interest.

Code of Federal Regulations, 2014 CFR

2014-10-01

... business units performing systems engineering and technical assistance, professional services, or... parent corporate entity, particularly the award of a subcontract for software integration or the development of a proprietary software system architecture; and (c) The performance by, or assistance of...

48 CFR 209.571-6 - Identification of organizational conflicts of interest.

Code of Federal Regulations, 2013 CFR

2013-10-01

... business units performing systems engineering and technical assistance, professional services, or... parent corporate entity, particularly the award of a subcontract for software integration or the development of a proprietary software system architecture; and (c) The performance by, or assistance of...

48 CFR 209.571-6 - Identification of organizational conflicts of interest.

Code of Federal Regulations, 2012 CFR

2012-10-01

... business units performing systems engineering and technical assistance, professional services, or... parent corporate entity, particularly the award of a subcontract for software integration or the development of a proprietary software system architecture; and (c) The performance by, or assistance of...

2005 8th Annual Systems Engineering Conference Volume 3 - Wednesday presentations

DTIC Science & Technology

2005-10-24

phasi s on s ystem s eng ineeri ng Imple menta tion o f SE P lans Requires PEO chief engineer Conduct of technical reviews SE Policy Addendum Signed by...in a Performance Based Logistics Environment, Denise Duncan, LMI Track 5 - Best Practices & Standardization: CMMI for Services, Mr. Juan Ceva...CMMI for Services Mr. Juan Ceva, Raytheon RIS TRACK 5 Logistics Session 3C5 TRACK 4 Net Centric Operations Session 3C4 TRACK 6 Modeling & Simulation

75 FR 23572 - Airworthiness Directives; Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, B4-2C...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-05-04

... cycles 6,700 flight 80A3 or Pratt & Whitney engines. flight cycles \\1\\. flight cycles or \\2\\. cycles or...-200 airplanes with GE CF6- 18,000 total 19,500 total 250 flight cycles 5,800 flight 80C2 engines... flight cycles 6,700 flight Pratt & Whitney JT9D engines. flight cycles \\1\\. flight cycles or \\2\\. cycles...

Drone Defense System Architecture for U.S. Navy Strategic Facilities

DTIC Science & Technology

2017-09-01

evaluation and weapons assignment (TEWA) to properly address threats. This report follows a systems engineering process to develop a software architecture...C-UAS requires a central system to connect these new and existing systems. The central system uses data fusion and threat evaluation and weapons...30  Table 6.  Decision Type Descriptions .......................................................................40  Table 7

Diagnostic and Condition Monitoring System Assessment for Army Helicopter Modular Turboshaft Engines.

DTIC Science & Technology

1980-10-01

from the sun. The longer bell mouth will also require that the water brake be located further from the engine, which mod- ifies the forward mount...unless there are over- riding considerations which are not readily quantifiable such as aircraft availabilit \\ and flight safety considerations...T M 1’ M Std (C) Moid. ’S-td C) M jSt- (C) 1I6’ 7 8 Prep and Install T700 4 4 5 4 5 4 5 4 Facility Check-Out and Water -Wash 1 1 /2 2 1 1-1 1!-󈧙 1

Publication Index and Retrieval System.

DTIC Science & Technology

1980-04-01

A0DA1087 279, NERNER AND CO WASHINGTON D C F/6 13/2 PUBLICATION INDEX AND RETRIEVAL SYSTEM . (U) APR 80 DAC3977-C0081 UNCLASSIFIED WES-OS-78-2 Nt.m*nn...Engineers. The objective was to develop an information index and retrieval system for the publications of the DMRP. The report was prepared by Herner...Development of the system and preparation and review of the report were under the super- vision of Dr. R. T. Saucier, Special Assistant for Dredged

Systems metabolic engineering design: Fatty acid production as an emerging case study

PubMed Central

Tee, Ting Wei; Chowdhury, Anupam; Maranas, Costas D; Shanks, Jacqueline V

2014-01-01

Increasing demand for petroleum has stimulated industry to develop sustainable production of chemicals and biofuels using microbial cell factories. Fatty acids of chain lengths from C6 to C16 are propitious intermediates for the catalytic synthesis of industrial chemicals and diesel-like biofuels. The abundance of genetic information available for Escherichia coli and specifically, fatty acid metabolism in E. coli, supports this bacterium as a promising host for engineering a biocatalyst for the microbial production of fatty acids. Recent successes rooted in different features of systems metabolic engineering in the strain design of high-yielding medium chain fatty acid producing E. coli strains provide an emerging case study of design methods for effective strain design. Classical metabolic engineering and synthetic biology approaches enabled different and distinct design paths towards a high-yielding strain. Here we highlight a rational strain design process in systems biology, an integrated computational and experimental approach for carboxylic acid production, as an alternative method. Additional challenges inherent in achieving an optimal strain for commercialization of medium chain-length fatty acids will likely require a collection of strategies from systems metabolic engineering. Not only will the continued advancement in systems metabolic engineering result in these highly productive strains more quickly, this knowledge will extend more rapidly the carboxylic acid platform to the microbial production of carboxylic acids with alternate chain-lengths and functionalities. PMID:24481660

Systems metabolic engineering design: fatty acid production as an emerging case study.

PubMed

Tee, Ting Wei; Chowdhury, Anupam; Maranas, Costas D; Shanks, Jacqueline V

2014-05-01

Increasing demand for petroleum has stimulated industry to develop sustainable production of chemicals and biofuels using microbial cell factories. Fatty acids of chain lengths from C6 to C16 are propitious intermediates for the catalytic synthesis of industrial chemicals and diesel-like biofuels. The abundance of genetic information available for Escherichia coli and specifically, fatty acid metabolism in E. coli, supports this bacterium as a promising host for engineering a biocatalyst for the microbial production of fatty acids. Recent successes rooted in different features of systems metabolic engineering in the strain design of high-yielding medium chain fatty acid producing E. coli strains provide an emerging case study of design methods for effective strain design. Classical metabolic engineering and synthetic biology approaches enabled different and distinct design paths towards a high-yielding strain. Here we highlight a rational strain design process in systems biology, an integrated computational and experimental approach for carboxylic acid production, as an alternative method. Additional challenges inherent in achieving an optimal strain for commercialization of medium chain-length fatty acids will likely require a collection of strategies from systems metabolic engineering. Not only will the continued advancement in systems metabolic engineering result in these highly productive strains more quickly, this knowledge will extend more rapidly the carboxylic acid platform to the microbial production of carboxylic acids with alternate chain-lengths and functionalities. © 2014 Wiley Periodicals, Inc.

Experiments in Sound and Structural Vibrations Using an Air-Analog Model Ducted Propulsion System

DTIC Science & Technology

2007-08-01

Department of Aerospace S~and Mechanical Engineering I 20070904056 I EXPERIMENTS IN SOUND AND STRUCTURAL VIBRATIONS USING AN AIR -ANALOG MODEL DUCTED...SOUND AND STRUCTURAL * VIBRATIONS USING AN AIR -ANALOG MODEL DUCTED PROPULSION SYSTEM FINAL TECHNICAL REPORT Prepared by: Scott C. Morris Assistant...Vibration Using Air - 5b. GRANT NUMBER Analog Model Ducted Propulsion Systems N00014-1-0522 5C. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER

Acquisition Management for Systems-of-Systems: Risk Dynamics and Exploratory Model Experimentation

DTIC Science & Technology

2011-03-03

Systems Engineering Research Center ( SERC ). The SERC , funded by the DDR&E and NRO primarily, was interested in hearing new ideas in systems engineering...research that was funded elsewhere but that could be leveraged in new ways for SERC specific research objectives. Third, a paper that focused on...0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1 74 76 78 80 82 84 86 88 90 dependency strength, S(i,j) ex pe ct ed c om pl et io n tim e [ti m e- st ep s

Pullout of a Rigid Insert Adhesively Bonded to an Elastic Half Plane.

DTIC Science & Technology

1983-12-01

COMMAND UNITED STATES AIR FORCE C-= °84 02 13 071. C,, W % d 6 This document was prepared by the Department of Engineering Mechanics, USAF Academy Faculty...THOMAS E. KULLGREN, Lt Col, USAF Project Engineer /Scientist Professor and Acting Head, Department of Engineering Mechanics KENNETH E. SIEGETH Lt Col...Department of Engineering (Ifapphicable) Mechanics USAFA/DFEM 6c. ADDRESS (City. State and ZIP Code) 7b. ADDRESS (City, Slate and ZIP Code) USAF Academy

Saturn V First Stage (S-1C) Ready for Assembly AT KSC

NASA Technical Reports Server (NTRS)

1968-01-01

This photograph shows the Saturn V first stage (S-1C) in the Vehicle Assembly Building at Kennedy Space Center ready to be mated with the second and third stages to complete the assembly of a Saturn V launch vehicle. This particular Saturn V was used for Apollo 6, which was a systems test flight. The towering 363-foot Saturn V was a multi-stage, multi-engine launch vehicle standing taller than the Statue of Liberty. Altogether, the Saturn V engines produced as much power as 85 Hoover Dams.

Development of a Gravity-Insensitive Heat Pump for Lunar Applications

NASA Technical Reports Server (NTRS)

Cole, Gregory S.; Scaringe, Robert P.; Grzyll, Lawrence R.; Ewert, Michael K.

2006-01-01

Mainstream Engineering Corporation is developing a gravity-insensitive system that will allow a vapor-compression-cycle heat pump to be used in both microgravity (10(exp -6)g) and lunar (10(exp -6)g) environments. System capacity is 5 kW to 15 kW at design refrigerant operating conditions of 4.44 C and 60 C evaporating and condensing temperatures, respectively. The current program, performed for NASA Johnson Space Center (JSC) and presented in this paper, includes compressor performance analysis, detailed system design, and thermal analysis. Future efforts, including prototype fabrication, integration of a solar power source and controls, ground-testing, and flight-testing support, are also discussed.

Metabolic engineering of Corynebacterium glutamicum for fermentative production of chemicals in biorefinery.

PubMed

Baritugo, Kei-Anne; Kim, Hee Taek; David, Yokimiko; Choi, Jong-Il; Hong, Soon Ho; Jeong, Ki Jun; Choi, Jong Hyun; Joo, Jeong Chan; Park, Si Jae

2018-05-01

Bio-based production of industrially important chemicals provides an eco-friendly alternative to current petrochemical-based processes. Because of the limited supply of fossil fuel reserves, various technologies utilizing microbial host strains for the sustainable production of platform chemicals from renewable biomass have been developed. Corynebacterium glutamicum is a non-pathogenic industrial microbial species traditionally used for L-glutamate and L-lysine production. It is a promising species for industrial production of bio-based chemicals because of its flexible metabolism that allows the utilization of a broad spectrum of carbon sources and the production of various amino acids. Classical breeding, systems, synthetic biology, and metabolic engineering approaches have been used to improve its applications, ranging from traditional amino-acid production to modern biorefinery systems for production of value-added platform chemicals. This review describes recent advances in the development of genetic engineering tools and techniques for the establishment and optimization of metabolic pathways for bio-based production of major C2-C6 platform chemicals using recombinant C. glutamicum.

Energy efficient engine: Flight propulsion system, preliminary analysis and design update

NASA Technical Reports Server (NTRS)

Stearns, E. M.

1982-01-01

The preliminary design of General Electric's Energy Efficient Engine (E3) was reported in detail in 1980. Since then, the design has been refined and the components have been rig-tested. The changes which have occurred in the engine and a reassessment of the economic payoff are presented in this report. All goals for efficiency, environmental considerations, and economic payoff are being met. The E3 Flight Propulsion System has 14.9% lower sfc than a CF6-50C. It provides a 7.1% reduction in direct operating cost for a short haul domestic transport and 14.5% reduction for an international long distance transport.

Collaborative Early Systems Engineering: Strategic Information Management Review

DTIC Science & Technology

2010-09-02

Early Systems Engineering: Strategic Information Management Review 2 Table of Contents Executive Summary...5  Center for Systems Engineering (CSE) .............................................................................. 6...Collaborative Early Systems Engineering .......................................................................... 6  Development Planning

C-5 Reliability Enhancement and Re-engining Program (C-5 RERP)

DTIC Science & Technology

2015-12-01

Production Estimate Current APB Production Objective/Threshold Demonstrated Performance Current Estimate Time To Climb/Initial Level Off 837,000 lbs...RCR - Runway Condition Reading SDD - System Design and Development SL - Sea Level C-5 RERP December 2015 SAR March 23, 2016 16:10:28 UNCLASSIFIED 12...5.3 5.3 Acq O&M 0.0 0.0 -- 0.0 0.0 0.0 0.0 Total 7146.6 7135.7 N/A 6698.0 7694.1 7510.7 7066.6 Confidence Level Confidence Level of cost estimate

14 CFR 33.91 - Engine system and component tests.

Code of Federal Regulations, 2010 CFR

2010-01-01

..., reliability, and durability. (c) Each unpressurized hydraulic fluid tank may not fail or leak when subjected... minimum operating values. [Doc. No. 3025, 29 FR 7453, June 10, 1964, as amended by Amdt. 33-6, 39 FR 35469...

11. 'Erection Plan, 1 208'101/2' C. to C. End ...

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

11. 'Erection Plan, 1 - 208'-10-1/2' C. to C. End Pins S. Tr. Thro. Skew Span, 6th Crossing Sacramento River, Pacific System, Southern Pacific Company, The Phoenix Bridge Co., C.O. 836D, Drawing No. 13, Scale 1/8' = 1'0', Engineer, B.M. Krohn, Draftsman, W.L. Clegg, Date, May 25th 1901' - Southern Pacific Railroad Shasta Route, Bridge No. 301.85, Milepost 301.85, Pollard Flat, Shasta County, CA

77 FR 48110 - Airworthiness Directives; General Electric Company Turbofan Engines

Federal Register 2010, 2011, 2012, 2013, 2014

2012-08-13

... Company Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... certain General Electric Company (GE) CF6-80C2 series turbofan engines. The existing AD requires... 2000-04-14, Amendment 39-11597 (65 FR 10698, February 29, 2000), for all GE CF6-80C2 series turbofan...

77 FR 76977 - Airworthiness Directives; General Electric Company Turbofan Engines

Federal Register 2010, 2011, 2012, 2013, 2014

2012-12-31

... Company Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Supplemental notice... proposed airworthiness directive (AD) for certain General Electric Company (GE) CF6-80C2 series turbofan... part 39 to include an AD that would apply to certain GE CF6-80C2 series turbofan engines. That NPRM...

Energy efficient engine: Flight propulsion system preliminary analysis and design

NASA Technical Reports Server (NTRS)

Johnston, R. P.; Beitler, R. S.; Bobinger, R. O.; Broman, C. L.; Gravitt, R. D.; Heineke, H.; Holloway, P. R.; Klem, J. S.; Nash, D. O.; Ortiz, P.

1980-01-01

The characteristics of an advanced flight propulsion system (FPS), suitable for introduction in the late 1980's to early 1990's, was more fully defined. It was determined that all goals for efficiency, environmental considerations, and economics could be met or exceeded with the possible exception of NOx emission. In evaluating the FPS, all aspects were considered including component design, performance, weight, initial cost, maintenance cost, engine system integration (including nacelle), and aircraft integration considerations. The current FPS installed specific fuel consumption was reduced 14.2% from that of the CF6-50C reference engine. When integrated into an advanced, subsonic, study transport, the FPS produced a fuel burn savings of 15 to 23% and a direct operating cost reduction of 5 to 12% depending on the mission and study aircraft characteristics relative to the reference engine.

Verification of a level-3 diesel emissions control strategy for transport refrigeration units

NASA Astrophysics Data System (ADS)

Shewalla, Umesh

Transport Refrigeration Units (TRUs) are refrigeration systems used to control the environment of temperature sensitive products while they are being transported from one place to another in trucks, trailers or shipping containers. The TRUs typically use an internal combustion engine to power the compressor of the refrigeration unit. In the United States TRUs are most commonly powered by diesel engines which vary from 9 to 40 horsepower. TRUs are capable of both heating and cooling. The TRU engines are relatively small, inexpensive and do not use emissions reduction techniques such as exhaust gas recirculation (EGR). A significant number of these engines operate in highly populated areas like distribution centers, truck stops, and other facilities which make them one of the potential causes for health risks to the people who live and work nearby. Diesel particulate matter (PM) is known for its adverse effects on both human beings and the environment. Considering these effects, regulatory bodies have imposed limitations on the PM emissions from a TRU engine. The objective of this study was to measure and analyze the regulated emissions from a TRU engine under both engine out and particulate filter system out conditions during pre-durability (when the filter system was new) and post-durability test (after the filter system was subjected to 1000 hours in-field trial). The verification program was performed by the Center for Alternative Fuel, Engines and Emissions (CAFEE) at West Virginia University (WVU). In this program, a catalyzed silicon carbide (SiC) diesel particulate filter (DPF) was evaluated and verified as a Level-3 Verified Diesel Emissions Control Strategy (VDECS) (. 85% PM reduction) under California Air Resources Board (CARB) regulations 2702 [1]. The emissions result showed that the filter system reduced diesel PM by a percentage of 96 +/- 1 over ISO 8178-C1 [2] cycle and 92 +/- 5 over EPA TRU [3] cycle, qualifying as a Level 3 VDECS. The percentage emission reduction in hydrocarbons (HC) and carbon monoxide (CO) was 76.8 +/- 4.8 and 72.2 +/- 5.2, respectively over both ISO 8178-C1 [2] and EPA TRU [3] cycles. It was also observed that there was 3.6 +/- 2.9 and 7.2 +/- 3.1 percentage reduction in oxides of nitrogen (NOx) and nitric oxide (NO), respectively with a slight increase in fuel consumption and carbon dioxide as a consequence of increased exhaust back pressure. It is required by the CARB regulations that the diesel emissions control strategy must not increase emissions of NO2 by more than 20% by mass over the baseline value. In this study, it was observed that the total increase in NO2 level was 5.6 +/- 2.6 percent, well within the limit specified by the CARB.

How Architecture-Driven Modernization Is Changing the Game in Information System Modernization

DTIC Science & Technology

2010-04-01

Health Administration MUMPS  to Java 300K 4 mo. State of OR Employee Retirement System COBOL to C# .Net 250K 4 mo. Civilian State of WA Off. of Super of...Jovial, Mumps , A MagnaX, Natural, B PVL, P owerBuilder, A SQL, Vax Basic, s V B 6, + Others E revolution, inc. C, Target System "To Be" C#, C...successfully completed in 4 months • Created a new JANUSTM MUMPS parser TM , Implementation • Final “To-Be” Documentation • JANUS rules engine

Turbocharging of Small Internal Combustion Engines as a Means of Improving Engine/Application System Fuel Economy.

DTIC Science & Technology

1979-01-01

OF SMALL INTERNAL COMBUSTION ENGINES AS A MEANS 0-.ETC(U) 1979 DAAK7O-78-C-O031 .hhuuufBuhhhh...Aerodyne Dallas th W__tIP FINAL REPORT CONTRACT* DAAK7-78-C-0031 FTURBOCHARGING OF SMALL INTERNAL COMBUSTION ENGINE AS A MEANS OF IMPROVING ENGINE ...DAAK70-78-C0031 TURBOCHARGING OF SMALL INTERNAL COMBUSTION ENGINES AS A MEANS OF IMPROVING ENGINE /APPLICATION SYSTEM FUEL ECONOMY Prepared by

14 CFR 21.6 - Manufacture of new aircraft, aircraft engines, and propellers.

Code of Federal Regulations, 2011 CFR

2011-01-01

... engines, and propellers. 21.6 Section 21.6 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Manufacture of new aircraft, aircraft engines, and propellers. (a) Except as specified in paragraphs (b) and (c) of this section, no person may manufacture a new aircraft, aircraft engine, or propeller based on...

14 CFR 21.6 - Manufacture of new aircraft, aircraft engines, and propellers.

Code of Federal Regulations, 2014 CFR

2014-01-01

... engines, and propellers. 21.6 Section 21.6 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Manufacture of new aircraft, aircraft engines, and propellers. (a) Except as specified in paragraphs (b) and (c) of this section, no person may manufacture a new aircraft, aircraft engine, or propeller based on...

14 CFR 21.6 - Manufacture of new aircraft, aircraft engines, and propellers.

Code of Federal Regulations, 2013 CFR

2013-01-01

... engines, and propellers. 21.6 Section 21.6 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Manufacture of new aircraft, aircraft engines, and propellers. (a) Except as specified in paragraphs (b) and (c) of this section, no person may manufacture a new aircraft, aircraft engine, or propeller based on...

14 CFR 21.6 - Manufacture of new aircraft, aircraft engines, and propellers.

Code of Federal Regulations, 2012 CFR

2012-01-01

... engines, and propellers. 21.6 Section 21.6 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Manufacture of new aircraft, aircraft engines, and propellers. (a) Except as specified in paragraphs (b) and (c) of this section, no person may manufacture a new aircraft, aircraft engine, or propeller based on...

Department of Defense In-House RDT and E Activities

DTIC Science & Technology

1977-10-30

SUPPRFSSI’N CWAMRFR, CAM EVAL & REF CEN, FUEL CELL t RTRY TEST STAS, ELEC PROPULSTON KTM, MPPS POWER TEST CELLS, nFRG TEST HANGAR, MORILE STRESS ANAL...TRIDENT,6S8,ETC) DESGNDEV E FVAL OF U/W TARGET SYSTEMS C MORILE /FIXD U/H TEST RANGES INTRODUCE TO FLEET C IN-SERVICE ENGINEERING OF MK 4S

Toward IVHM Prognostics

NASA Technical Reports Server (NTRS)

Walsh, Kevin; Venti, Mike

2007-01-01

This viewgraph presentation reviews the prognostics of Integrated Vehicle Health Management. The contents include: 1) Aircraft Operations-Today's way of doing business; 2) Prognostics; 3) NASA's instrumentation data-system rack; 4) Data mining for IVHM; 5) NASA GRC's C-MAPSS generic engine model; and 6) Concluding thoughts.

76 FR 39795 - Special Conditions: Pratt and Whitney Canada Model PT6C-67E Turboshaft Engine

Federal Register 2010, 2011, 2012, 2013, 2014

2011-07-07

... Whitney Canada (PWC) model PT6C-67E engines. The engine model will have a novel or unusual design feature... regulations do not contain adequate or appropriate safety standards for this design feature. These proposed... pre-addressed, stamped postcard on which the docket number appears. We will stamp the date on the...

cFE/CFS (Core Flight Executive/Core Flight System)

NASA Technical Reports Server (NTRS)

Wildermann, Charles P.

2008-01-01

This viewgraph presentation describes in detail the requirements and goals of the Core Flight Executive (cFE) and the Core Flight System (CFS). The Core Flight Software System is a mission independent, platform-independent, Flight Software (FSW) environment integrating a reusable core flight executive (cFE). The CFS goals include: 1) Reduce time to deploy high quality flight software; 2) Reduce project schedule and cost uncertainty; 3) Directly facilitate formalized software reuse; 4) Enable collaboration across organizations; 5) Simplify sustaining engineering (AKA. FSW maintenance); 6) Scale from small instruments to System of Systems; 7) Platform for advanced concepts and prototyping; and 7) Common standards and tools across the branch and NASA wide.

Powder metallurgy Rene 95 rotating turbine engine parts, volume 2

NASA Technical Reports Server (NTRS)

Wilbers, L. G.; Redden, T. K.

1981-01-01

A Rene 95 alloy as-HIP high pressure turbine aft shaft in the CF6-50 engine and a HIP plus forged Rene 95 compressor disk in the CFM56 engine were tested. The CF6-50 engine test was conducted for 1000 C cycles and the CFM56 test for 2000 C cycles. Post test evaluation and analysis of the CF6-50 shaft and the CFM56 compressor disk included visual, fluorescent penetrant, and dimensional inspections. No defects or otherwise discrepant conditions were found. These parts were judged to have performed satisfactorily.

46 CFR 56.50-20 - Pressure relief piping.

Code of Federal Regulations, 2013 CFR

2013-10-01

... Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) MARINE ENGINEERING PIPING SYSTEMS AND... authorized by the Marine Safety Center. (b) Discharge lines (reproduces 122.6.2(d)). Discharge lines from pressure-relieving safety devices shall be designed to facilitate drainage. (c) Stop valves. Stop valves...

46 CFR 56.50-20 - Pressure relief piping.

Code of Federal Regulations, 2014 CFR

2014-10-01

... Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) MARINE ENGINEERING PIPING SYSTEMS AND... authorized by the Marine Safety Center. (b) Discharge lines (reproduces 122.6.2(d)). Discharge lines from pressure-relieving safety devices shall be designed to facilitate drainage. (c) Stop valves. Stop valves...

Diversity of sulfate-reducing bacteria in a plant using deep geothermal energy

NASA Astrophysics Data System (ADS)

Alawi, Mashal; Lerm, Stephanie; Vetter, Alexandra; Wolfgramm, Markus; Seibt, Andrea; Würdemann, Hilke

2011-06-01

Enhanced process understanding of engineered geothermal systems is a prerequisite to optimize plant reliability and economy. We investigated microbial, geochemical and mineralogical aspects of a geothermal groundwater system located in the Molasse Basin by fluid analysis. Fluids are characterized by temperatures ranging from 61°C to 103°C, salinities from 600 to 900 mg/l and a dissolved organic carbon content (DOC) between 6.4 to 19.3 mg C/l. The microbial population of fluid samples was analyzed by genetic fingerprinting techniques based on PCR-amplified 16S rRNA- and dissimilatory sulfite reductase genes. Despite of the high temperatures, microbes were detected in all investigated fluids. Fingerprinting and DNA sequencing enabled a correlation to metabolic classes and biogeochemical processes. The analysis revealed a broad diversity of sulfate-reducing bacteria. Overall, the detection of microbes known to be involved in biocorrosion and mineral precipitation indicates that microorganisms could play an important role for the understanding of processes in engineered geothermal systems.

Development and Property Evaluation of Selected HfO2-Silicon and Rare Earth-Silicon Based Bond Coats and Environmental Barrier Coating Systems for SiC/SiC Ceramic Matrix Composites

NASA Technical Reports Server (NTRS)

Zhu, Dongming

2016-01-01

Ceramic environmental barrier coatings (EBC) and SiC/SiC ceramic matrix composites (CMCs) will play a crucial role in future aircraft propulsion systems because of their ability to significantly increase engine operating temperatures, improve component durability, reduce engine weight and cooling requirements. Advanced EBC systems for SiC/SiC CMC turbine and combustor hot section components are currently being developed to meet future turbine engine emission and performance goals. One of the significant material development challenges for the high temperature CMC components is to develop prime-reliant, high strength and high temperature capable environmental barrier coating bond coat systems, since the current silicon bond coat cannot meet the advanced EBC-CMC temperature and stability requirements. In this paper, advanced NASA HfO2-Si and rare earth Si based EBC bond coat EBC systems for SiC/SiC CMC combustor and turbine airfoil applications are investigated. High temperature properties of the advanced EBC systems, including the strength, fracture toughness, creep and oxidation resistance have been studied and summarized. The advanced NASA EBC systems showed some promise to achieve 1500C temperature capability, helping enable next generation turbine engines with significantly improved engine component temperature capability and durability.

76 FR 5507 - Airworthiness Directives; Airbus Model A300 B4-601, B4-603, B4-605R, C4-605R Variant F, and F4...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-02-01

...-80C2 forward engine mounts (skinny cast yoke) does not meet the Design Service Goal (DSG) requirements... forward engine mount. * * * * * The unsafe condition is possible separation of the engine from the engine... that, among the types of yokes in service, one component on the CF6-80C2 forward engine mounts (skinny...

Phase Interrogation Used for a Wireless Passive Pressure Sensor in an 800 °C High-Temperature Environment

PubMed Central

Zhang, Huixin; Hong, Yingping; Liang, Ting; Zhang, Hairui; Tan, Qiulin; Xue, Chenyang; Liu, Jun; Zhang, Wendong; Xiong, Jijun

2015-01-01

A wireless passive pressure measurement system for an 800 °C high-temperature environment is proposed and the impedance variation caused by the mutual coupling between a read antenna and a LC resonant sensor is analyzed. The system consists of a ceramic-based LC resonant sensor, a readout device for impedance phase interrogation, heat insulating material, and a composite temperature-pressure test platform. Performances of the pressure sensor are measured by the measurement system sufficiently, including pressure sensitivity at room temperature, zero drift from room temperature to 800 °C, and the pressure sensitivity under the 800 °C high temperature environment. The results show that the linearity of sensor is 0.93%, the repeatability is 6.6%, the hysteretic error is 1.67%, and the sensor sensitivity is 374 KHz/bar. The proposed measurement system, with high engineering value, demonstrates good pressure sensing performance in a high temperature environment. PMID:25690546

Creep Behavior of Hafnia and Ytterbium Silicate Environmental Barrier Coating Systems on SiC/SiC Ceramic Matrix Composites

NASA Technical Reports Server (NTRS)

Zhu, Dongming; Fox, Dennis S.; Ghosn, Louis J.; Harder, Bryan

2011-01-01

Environmental barrier coatings will play a crucial role in future advanced gas turbine engines because of their ability to significantly extend the temperature capability and stability of SiC/SiC ceramic matrix composite (CMC) engine components, thus improving the engine performance. In order to develop high performance, robust coating systems for engine components, appropriate test approaches simulating operating temperature gradient and stress environments for evaluating the critical coating properties must be established. In this paper, thermal gradient mechanical testing approaches for evaluating creep and fatigue behavior of environmental barrier coated SiC/SiC CMC systems will be described. The creep and fatigue behavior of Hafnia and ytterbium silicate environmental barrier coatings on SiC/SiC CMC systems will be reported in simulated environmental exposure conditions. The coating failure mechanisms will also be discussed under the heat flux and stress conditions.

Tuning optical properties of opal photonic crystals by structural defects engineering

NASA Astrophysics Data System (ADS)

di Stasio, F.; Cucini, M.; Berti, L.; Comoretto, D.; Abbotto, A.; Bellotto, L.; Manfredi, N.; Marinzi, C.

2009-06-01

We report on the preparation and optical characterization of three dimensional colloidal photonic crystal (PhC) containing an engineered planar defect embedding photoactive push-pull dyes. Free standing polystyrene films having thickness between 0.6 and 3 mm doped with different dipolar chromophores were prepared. These films were sandwiched between two artificial opals creating a PhC structure with planar defect. The system was characterized by reflectance at normal incidence angle (R), variable angle transmittance (T) and photoluminescence spectroscopy (PL) Evidence of defect states were observed in T and R spectra which allow the light to propagate for selected frequencies within the pseudogap (stop band).

Fabrication and Testing of Low Cost 2D Carbon-Carbon Nozzle Extensions at NASA/MSFC

NASA Technical Reports Server (NTRS)

Greene, Sandra Elam; Shigley, John K.; George, Russ; Roberts, Robert

2015-01-01

Subscale liquid engine tests were conducted at NASA/MSFC using a 1.2 Klbf engine with liquid oxygen (LOX) and gaseous hydrogen. Testing was performed for main-stage durations ranging from 10 to 160 seconds at a chamber pressure of 550 psia and a mixture ratio of 5.7. Operating the engine in this manner demonstrated a new and affordable test capability for evaluating subscale nozzles by exposing them to long duration tests. A series of 2D C-C nozzle extensions were manufactured, oxidation protection applied and then tested on a liquid engine test facility at NASA/MSFC. The C-C nozzle extensions had oxidation protection applied using three very distinct methods with a wide range of costs and process times: SiC via Polymer Impregnation & Pyrolysis (PIP), Air Plasma Spray (APS) and Melt Infiltration. The tested extensions were about 6" long with an exit plane ID of about 6.6". The test results, material properties and performance of the 2D C-C extensions and attachment features will be discussed.

Base-resolution detection of N 4-methylcytosine in genomic DNA using 4mC-Tet-assisted-bisulfite-sequencing

DOE PAGES

Yu, Miao; Ji, Lexiang; Neumann, Drexel A.; ...

2015-07-15

Restriction-modification (R-M) systems pose a major barrier to DNA transformation and genetic engineering of bacterial species. Systematic identification of DNA methylation in R-M systems, including N 6-methyladenine (6mA), 5-methylcytosine (5mC) and N 4-methylcytosine (4mC), will enable strategies to make these species genetically tractable. Although single-molecule, real time (SMRT) sequencing technology is capable of detecting 4mC directly for any bacterial species regardless of whether an assembled genome exists or not, it is not as scalable to profiling hundreds to thousands of samples compared with the commonly used next-generation sequencing technologies. Here, we present 4mC-Tet-assisted bisulfite-sequencing (4mC-TAB-seq), a next-generation sequencing method thatmore » rapidly and cost efficiently reveals the genome-wide locations of 4mC for bacterial species with an available assembled reference genome. In 4mC-TAB-seq, both cytosines and 5mCs are read out as thymines, whereas only 4mCs are read out as cytosines, revealing their specific positions throughout the genome. We applied 4mC-TAB-seq to study the methylation of a member of the hyperthermophilc genus, Caldicellulosiruptor, in which 4mC-related restriction is a major barrier to DNA transformation from other species. Lastly, in combination with MethylC-seq, both 4mC- and 5mC-containing motifs are identified which can assist in rapid and efficient genetic engineering of these bacteria in the future.« less

SIMULATION OF ION CONDUCTION IN α-HEMOLYSIN NANOPORES WITH COVALENTLY ATTACHED β-CYCLODEXTRIN BASED ON BOLTZMANN TRANSPORT MONTE CARLO MODEL

PubMed Central

Toghraee, Reza; Lee, Kyu-Il; Papke, David; Chiu, See-Wing; Jakobsson, Eric; Ravaioli, Umberto

2009-01-01

Ion channels, as natures’ solution to regulating biological environments, are particularly interesting to device engineers seeking to understand how natural molecular systems realize device-like functions, such as stochastic sensing of organic analytes. What’s more, attaching molecular adaptors in desired orientations inside genetically engineered ion channels, enhances the system functionality as a biosensor. In general, a hierarchy of simulation methodologies is needed to study different aspects of a biological system like ion channels. Biology Monte Carlo (BioMOCA), a three-dimensional coarse-grained particle ion channel simulator, offers a powerful and general approach to study ion channel permeation. BioMOCA is based on the Boltzmann Transport Monte Carlo (BTMC) and Particle-Particle-Particle-Mesh (P3M) methodologies developed at the University of Illinois at Urbana-Champaign. In this paper, we have employed BioMOCA to study two engineered mutations of α-HL, namely (M113F)6(M113C-D8RL2)1-β-CD and (M113N)6(T117C-D8RL3)1-β-CD. The channel conductance calculated by BioMOCA is slightly higher than experimental values. Permanent charge distributions and the geometrical shape of the channels gives rise to selectivity towards anions and also an asymmetry in I-V curves, promoting a rectification largely for cations. PMID:20938493

An In Vitro Perfusion System to Enhance Outflow Studies in Mouse Eyes

PubMed Central

Kizhatil, Krishnakumar; Chlebowski, Arthur; Tolman, Nicholas G.; Freeburg, Nelson F.; Ryan, Margaret M.; Shaw, Nicholas N.; Kokini, Alexander D. M.; Marchant, Jeffrey K.; John, Simon W. M.

2016-01-01

Purpose The molecular mechanisms controlling aqueous humor (AQH) outflow and IOP need much further definition. The mouse is a powerful system for characterizing the mechanistic basis of AQH outflow. To enhance outflow studies in mice, we developed a perfusion system that is based on human anterior chamber perfusion culture systems. Our mouse system permits previously impractical experiments. Methods We engineered a computer-controlled, pump-based perfusion system with a platform for mounting whole dissected mouse eyes (minus lens and iris, ∼45% of drainage tissue is perfused). We tested the system's ability to monitor outflow and tested the effects of the outflow-elevating drug, Y27632, a rho-associated protein kinase (ROCK) inhibitor. Finally, we tested the system's ability to detect genetically determined decreases in outflow by determining if deficiency of the candidate genes Nos3 and Cav1 alter outflow. Results Using our system, the outflow facility (C) of C57BL/6J mouse eyes was found to range between 7.7 and 10.4 nl/minutes/mm Hg (corrected for whole eye). Our system readily detected a 74.4% Y27632-induced increase in C. The NOS3 inhibitor L-NG-nitroarginine methyl ester (L-NAME) and a Nos3 null mutation reduced C by 28.3% and 35.8%, respectively. Similarly, in Cav1 null eyes C was reduced by 47.8%. Conclusions We engineered a unique perfusion system that can accurately measure changes in C. We then used the system to show that NOS3 and CAV1 are key components of mechanism(s) controlling outflow. PMID:27701632

78 FR 6400 - Twenty Third Meeting: RTCA Special Committee 203, Unmanned Aircraft Systems

Federal Register 2010, 2011, 2012, 2013, 2014

2013-01-30

..., Washington, DC 20036, or by telephone at (202) 833- 9339, fax at (202) 833-9434, or Web site at http://www...-Morning/Afternoon Workgroup Breakout Sessions System Engineering Workgroup Human Factors Subgroup C&C... Breakout Sessions System Engineering Workgroup C&C Workgroup S&A Workgroup Safety Workgroup Friday...

Foundations for Security Aware Software Development Education

DTIC Science & Technology

2005-11-22

depending on the budget, that support robustness. We discuss the educational customer base, projected lifetime, and complexity of paradigm shift that should...in Honour of Sir Tony Hoar, [6] Cheetham, C. and Ferraiolo, K., "The Systems Security Millenial Perspectives in Computer Science, Engineering...Capability Maturity Model", 21st 2002, 229-246. National Information Systems Security Conference, [15] Schwartz, J., "Object Oriented Extensions to October 5

Probabilistic Structural Analysis Program

NASA Technical Reports Server (NTRS)

Pai, Shantaram S.; Chamis, Christos C.; Murthy, Pappu L. N.; Stefko, George L.; Riha, David S.; Thacker, Ben H.; Nagpal, Vinod K.; Mital, Subodh K.

2010-01-01

NASA/NESSUS 6.2c is a general-purpose, probabilistic analysis program that computes probability of failure and probabilistic sensitivity measures of engineered systems. Because NASA/NESSUS uses highly computationally efficient and accurate analysis techniques, probabilistic solutions can be obtained even for extremely large and complex models. Once the probabilistic response is quantified, the results can be used to support risk-informed decisions regarding reliability for safety-critical and one-of-a-kind systems, as well as for maintaining a level of quality while reducing manufacturing costs for larger-quantity products. NASA/NESSUS has been successfully applied to a diverse range of problems in aerospace, gas turbine engines, biomechanics, pipelines, defense, weaponry, and infrastructure. This program combines state-of-the-art probabilistic algorithms with general-purpose structural analysis and lifting methods to compute the probabilistic response and reliability of engineered structures. Uncertainties in load, material properties, geometry, boundary conditions, and initial conditions can be simulated. The structural analysis methods include non-linear finite-element methods, heat-transfer analysis, polymer/ceramic matrix composite analysis, monolithic (conventional metallic) materials life-prediction methodologies, boundary element methods, and user-written subroutines. Several probabilistic algorithms are available such as the advanced mean value method and the adaptive importance sampling method. NASA/NESSUS 6.2c is structured in a modular format with 15 elements.

ML-o-Scope: A Diagnostic Visualization System for Deep Machine Learning Pipelines

DTIC Science & Technology

2014-05-16

ML-o-scope: a diagnostic visualization system for deep machine learning pipelines Daniel Bruckner Electrical Engineering and Computer Sciences... machine learning pipelines 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e. TASK NUMBER 5f...the system as a support for tuning large scale object-classification pipelines. 1 Introduction A new generation of pipelined machine learning models

First Article Test Noise Survey of the A/F32T-9 Large Turbo Fan Engine Enclosed Noise Suppressor System, Sky Harbor IAP (International Airport), Phoenix, Arizona.

DTIC Science & Technology

1987-06-01

21.6 **DOUERRLL LEUELS ɝ 1000Hz)* ORSPL - 68.8 dO ORSLR - 52.7 dB<R) ORSLC - 67.0 dB(C) C-R URLUE - *14.4 57 LEV’EL (Dec:i bels ~) 2.0- -4.0 8.0- N1 ...100.7 dO<C> C-A URLUE = 20.5 129 2. -󈨂 , : . ’ - . .. -. ;. _ . . . . .. . . ., ., ., , . . . . . . . . ..- .- - L.Et./EL ( DEec ’:ibels’)I .L. Ln

GN&C Engineering Best Practices for Human-Rated Spacecraft Systems

NASA Technical Reports Server (NTRS)

Dennehy, Cornelius J.; Lebsock, Kenneth; West, John

2007-01-01

The NASA Engineering and Safety Center (NESC) recently completed an in-depth assessment to identify a comprehensive set of engineering considerations for the Design, Development, Test and Evaluation (DDT&E) of safe and reliable human-rated spacecraft systems. Reliability subject matter experts, discipline experts, and systems engineering experts were brought together to synthesize the current "best practices" both at the spacecraft system and subsystems levels. The objective of this paper is to summarize, for the larger Community of Practice, the initial set of Guidance, Navigation and Control (GN&C) engineering Best Practices as identified by this NESC assessment process.

GN&C Engineering Best Practices for Human-Rated Spacecraft System

NASA Technical Reports Server (NTRS)

Dennehy, Cornelius J.; Lebsock, Kenneth; West, John

2008-01-01

The NASA Engineering and Safety Center (NESC) recently completed an in-depth assessment to identify a comprehensive set of engineering considerations for the Design, Development, Test and Evaluation (DDT&E) of safe and reliable human-rated spacecraft systems. Reliability subject matter experts, discipline experts, and systems engineering experts were brought together to synthesize the current "best practices" both at the spacecraft system and subsystems levels. The objective of this paper is to summarize, for the larger Community of Practice, the initial set of Guidance, Navigation and Control (GN&C) engineering Best Practices as identified by this NESC assessment process.

GN&C Engineering Best Practices For Human-Rated Spacecraft Systems

NASA Technical Reports Server (NTRS)

Dennehy, Cornelius J.; Lebsock, Kenneth; West, John

2007-01-01

The NASA Engineering and Safety Center (NESC) recently completed an in-depth assessment to identify a comprehensive set of engineering considerations for the Design, Development, Test and Evaluation (DDT&E) of safe and reliable human-rated spacecraft systems. Reliability subject matter experts, discipline experts, and systems engineering experts were brought together to synthesize the current "best practices" both at the spacecraft system and subsystems levels. The objective of this paper is to summarize, for the larger Community of Practice, the initial set of Guidance, Navigation and Control (GN&C) engineering Best Practices as identified by this NESC assessment process.

78 FR 19983 - Airworthiness Directives; General Electric Company Turbofan Engines

Federal Register 2010, 2011, 2012, 2013, 2014

2013-04-03

... Airworthiness Directives; General Electric Company Turbofan Engines AGENCY: Federal Aviation Administration (FAA... Electric Company (GE) CF34-8C and CF34-8E turbofan engines with certain part numbers (P/N) of operability...-8E6, and CF34-8E6A1 turbofan engines, with an operability bleed valve (OBV) part number (P/N...

Seepage and Piping through Levees and Dikes using 2D and 3D Modeling Codes

DTIC Science & Technology

2016-06-01

by the Hydrologic Systems Branch of the Flood and Storm Protection Division (CEERD-HF), U.S. Army Engineer Research and Development Center, Coastal ...ER D C/ CH L TR -1 6- 6 Flood & Coastal Storm Damage Reduction Program Seepage and Piping through Levees and Dikes Using 2D and 3D...Flood & Coastal Storm Damage Reduction Program ERDC/CHL TR-16-6 June 2016 Seepage and Piping through Levees and Dikes Using 2D and 3D Modeling Codes

T-6A Texan II Systems Engineering Case Study

DTIC Science & Technology

2010-01-01

response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and...Appendix C. T-6 Type Certificate Data Sheet….……………………………...……….....74 Appendix D. Amendment……………….………………...………………...………….….78 T-6A Texan II...DOCUMENT (SRD) ANTHROPOMETRY , REQUIRED VERSUS DESIRED

Graphite|LiFePO4 lithium-ion battery working at the heat engine coolant temperature

NASA Astrophysics Data System (ADS)

Lewandowski, Andrzej; Kurc, Beata; Swiderska-Mocek, Agnieszka; Kusa, Natalia

2014-11-01

Electrochemical properties of the graphite anode and the LiFePO4 cathode, working together with the 1 M LiPF6 in TMS (sulpholane) at 90 °C have been studied. The general aim of the investigation was to demonstrate a potential application for a Li-ion cell working in the cooling system of a car heat engine (90 °C). Electrodes were characterized with the use of electrochemical impedance spectroscopy (EIS), scanning electron microscopy (SEM) as well as galvanostatic charging/discharging tests. SEM images of both electrodes after charging/discharging processes were covered with a film (electrochemical SEI formation). The charge transfer resistance at 90 °C, Rct, of the C6Li|Li+ anode and the LiFePO4 cathode was 24 Ω and 110 Ω, respectively. Reversible capacity of the LiC6 anode after 10-20 cycles, at a low current rate was close to the theoretical value of 370 mAh g-1 however an increasing current rate decreased to ca. 200 mAh g-1 (for 1C). The reversibility of the process was close to 95%. The capacity of the LiFePO4 cathode was ca. 150 mAh g-1, almost independent of the current rate and close to the theoretical value of 170 mAh g-1.

A Theory of Diagnostic Inference: Contract Final Report,

DTIC Science & Technology

1983-11-01

and I-bLications ftlated to this Contract ........ 19 1caml.igmnts and Scientific I&VOuMM1.......................... 21 M&i 2 This report esunarizes our... Comunications Sciences Division Naval Training Equipment Center Code 7500 Orlando, FL 32813 Naval Research Laboratory Washington, D. C. 20375 Dr. Gary...Dr. A. L. Slafkosky Scientific Advisor Commander Commandant of the Marine Corps Naval Electronics Systems Co-and C6de RD-1 Human Factors Engineering

An investigation of enhanced capability thermal barrier coating systems for diesel engine components

NASA Technical Reports Server (NTRS)

Holtzman, R. L.; Layne, J. L.; Schechter, B.

1984-01-01

Material systems and processes for the development of effective and durable thermal barriers for heavy duty diesel engines were investigated. Seven coating systems were evaluated for thermal conductivity, erosion resistance, corrosion/oxidation resistance, and thermal shock resistance. An advanced coating system based on plasma sprayed particle yttria stabilized zirconia (PS/HYSZ) was judged superior in these tests. The measured thermal conductivity of the selected coating was 0.893 W/m C at 371 C. The PS/HYSZ coating system was applied to the piston crown, fire deck and valves of a single cylinder low heat rejection diesel engine. The coated engine components were tested for 24 hr at power levels from 0.83 MPa to 1.17 MPa brake mean effective pressure. The component coatings survived the engine tests with a minimum of distress. The measured fire deck temperatures decreased 86 C (155 F) on the intake side and 42 C (75 F) on the exhaust side with the coating applied.

46 CFR 162.161-2 - Incorporation by reference.

Code of Federal Regulations, 2014 CFR

2014-10-01

...) (June 4, 2008), (“MSC.1/Circ. 1267”), IBR approved for § 162.161-6. (c) National Fire Protection...: SPECIFICATIONS AND APPROVAL ENGINEERING EQUIPMENT Fixed Clean Agent Fire Extinguishing Systems § 162.161-2... from the sources listed below. It is also available for inspection at the National Archives and Records...

46 CFR 162.161-2 - Incorporation by reference.

Code of Federal Regulations, 2013 CFR

2013-10-01

...) (June 4, 2008), (“MSC.1/Circ. 1267”), IBR approved for § 162.161-6. (c) National Fire Protection...: SPECIFICATIONS AND APPROVAL ENGINEERING EQUIPMENT Fixed Clean Agent Fire Extinguishing Systems § 162.161-2... from the sources listed below. It is also available for inspection at the National Archives and Records...

46 CFR 162.161-2 - Incorporation by reference.

Code of Federal Regulations, 2012 CFR

2012-10-01

.../Circ. 848) (June 4, 2008), (“MSC.1/Circ. 1267”), IBR approved for § 162.161-6. (c) National Fire...: SPECIFICATIONS AND APPROVAL ENGINEERING EQUIPMENT Fixed Clean Agent Fire Extinguishing Systems § 162.161-2... is available from the sources listed below. It is also available for inspection at the National...

6. Historic photo of rocket engine test facility Building 202 ...

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

6. Historic photo of rocket engine test facility Building 202 complex in operation at night, September 12, 1957. On file at NASA Plumbrook Research Center, Sandusky, Ohio. NASA GRC photo number C-45924. - Rocket Engine Testing Facility, NASA Glenn Research Center, Cleveland, Cuyahoga County, OH

Environmental Stability and Oxidation Behavior of HfO2-Si and YbGd(O) Based Environmental Barrier Coating Systems for SiCSiC Ceramic Matrix Composites

NASA Technical Reports Server (NTRS)

Zhu, Dongming; Farmer, Serene; McCue, Terry R.; Harder, Bryan; Hurst, Janet B.

2017-01-01

Ceramic environmental barrier coatings (EBC) and SiCSiC ceramic matrix composites (CMCs) will play a crucial role in future aircraft propulsion systems because of their ability to significantly increase engine operating temperatures, improve component durability, reduce engine weight and cooling requirements. Advanced EBC systems for SiCSiC CMC turbine and combustor hot section components are currently being developed to meet future turbine engine emission and performance goals. One of the significant material development challenges for the high temperature CMC components is to develop prime-reliant, environmental durable environmental barrier coating systems. In this paper, the durability and performance of advanced Electron Beam-Physical Vapor Deposition (EB-PVD) NASA HfO2-Si and YbGdSi(O) EBC bond coat top coat systems for SiCSiC CMC have been summarized. The high temperature thermomechanical creep, fatigue and oxidation resistance have been investigated in the laboratory simulated high-heat-flux environmental test conditions. The advanced NASA EBC systems showed promise to achieve 1500C temperature capability, helping enable next generation turbine engines with significantly improved engine component temperature capability and durability.

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.

78 FR 24671 - Airworthiness Directives; General Electric Company Turbofan Engines

Federal Register 2010, 2011, 2012, 2013, 2014

2013-04-26

... Airworthiness Directives; General Electric Company Turbofan Engines AGENCY: Federal Aviation Administration (FAA... certain General Electric Company (GE) CF6-80C2 series turbofan engines. That AD currently requires.../B1F/B2F/B4F/B6F/B7F/D1F turbofan engines with any of the following installed: (1) Fuel tube, part...

Synthesis and Engineering Materials Properties of Fluid Phase Chemical Hydrogen Storage Materials for Automotive Applications

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

Choi, Young Joon; Westman, Matthew P.; Karkamkar, Abhijeet J.

Among candidates for chemical hydrogen storage in PEM fuel cell automotive applications, ammonia borane (AB, NH3BH3) is considered to be one of the most promising materials due to its high practical hydrogen content of 14-16 wt%. This material is selected as a surrogate chemical for a hydrogen storage system. For easier transition to the existing infrastructure, a fluid phase hydrogen storage material is very attractive and thus, we investigated the engineering materials properties of AB in liquid carriers for a chemical hydrogen storage slurry system. Slurries composed of AB and high temperature liquids were prepared by mechanical milling and sonicationmore » in order to obtain stable and fluidic properties. Volumetric gas burette system was adopted to observe the kinetics of the H2 release reactions of the AB slurry and neat AB. Viscometry and microscopy were employed to further characterize slurries engineering properties. Using a tip-sonication method we have produced AB/silicone fluid slurries at solid loadings up to 40wt% (6.5wt% H2) with viscosities less than 500cP at 25°C.« less

Metabolism of waste engine oil by Pseudomonas species.

PubMed

Salam, Lateef B

2016-06-01

Two bacterial strains phylogenetically identified as Pseudomonas aeruginosa strains RM1 and SK1 displayed extensive degradation ability on waste engine oil (SAE 40W) in batch cultures. Spectrophotometric analysis revealed the presence of various heavy metals such as lead, chromium and nickel in the waste engine oil. The rate of degradation of waste engine oil by the isolates, for the first 12 days and the last 9 days were 66.3, 31.6 mg l -1  day -1   and 69.6, 40.0 mg l -1  day -1 for strains RM1 and SK1, respectively. Gas chromatographic (GC) analyses of residual waste engine oil, revealed that 66.58, 89.06 % and 63.40, 90.75 % of the initial concentration of the waste engine oil were degraded by strains RM1 and SK1 within 12 and 21 days. GC fingerprints of the waste engine oil after 12 days of incubation of strains RM1 and SK1 showed total disappearance of C 15 , C 23 , C 24 , C 25 and C 26 hydrocarbon fractions as well as drastic reductions of C 13 , C 14 , C 16 and PAHs fractions such as C 19 -anthracene and C 22 -pyrene. At the end of 21 days incubation, total disappearance of C 17 -pristane, C 22 -pyrene, one of the C 19 -anthracene and significant reduction of C 18 -phytane (97.2 %, strain RM1; 95.1 %, strain SK1) fractions were observed. In addition, <10 % of Day 0 values of medium fraction ranges C 13 , and C 16 were discernible after 21 days. This study has established the potentials of P. aeruginosa strains RM1 and SK1 in the degradation of aliphatic, aromatic and branched alkane components of waste engine oils.

Systems engineering for Air Force C3I systems

NASA Astrophysics Data System (ADS)

Monahan, John H.

1993-06-01

Each day, sophisticated information systems provide the U.S. with crucial capabilities both to understand the world situation and to react effectively as required by our nation's decision makers. These systems attest to the success of the cooperative efforts of government and industry. Over the last 35 years, to help provide those capabilities, The MITRE Corporation has been privileged to fulfill the role of systems engineer on more than 100 different command, control, communications, and intelligence (C3I) systems for the Air Force and other elements of the Department of Defense (DOD). A long history of successful performance in this broad role provides MITRE with detailed knowledge of the systems' operational capabilities and needs, proficiency in their systems engineering, and a C3I-related corporate memory unmatched by any other organization. That background is the foundation of this book on systems engineering at MITRE.

Performance and Durability of Environmental Barrier Coatings on SiC/SiC Ceramic Matrix Composites

NASA Technical Reports Server (NTRS)

Zhu, Dongming; Harder, Bryan; Bhatt, Ramakrishna

2016-01-01

This presentation highlights advanced environmental barrier coating (EBC) and SiC-SiC Ceramic Matrix Composites (CMC) systems for next generation turbine engines. The emphasis will be placed on fundamental coating and CMC property evaluations; and the integrated system performance and degradation mechanisms in simulated laboratory turbine engine testing environments. Long term durability tests in laser rig simulated high heat flux the rmomechanical creep and fatigue loading conditions will also be presented. The results can help improve the future EBC-CMC system designs, validating the advanced EBC-CMC technologies for hot section turbine engine applications.

Fuel system design concepts for broad property fuels

NASA Technical Reports Server (NTRS)

Versaw, E. F.

1984-01-01

The results of a study assessing the impact of using jet fuel with relaxed specification properties on an aircraft fuel system are given. The study objectives were to identify credible values for specific fuel properties which might be relaxed, to evolve advanced fuel system designs for airframe and engines which would permit use of the specified relaxed properties fuels, and to evaluate performance of the candidate advanced fuel systems and the relaxed property fuels in a typical transport aircraft. The study used, as a baseline, the fuel system incorporated in the Lockheed Tristar. This aircraft is powered by three RB.211-524 Rolls-Royce engines and incorporates a Pratt and Whitney ST6C-421 auxiliary power unit for engine starting and inflight emergency electrical power. The fuel property limits examined are compared with commercial Jet A kerosene and the NASA RFP fuel properties. A screening of these properties established that a higher freezing point and a lower thermal stability would impact fuel system design more significantly than any of the other property changes. Three candidate fuel systems which combine the ability to operate with fuels having both a high freeze point and a low thermal stability are described. All candidates employ bleed air to melt fuel freeze-out prior to starting the APU or an inoperable engine. The effects of incorporating these systems on aircraft weight and engine specific fuel consumption are given.

14 CFR 25.1165 - Engine ignition systems.

Code of Federal Regulations, 2010 CFR

2010-01-01

... automatically available as an alternate source of electrical energy to allow continued engine operation if any... simultaneous demands of the engine ignition system and the greatest demands of any electrical system components that draw electrical energy from the same source. (c) The design of the engine ignition system must...

14 CFR 25.1165 - Engine ignition systems.

Code of Federal Regulations, 2011 CFR

2011-01-01

... automatically available as an alternate source of electrical energy to allow continued engine operation if any... simultaneous demands of the engine ignition system and the greatest demands of any electrical system components that draw electrical energy from the same source. (c) The design of the engine ignition system must...

Growth of Solid Solutions of Aluminum Nitride and Silicon Carbide by Metalorganic Chemical Vapor Deposition

DTIC Science & Technology

1992-08-27

Materials Science Center of Excellence REPORT NUMBER Howard University School of Engineering MSRCE ONR 1 2300 6th St., N.W. Washington, D.C. 20059 9...Research Center of Excellence, Department of Electrical Engineering, School of Engineering, Howard University , Washington, D.C., USA Abstract We report

Atlas 1.1 Implementation Guide: Moving from Theory into Practice

DTIC Science & Technology

2018-01-16

Math /Science/General Engienering...six proficiency areas based on the Helix interview data, as shown in Figure 6 below. Figure 6. Proficiency Areas for Systems Engineers 1. Math ...the problem domain and solution Math / Science / General Engineering System’s Domain & Opera:onal Context Systems Engineering

Combined Thermomechanical and Environmental Durability of Environmental Barrier Coating Systems on SiC/SiC Ceramic Matrix Composites

NASA Technical Reports Server (NTRS)

Zhu, Dongming; Harder, Bryan; Bhatt, Ramakrishna

2016-01-01

Environmental barrier coatings (EBCs) and SiC/SiC ceramic matrix composites (CMCs) will play a crucial role in next generation turbine engines for hot-section component applications. The development of prime-reliant environmental barrier coatings is essential to the EBC-CMC system durability, ensuring the successful implementations of the high temperature and lightweight engine component technologies for engine applications.This paper will emphasize recent NASA environmental barrier coating and CMC developments for SiC/SiC turbine airfoil components, utilizing advanced coating compositions and processing methods. The emphasis has been particularly placed on thermomechanical and environment durability evaluations of EBC-CMC systems. We have also addressed the integration of the EBCs with advanced SiC/SiC CMCs, and studied the effects of combustion environments and Calcium-Magnesium-Alumino-Silicate (CMAS) deposits on the durability of the EBC-CMC systems under thermal gradient and mechanical loading conditions. Advanced environmental barrier coating systems, including multicomponent rare earth silicate EBCs and HfO2-Si based bond coats, will be discussed for the performance improvements to achieve better temperature capability and CMAS resistance for future engine operating conditions.

User's Guide for the Commercial Modular Aero-Propulsion System Simulation (C-MAPSS)

NASA Technical Reports Server (NTRS)

Frederick, Dean K.; DeCastro, Jonathan A.; Litt, Jonathan S.

2007-01-01

This report is a Users Guide for the NASA-developed Commercial Modular Aero-Propulsion System Simulation (C-MAPSS) software, which is a transient simulation of a large commercial turbofan engine (up to 90,000-lb thrust) with a realistic engine control system. The software supports easy access to health, control, and engine parameters through a graphical user interface (GUI). C-MAPSS provides the user with a graphical turbofan engine simulation environment in which advanced algorithms can be implemented and tested. C-MAPSS can run user-specified transient simulations, and it can generate state-space linear models of the nonlinear engine model at an operating point. The code has a number of GUI screens that allow point-and-click operation, and have editable fields for user-specified input. The software includes an atmospheric model which allows simulation of engine operation at altitudes from sea level to 40,000 ft, Mach numbers from 0 to 0.90, and ambient temperatures from -60 to 103 F. The package also includes a power-management system that allows the engine to be operated over a wide range of thrust levels throughout the full range of flight conditions.

Access Point Selection for Multi-Rate IEEE 802.11 Wireless LANs

DTIC Science & Technology

2014-05-16

Mobile Systems, Applications and Services, 2006. [2] S . Vasudevan, K. Papagiannaki, C . Diot, J. Kurose, and D. Towsley, “Facilitating Access Point...LANs 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR( S ) 5d. PROJECT NUMBER 5e. TASK NUMBER 5f. WORK UNIT NUMBER 7...PERFORMING ORGANIZATION NAME( S ) AND ADDRESS(ES) University of California at Berkeley,Electrical Engineering and Computer Sciences,Berkeley,CA,94720 8

Technical Capability Upgrades to the NASA Langley Research Center 6 ft. by 6 ft. Thermal Vacuum Chamber

NASA Technical Reports Server (NTRS)

Thornblom, Mark N.; Beverly, Joshua; O'Connell, Joseph J.; Mau, Johnny C.; Duncan, Dwight L.

2014-01-01

The 6 ft. by 6 ft. thermal vacuum chamber (TVAC), housed in Building 1250 at the NASA Langley Research Center (LaRC), and managed by the Systems Integration and Test Branch within the Engineering Directorate, has undergone several significant modifications to increase testing capability, safety, and quality of measurements of articles under environmental test. Significant modifications include: a new nitrogen thermal conditioning unit for controlling shroud temperatures from -150degC to +150degC; two horizontal auxiliary cold plates for independent temperature control from -150degC to +200degC; a suite of contamination monitoring sensors for outgassing measurements and species identification; signal and power feed-throughs; new pressure gauges; and a new data acquisition and control commanding system including safety interlocks. This presentation will provide a general overview of the LaRC 6 ft. by 6 ft. TVAC chamber, an overview of the new technical capabilities, and illustrate each upgrade in detail, in terms of mechanical design and predicted performance. Additionally, an overview of the scope of tests currently being performed in the chamber will be documented, and sensor plots from tests will be provided to show chamber temperature and pressure performance with actual flight hardware under test.

Spectral Assessment of Soil Properties: Standoff Quantification of Soil Organic Matter Content in Surface Mineral Soils and Alaskan Peat

DTIC Science & Technology

2017-08-01

ER D C TR -1 7- 9 ERDC 6.1 Geospatial Research and Engineering (GRE) and ERDC 6.2 GRE ARTEMIS STO-R DRTSPORE Spectral Assessment of...The U.S. Army Engineer Research and Development Center (ERDC) solves the nation’s toughest engineering and environmental challenges. ERDC...published by ERDC, visit the ERDC online library at http://acwc.sdp.sirsi.net/client/default. ERDC 6.1 Geospatial Research and Engineering (GRE) and

Fermentative Production of the Diamine Putrescine: System Metabolic Engineering of Corynebacterium Glutamicum

PubMed Central

Nguyen, Anh Q. D.; Schneider, Jens; Reddy, Gajendar Komati; Wendisch, Volker F.

2015-01-01

Corynebacterium glutamicum shows great potential for the production of the glutamate-derived diamine putrescine, a monomeric compound of polyamides. A genome-scale stoichiometric model of a C. glutamicum strain with reduced ornithine transcarbamoylase activity, derepressed arginine biosynthesis, and an anabolic plasmid-addiction system for heterologous expression of E. coli ornithine decarboxylase gene speC was investigated by flux balance analysis with respect to its putrescine production potential. Based on these simulations, enhancing glycolysis and anaplerosis by plasmid-borne overexpression of the genes for glyceraldehyde 3-phosphate dehydrogenase and pyruvate carboxylase as well as reducing 2-oxoglutarate dehydrogenase activity were chosen as targets for metabolic engineering. Changing the translational start codon of the chromosomal gene for 2-oxoglutarate dehydrogenase subunit E1o to the less preferred TTG and changing threonine 15 of OdhI to alanine reduced 2-oxoglutarate dehydrogenase activity about five fold and improved putrescine titers by 28%. Additional engineering steps improved further putrescine production with the largest contributions from preventing the formation of the by-product N-acetylputrescine by deletion of spermi(di)ne N-acetyltransferase gene snaA and from overexpression of the gene for a feedback-resistant N-acetylglutamate kinase variant. The resulting C. glutamicum strain NA6 obtained by systems metabolic engineering accumulated two fold more putrescine than the base strain, i.e., 58.1 ± 0.2 mM, and showed a specific productivity of 0.045 g·g−1·h−1 and a yield on glucose of 0.26 g·g−1. PMID:25919117

The Development of Environmental Barrier Coatings for SiCSiC Ceramic Matrix Composites: Challenges and Opportunities

NASA Technical Reports Server (NTRS)

Zhu, Dongming

2014-01-01

Environmental barrier coatings (EBCs) and SiC/SiC ceramic matrix composites (CMCs) systems will play a crucial role in future turbine engines for hot-section component applications because of their ability to significantly increase engine operating temperatures, reduce engine weight and cooling requirements. The development of prime-reliant environmental barrier coatings is a key to enable the applications of the envisioned CMC components to help achieve next generation engine performance and durability goals. This paper will primarily address the performance requirements and design considerations of environmental barrier coatings for turbine engine applications. The emphasis is placed on current candidate environmental barrier coating systems for SiCSiC CMCs, their performance benefits and design limitations in long-term operation and combustion environments. Major technical barriers in developing advanced environmental barrier coating systems, the coating integrations with next generation CMC turbine components having improved environmental stability, cyclic durability and system performance will be described. The development trends for turbine environmental barrier coating systems by utilizing improved compositions, state-of-the-art processing methods, and simulated environment testing and durability modeling will be discussed.

Department of the Air Force Justification of Estimates for Fiscal Year 1981, Submitted to Congress January 1980, Aircraft Procurement, Air Force, Missile Procurement, Air Force, Other Procurement, Air Force.

DTIC Science & Technology

1980-01-01

10-0 6 EL4 -022 8L LLý 0 0 a 0 CLcc - 3 E CL 0 ;i *1 XO go10 ,* . , -8 rt -C CL.* L. OLc L ’i go 0 0 0 L +1%- 00 00I :) I.- I - - 51 .0 Cc a,,0 c0...of Test Cells M34 and M35. The bldg will be a prefabri- cated steel structure with several work stations. The work stations will have hoist systems...mate/demate the engine to its mount. The work stations will incorporate cell type interfaces for a limited checkout of engine in- strumentation. These

Advanced subsystems development

NASA Technical Reports Server (NTRS)

Livingston, F. R.

1978-01-01

The concept design for a small (less than 10 MWe) solar thermal electric generating plant was completed using projected 1985 technology. The systems requirements were defined and specified. The components, including an engineering prototype for one 15 kWe module of the generating plant, were conceptually designed. Significant features of the small solar thermal power plant were identified as the following: (1) 15 kWe Stirling-cycle engine/alternator with constant power output; (2) 10 meter point-focusing paraboloidal concentrator with cantilevered cellular glass reflecting panels; (3) primary heat pipe with 800 C output solar cavity receiver; (4) secondary heat pipe with molten salt thermal energy storage unit; (5) electric energy transport system; and (6) advanced battery energy storage capability.

Auto Mechanics I. Learning Activity Packets (LAPs). Section C--Engine.

ERIC Educational Resources Information Center

Oklahoma State Board of Vocational and Technical Education, Stillwater. Curriculum and Instructional Materials Center.

This document contains five learning activity packets (LAPs) that outline the study activities for the "engine" instructional area for an Auto Mechanics I course. The five LAPs cover the following topics: basic engine principles, cooling system, engine lubrication system, exhaust system, and fuel system. Each LAP contains a cover sheet…

Studies of Heat Transfer in Complex Internal Flows.

DTIC Science & Technology

1982-01-01

D.C. 20362 (Tel 202-692-6874) Mr. Richard S. Carlton Director, Engines Division, Code 523 NC #4 Naval Sea Systems Command Washington, D.C. 20362...Walter Ritz Code 033C Naval Ships Systems Engineering Station Philadelphia, Pennsylvania 19112 (Tel. 215-755-3841) Dr. Simion Kuo United Tech. Res

Engineering Design Handbook. Helicopter Engineering. Part One. Preliminary Design

DTIC Science & Technology

1974-08-30

1.3 ENGINE REPLACEMENT .............. ......................... 8-1 8-1.4 ENGINE AIR INDUCTION SYSTEM .............................. 8-2 8-1.5 ENGINE ...8-5 8-2.2 ENGINE AIR INDUCTION SYSTEM .............................. 8-5 8-2.2.1 G eneral Design...8-5 8-2.2.2 Air Induction System Inlet Location ............................... 8-6 8-2.2.3 Engine Air Induction System Pressure Losses

DMPL: Programming and Verifying Distributed Mixed Synchrony and Mixed Critical Software

DTIC Science & Technology

2016-06-16

ference on Intelligent Robots and Systems, pages 1495–1502, Chicago, IL, September 2014. IEEE Computer Society. [21] MADARA website . http://sourceforge.net...4.6 DMPL program for 5- robot reconnaissance example 19 Figure 5.1 Generated C++ code for example DMPL program. In practice, local vari- ables (lines...examples of collision avoidance in multi- robot systems. CMU/SEI-2016-TR-005 | SOFTWARE ENGINEERING INSTITUTE | Carnegie Mellon University vii

JPRS Report, Science & Technology. China.

DTIC Science & Technology

1989-03-29

Commun ., Vol COM-29, No 6, pp 895-901, June 1981. [4] R.C. Titsworth , "A Boolean-Function-Multiplexed Telemetry System," IEEE Trans, on SET, pp 42...Reagents 39 Gene-Engineered Human Epithelium Growth Factor (hEGF) 39 Superfine Snake Venom 39 COMPUTERS Ai Computer System LISP-MI [Zheng Shouqi, et...XUEBAO, No 3, Jun 88] 134 Coordinated Development of Microwave, Optical Communications [Zhang Xu; DIANXIN KUAIBAO, No 11, Nov 88] 143 Error

Improved Problem Formulation in Engineering Systems Design

DTIC Science & Technology

1990-05-01

Journal model is ASME Journal of Mechanical Design. 2 1.1 Research Objective and Methods The objective of this research project was to improve...Methods and Theories, Journal of Design Methods Group, Vol. 20, No. 2, 1986, p. 410. 19 Nadler, G., Smith, J. M. and Frey, C. E., "Problem...sources do you routinely use to gather the information you need to develop a packaging system? 26 Trade journals 6 Consultants 21 Reference books 26

Superovulation Using the Combined Administration of Inhibin Antiserum and Equine Chorionic Gonadotropin Increases the Number of Ovulated Oocytes in C57BL/6 Female Mice

PubMed Central

Takeo, Toru; Nakagata, Naomi

2015-01-01

Superovulation is a reproductive technique generally used to produce genetically engineered mice. Superovulation in mice involves the administration of equine chorionic gonadotropin (eCG) to promote follicle growth and then that of human chorionic gonadotropin (hCG) to induce ovulation. Previously, some published studies reported that inhibin antiserum (IAS) increased the number of ovulated oocytes in ddY and wild-derived strains of mice. However, the effect of IAS on the C57BL/6 strain, which is the most widely used inbred strain for the production of genetically engineered mice, has not been investigated. In addition, the combined effect of IAS and eCG (IASe) on the number of ovulated oocytes in superovulation treatment has not been examined. In this study, we examined the effect of IAS and eCG on the number of ovulated oocytes in immature female mice of the C57BL/6 strain in superovulation treatment. Furthermore, we evaluated the quality of obtained oocytes produced by superovulation using IASe by in vitro fertilization (IVF) with sperm from C57BL/6 or genetically engineered mice. The developmental ability of fresh or cryopreserved embryos was examined by embryo transfer. The administration of IAS or eCG had a similar effect on the number of ovulated oocytes in C57BL/6 female mice. The number of ovulated oocytes increased to about 3-fold by the administration of IASe than by the administration of IAS or eCG alone. Oocytes derived from superovulation using IASe normally developed into 2-cell embryos by IVF using sperm from C57BL/6 mice. Fresh or cryopreserved 2-cell embryos produced by IVF between oocytes of C57BL/6 mice and sperm from genetically engineered mice normally developed into live pups following embryo transfer. In summary, a novel technique of superovulation using IASe is extremely useful for producing a great number of oocytes and offspring from genetically engineered mice. PMID:26024317

Engine Icing Modeling and Simulation (Part 2): Performance Simulation of Engine Rollback Phenomena

NASA Technical Reports Server (NTRS)

May, Ryan D.; Guo, Ten-Huei; Veres, Joseph P.; Jorgenson, Philip C. E.

2011-01-01

Ice buildup in the compressor section of a commercial aircraft gas turbine engine can cause a number of engine failures. One of these failure modes is known as engine rollback: an uncommanded decrease in thrust accompanied by a decrease in fan speed and an increase in turbine temperature. This paper describes the development of a model which simulates the system level impact of engine icing using the Commercial Modular Aero-Propulsion System Simulation 40k (C-MAPSS40k). When an ice blockage is added to C-MAPSS40k, the control system responds in a manner similar to that of an actual engine, and, in cases with severe blockage, an engine rollback is observed. Using this capability to simulate engine rollback, a proof-of-concept detection scheme is developed and tested using only typical engine sensors. This paper concludes that the engine control system s limit protection is the proximate cause of iced engine rollback and that the controller can detect the buildup of ice particles in the compressor section. This work serves as a feasibility study for continued research into the detection and mitigation of engine rollback using the propulsion control system.

75 FR 46868 - Airworthiness Directives; The Boeing Company Model 747 Airplanes and Model 767 Airplanes Equipped...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-08-04

... crystal accretion. However, at this time, we do not agree to pursue research to develop an ice detector... significantly different type-design booster from that of the GE Model CF6-80C2 series engines (GE Model CF6-80A... events recorded on GE Model CF6-80A series engines. While this engine has a similar compressor design...

Discovery of gigantic molecular nanostructures using a flow reaction array as a search engine.

PubMed

Zang, Hong-Ying; de la Oliva, Andreu Ruiz; Miras, Haralampos N; Long, De-Liang; McBurney, Roy T; Cronin, Leroy

2014-04-28

The discovery of gigantic molecular nanostructures like coordination and polyoxometalate clusters is extremely time-consuming since a vast combinatorial space needs to be searched, and even a systematic and exhaustive exploration of the available synthetic parameters relies on a great deal of serendipity. Here we present a synthetic methodology that combines a flow reaction array and algorithmic control to give a chemical 'real-space' search engine leading to the discovery and isolation of a range of new molecular nanoclusters based on [Mo(2)O(2)S(2)](2+)-based building blocks with either fourfold (C4) or fivefold (C5) symmetry templates and linkers. This engine leads us to isolate six new nanoscale cluster compounds: 1, {Mo(10)(C5)}; 2, {Mo(14)(C4)4(C5)2}; 3, {Mo(60)(C4)10}; 4, {Mo(48)(C4)6}; 5, {Mo(34)(C4)4}; 6, {Mo(18)(C4)9}; in only 200 automated experiments from a parameter space spanning ~5 million possible combinations.

Reducing Uncertainty in Fatigue Life Limits of Turbine Engine Alloys (Preprint)

DTIC Science & Technology

2012-08-01

materials and components designs Conclusions This paper used electropolished specimens of the high-strength titanium alloy Ti-6Al- 2Sn-4Zr-6Mo to...From - To) August 2012 Technical Paper 1 July 2012 – 1 August 2012 4 . TITLE AND SUBTITLE REDUCING UNCERTAINTY IN FATIGUE LIFE LIMITS OF TURBINE...ENGINE ALLOYS (PREPRINT) 5a. CONTRACT NUMBER In-house 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 62102F 6 . AUTHOR(S) J.M. Larsen, C.J

40 CFR 94.308 - Maintenance of records.

Code of Federal Regulations, 2010 CFR

2010-07-01

...) Purchaser and destination; and (6) Assembly plant. (b) The manufacturer of any engine family that is... the calendar year; and (6) Useful life. (c) Any manufacturer producing an engine family participating... dispersed; and (6) How and through what means credit deficits are met. (d) The manufacturer must retain all...

Performance and Long Duration Test of a 30 kw Thermal Arcjet Engine.

DTIC Science & Technology

1987-11-01

Surface ____________________________ 69 50. SEM Close-up of Cathode Crater Surface Completely Covered with Arc Microspots and Splashed Tung- sten ...gaskets, and possibly stretching the bolts and/or nuts. 17 CL 4- C4 ---- 40 as 00 CiC E 18~ le J .Ir e 5 Figure 11 is a composite picture of the... composition . This transducer was zeroed both electronically and with reference to an ion gauge in a second vacuum system pumped by 26 F6 W. 320 a 280- (n, gis

Stochastic Models for Closed Boundary Analysis: Part I. Representation and Reconstruction.

DTIC Science & Technology

1980-07-01

discussed. In a subsequent paper we will consider the classification problem. C> * School of Electrical Engineering, Purdue University, West Lafayette, IN...1972. 2. T. S. Huang, "Coding of Two Tone Images," TR EE 77-10, School of Elec. Engr., Purdue University, W. Lafeyette, IN 47907. 3. A. Oosterlink, A...Jan. 1977. 5. A. Ambler et al., "A Versatile computer controlled assembly system," Third Intl. Conf. on Art . Intel., 1973, pp. 298-303. 6. C. Rosen

Informed Materials Discovery: Designing New Engineering Polymer Systems Using High Throughput Modeling Techniques

DTIC Science & Technology

2016-10-27

and molecu- lar physical structure into the prediction of the macroscopic constitutive properties and behaviour of the polymers. GIM uses a mean field...Cβ and Cg are related to the loss of DOFs over beta and glass transitions, where R is the molar gas constant and C is defined by: (2) C = NR (6.7T θ1...The compression yield behaviour of polymethyl methacrylate over a wide range of temperatures and strain-rates, Journal of Materials Science 8 (7

Sunmaster: An SEP cargo vehicle for Mars missions

NASA Technical Reports Server (NTRS)

Chiles, Aleasa; Fraser, Jennifer; Halsey, Andy; Honeycutt, David; Madden, Michael; Mcgough, Brian; Paulsen, David; Spear, Becky; Tarkenton, Lynne; Westley, Kevin

1991-01-01

Options are examined for an unmanned solar powered electric propulsion cargo vehicle for Mars missions. The 6 prime areas of study include: trajectory, propulsion system, power system, supporting structure, control system, and launch consideration. Optimization of the low thrust trajectory resulted in a total round trip mission time just under 4 years. The argon propelled electrostatic ion thruster system consists of seventeen 5 N engines and uses a specific impulse of 10,300 secs. At Earth, the system uses 13 engines to produce 60 N of thrust; at Mars, five engines are used, producing 25 N thrust. The thrust of the craft is varied between 60 N at Earth and 24 N at Mars due to reduced solar power available. Solar power is collected by a Fresnel lens concentrator system using a multistacked cell. This system provides 3.5 MW to the propulsion system after losses. Control and positioning to the craft are provided by a system of three double gimballed control moment gyros. Four shuttle 'C' launches will be used to transport the unassembled vehicle in modular units to low Earth orbit where it will be assembled using the Mobile Transporter of the Space Station Freedom.

Creep, Fatigue and Fracture Behavior of Environmental Barrier Coating and SiC-SiC Ceramic Matrix Composite Systems: The Role of Environment Effects

NASA Technical Reports Server (NTRS)

Zhu, Dongming; Ghosn, Louis J.

2015-01-01

Advanced environmental barrier coating (EBC) systems for low emission SiCSiC CMC combustors and turbine airfoils have been developed to meet next generation engine emission and performance goals. This presentation will highlight the developments of NASAs current EBC system technologies for SiC-SiC ceramic matrix composite combustors and turbine airfoils, their performance evaluation and modeling progress towards improving the engine SiCSiC component temperature capability and long-term durability. Our emphasis has also been placed on the fundamental aspects of the EBC-CMC creep and fatigue behaviors, and their interactions with turbine engine oxidizing and moisture environments. The EBC-CMC environmental degradation and failure modes, under various simulated engine testing environments, in particular involving high heat flux, high pressure, high velocity combustion conditions, will be discussed aiming at quantifying the protective coating functions, performance and durability, and in conjunction with damage mechanics and fracture mechanics approaches.

Microstructure Evolution and Durability of Advanced Environmental Barrier Coating Systems for SiC/SiC Ceramic Matrix Composites

NASA Technical Reports Server (NTRS)

Zhu, Dongming; Evans, Laura J.; McCue, Terry R.; Harder, Bryan

2016-01-01

Environmental barrier coated SiC-SiC ceramic matrix composites (CMCs) systems will play a crucial role in next generation turbine engines for hot-section component applications because of their ability to significantly increase engine operating temperatures with improved efficiency, reduce engine weight and cooling requirements. Advanced HfO2 and rare earth silicate environmental barrier coatings (EBCs), along with multicomponent hafnium and rare earth silicide EBC bond coats have been developed. The coating degradation mechanisms in the laboratory simulated engine thermal cycling, and fatigue-creep operating environments are also being investigated. This paper will focus on the microstructural and compositional evolutions of an advanced environmental barrier coating system on a SiC-SiC CMC substrate during the high temperature simulated durability tests, by using a Field Emission Gun Scanning Electron Microscopy, Energy Dispersive Spectroscopy (EDS) and Wavelength Dispersive Spectroscopy (WDS). The effects of Calcium-Magnesium-Alumino-Silicate (CMAS) from road sand or volcano-ash deposits on the degradation mechanisms of the environmental barrier coating systems will also be discussed. The detailed analysis results help understand the EBC-CMC system performance, aiming at the durability improvements to achieve more robust, prime-reliant environmental barrier coatings.

3D heterogeneous islet organoid generation from human embryonic stem cells using a novel engineered hydrogel platform.

PubMed

Candiello, Joseph; Grandhi, Taraka Sai Pavan; Goh, Saik Kia; Vaidya, Vimal; Lemmon-Kishi, Maya; Eliato, Kiarash Rahmani; Ros, Robert; Kumta, Prashant N; Rege, Kaushal; Banerjee, Ipsita

2018-05-25

Organoids, which exhibit spontaneous organ specific organization, function, and multi-cellular complexity, are in essence the in vitro reproduction of specific in vivo organ systems. Recent work has demonstrated human pluripotent stem cells (hPSCs) as a viable regenerative cell source for tissue-specific organoid engineering. This is especially relevant for engineering islet organoids, due to the recent advances in generating functional beta-like cells from human pluripotent stem cells. In this study, we report specific engineering of regenerative islet organoids of precise size and cellular heterogeneity, using a novel hydrogel system, Amikagel. Amikagel facilitated controlled and spontaneous aggregation of human embryonic stem cell derived pancreatic progenitor cells (hESC-PP) into robust homogeneous spheroids. This platform further allowed fine control over the integration of multiple cell populations to produce heterogeneous spheroids, which is a necessity for complex organoid engineering. Amikagel induced hESC-PP spheroid formation enhanced pancreatic islet-specific Pdx-1 and NKX6.1 gene and protein expression, while also increasing the percentage of committed population. hESC-PP spheroids were further induced towards mature beta-like cells which demonstrated increased Beta-cell specific INS1 gene and C-peptide protein expression along with functional insulin production in response to in vitro glucose challenge. Further integration of hESC-PP with biologically relevant supporting endothelial cells resulted in multicellular organoids which demonstrated spontaneous maturation towards islet-specific INS1 gene and C-peptide protein expression along with a significantly developed extracellular matrix support system. These findings establish Amikagel -facilitated platform ideal for islet organoid engineering. Copyright © 2018. Published by Elsevier Ltd.

Current status and recent research achievements in SiC/SiC composites

NASA Astrophysics Data System (ADS)

Katoh, Y.; Snead, L. L.; Henager, C. H.; Nozawa, T.; Hinoki, T.; Iveković, A.; Novak, S.; Gonzalez de Vicente, S. M.

2014-12-01

The silicon carbide fiber-reinforced silicon carbide matrix (SiC/SiC) composite system for fusion applications has seen a continual evolution from development a fundamental understanding of the material system and its behavior in a hostile irradiation environment to the current effort which is directed at a broad-based program of technology maturation program. In essence, over the past few decades this material system has steadily moved from a laboratory curiosity to an engineering material, both for fusion structural applications and other high performance application such as aerospace. This paper outlines the recent international scientific and technological achievements towards the development of SiC/SiC composite material technologies for fusion application and discusses future research directions. It also reviews the materials system in the larger context of progress to maturity as an engineering material for both the larger nuclear community and broader engineering applications.

CF6 jet engine performance improvement: New fan

NASA Technical Reports Server (NTRS)

Fasching, W. A.

1980-01-01

As part of the NASA sponsored engine component improvement program, and fan package was developed to reduce fuel consumption in current CF6 turbofan aircraft engine. The new fan package consist of an improved fan blade, reduced fan tip clearance due to a fan case stiffener, and a smooth fan casing tip shroud. CF6 engine performance and acoustic tests demonstrated the predicted 1.8% improvement in cruise sfc without an increase in engine noise. Power management thrust/fan speed characteristics were defined. Mechanical and structural integrity was demonstrated in model fan rotor photoelastic stress tests, full-size fan blade bench fatigue tests, and CF6 engine bird ingestion, crosswind, and cyclic endurance tests. The fan was certified in the CF6-500c2/E2 engines and is in commerical service on the Boeing 747-200, Douglas DC-10-30, and Atrbus industrie A300B aircraft.

Energy efficient engine component development and integration program

NASA Technical Reports Server (NTRS)

1981-01-01

The technology that will improve the energy efficiency of propulsion systems for subsonic commercial aircraft is investigated. A reduction of 14.4% in cruise installed sfc (0.572 versus 0.668 for the CF6-50C) and a direct operation cost reduction in excess of the 5% goal is projected. Noise and emissions projections are consistent with the established goals.

Performance Evaluation of the SPT-140

NASA Technical Reports Server (NTRS)

Manzella, David; Sarmiento, Charles; Sankovic, John; Haag, Tom

1997-01-01

As part of an on-going cooperative program with industry, an engineering model SPT-140 Hall thruster, which may be suitable for orbit insertion and station-keeping of geosynchronous communication satellites, was evaluated with respect to thrust and radiated electromagnetic interference at the NASA Lewis Research Center. Performance measurements were made using a laboratory model propellant feed system and commercial power supplies. The engine was operated in a space simulation chamber capable of providing background pressures of 4 x 10(exp -6) Torr or less during thruster operation. Thrust was measured at input powers ranging from 1.5 to 5 kilowatts with two different output filter configurations. The broadband electromagnetic emission spectra generated by the engine was also measured for a range of frequencies from 0.01 to 18,000 Mhz. These results are compared to the noise threshold of the measurement system and MIL-STD-461C where appropriate.

The Development of 2700-3000 F Environmental Barrier Coatings for SiC/SiC Ceramic Matrix Composites: Challenges and Opportunities

NASA Technical Reports Server (NTRS)

Zhu, Dongming

2015-01-01

Environmental barrier coatings (EBCs) and SiCSiC ceramic matrix composites (CMCs) systems will play a crucial role in future turbine engines for hot-section component applications because of their ability to significantly increase engine operating temperatures, reduce engine weight and cooling requirements. The development of prime-reliant environmental barrier coatings is a key to enable the applications of the envisioned 2700-3000F EBC - CMC systems to help achieve next generation engine performance and durability goals. This paper will primarily address the performance requirements and design considerations of environmental barrier coatings for turbine engine applications. The emphasis is placed on current NASA candidate environmental barrier coating systems for SiCSiC CMCs, their performance benefits and design limitations in long-term operation and combustion environments. The efforts have been also directed to developing prime-reliant, self-healing 2700F EBC bond coat; and high stability, lower thermal conductivity, and durable EBC top coats. Major technical barriers in developing environmental barrier coating systems, the coating integrations with next generation CMCs having the improved environmental stability, cyclic durability, erosion-impact resistance, and long-term system performance will be described. The research and development opportunities for turbine engine environmental barrier coating systems by utilizing improved compositions, state-of-the-art processing methods, and simulated environment testing and durability modeling will be discussed.

Orbital Transfer Rocket Engine Technology. Advanced Engine Study, Task D.6 Final Report

DTIC Science & Technology

1992-06-01

PROPERTIES _- -,mr m" , MANUAL a PAQ *E,- 7.3.2.1.2. IA .A.2 ,C -- 70-t’ i Rl I _ N -’.±v-j-. .......-441I 0.2% YS Design Allowable • -’Moo 0 2W0" 6W...Storage External Radiation Environment ( Buried Engine) The engine thrust chamber would be cold to the touch even at full thrust operation from the

Proceedings of the Ship Control Systems Symposium (5th), Held at U. S. Naval Academy, Annapolis, Maryland on October 30 - November 3, 1978. Volume 6,

DTIC Science & Technology

1978-11-03

Engineering with endorsements in Control Engineering and Applied Electronics. He joined his present company , Y-ARD Ltd, in 1972 and has been primarily...functions Io, II is 8(t 2-a 2). These formulae are derived on the assumption that the medium is infinite in extent; so they only apply if both source and...The author is indebted to the Danish Shipping Company A.P.Moller for providing the data from the full scale experiments. C 3-26 i. = -- -nm.i i Int I

An Integration of the Turbojet and Single-Throat Ramjet

NASA Technical Reports Server (NTRS)

Trefny, C. J.; Benson, T. J.

1995-01-01

A turbine-engine-based hybrid propulsion system is described. Turbojet engines are integrated with a single-throat ramjet so as to minimize variable geometry and eliminate redundant propulsion components. The result is a simple, lightweight system that is operable from takeoff to high Mach numbers. Non-afterburning turbojets are mounted within the ramjet duct. They exhaust through a converging-diverging (C-D) nozzle into a common ramjet burner section. At low speed the ejector effect of the C-D nozzle aerodynamically isolates the relatively high pressure turbojet exhaust stream from the ramjet duct. As the Mach number increases, and the turbojet pressure ratio diminishes, the system is biased naturally toward ramjet operation. The common ramjet burner is fueled with hydrogen and thermally choked, thus avoiding the weight and complexity of a variable geometry, split-flow exhaust system. The mixed-compression supersonic inlet and subsonic diffuser are also common to both the turbojet and ramjet cycles. As the compressor face total temperature limit is approached, a two-position flap within the inlet is actuated, which closes off the turbojet inlet and provides increased internal contraction for ramjet operation. Similar actuation of the turbojet C-D nozzle flap completes the enclosure of the turbojet. Performance of the hybrid system is compared herein to that of the discrete turbojet and ramjet engines from takeoff to Mach 6. The specific impulse of the hybrid system falls below that of the non-integrated turbojet and ramjet because of ejector and Rayleigh losses. Unlike the discrete turbojet or ramjet however, the hybrid system produces thrust over the entire Mach number range. An alternate mode of operation for takeoff and low speed is also described. In this mode the C-D nozzle flap is deflected to a third position, which closes off the ramjet duct and eliminates the ejector total pressure loss.

14 CFR 25.1165 - Engine ignition systems.

Code of Federal Regulations, 2013 CFR

2013-01-01

... automatically available as an alternate source of electrical energy to allow continued engine operation if any... that draw electrical energy from the same source. (c) The design of the engine ignition system must...

14 CFR 25.1165 - Engine ignition systems.

Code of Federal Regulations, 2012 CFR

2012-01-01

... automatically available as an alternate source of electrical energy to allow continued engine operation if any... that draw electrical energy from the same source. (c) The design of the engine ignition system must...

76 FR 64291 - Airworthiness Directives; General Electric Company (GE) Turbofan Engines

Federal Register 2010, 2011, 2012, 2013, 2014

2011-10-18

... Company (GE) Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of... turbofan engines, including engines marked on the engine data plate as CF6-80C2B7F1. This proposed AD was... on engines in service. This proposed AD would require a one- time inspection of the No. 3 bearing...

14 CFR 25.857 - Cargo compartment classification.

Code of Federal Regulations, 2012 CFR

2012-01-01

... detector or fire detector system to give warning at the pilot or flight engineer station. (c) Class C. A... compartment but in which— (1) There is a separate approved smoke detector or fire detector system to give... a separate approved smoke or fire detector system to give warning at the pilot or flight engineer...

14 CFR 25.857 - Cargo compartment classification.

Code of Federal Regulations, 2010 CFR

2010-01-01

... detector or fire detector system to give warning at the pilot or flight engineer station. (c) Class C. A... compartment but in which— (1) There is a separate approved smoke detector or fire detector system to give... a separate approved smoke or fire detector system to give warning at the pilot or flight engineer...

14 CFR 25.857 - Cargo compartment classification.

Code of Federal Regulations, 2013 CFR

2013-01-01

... detector or fire detector system to give warning at the pilot or flight engineer station. (c) Class C. A... compartment but in which— (1) There is a separate approved smoke detector or fire detector system to give... a separate approved smoke or fire detector system to give warning at the pilot or flight engineer...

14 CFR 25.857 - Cargo compartment classification.

Code of Federal Regulations, 2014 CFR

2014-01-01

... detector or fire detector system to give warning at the pilot or flight engineer station. (c) Class C. A... compartment but in which— (1) There is a separate approved smoke detector or fire detector system to give... a separate approved smoke or fire detector system to give warning at the pilot or flight engineer...

14 CFR 25.857 - Cargo compartment classification.

Code of Federal Regulations, 2011 CFR

2011-01-01

... detector or fire detector system to give warning at the pilot or flight engineer station. (c) Class C. A... compartment but in which— (1) There is a separate approved smoke detector or fire detector system to give... a separate approved smoke or fire detector system to give warning at the pilot or flight engineer...

User's Guide for the Commercial Modular Aero-Propulsion System Simulation (C-MAPSS): Version 2

NASA Technical Reports Server (NTRS)

Liu, Yuan; Frederick, Dean K.; DeCastro, Jonathan A.; Litt, Jonathan S.; Chan, William W.

2012-01-01

This report is a Users Guide for version 2 of the NASA-developed Commercial Modular Aero-Propulsion System Simulation (C-MAPSS) software, which is a transient simulation of a large commercial turbofan engine (up to 90,000-lb thrust) with a realistic engine control system. The software supports easy access to health, control, and engine parameters through a graphical user interface (GUI). C-MAPSS v.2 has some enhancements over the original, including three actuators rather than one, the addition of actuator and sensor dynamics, and an improved controller, while retaining or improving on the convenience and user-friendliness of the original. C-MAPSS v.2 provides the user with a graphical turbofan engine simulation environment in which advanced algorithms can be implemented and tested. C-MAPSS can run user-specified transient simulations, and it can generate state-space linear models of the nonlinear engine model at an operating point. The code has a number of GUI screens that allow point-and-click operation, and have editable fields for user-specified input. The software includes an atmospheric model which allows simulation of engine operation at altitudes from sea level to 40,000 ft, Mach numbers from 0 to 0.90, and ambient temperatures from -60 to 103 F. The package also includes a power-management system that allows the engine to be operated over a wide range of thrust levels throughout the full range of flight conditions.

Environmental Barrier Coating Development for SiC/SiC Ceramic Matrix Composites: Recent Advances and Future Directions

NASA Technical Reports Server (NTRS)

Zhu, Dongming

2016-01-01

This presentation briefly reviews the SiC/SiC major environmental and environment-fatigue degradations encountered in simulated turbine combustion environments, and thus NASA environmental barrier coating system evolution for protecting the SiC/SiC Ceramic Matrix Composites for meeting the engine performance requirements. The presentation will review several generations of NASA EBC materials systems, EBC-CMC component system technologies for SiC/SiC ceramic matrix composite combustors and turbine airfoils, highlighting the temperature capability and durability improvements in simulated engine high heat flux, high pressure, high velocity, and with mechanical creep and fatigue loading conditions. This paper will also focus on the performance requirements and design considerations of environmental barrier coatings for next generation turbine engine applications. The current development emphasis is placed on advanced NASA candidate environmental barrier coating systems for SiC/SiC CMCs, their performance benefits and design limitations in long-term operation and combustion environments. The efforts have been also directed to developing prime-reliant, self-healing 2700F EBC bond coat; and high stability, lower thermal conductivity, and durable EBC top coats. Major technical barriers in developing environmental barrier coating systems, the coating integrations with next generation CMCs having the improved environmental stability, erosion-impact resistance, and long-term fatigue-environment system durability performance will be described. The research and development opportunities for turbine engine environmental barrier coating systems by utilizing improved compositions, state-of-the-art processing methods, and simulated environment testing and durability modeling will be briefly discussed.

14 CFR 25.951 - General.

Code of Federal Regulations, 2010 CFR

2010-01-01

... STANDARDS: TRANSPORT CATEGORY AIRPLANES Powerplant Fuel System § 25.951 General. (a) Each fuel system must... to be in operation. (b) Each fuel system must be arranged so that any air which is introduced into... engines; or (2) Flameout for turbine engines. (c) Each fuel system for a turbine engine must be capable of...

14 CFR 25.951 - General.

Code of Federal Regulations, 2012 CFR

2012-01-01

... STANDARDS: TRANSPORT CATEGORY AIRPLANES Powerplant Fuel System § 25.951 General. (a) Each fuel system must... to be in operation. (b) Each fuel system must be arranged so that any air which is introduced into... engines; or (2) Flameout for turbine engines. (c) Each fuel system for a turbine engine must be capable of...

14 CFR 25.951 - General.

Code of Federal Regulations, 2011 CFR

2011-01-01

... STANDARDS: TRANSPORT CATEGORY AIRPLANES Powerplant Fuel System § 25.951 General. (a) Each fuel system must... to be in operation. (b) Each fuel system must be arranged so that any air which is introduced into... engines; or (2) Flameout for turbine engines. (c) Each fuel system for a turbine engine must be capable of...

14 CFR 25.951 - General.

Code of Federal Regulations, 2014 CFR

2014-01-01

... STANDARDS: TRANSPORT CATEGORY AIRPLANES Powerplant Fuel System § 25.951 General. (a) Each fuel system must... to be in operation. (b) Each fuel system must be arranged so that any air which is introduced into... engines; or (2) Flameout for turbine engines. (c) Each fuel system for a turbine engine must be capable of...

14 CFR 25.951 - General.

Code of Federal Regulations, 2013 CFR

2013-01-01

... STANDARDS: TRANSPORT CATEGORY AIRPLANES Powerplant Fuel System § 25.951 General. (a) Each fuel system must... to be in operation. (b) Each fuel system must be arranged so that any air which is introduced into... engines; or (2) Flameout for turbine engines. (c) Each fuel system for a turbine engine must be capable of...

Advanced Concepts of Naval Engineering Maintenance Training. Volume 2. Appendix F

DTIC Science & Technology

1976-05-01

maintenance instruction, the Hagan Automatic Boiler Control (ABC) course. These job requirements also included the tasks, skills, and knowledges for all...Pressure 1 3/4 NAVTRAEQÜIPCEN 74-C-0151-1 TABLE OF CONTENTS VOLUME II OF II APPENDIX F Page Hagan Automatic Boiler Controls Systems (FAS) 6...a c a ■* w ■H u 0 M « s? u ’• B n J-riH 3 o c 0 hhO a a o -i •H -I 0 -H 9J ■ a a oi « C -a u <rl « vi) •a - 8 ai >> u u

Opportunities Analysis of Potential Advanced Vortex Systems Separation Standards,

DTIC Science & Technology

1979-07-01

IAH 32 16 42 10 48 13 28 11 CLE 33 11 45 11 33 14 38 15 SEA 22 23 36 19 25 27 27 21 B-2 TABLE B-2 1985 IFR CAPACITIES IN OPERATIONS PER HOUR 20...18 53 23 EWR 7 23 54 16 9 28 44 19 IAN 7 22 50 13 8 24 49 19 CLE 5 16 64 15 6 20 53 21 4 SEA 9 27 42 22 11 32 32 25 C-2 TABLE C-2 1985 IFR CAPACITIES...Administration Office of Systems Engineering Management 14. SposoingAg, Cede Washington, DC 20591 AEM- 100 15. Supplementary Notes 16 . Abstract The

Current Status and Recent Research Achievements in SiC/SiC Composites

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

Katoh, Yutai; Snead, Lance L.; Henager, Charles H.

2014-12-01

The development and maturation of the silicon carbide fiber-reinforced silicon carbide matrix (SiC/SiC) composite system for fusion applications has seen the evolution from fundamental development and understanding of the material system and its behavior in a hostile irradiation environment to the current effort which essentially is a broad-based program of technology, directed at moving this material class from a laboratory curiosity to an engineering material. This paper lays out the recent international scientific and technological achievements in the development of SiC/SiC composite material technologies for fusion application and will discuss future research directions. It also reviews the materials system inmore » the larger context of progress to maturity as an engineering material for both the larger nuclear community and for general engineering applications.« less

14 CFR 29.1165 - Engine ignition systems.

Code of Federal Regulations, 2012 CFR

2012-01-01

... automatically available as an alternate source of electrical energy to allow continued engine operation if any... that draw from the same source. (c) The design of the engine ignition system must account for— (1) The...

14 CFR 29.1165 - Engine ignition systems.

Code of Federal Regulations, 2013 CFR

2013-01-01

... automatically available as an alternate source of electrical energy to allow continued engine operation if any... that draw from the same source. (c) The design of the engine ignition system must account for— (1) The...

Genetically programmed chiral organoborane synthesis

NASA Astrophysics Data System (ADS)

Kan, S. B. Jennifer; Huang, Xiongyi; Gumulya, Yosephine; Chen, Kai; Arnold, Frances H.

2017-12-01

Recent advances in enzyme engineering and design have expanded nature’s catalytic repertoire to functions that are new to biology. However, only a subset of these engineered enzymes can function in living systems. Finding enzymatic pathways that form chemical bonds that are not found in biology is particularly difficult in the cellular environment, as this depends on the discovery not only of new enzyme activities, but also of reagents that are both sufficiently reactive for the desired transformation and stable in vivo. Here we report the discovery, evolution and generalization of a fully genetically encoded platform for producing chiral organoboranes in bacteria. Escherichia coli cells harbouring wild-type cytochrome c from Rhodothermus marinus (Rma cyt c) were found to form carbon-boron bonds in the presence of borane-Lewis base complexes, through carbene insertion into boron-hydrogen bonds. Directed evolution of Rma cyt c in the bacterial catalyst provided access to 16 novel chiral organoboranes. The catalyst is suitable for gram-scale biosynthesis, providing up to 15,300 turnovers, a turnover frequency of 6,100 h-1, a 99:1 enantiomeric ratio and 100% chemoselectivity. The enantiopreference of the biocatalyst could also be tuned to provide either enantiomer of the organoborane products. Evolved in the context of whole-cell catalysts, the proteins were more active in the whole-cell system than in purified forms. This study establishes a DNA-encoded and readily engineered bacterial platform for borylation; engineering can be accomplished at a pace that rivals the development of chemical synthetic methods, with the ability to achieve turnovers that are two orders of magnitude (over 400-fold) greater than those of known chiral catalysts for the same class of transformation. This tunable method for manipulating boron in cells could expand the scope of boron chemistry in living systems.

48 CFR 836.606-73 - Application of 6 percent architect-engineer fee limitation.

Code of Federal Regulations, 2012 CFR

2012-10-01

... architect-engineer fee limitation. 836.606-73 Section 836.606-73 Federal Acquisition Regulations System DEPARTMENT OF VETERANS AFFAIRS SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 836.606-73 Application of 6 percent architect-engineer fee limitation...

48 CFR 836.606-73 - Application of 6 percent architect-engineer fee limitation.

Code of Federal Regulations, 2011 CFR

2011-10-01

... architect-engineer fee limitation. 836.606-73 Section 836.606-73 Federal Acquisition Regulations System DEPARTMENT OF VETERANS AFFAIRS SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 836.606-73 Application of 6 percent architect-engineer fee limitation...

48 CFR 836.606-73 - Application of 6 percent architect-engineer fee limitation.

Code of Federal Regulations, 2014 CFR

2014-10-01

... architect-engineer fee limitation. 836.606-73 Section 836.606-73 Federal Acquisition Regulations System DEPARTMENT OF VETERANS AFFAIRS SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 836.606-73 Application of 6 percent architect-engineer fee limitation...

48 CFR 836.606-73 - Application of 6 percent architect-engineer fee limitation.

Code of Federal Regulations, 2013 CFR

2013-10-01

... architect-engineer fee limitation. 836.606-73 Section 836.606-73 Federal Acquisition Regulations System DEPARTMENT OF VETERANS AFFAIRS SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 836.606-73 Application of 6 percent architect-engineer fee limitation...

Durability and CMAS Resistance of Advanced Environmental Barrier Coatings Systems for SiC/SiC Ceramic Matrix Composites

NASA Technical Reports Server (NTRS)

Zhu, Dongming

2015-01-01

Environmental barrier coatings (EBCs) and SiCSiC ceramic matrix composites (CMCs) systems will play a crucial role in next generation turbine engines for hot-section component applications because of their ability to significantly increase engine operating temperatures with improved efficiency, reduce engine weight and cooling requirements. This paper will emphasize advanced environmental barrier coating developments for SiCSiC turbine airfoil components, by using advanced coating compositions and processing, in conjunction with mechanical and environment testing and durability validations. The coating-CMC degradations and durability in the laboratory simulated engine fatigue-creep and complex operating environments are being addressed. The effects of Calcium-Magnesium-Alumino-Silicate (CMAS) from road sand or volcano-ash deposits on the degradation mechanisms of the environmental barrier coating systems will be discussed. The results help understand the advanced EBC-CMC system performance, aiming at the durability improvements of more robust, prime-reliant environmental barrier coatings for successful applications of the component technologies and lifing methodologies.

Reliability study of an emerging fire suppression system

DOE PAGES

Miller, David A.; Rossati, Lyric M.; Fritz, Nathan K.; ...

2015-11-01

Self-contained fire extinguishers are a robust, reliable and minimally invasive means of fire suppression for gloveboxes. Plutonium gloveboxes are known to present harsh environmental conditions for polymer materials, these include radiation damage and chemical exposure, both of which tend to degrade the lifetime of engineered polymer components. The primary component of interest in self-contained fire extinguishers is the nylon 6-6 machined tube that comprises the main body of the system.Thermo-mechanical modeling and characterization of nylon 6-6 for use in plutonium glovebox applications has been carried out. Data has been generated regarding property degradation leading to poor, or reduced, engineering performancemore » of nylon 6-6 components. In this study, nylon 6-6 tensile specimens conforming to the casing of self-contained fire extinguisher systems have been exposed to hydrochloric, nitric, and sulfuric acids. This information was used to predict the performance of a load bearing engineering component comprised of nylon 6-6 and designed to operate in a consistent manner over a specified time period. The study provides a fundamental understanding of the engineering performance of the fire suppression system and the effects of environmental degradation due to acid exposure on engineering performance. Data generated help identify the limitations of self-contained fire extinguishers. No critical areas of concern for plutonium glovebox applications of nylon 6-6 have been identified when considering exposure to mineral acid.« less

Reliability study of an emerging fire suppression system

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

Miller, David A.; Rossati, Lyric M.; Fritz, Nathan K.

Self-contained fire extinguishers are a robust, reliable and minimally invasive means of fire suppression for gloveboxes. Plutonium gloveboxes are known to present harsh environmental conditions for polymer materials, these include radiation damage and chemical exposure, both of which tend to degrade the lifetime of engineered polymer components. The primary component of interest in self-contained fire extinguishers is the nylon 6-6 machined tube that comprises the main body of the system.Thermo-mechanical modeling and characterization of nylon 6-6 for use in plutonium glovebox applications has been carried out. Data has been generated regarding property degradation leading to poor, or reduced, engineering performancemore » of nylon 6-6 components. In this study, nylon 6-6 tensile specimens conforming to the casing of self-contained fire extinguisher systems have been exposed to hydrochloric, nitric, and sulfuric acids. This information was used to predict the performance of a load bearing engineering component comprised of nylon 6-6 and designed to operate in a consistent manner over a specified time period. The study provides a fundamental understanding of the engineering performance of the fire suppression system and the effects of environmental degradation due to acid exposure on engineering performance. Data generated help identify the limitations of self-contained fire extinguishers. No critical areas of concern for plutonium glovebox applications of nylon 6-6 have been identified when considering exposure to mineral acid.« less

Complete matrix properties of [001](c) and [011](c) poled 0.33Pb(In(1/2)Nb(1/2))O(3)-0.38Pb(Mg(1/3)Nb(2/3))O(3)-0.29PbTiO(3) single crystals.

PubMed

Sun, Enwei; Zhang, Rui; Wu, Fengmin; Cao, Wenwu

2013-03-15

The elastic, piezoelectric, and dielectric properties of [001](c) and [011](c) poled 0.33Pb(In(1/2)Nb(1/2))O(3)-0.38Pb(Mg(1/3)Nb(2/3))O(3)-0.29PbTiO(3) single crystals have been fully characterized at room temperature, and the temperature and frequency dependence of the dielectric susceptibility ε(33) were also measured. The depoling temperature of this crystal is more than 20 °C higher than that of the corresponding binary 0.71Pb(Mg(1/3)Nb(2/3))O(3)-0.29PbTiO(3) system. From the measured P-E hysteresis loops, the coercive fields along [001](c) and [011](c) directions have been determined to be 6.0 kV/cm and 6.6 kV/cm, respectively, which indicate that these domain engineered ternary relaxor-based ferroelectric single crystals are excellent candidates for high-power applications.

Innovative Methods for Engine Health Monitoring

DTIC Science & Technology

2006-11-30

ELEMENT NUMBER 6. AUTHOR(S) 6d. PROJECT NUMBER C. L. Philip Chen, Z. Pantic-Tanner, H. Millwater , S. Hudak, Y. Huang, P. Cotae, D. Tanner, E. John, K. Chan...Philip Chen’, Z. Pantic-Tanner 2, H. Millwater 3, S. Hudak 4, Y. Huang5, P. Cotae6, D. Tanner 7, E. Johns, K.Chan9, X. Wang𔃺 1 - Professor and Chair... Millwater , R.C. McClung, M.P. Enright, "A new tool for design and certification of aircraft turbine rotors," Journal of Engineering for Gas Turbines

DYGABCD: A program for calculating linear A, B, C, and D matrices from a nonlinear dynamic engine simulation

NASA Technical Reports Server (NTRS)

Geyser, L. C.

1978-01-01

A digital computer program, DYGABCD, was developed that generates linearized, dynamic models of simulated turbofan and turbojet engines. DYGABCD is based on an earlier computer program, DYNGEN, that is capable of calculating simulated nonlinear steady-state and transient performance of one- and two-spool turbojet engines or two- and three-spool turbofan engines. Most control design techniques require linear system descriptions. For multiple-input/multiple-output systems such as turbine engines, state space matrix descriptions of the system are often desirable. DYGABCD computes the state space matrices commonly referred to as the A, B, C, and D matrices required for a linear system description. The report discusses the analytical approach and provides a users manual, FORTRAN listings, and a sample case.

Video-Game-Like Engine for Depicting Spacecraft Trajectories

NASA Technical Reports Server (NTRS)

Upchurch, Paul R.

2009-01-01

GoView is a video-game-like software engine, written in the C and C++ computing languages, that enables real-time, three-dimensional (3D)-appearing visual representation of spacecraft and trajectories (1) from any perspective; (2) at any spatial scale from spacecraft to Solar-system dimensions; (3) in user-selectable time scales; (4) in the past, present, and/or future; (5) with varying speeds; and (6) forward or backward in time. GoView constructs an interactive 3D world by use of spacecraft-mission data from pre-existing engineering software tools. GoView can also be used to produce distributable application programs for depicting NASA orbital missions on personal computers running the Windows XP, Mac OsX, and Linux operating systems. GoView enables seamless rendering of Cartesian coordinate spaces with programmable graphics hardware, whereas prior programs for depicting spacecraft trajectories variously require non-Cartesian coordinates and/or are not compatible with programmable hardware. GoView incorporates an algorithm for nonlinear interpolation between arbitrary reference frames, whereas the prior programs are restricted to special classes of inertial and non-inertial reference frames. Finally, whereas the prior programs present complex user interfaces requiring hours of training, the GoView interface provides guidance, enabling use without any training.

Metastable Polymers for On Demand Transient Electronic Packaging

DTIC Science & Technology

2018-01-17

a triggerable polymer for engineering applications. 25 Approved for public release; distribution is unlimited. 6 REFERENCES (1) Aso, C.; Tagami, S...R. Advanced Materials 2014, 26, 7637. (4) Ito, H.; Willson, C. G. Polymer Engineering & Science 1983, 23, 1012. (5) Ito, H.; England, W. P.; Ueda, M

ELF Communications System Ecological Monitoring Program: Electromagnetic Field Measurements and Engineering Support

DTIC Science & Technology

1994-04-01

1 lfm ýA a I - @0 38Ud U 0 E loll I0 F4J O 3Uv ~:~3 Igaas .1c % jWC (9 Um IDP. 0 di d0 1.00 00 .d .d d V d d~ di dI C-14 rM D0209- II dUmW o iNc cl...5C15-1 (In River) I FIGURE E-6. MEASUREMENT POINT AT TRANSMISSION UNE; 5C15-1. E-9 IITRI D06209-1 I I 0CS I C .00o tD I I- U, I S IcEoE 0 E0 a-0

Combined Heat and Power Systems Technology Development and Demonstration 370 kW High Efficiency Microturbine

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

none,

The C370 Program was awarded in October 2010 with the ambitious goal of designing and testing the most electrically efficient recuperated microturbine engine at a rated power of less than 500 kW. The aggressive targets for electrical efficiency, emission regulatory compliance, and the estimated price point make the system state-of-the-art for microturbine engine systems. These goals will be met by designing a two stage microturbine engine identified as the low pressure spool and high pressure spool that are based on derivative hardware of Capstone’s current commercially available engines. The development and testing of the engine occurred in two phases. Phasemore » I focused on developing a higher power and more efficient engine, that would become the low pressure spool which is based on Capstone’s C200 (200kW) engine architecture. Phase II integrated the low pressure spool created in Phase I with the high pressure spool, which is based on Capstone’s C65 (65 kW) commercially available engine. Integration of the engines, based on preliminary research, would allow the dual spool engine to provide electrical power in excess of 370 kW, with electrical efficiency approaching 42%. If both of these targets were met coupled with the overall CHP target of 85% total combined heating and electrical efficiency California Air Resources Board (CARB) level emissions, and a price target of $600 per kW, the system would represent a step change in the currently available commercial generation technology. Phase I of the C370 program required the development of the C370 low pressure spool. The goal was to increase the C200 engine power by a minimum of 25% — 250 kW — and efficiency from 32% to 37%. These increases in the C200 engine output were imperative to meet the power requirements of the engine when both spools were integrated. An additional benefit of designing and testing the C370 low pressure spool was the possibility of developing a stand-alone product for possible commercialization. The low pressure spool design activity focused on an aeropath derivative of the current C200 engine. The aeropath derivative included changes to the compressor section —compressor and inducer — and to the turbine nozzle. The increased power also necessitated a larger, more powerful generator and generator controller to support the increased power requirements. These two major design changes were completed by utilizing both advanced 3D modeling and computational fluid dynamics modelling. After design, modeling, and analysis, the decision was made to acquire and integrate the components for testing. The second task of Phase I was to integrate and test the components of the low pressure spool to validate power and efficiency. Acquisition of the components for the low pressure spool was completed utilizing Capstone’s current supplier base. Utilization of Capstone’s supply base for integration of the test article would allow — if the decision was made —expedited commercialization of the product. After integration of the engine components, the engine was tested and evaluated for performance and emissions. Test data analysis confirmed that the engine met all power and efficiency requirements and did so while maintaining CARB level emissions. The emissions were met without the use of any post processing or catalyst. After testing was completed, the DOE authorized — via a milestone review — proceeding to Phase II: the development of the integrated C370 engine. The C370 high pressure spool design activity required significant changes to the C65 engine architecture. The engine required a high power density generator, completely redesigned compressor stage, turbine section, recuperator, controls architecture, and intercooler stage asThe two most critical design challenges were the turbine section (the nozzle and turbine) and the controls architecture. The design and analysis of all of the components was completed and integrated into a system model. The system model — after numerous iterations — indicated that, once integrated, the engine will meet or exceed all system requirements. Unfortunately, the turbine section’s life requirements remain a technical challenge and will require continued refinement of the bi-metallic turbine wheel design and manufacturing approach to meet the life requirement at theses high temperatures. The current controls architecture requires substantial effort to develop a system capable of handling the high-speed, near real-time controls requirement, but it was determined not to be a technical roadblock for the project. The C370 Program has been a significant effort with state-of-the-art technical targets. The targets have pushed Capstone’s designers to the limits of current technology. The program has been fortunate to see many successes: the successful testing of the low pressure spool (C250), the development of new material processes, and the implementation of new design practices. The technology and practices learned during the program will be utilized in Capstone’s current product lines and future products. The C370 Program has been a resounding success on many fronts for the DOE and for Capstone.« less

Towards a Science of Command and Control (C2)

DTIC Science & Technology

2005-06-01

Topic: C4ISR/C2 Architecture Associate Professor David H Cropley Systems Engineering & Evaluation Centre, University of South Australia Mawson ...Lakes Campus, Mawson Lakes, SA 5095, Australia Tel: (+618) 8302 3301 Fax: (+618) 8302 5344 Email: david.cropley@unisa.edu.au Report...ADDRESS(ES) Systems Engineering & Evaluation Centre,University of South Australia, Mawson Lakes Campus, Mawson Lakes, SA 5095, Australia, , 8

Discovery of gigantic molecular nanostructures using a flow reaction array as a search engine

PubMed Central

Zang, Hong-Ying; de la Oliva, Andreu Ruiz; Miras, Haralampos N.; Long, De-Liang; McBurney, Roy T.; Cronin, Leroy

2014-01-01

The discovery of gigantic molecular nanostructures like coordination and polyoxometalate clusters is extremely time-consuming since a vast combinatorial space needs to be searched, and even a systematic and exhaustive exploration of the available synthetic parameters relies on a great deal of serendipity. Here we present a synthetic methodology that combines a flow reaction array and algorithmic control to give a chemical ‘real-space’ search engine leading to the discovery and isolation of a range of new molecular nanoclusters based on [Mo2O2S2]2+-based building blocks with either fourfold (C4) or fivefold (C5) symmetry templates and linkers. This engine leads us to isolate six new nanoscale cluster compounds: 1, {Mo10(C5)}; 2, {Mo14(C4)4(C5)2}; 3, {Mo60(C4)10}; 4, {Mo48(C4)6}; 5, {Mo34(C4)4}; 6, {Mo18(C4)9}; in only 200 automated experiments from a parameter space spanning ~5 million possible combinations. PMID:24770632

Effect of water on hydrogen permeability. [Stirling engines

NASA Technical Reports Server (NTRS)

Hulligan, D. D.; Tomazic, W. A.

1984-01-01

Doping of hydrogen with CO or CO2 was developed to reduce hydrogen permeation in Stirling engines by forming low permeability oxide coatings in the heater tubes. An end product of this process is water - which can condense in the cold parts of the engine system. If the water vapor is reduced to a low enough level, the hydrogen can reduce the oxide coating resulting in increased permeability. The equilibrium level of water (oxygen bearing gas) required to avoid reduction of the oxide coating was investigated. Results at 720 C and 13.8 MPa have shown that: (1) pure hydrogen will reduce the coating; (2) 500 ppm CO (500 ppm water equivalent) does not prevent the reduction; and (3) 500 ppm CO2 (1000 ppm water) appears to be close to the equilibrium level. Further tests are planned to define the equilibrium level more precisely and to extend the data to 820 C and 3.4, 6.9, and 13.8 MPa.

Approximation of Engine Casing Temperature Constraints for Casing Mounted Electronics

NASA Technical Reports Server (NTRS)

Kratz, Jonathan L.; Culley, Dennis E.; Chapman, Jeffryes W.

2017-01-01

The performance of propulsion engine systems is sensitive to weight and volume considerations. This can severely constrain the configuration and complexity of the control system hardware. Distributed Engine Control technology is a response to these concerns by providing more flexibility in designing the control system, and by extension, more functionality leading to higher performing engine systems. Consequently, there can be a weight benefit to mounting modular electronic hardware on the engine core casing in a high temperature environment. This paper attempts to quantify the in-flight temperature constraints for engine casing mounted electronics. In addition, an attempt is made at studying heat soak back effects. The Commercial Modular Aero Propulsion System Simulation 40k (C-MAPSS40k) software is leveraged with real flight data as the inputs to the simulation. A two-dimensional (2-D) heat transfer model is integrated with the engine simulation to approximate the temperature along the length of the engine casing. This modification to the existing C-MAPSS40k software will provide tools and methodologies to develop a better understanding of the requirements for the embedded electronics hardware in future engine systems. Results of the simulations are presented and their implications on temperature constraints for engine casing mounted electronics is discussed.

Approximation of Engine Casing Temperature Constraints for Casing Mounted Electronics

NASA Technical Reports Server (NTRS)

Kratz, Jonathan; Culley, Dennis; Chapman, Jeffryes

2016-01-01

The performance of propulsion engine systems is sensitive to weight and volume considerations. This can severely constrain the configuration and complexity of the control system hardware. Distributed Engine Control technology is a response to these concerns by providing more flexibility in designing the control system, and by extension, more functionality leading to higher performing engine systems. Consequently, there can be a weight benefit to mounting modular electronic hardware on the engine core casing in a high temperature environment. This paper attempts to quantify the in-flight temperature constraints for engine casing mounted electronics. In addition, an attempt is made at studying heat soak back effects. The Commercial Modular Aero Propulsion System Simulation 40k (C-MAPSS40k) software is leveraged with real flight data as the inputs to the simulation. A two-dimensional (2-D) heat transfer model is integrated with the engine simulation to approximate the temperature along the length of the engine casing. This modification to the existing C-MAPSS40k software will provide tools and methodologies to develop a better understanding of the requirements for the embedded electronics hardware in future engine systems. Results of the simulations are presented and their implications on temperature constraints for engine casing mounted electronics is discussed.

Genomic landscapes of endogenous retroviruses unveil intricate genetics of conventional and genetically-engineered laboratory mouse strains.

PubMed

Lee, Kang-Hoon; Lim, Debora; Chiu, Sophia; Greenhalgh, David; Cho, Kiho

2016-04-01

Laboratory strains of mice, both conventional and genetically engineered, have been introduced as critical components of a broad range of studies investigating normal and disease biology. Currently, the genetic identity of laboratory mice is primarily confirmed by surveying polymorphisms in selected sets of "conventional" genes and/or microsatellites in the absence of a single completely sequenced mouse genome. First, we examined variations in the genomic landscapes of transposable repetitive elements, named the TREome, in conventional and genetically engineered mouse strains using murine leukemia virus-type endogenous retroviruses (MLV-ERVs) as a probe. A survey of the genomes from 56 conventional strains revealed strain-specific TREome landscapes, and certain families (e.g., C57BL) of strains were discernible with defined patterns. Interestingly, the TREome landscapes of C3H/HeJ (toll-like receptor-4 [TLR4] mutant) inbred mice were different from its control C3H/HeOuJ (TLR4 wild-type) strain. In addition, a CD14 knock-out strain had a distinct TREome landscape compared to its control/backcross C57BL/6J strain. Second, an examination of superantigen (SAg, a "TREome gene") coding sequences of mouse mammary tumor virus-type ERVs in the genomes of the 46 conventional strains revealed a high diversity, suggesting a potential role of SAgs in strain-specific immune phenotypes. The findings from this study indicate that unexplored and intricate genomic variations exist in laboratory mouse strains, both conventional and genetically engineered. The TREome-based high-resolution genetics surveillance system for laboratory mice would contribute to efficient study design with quality control and accurate data interpretation. This genetics system can be easily adapted to other species ranging from plants to humans. Copyright © 2016 Elsevier Inc. All rights reserved.

Fuel Maps for the GEP 6.5LT Engine When Operating on at J/JP-8 Fuel Blends at Ambient and Elevated Temperatures

DTIC Science & Technology

2015-04-01

system. The new calibrated fuel injection pump and injectors were installed, and the fuel injection timing of the new fuel injection system was set to...Product 6.5L Turbocharged diesel engine at two inlet temperature conditions. The GEP 6.5LT engine represents legacy diesel engine design with...derived cetane number DF-2 Diesel Fuel number 2 ft Foot HEFA Hydro-treated Esters and Fatty Acid(s) HP or hp Horsepower hr Hour in Inch in³ cubic

40 CFR Appendix I to Part 94 - Emission-Related Engine Parameters and Specifications

Code of Federal Regulations, 2012 CFR

2012-07-01

.... Temperature control system calibration. 4. Maximum allowable inlet air restriction. III. Fuel System. 1. General. a. Engine idle speed. 2. Fuel injection—compression ignition engines. a. Control parameters and calibrations. b. Transient enrichment system calibration. c. Air-fuel flow calibration. d. Altitude...

40 CFR Appendix I to Part 94 - Emission-Related Engine Parameters and Specifications

Code of Federal Regulations, 2011 CFR

2011-07-01

.... Temperature control system calibration. 4. Maximum allowable inlet air restriction. III. Fuel System. 1. General. a. Engine idle speed. 2. Fuel injection—compression ignition engines. a. Control parameters and calibrations. b. Transient enrichment system calibration. c. Air-fuel flow calibration. d. Altitude...

40 CFR Appendix I to Part 94 - Emission-Related Engine Parameters and Specifications

Code of Federal Regulations, 2014 CFR

2014-07-01

.... Temperature control system calibration. 4. Maximum allowable inlet air restriction. III. Fuel System. 1. General. a. Engine idle speed. 2. Fuel injection—compression ignition engines. a. Control parameters and calibrations. b. Transient enrichment system calibration. c. Air-fuel flow calibration. d. Altitude...

40 CFR Appendix I to Part 94 - Emission-Related Engine Parameters and Specifications

Code of Federal Regulations, 2013 CFR

2013-07-01

.... Temperature control system calibration. 4. Maximum allowable inlet air restriction. III. Fuel System. 1. General. a. Engine idle speed. 2. Fuel injection—compression ignition engines. a. Control parameters and calibrations. b. Transient enrichment system calibration. c. Air-fuel flow calibration. d. Altitude...

78 FR 37958 - Special Conditions: Cessna Aircraft Company, Model J182T; Electronic Engine Control System...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-06-25

...; Electronic Engine Control System Installation AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... feature(s) associated with the installation of an electronic engine control. The applicable airworthiness...) Engines, Inc. SR305-230E-C1 which is a four-stroke, air cooled, diesel cycle engine that uses turbine (jet...

A Logical Design of the Naval Postgraduate School Housing Office.

DTIC Science & Technology

1985-03-01

34 March 1985 L C -:0 Thesis Advisor: Barry A. Frew LU Approved for public release; distribution is unlimited 85 6 3 057...Information Systems Development : Analysis and Design, South-Western, 1984. Pressman , R. S. , Software Engineering A Practitioner’s Approach, McGraw...Postgraduate School Monterey, California 93943 3. Lt. Barry A. Frew 2 Code 54 Fw Administrative Services Department Naval Postgraduate School Monterey

Task 6 -- Advanced turbine systems program conceptual design and product development

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

NONE

1996-01-10

The Allison Engine Company has completed the Task 6 Conceptual Design and Analysis of Phase 2 of the Advanced Turbine System (ATS) contract. At the heart of Allison`s system is an advanced simple cycle gas turbine engine. This engine will incorporate components that ensure the program goals are met. Allison plans to commercialize the ATS demonstrator and market a family of engines incorporating this technology. This family of engines, ranging from 4.9 MW to 12 MW, will be suitable for use in all industrial engine applications, including electric power generation, mechanical drive, and marine propulsion. In the field of electricmore » power generation, the engines will be used for base load, standby, cogeneration, and distributed generation applications.« less

Sustainable Range Management of RDX and TNT by Phytoremediation with Engineered Plants

DTIC Science & Technology

2016-04-01

FINAL REPORT Sustainable Range Management of RDX and TNT by Phytoremediation with Engineered Plants SERDP Project ER-1498 APRIL 2016...specific commercial product, process, or service by trade name, trademark, manufacturer, or otherwise, does not necessarily constitute or imply its...by Phyoremediation with Engineered Plants 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER ER-1498 Neil C

Nuclear Aircraft Feasibility Study. Volume 1

DTIC Science & Technology

1975-03-01

Cycle 6-36 6.2.2 Helium Mass Flow 6-42 6.2.3 Fan Pressure Ratio 6-42 6.2.4 Regenerative Cycle Application 6-43 6.2.5 Brayton Cycle...6-8 Engine Systems Summary 6-9 T-S Diagram of Ideal Brayton Cycle 6-13 T-S Diagram of Brayton Cycle for Turbofan Engine 6-15 Comparison of... Brayton Closed Cycle Thermodynamic Analysis 6-50 6.2.8-1 Indirect Cycle Gas Circulation System 6-53 6.2.8-2 Gas Turbine Generator — Pump Cycle

Development and Performance Evaluations of HfO2-Si and Rare Earth-Si Based Environmental Barrier Bond Coat Systems for SiC/SiC Ceramic Matrix Composites

NASA Technical Reports Server (NTRS)

Zhu, Dongming

2014-01-01

Ceramic environmental barrier coatings (EBC) and SiCSiC ceramic matrix composites (CMCs) will play a crucial role in future aircraft propulsion systems because of their ability to significantly increase engine operating temperatures, improve component durability, reduce engine weight and cooling requirements. Advanced EBC systems for SiCSiC CMC turbine and combustor hot section components are currently being developed to meet future turbine engine emission and performance goals. One of the significant material development challenges for the high temperature CMC components is to develop prime-reliant, high strength and high temperature capable environmental barrier coating bond coat systems, since the current silicon bond coat cannot meet the advanced EBC-CMC temperature and stability requirements. In this paper, advanced NASA HfO2-Si based EBC bond coat systems for SiCSiC CMC combustor and turbine airfoil applications are investigated. The coating design approach and stability requirements are specifically emphasized, with the development and implementation focusing on Plasma Sprayed (PS) and Electron Beam-Physic Vapor Deposited (EB-PVD) coating systems and the composition optimizations. High temperature properties of the HfO2-Si based bond coat systems, including the strength, fracture toughness, creep resistance, and oxidation resistance were evaluated in the temperature range of 1200 to 1500 C. Thermal gradient heat flux low cycle fatigue and furnace cyclic oxidation durability tests were also performed at temperatures up to 1500 C. The coating strength improvements, degradation and failure modes of the environmental barrier coating bond coat systems on SiCSiC CMCs tested in simulated stress-environment interactions are briefly discussed and supported by modeling. The performance enhancements of the HfO2-Si bond coat systems with rare earth element dopants and rare earth-silicon based bond coats are also highlighted. The advanced bond coat systems, when integrated with advanced EBC top coats, showed promise to achieve 1500 C temperature capability, helping enable next generation turbine engines with significantly improved engine component temperature capability and long-term durability.

26. Photograph of a line drawing. 'PLAN LAYOUT AND CROSS ...

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

26. Photograph of a line drawing. 'PLAN LAYOUT AND CROSS SECTION OF PART I, SECTION 8, BUILDINGS NO. C-1, C-3, C-5, C-6, C-7, C-9, MIXING, MANUFACTURING AREA, PLANT B AS OF 4-24-44.' From the U.S. Army Corps of Engineers. Industrial Facilities Inventory, Holston Ordnance Works, Kingsport, Tennessee. Plant B, Parts II, III. (Nashville, TN: Office of the District Engineer, 1944). - Holston Army Ammunition Plant, RDX-and-Composition-B Manufacturing Line 9, Kingsport, Sullivan County, TN

27. Photograph of a line drawing. 'PLAN LAYOUT AND CROSS ...

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

27. Photograph of a line drawing. 'PLAN LAYOUT AND CROSS SECTION OF PART III, SECTION 1, EQUIPMENT LAYOUT, BUILDINGS C-1, C-3, C-5, C-6, C-7, C-9 INCL., MIXING, MANUFACTURING AREA, PLANT 'B'.' From the U.S. Army Corps of Engineers. Industrial Facilities Inventory, Holston Ordnance Works, Kingsport, Tennessee. Plant B, Parts II, III. (Nashville, TN: Office of the District Engineer, 1944). - Holston Army Ammunition Plant, RDX-and-Composition-B Manufacturing Line 9, Kingsport, Sullivan County, TN

Rapid Measurement of Emissions From Military Aircraft Turbine Engines by Downstream Extractive Sampling of Aircraft on the Ground: Results for C-130 and F-15 Aircraft (POSTPRINT)

DTIC Science & Technology

2009-02-01

four Allison T56 -A-15 turboprop engines which can generate in excess of 4500 horsepower at maximum power. This engine type uses a single entry, 14-stage...JP-8 JP-8 þ 100 Aircraft C-130H F-15 Engine Allison T56 P & W F100-PE-100 Composition (Vol %) Aromatics 16.3 12.4 Alkenes 1.6 2.5 Alkanes 82.1 85.1...respectively. Results are shown for the lowest and highest throttle settings for each of the engine types. The intra-engine variability of two T56

Combining CRISPR and CRISPRi Systems for Metabolic Engineering of E. coli and 1,4-BDO Biosynthesis.

PubMed

Wu, Meng-Ying; Sung, Li-Yu; Li, Hung; Huang, Chun-Hung; Hu, Yu-Chen

2017-12-15

Biosynthesis of 1,4-butanediol (1,4-BDO) in E. coli requires an artificial pathway that involves six genes and time-consuming, iterative genome engineering. CRISPR is an effective gene editing tool, while CRISPR interference (CRISPRi) is repurposed for programmable gene suppression. This study aimed to combine both CRISPR and CRISPRi for metabolic engineering of E. coli and 1,4-BDO production. We first exploited CRISPR to perform point mutation of gltA, replacement of native lpdA with heterologous lpdA, knockout of sad and knock-in of two large (6.0 and 6.3 kb in length) gene cassettes encoding the six genes (cat1, sucD, 4hbd, cat2, bld, bdh) in the 1,4-BDO biosynthesis pathway. The successive E. coli engineering enabled production of 1,4-BDO to a titer of 0.9 g/L in 48 h. By combining the CRISPRi system to simultaneously suppress competing genes that divert the flux from the 1,4-BDO biosynthesis pathway (gabD, ybgC and tesB) for >85%, we further enhanced the 1,4-BDO titer for 100% to 1.8 g/L while reducing the titers of byproducts gamma-butyrolactone and succinate for 55% and 83%, respectively. These data demonstrate the potential of combining CRISPR and CRISPRi for genome engineering and metabolic flux regulation in microorganisms such as E. coli and production of chemicals (e.g., 1,4-BDO).

14 CFR 34.21 - Standards for exhaust emissions.

Code of Federal Regulations, 2014 CFR

2014-01-01

... after January 1, 1976, shall not exceed SN = 83.6 (rO) −0.274 (rO is in kN). (c) Exhaust emission of... output: (i) Engines manufactured on or after January 1, 1984: Hydrocarbons: 19.6 g/kN rO. (ii) Engines manufactured on or after July 7, 1997: Carbon Monoxide: 118 g/kN rO. (iii) Engines of a type or model of which...

14 CFR 34.21 - Standards for exhaust emissions.

Code of Federal Regulations, 2013 CFR

2013-01-01

... after January 1, 1976, shall not exceed SN = 83.6 (rO) −0.274 (rO is in kN). (c) Exhaust emission of... output: (i) Engines manufactured on or after January 1, 1984: Hydrocarbons: 19.6 g/kN rO. (ii) Engines manufactured on or after July 7, 1997: Carbon Monoxide: 118 g/kN rO. (iii) Engines of a type or model of which...

Laboratory Evaluation of Multiviscosity-Grade Engine Oils in U.S. Army Diesel Engines

DTIC Science & Technology

1981-05-01

0.001 0.007 - 0.007 A-14 C L U 0i L zw 0 200 Lu 0 0- 0 ~~ U.’ L L u, C𔃾 H~~~( I - --- d z r- 8 0 0 0 r n CD 00 c z ’Uz 2 C3 ,’U tD z~ *C( 0% UJZ us...fl- ~ r %0 IT It r H- c c.0I I IHq * cI n CV 00r)0C) (n C ’OC4 C’JC.4 c 1-1 Ln 100 M0 0o 130 U 000 00 -- 13.6 30 L-6 TEST 3 9.1 ~ 20 LUBRICANT: AL...ARMOR SCHOOL ATTN ATSB- TD FORT KNOX KY 40121 Page 3 of 5 CDR DEPARTMENT OF THE NAVY US ARMY LOGISTICS CTR HQ, US HARINE CORPS ATTN ATCL-MS (MR A MARSHALL

Development of Advanced Environmental Barrier Coatings for SiC/SiC Composites at NASA GRC: Prime-Reliant Design and Durability Perspectives

NASA Technical Reports Server (NTRS)

Zhu, Dongming

2017-01-01

Environmental barrier coatings (EBCs) are considered technologically important because of the critical needs and their ability to effectively protect the turbine hot-section SiC/SiC ceramic matrix composite (CMC) components in harsh engine combustion environments. The development of NASA's advanced environmental barrier coatings have been aimed at significantly improved the coating system temperature capability, stability, erosion-impact, and CMAS resistance for SiC/SiC turbine airfoil and combustors component applications. The NASA environmental barrier coating developments have also emphasized thermo-mechanical creep and fatigue resistance in simulated engine heat flux and environments. Experimental results and models for advanced EBC systems will be presented to help establishing advanced EBC composition design methodologies, performance modeling and life predictions, for achieving prime-reliant, durable environmental coating systems for 2700-3000 F engine component applications. Major technical barriers in developing environmental barrier coating systems and the coating integration with next generation composites having further improved temperature capability, environmental stability, EBC-CMC fatigue-environment system durability will be discussed.

Advanced Environmental Barrier Coatings Development for Si-Based Ceramics

NASA Technical Reports Server (NTRS)

Zhu, Dong-Ming; Choi, R. Sung; Robinson, Raymond C.; Lee, Kang N.; Bhatt, Ramakrishna T.; Miller, Robert A.

2005-01-01

Advanced environmental barrier coating concepts based on multi-component HfO2 (ZrO2) and modified mullite systems are developed for monolithic Si3N4 and SiC/SiC ceramic matrix composite (CMC) applications. Comprehensive testing approaches were established using the water vapor cyclic furnace, high pressure burner rig and laser heat flux steam rig to evaluate the coating water vapor stability, cyclic durability, radiation and erosion resistance under simulated engine environments. Test results demonstrated the feasibility and durability of the environmental barrier coating systems for 2700 to 3000 F monolithic Si3N4 and SiC/SiC CMC component applications. The high-temperature-capable environmental barrier coating systems are being further developed and optimized in collaboration with engine companies for advanced turbine engine applications.

NASA's Advanced Environmental Barrier Coatings Development for SiC/SiC Ceramic Matrix Composites: Understanding Calcium Magnesium Alumino-Silicate (CMAS) Degradations and Resistance

NASA Technical Reports Server (NTRS)

Zhu, Dongming

2014-01-01

Environmental barrier coatings (EBCs) and SiCSiC ceramic matrix composites (CMCs) systems will play a crucial role in next generation turbine engines for hot-section component applications because of their ability to significantly increase engine operating temperatures with improved efficiency, reduce engine weight and cooling requirements. The development of prime-reliant environmental barrier coatings is essential to the viability and reliability of the envisioned CMC engine component applications, ensuring integrated EBC-CMC system durability and designs are achievable for successful applications of the game-changing component technologies and lifing methodologies.This paper will emphasize recent NASA environmental barrier coating developments for SiCSiC turbine airfoil components, utilizing advanced coating compositions, state-of-the-art processing methods, and combined mechanical and environment testing and durability evaluations. The coating-CMC degradations in the engine fatigue-creep and operating environments are particularly complex; one of the important coating development aspects is to better understand engine environmental interactions and coating life debits, and we have particularly addressed the effect of Calcium-Magnesium-Alumino-Silicate (CMAS) from road sand or volcano-ash deposits on the durability of the environmental barrier coating systems, and how the temperature capability, stability and cyclic life of the candidate rare earth oxide and silicate coating systems will be impacted in the presence of the CMAS at high temperatures and under simulated heat flux conditions. Advanced environmental barrier coating systems, including HfO2-Si with rare earth dopant based bond coat systems, will be discussed for the performance improvements to achieve better temperature capability and CMAS resistance for future engine operating conditions.

Design of c-band telecontrol transmitter local oscillator for UAV data link

NASA Astrophysics Data System (ADS)

Cao, Hui; Qu, Yu; Song, Zuxun

2018-01-01

A C-band local oscillator of an Unmanned Aerial Vehicle (UAV) data link radio frequency (RF) transmitter unit with high-stability, high-precision and lightweight was designed in this paper. Based on the highly integrated broadband phase-locked loop (PLL) chip HMC834LP6GE, the system performed fractional-N control by internal modules programming to achieve low phase noise and small frequency resolution. The simulation and testing methods were combined to optimize and select the loop filter parameters to ensure the high precision and stability of the frequency synthesis output. The theoretical analysis and engineering prototype measurement results showed that the local oscillator had stable output frequency, accurate frequency step, high spurious suppression and low phase noise, and met the design requirements. The proposed design idea and research method have theoretical guiding significance for engineering practice.

History of Command and Control at KSC: Kennedy Engineering Academy Series

NASA Technical Reports Server (NTRS)

Hurt, George Richard

2007-01-01

Agenda for this presentation is: Evolution of Command and Control (C&C), C&C history, Launch Processing System overview, Core System Overview, Checkout & Launch Control System, Overview and Commercial-Off-The-Shelf guidelines

Evaluation of Lightweight, Relocatable Structures for Use in Theaters of Operations.

DTIC Science & Technology

1982-05-01

ADA117 02& CONSTRUCTION ENGINEERING RESEARCH LAB (ARMY) CHAMPAIGN IL F/6 13/2EVALUATION OF LI HThEISHT, RELOCATABLE STRUCTURES FOR USE IN TH-ETC(U...NUMBER(s) M. Frisch J. LambertM._ Ptak 9. PERFORMING ORGANIZATION NAME AND ADDRESS 10. PROGRAM ELEMENT. PROJECT, TASK U.S. ARMY 4A 6 - T CONSTRUCTION ...System prefabricated buildings portable shelters 24L A2rRACT (C60901we S ,ewInd efb nOee -e and ldenif 7 by block numbe) The U.S. Army Construction

A Comprehensive Guide to C3 System Development

DTIC Science & Technology

1990-03-01

This thesis provides guidelines to develop a C3 system, including both organizational and physical systems. It contains the concept, architecture ... design and engineering approaches, the integrated C3 framework, test and evaluation methodologies, system acquisition procedures, system development

Development of a Twin-spool Turbofan Engine Simulation Using the Toolbox for Modeling and Analysis of Thermodynamic Systems (T-MATS)

NASA Technical Reports Server (NTRS)

Zinnecker, Alicia M.; Chapman, Jeffryes W.; Lavelle, Thomas M.; Litt, Johathan S.

2014-01-01

The Toolbox for Modeling and Analysis of Thermodynamic Systems (T-MATS) is a tool that has been developed to allow a user to build custom models of systems governed by thermodynamic principles using a template to model each basic process. Validation of this tool in an engine model application was performed through reconstruction of the Commercial Modular Aero-Propulsion System Simulation (C-MAPSS) (v2) using the building blocks from the T-MATS (v1) library. In order to match the two engine models, it was necessary to address differences in several assumptions made in the two modeling approaches. After these modifications were made, validation of the engine model continued by integrating both a steady-state and dynamic iterative solver with the engine plant and comparing results from steady-state and transient simulation of the T-MATS and C-MAPSS models. The results show that the T-MATS engine model was accurate within 3 of the C-MAPSS model, with inaccuracy attributed to the increased dimension of the iterative solver solution space required by the engine model constructed using the T-MATS library. This demonstrates that, given an understanding of the modeling assumptions made in T-MATS and a baseline model, the T-MATS tool provides a viable option for constructing a computational model of a twin-spool turbofan engine that may be used in simulation studies.

Automotive Stirling reference engine design report

NASA Technical Reports Server (NTRS)

1981-01-01

The reference Stirling engine system is described which provides the best possible fuel economy while meeting or exceeding all other program objectives. The system was designed to meet the requirements of a 1984 Pontiac Phoenix (X-body). This design utilizes all new technology that can reasonably be expected to be developed by 1984 and that is judged to provide significant improvement, relative to development risk and cost. Topics covered include: (1) external heat system; (2) hot engine system; (3) cold engine system; (4) engine drive system; (5) power control system and auxiliaries; (6) engine instalation; (7) optimization and vehicle simulation; (8) engine materials; and (9) production cost analysis.

IDEF3 Formalization Report

DTIC Science & Technology

1991-10-01

SUBJECT TERMS 15. NUMBER OF PAGES engineering management information systems method formalization 60 information engineering process modeling 16 PRICE...CODE information systems requirements definition methods knowlede acquisition methods systems engineering 17. SECURITY CLASSIFICATION ji. SECURITY... Management , Inc., Santa Monica, California. CORYNEN, G. C., 1975, A Mathematical Theory of Modeling and Simula- tion. Ph.D. Dissertation, Department

Toward a Capability Engineering Process

DTIC Science & Technology

2004-12-01

TOWARD A CAPABILITY ENGINEERING PROCESS M. Lizotte, F. Bernier, M. Mokhtari , M. Couture, G. Dussault, C. Lalancette, F. Lemieux System of Systems...Lizotte, F. Lemieux, the US DoD 5000 acquisition strategies?; and (8) since a M. Mokhtari , 2004: Toward Capability Engineering capability can be

14 CFR 91.1033 - Operating information required.

Code of Federal Regulations, 2014 CFR

2014-01-01

...) Before takeoff; (3) Cruise; (4) Before landing; (5) After landing; and (6) Stopping engines. (c) Each.... (2) Emergency operation of instruments and controls. (3) Engine inoperative procedures. (4) Any other...

14 CFR 91.1033 - Operating information required.

Code of Federal Regulations, 2013 CFR

2013-01-01

...) Before takeoff; (3) Cruise; (4) Before landing; (5) After landing; and (6) Stopping engines. (c) Each.... (2) Emergency operation of instruments and controls. (3) Engine inoperative procedures. (4) Any other...

14 CFR 91.1033 - Operating information required.

Code of Federal Regulations, 2012 CFR

2012-01-01

...) Before takeoff; (3) Cruise; (4) Before landing; (5) After landing; and (6) Stopping engines. (c) Each.... (2) Emergency operation of instruments and controls. (3) Engine inoperative procedures. (4) Any other...

14 CFR 91.1033 - Operating information required.

Code of Federal Regulations, 2011 CFR

2011-01-01

...) Before takeoff; (3) Cruise; (4) Before landing; (5) After landing; and (6) Stopping engines. (c) Each.... (2) Emergency operation of instruments and controls. (3) Engine inoperative procedures. (4) Any other...

14 CFR 91.1033 - Operating information required.

Code of Federal Regulations, 2010 CFR

2010-01-01

...) Before takeoff; (3) Cruise; (4) Before landing; (5) After landing; and (6) Stopping engines. (c) Each.... (2) Emergency operation of instruments and controls. (3) Engine inoperative procedures. (4) Any other...

Engineering and systems-level analysis of Saccharomyces cerevisiae for production of 3-hydroxypropionic acid via malonyl-CoA reductase-dependent pathway.

PubMed

Kildegaard, Kanchana R; Jensen, Niels B; Schneider, Konstantin; Czarnotta, Eik; Özdemir, Emre; Klein, Tobias; Maury, Jérôme; Ebert, Birgitta E; Christensen, Hanne B; Chen, Yun; Kim, Il-Kwon; Herrgård, Markus J; Blank, Lars M; Forster, Jochen; Nielsen, Jens; Borodina, Irina

2016-03-15

In the future, oil- and gas-derived polymers may be replaced with bio-based polymers, produced from renewable feedstocks using engineered cell factories. Acrylic acid and acrylic esters with an estimated world annual production of approximately 6 million tons by 2017 can be derived from 3-hydroxypropionic acid (3HP), which can be produced by microbial fermentation. For an economically viable process 3HP must be produced at high titer, rate and yield and preferably at low pH to minimize downstream processing costs. Here we describe the metabolic engineering of baker's yeast Saccharomyces cerevisiae for biosynthesis of 3HP via a malonyl-CoA reductase (MCR)-dependent pathway. Integration of multiple copies of MCR from Chloroflexus aurantiacus and of phosphorylation-deficient acetyl-CoA carboxylase ACC1 genes into the genome of yeast increased 3HP titer fivefold in comparison with single integration. Furthermore we optimized the supply of acetyl-CoA by overexpressing native pyruvate decarboxylase PDC1, aldehyde dehydrogenase ALD6, and acetyl-CoA synthase from Salmonella enterica SEacs (L641P). Finally we engineered the cofactor specificity of the glyceraldehyde-3-phosphate dehydrogenase to increase the intracellular production of NADPH at the expense of NADH and thus improve 3HP production and reduce formation of glycerol as by-product. The final strain produced 9.8 ± 0.4 g L(-1) 3HP with a yield of 13% C-mol C-mol(-1) glucose after 100 h in carbon-limited fed-batch cultivation at pH 5. The 3HP-producing strain was characterized by (13)C metabolic flux analysis and by transcriptome analysis, which revealed some unexpected consequences of the undertaken metabolic engineering strategy, and based on this data, future metabolic engineering directions are proposed. In this study, S. cerevisiae was engineered for high-level production of 3HP by increasing the copy numbers of biosynthetic genes and improving flux towards precursors and redox cofactors. This strain represents a good platform for further optimization of 3HP production and hence an important step towards potential commercial bio-based production of 3HP.

Progress report of the innovated KIST ion beam facility

NASA Astrophysics Data System (ADS)

Kim, Joonkon; Eliades, John A.; Yu, Byung-Yong; Lim, Weon Cheol; Chae, Keun Hwa; Song, Jonghan

2017-01-01

The Korea Institute of Science and Technology (KIST, Seoul, Republic of (S.) Korea) ion beam facility consists of three electrostatic accelerators: a 400 kV single ended ion implanter, a 2 MV tandem accelerator system and a 6 MV tandem accelerator system. The 400 kV and 6 MV systems were purchased from High Voltage Engineering Europa (HVEE, Netherlands) and commissioned in 2013, while the 2 MV system was purchased from National Electrostatics Corporation (NEC, USA) in 1995. These systems are used to provide traditional ion beam analysis (IBA), isotope ratio analysis (ex. accelerator mass spectrometry, AMS), and ion implantation/irradiation for domestic industrial and academic users. The main facility is the 6 MV HVEE Tandetron system that has an AMS line currently used for 10Be, 14C, 26Al, 36 Cl, 41Ca and 129I analyses, and three lines for IBA that are under construction. Here, these systems are introduced with their specifications and initial performance results.

Enhancing Decision Topology Assessment in Engineering Design

DTIC Science & Technology

2014-04-10

in engineering design decision making. References 1. Clemen , R. T., 1997, Making Hard Decisions, Second Edition, Duxbury Press. 2. Hazelrigg, G. A...United Kingdom. 6. Lewis, K., Chen, W. and L. C. Schmidt , Editors, 2006, Decision Making in Engineering Design, ASME Press, New York. 7. Myers

An antenna-pointing mechanism for the ETS-6 K-band Single Access (KSA) antenna

NASA Technical Reports Server (NTRS)

Takada, Noboru; Amano, Takahiro; Ohhashi, Toshiro; Wachi, Shigeo

1991-01-01

Both the design philosophy for the Antenna Pointing Mechanism (APM) to be used for the K-band Single Access (KSA) antenna system and experimental results of the APM Engineering Model (EM) tests are described. The KSA antenna system will be flown on the Engineering Test Satellite 6 (ETS-6).

Advanced Environmental Barrier Coating Development for SiC-SiC Ceramic Matrix Composite Components

NASA Technical Reports Server (NTRS)

Zhu, Dongming; Harder, Bryan; Bhatt, Ramakrishna; Kiser, Doug; Wiesner, Valerie L.

2016-01-01

This presentation reviews the NASA advanced environmental barrier coating (EBC) system development for SiCSiC Ceramic Matrix Composite (CMC) components for next generation turbine engines. The emphasis has been placed on the current design challenges of the 2700F environmental barrier coatings; coating processing and integration with SiCSiC CMCs and component systems; and performance evaluation and demonstration of EBC-CMC systems. This presentation also highlights the EBC-CMC system temperature capability and durability improvements through advanced compositions and architecture designs, as shown in recent simulated engine high heat flux, combustion environment, in conjunction with mechanical creep and fatigue loading testing conditions.

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.

Autoregressive Methods for Spectral Estimation from Interferograms.

DTIC Science & Technology

1986-09-19

RL83 6?6 AUTOREGRESSIVE METHODS FOR SPECTRAL. ESTIMTION FROM / SPACE ENGINEERING E N RICHARDS ET AL. 19 SEPINEFRGAS.()UA TT NV GNCNE O C: 31SSF...was AUG1085 performed under subcontract to . Center for Space Engineering Utah State University Logan, UT 84322-4140 4 4 Scientific Report No. 17 AFGL...MONITORING ORGANIZATION Center for Space Engineering (iapplicable) Air Force Geophysics Laboratory e. AORESS (City. State and ZIP Code) 7b. AOORESS (City

Structure-based engineering of alkaline α-amylase from alkaliphilic Alkalimonas amylolytica for improved thermostability.

PubMed

Deng, Zhuangmei; Yang, Haiquan; Li, Jianghua; Shin, Hyun-Dong; Du, Guocheng; Liu, Long; Chen, Jian

2014-05-01

This study aimed to improve the thermostability of alkaline α-amylase from Alkalimonas amylolytica through structure-based rational design and systems engineering of its catalytic domain. Separate engineering strategies were used to increase alkaline α-amylase thermostability: (1) replace histidine residues with leucine to stabilize the least similar region in domain B, (2) change residues (glycine, proline, and glutamine) to stabilize the highly conserved α-helices in domain A, and (3) decrease the free energy of folding predicted by the PoPMuSiC program to stabilize the overall protein structure. A total of 15 single-site mutants were obtained, and four mutants - H209L, Q226V, N302W, and P477V - showed enhanced thermostability. Combinational mutations were subsequently introduced, and the best mutant was triple mutant H209L/Q226V/P477V. Its half-life at 60 °C was 3.8-fold of that of the wild type and displayed a 3.2 °C increase in melting temperature compared with that of the wild type. Interestingly, other biochemical properties of this mutant also improved: the optimum temperature increased from 50 °C to 55 °C, the optimum pH shifted from 9.5 to 10.0, the stable pH range expanded from 7.0-11.0 to 6.0-12.0, the specific activity increased by 24 %, and the catalytic efficiency (k cat/K m) increased from 1.8×10(4) to 3.5 × 10(4) l/(g min). Finally, the mechanisms responsible for the increased thermostability were analyzed through comparative analysis of structure models. The structure-based rational design and systems engineering strategies in this study may also improve the thermostability of other industrial enzymes.

Preliminary design of propulsion system for V/STOL research and technology aircraft

NASA Technical Reports Server (NTRS)

1977-01-01

The V/STOL Research and Technology Aircraft (RTA)propulsion system design effort is limited to components of the lift/cruise engines, turboshaft engine modifications, lift fan assembly, and propulsion system performance generation. The uninstalled total net thrust with all engines and fans operating at intermediate power was 37,114 pounds. Uninstalled system total net thrust was 27,102 pounds when one lift/cruise is inoperative. Components have lives above the 500 hours of the RTA duty cycle. The L/C engine used in a fixed nacelle has the cross shaft forward of the reduction gear whereas the cross shaft is aft of the reduction gear in a tilt nacelle L/C engine. The lift/cruise gearbox contains components and technologies from other DDA engines. The rotor has a 62-inch diameter and contains 22 composite blades that have a hub/tip ratio of 0.454. The blade pitch change mechanism contains hydraulic and mechanical redundancy. The lift fan assembly is completely self-contained including oil cooling in 10 exit vanes.

The SCSTPE organic Rankine engine

NASA Technical Reports Server (NTRS)

Boda, F. P.

1980-01-01

The organic Rankine cycle engine under consideration for a solar thermal system being developed is described. Design parameters, method of control, performance and cost data are provided for engine power levels up to 80 kWe; efficiency is shown as a function of turbine inlet temperature in the range of 149 C to 427 C.

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

Performance of the Satellite Test Assistant Robot in JPL's Space Simulation Facility

NASA Technical Reports Server (NTRS)

Mcaffee, Douglas; Long, Mark; Johnson, Ken; Siebes, Georg

1995-01-01

An innovative new telerobotic inspection system called STAR (the Satellite Test Assistant Robot) has been developed to assist engineers as they test new spacecraft designs in simulated space environments. STAR operates inside the ultra-cold, high-vacuum, test chambers and provides engineers seated at a remote Operator Control Station (OCS) with high resolution video and infrared (IR) images of the flight articles under test. STAR was successfully proof tested in JPL's 25-ft (7.6-m) Space Simulation Chamber where temperatures ranged from +85 C to -190 C and vacuum levels reached 5.1 x 10(exp -6) torr. STAR's IR Camera was used to thermally map the entire interior of the chamber for the first time. STAR also made several unexpected and important discoveries about the thermal processes occurring within the chamber. Using a calibrated test fixture arrayed with ten sample spacecraft materials, the IR camera was shown to produce highly accurate surface temperature data. This paper outlines STAR's design and reports on significant results from the thermal vacuum chamber test.

System Engineering Infrastructure Evolution Galileo IOV and the Steps Beyond

NASA Astrophysics Data System (ADS)

Eickhoff, J.; Herpel, H.-J.; Steinle, T.; Birn, R.; Steiner, W.-D.; Eisenmann, H.; Ludwig, T.

2009-05-01

The trends to more and more constrained financial budgets in satellite engineering require a permanent optimization of the S/C system engineering processes and infrastructure. Astrium in the recent years already has built up a system simulation infrastructure - the "Model-based Development & Verification Environment" - which meanwhile is well known all over Europe and is established as Astrium's standard approach for ESA, DLR projects and now even the EU/ESA-Project Galileo IOV. The key feature of the MDVE / FVE approach is to provide entire S/C simulation (with full featured OBC simulation) already in early phases to start OBSW code tests on a simulated S/C and to later add hardware in the loop step by step up to an entire "Engineering Functional Model (EFM)" or "FlatSat". The subsequent enhancements to this simulator infrastructure w.r.t. spacecraft design data handling are reported in the following sections.

Patchoulol Production with Metabolically Engineered Corynebacterium glutamicum

PubMed Central

Wichmann, Julian; Baier, Thomas; Frohwitter, Jonas; Risse, Joe M.; Peters-Wendisch, Petra; Kruse, Olaf

2018-01-01

Patchoulol is a sesquiterpene alcohol and an important natural product for the perfume industry. Corynebacterium glutamicum is the prominent host for the fermentative production of amino acids with an average annual production volume of ~6 million tons. Due to its robustness and well established large-scale fermentation, C. glutamicum has been engineered for the production of a number of value-added compounds including terpenoids. Both C40 and C50 carotenoids, including the industrially relevant astaxanthin, and short-chain terpenes such as the sesquiterpene valencene can be produced with this organism. In this study, systematic metabolic engineering enabled construction of a patchoulol producing C. glutamicum strain by applying the following strategies: (i) construction of a farnesyl pyrophosphate-producing platform strain by combining genomic deletions with heterologous expression of ispA from Escherichia coli; (ii) prevention of carotenoid-like byproduct formation; (iii) overproduction of limiting enzymes from the 2-c-methyl-d-erythritol 4-phosphate (MEP)-pathway to increase precursor supply; and (iv) heterologous expression of the plant patchoulol synthase gene PcPS from Pogostemon cablin. Additionally, a proof of principle liter-scale fermentation with a two-phase organic overlay-culture medium system for terpenoid capture was performed. To the best of our knowledge, the patchoulol titers demonstrated here are the highest reported to date with up to 60 mg L−1 and volumetric productivities of up to 18 mg L−1 d−1. PMID:29673223

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

Li, Y; Liu, B; Liang, B

Purpose: Current CyberKnife treatment planning system (TPS) provided two dose calculation algorithms: Ray-tracing and Monte Carlo. Ray-tracing algorithm is fast, but less accurate, and also can’t handle irregular fields since a multi-leaf collimator system was recently introduced to CyberKnife M6 system. Monte Carlo method has well-known accuracy, but the current version still takes a long time to finish dose calculations. The purpose of this paper is to develop a GPU-based fast C/S dose engine for CyberKnife system to achieve both accuracy and efficiency. Methods: The TERMA distribution from a poly-energetic source was calculated based on beam’s eye view coordinate system,more » which is GPU friendly and has linear complexity. The dose distribution was then computed by inversely collecting the energy depositions from all TERMA points along 192 collapsed-cone directions. EGSnrc user code was used to pre-calculate energy deposition kernels (EDKs) for a series of mono-energy photons The energy spectrum was reconstructed based on measured tissue maximum ratio (TMR) curve, the TERMA averaged cumulative kernels was then calculated. Beam hardening parameters and intensity profiles were optimized based on measurement data from CyberKnife system. Results: The difference between measured and calculated TMR are less than 1% for all collimators except in the build-up regions. The calculated profiles also showed good agreements with the measured doses within 1% except in the penumbra regions. The developed C/S dose engine was also used to evaluate four clinical CyberKnife treatment plans, the results showed a better dose calculation accuracy than Ray-tracing algorithm compared with Monte Carlo method for heterogeneous cases. For the dose calculation time, it takes about several seconds for one beam depends on collimator size and dose calculation grids. Conclusion: A GPU-based C/S dose engine has been developed for CyberKnife system, which was proven to be efficient and accurate for clinical purpose, and can be easily implemented in TPS.« less

Jet impingement heat transfer enhancement for the GPU-3 Stirling engine

NASA Technical Reports Server (NTRS)

Johnson, D. C.; Congdon, C. W.; Begg, L. L.; Britt, E. J.; Thieme, L. G.

1981-01-01

A computer model of the combustion-gas-side heat transfer was developed to predict the effects of a jet impingement system and the possible range of improvements available. Using low temperature (315 C (600 F)) pretest data in an updated model, a high temperature silicon carbide jet impingement heat transfer system was designed and fabricated. The system model predicted that at the theoretical maximum limit, jet impingement enhanced heat transfer can: (1) reduce the flame temperature by 275 C (500 F); (2) reduce the exhaust temperature by 110 C (200 F); and (3) increase the overall heat into the working fluid by 10%, all for an increase in required pumping power of less than 0.5% of the engine power output. Initial tests on the GPU-3 Stirling engine at NASA-Lewis demonstrated that the jet impingement system increased the engine output power and efficiency by 5% - 8% with no measurable increase in pumping power. The overall heat transfer coefficient was increased by 65% for the maximum power point of the tests.

14 CFR 27.907 - Engine vibration.

Code of Federal Regulations, 2010 CFR

2010-01-01

... engine to excessive vibration stresses. This must be shown by a vibration investigation. (c) No part of the rotor drive system may be subjected to excessive vibration stresses. Rotor Drive System ...

14 CFR 27.907 - Engine vibration.

Code of Federal Regulations, 2012 CFR

2012-01-01

... engine to excessive vibration stresses. This must be shown by a vibration investigation. (c) No part of the rotor drive system may be subjected to excessive vibration stresses. Rotor Drive System ...

14 CFR 27.907 - Engine vibration.

Code of Federal Regulations, 2014 CFR

2014-01-01

... engine to excessive vibration stresses. This must be shown by a vibration investigation. (c) No part of the rotor drive system may be subjected to excessive vibration stresses. Rotor Drive System ...

14 CFR 27.907 - Engine vibration.

Code of Federal Regulations, 2013 CFR

2013-01-01

... engine to excessive vibration stresses. This must be shown by a vibration investigation. (c) No part of the rotor drive system may be subjected to excessive vibration stresses. Rotor Drive System ...

14 CFR 27.907 - Engine vibration.

Code of Federal Regulations, 2011 CFR

2011-01-01

... engine to excessive vibration stresses. This must be shown by a vibration investigation. (c) No part of the rotor drive system may be subjected to excessive vibration stresses. Rotor Drive System ...

Appraisal Requirements for CMMI (Registered Trademark) Version 1.3 (ARC, V1.3)

DTIC Science & Technology

2011-04-01

Software Engineering Institute) • Rassa, Robert C . (Raytheon Space and Airborne Systems ) • Richter, Karen (OSD/IDA) • Young, Rusty (Software...CMU/SEI-2011-TR-006 | 21 • Penn, Lynn (Lockheed Martin) • Rassa, Robert C . (Raytheon Space and Airborne Systems) • Wilson, Harold G. (Northrop...Government Contract Number FA8721-05- C -0003 with Carnegie Mellon University for the operation of the Software Engineering Institute, a federally funded

Pop tests of storable biopropellant liquid apogee engine

NASA Astrophysics Data System (ADS)

Kuroda, Yukio; Tadano, Makoto; Sato, Masahiro; Kusaka, Kazuo; Kobayashi, Hideyuki; Iihara, Sigeyasu; Ban, Hiroyuki

1994-10-01

A pressure-fed, blowdown, hydrazine/NTO apogee propulsion system had been selected for the ETS-6. One of the problems encountered during the development of the engine was the occurrence of pops (popping) at the higher operating chamber pressures. Pops are irregular high amplitude pressure pulses. It is generally agreed that pops is a liquid spray/gas two-phase explosion triggered by a local explosion near the jet impingement region. The effects of operating parameters on pops observed in the development tests of the apogee engine for the ETS-6 were inconsistent with those reported earlier for single impingement injectors; pops with the apogee engine injectors was more likely to occur at higher chamber pressures, higher injection velocities, and higher propellant temperatures. Pops data were correlated fairly well in chamber pressures (bar-P(sub c)) vs. fuel Reynolds number (R(sub ef)) plane. However, the range of operating parameters for the above correlation were very narrow since they were obtained during injector screening tests for a particular application to the apogee engine. It was also felt that the above correlation was too simplistic to capture any effect of design parameters of multi-element injectors. In the present study, the demarcation between pops and the pops-free region was determined in broader operating ranges and design parameters. The range of bar-P(sub c) and R(sub ef) was extended by exchanging graphite nozzle throat inserts with different throat diameters. The injectors were carefully selected to obtain effects, if any, of (1) film cooling fraction, (2) secondary mixing, and (3) number of elements and/or fuel orifice diameters. It was found that there was a threshold fuel Reynolds number below which no pops were observed at any chamber pressures and that the pops region curve in the bar-P(sub c)-R(sub ef) plane had two branches: upper branches and lower branches.

Plasma Engines,

DTIC Science & Technology

1982-09-08

low thrust, long duration power device, the plasma engine 6 has certain distinct advantages. For a chemical fuel rocket engine , a thrust of M.’)1...PLASMA ENGINES.CU) UNCLASSZICD FTO-ZIftS)T-0636-98 NL * UUUUU UUMile ~ FTD-ID(RS)T-0636-82 FOREIGN TECHNOLOGY DIVISION q 14 PLASMA ENGINES bv Sung...8 September 1982 MICROFICHE NR: FTD-82-C-001198 PLASMA ENGINES By: Sung Yuyang English pages: 7 Source: Hangkong Zhishi, March 1982, pp. 12-13 Country

Development of a genetically engineered Escherichia coli strain for plasmid transformation in Corynebacterium glutamicum.

PubMed

Li, Hedan; Zhang, Lirong; Guo, Wei; Xu, Daqing

2016-12-01

Gene disruption and replacement in Corynebacterium glutamicum is dependent upon a high transformation efficiency. The cglIR-cgIIR restriction system is a major barrier to introduction of foreign DNA into Corynebacterium glutamicum cells. To improve the transformation efficiency of C. glutamicum, the cglIM gene encoding methyltransferase in the cglIR-cglIIR-cglIM restriction-modification system of C. glutamicum ATCC 13032 was chromosomally integrated and expressed in Escherichia coli, resulting in an engineered strain E. coli AU1. The electro-transformation experiments of C. glutamicum ATCC 13032 with the E. coli-C. glutamicum shuttle plasmid pAU4 showed that the transformation efficiency of C. glutamicum with pAU4 DNA extracted from E. coli TG1/pAU4 was 1.80±0.21×10 2 cfu/μg plasmid DNA, while using pAU4 DNA extracted from E. coli AU1/pAU4, the transformation efficiency reached up to 5.22±0.33×10 6 cfu/μg plasmid DNA. The results demonstrated that E. coli AU1 is able to confer the cglIM-specific DNA methylation pattern to its resident plasmid, which makes the plasmid resistant to the cglIR-cglIIR restriction and efficiently transferred into C. glutamicum. E. coli AU1 is a useful intermediate host for efficient transformation of C. glutamicum. Copyright © 2016. Published by Elsevier B.V.

Rational engineering of multiple module pathways for the production of L-phenylalanine in Corynebacterium glutamicum.

PubMed

Zhang, Chuanzhi; Zhang, Junli; Kang, Zhen; Du, Guocheng; Chen, Jian

2015-05-01

Microbial production of L-phenylalanine (L-Phe) from renewable sources has attracted much attention recently. In the present study, Corynebacterium glutamicum 13032 was rationally engineered to produce L-Phe from inexpensive glucose. First, all the L-Phe biosynthesis pathway genes were investigated and the results demonstrated that in addition to AroF and PheA, the native PpsA, TktA, AroE and AroA, and the heterologous AroL and TyrB were also the key enzymes for L-Phe biosynthesis. Through combinational expression of these key enzymes, the L-Phe production was increased to 6.33 ± 0.13 g l(-1) which was about 1.48-fold of that of the parent strain C. glutamicum (pXM-pheA (fbr)-aroF (fbr)) (fbr, feedback-inhibition resistance). Furthermore, the production of L-Phe was improved to 9.14 ± 0.21 g l(-1) by modifying the glucose and L-Phe transport systems and blocking the acetate and lactate biosynthesis pathways. Eventually, the titer of L-Phe was enhanced to 15.76 ± 0.23 g l(-1) with a fed-batch fermentation strategy. To the best of our knowledge, this was the highest value reported in rationally engineered C. glutamicum 13032 strains. The results obtained will also contribute to rational engineering of C. glutamicum for production of other valuable aromatic compounds.

Thermal and Environmental Barrier Coating Development for Advanced Propulsion Engine Systems

NASA Technical Reports Server (NTRS)

Zhu, Dongming; Miller, Robert A.; Fox, Dennis S.

2008-01-01

Ceramic thermal and environmental barrier coatings (TEBCs) are used in gas turbine engines to protect engine hot-section components in the harsh combustion environments, and extend component lifetimes. Advanced TEBCs that have significantly lower thermal conductivity, better thermal stability and higher toughness than current coatings will be beneficial for future low emission and high performance propulsion engine systems. In this paper, ceramic coating design and testing considerations will be described for turbine engine high temperature and high-heat-flux applications. Thermal barrier coatings for metallic turbine airfoils and thermal/environmental barrier coatings for SiC/SiC ceramic matrix composite (CMC) components for future supersonic aircraft propulsion engines will be emphasized. Further coating capability and durability improvements for the engine hot-section component applications can be expected by utilizing advanced modeling and design tools.

Enhanced Shewanella biofilm promotes bioelectricity generation.

PubMed

Liu, Ting; Yu, Yang-Yang; Deng, Xiao-Peng; Ng, Chun Kiat; Cao, Bin; Wang, Jing-Yuan; Rice, Scott A; Kjelleberg, Staffan; Song, Hao

2015-10-01

Electroactive biofilms play essential roles in determining the power output of microbial fuel cells (MFCs). To engineer the electroactive biofilm formation of Shewanella oneidensis MR-1, a model exoelectrogen, we herein heterologously overexpressed a c-di-GMP biosynthesis gene ydeH in S. oneidensis MR-1, constructing a mutant strain in which the expression of ydeH is under the control of IPTG-inducible promoter, and a strain in which ydeH is under the control of a constitutive promoter. Such engineered Shewanella strains had significantly enhanced biofilm formation and bioelectricity generation. The MFCs inoculated with these engineered strains accomplished a maximum power density of 167.6 ± 3.6 mW/m(2) , which was ∼ 2.8 times of that achieved by the wild-type MR-1 (61.0 ± 1.9 mW/m(2) ). In addition, the engineered strains in the bioelectrochemical system at poised potential of 0.2 V vs. saturated calomel electrode (SCE) generated a stable current density of 1100 mA/m(2) , ∼ 3.4 times of that by wild-type MR-1 (320 mA/m(2) ). © 2015 Wiley Periodicals, Inc.

High-Performance SiC/SiC Ceramic Composite Systems Developed for 1315 C (2400 F) Engine Components

NASA Technical Reports Server (NTRS)

DiCarlo, James A.; Yun, Hee Mann; Morscher, Gregory N.; Bhatt, Ramakrishna T.

2004-01-01

As structural materials for hot-section components in advanced aerospace and land-based gas turbine engines, silicon carbide (SiC) ceramic matrix composites reinforced by high performance SiC fibers offer a variety of performance advantages over current bill-of-materials, such as nickel-based superalloys. These advantages are based on the SiC/SiC composites displaying higher temperature capability for a given structural load, lower density (approximately 30- to 50-percent metal density), and lower thermal expansion. These properties should, in turn, result in many important engine benefits, such as reduced component cooling air requirements, simpler component design, reduced support structure weight, improved fuel efficiency, reduced emissions, higher blade frequencies, reduced blade clearances, and higher thrust. Under the NASA Ultra-Efficient Engine Technology (UEET) Project, much progress has been made at the NASA Glenn Research Center in identifying and optimizing two highperformance SiC/SiC composite systems. The table compares typical properties of oxide/oxide panels and SiC/SiC panels formed by the random stacking of balanced 0 degrees/90 degrees fabric pieces reinforced by the indicated fiber types. The Glenn SiC/SiC systems A and B (shaded area of the table) were reinforced by the Sylramic-iBN SiC fiber, which was produced at Glenn by thermal treatment of the commercial Sylramic SiC fiber (Dow Corning, Midland, MI; ref. 2). The treatment process (1) removes boron from the Sylramic fiber, thereby improving fiber creep, rupture, and oxidation resistance and (2) allows the boron to react with nitrogen to form a thin in situ grown BN coating on the fiber surface, thereby providing an oxidation-resistant buffer layer between contacting fibers in the fabric and the final composite. The fabric stacks for all SiC/SiC panels were provided to GE Power Systems Composites for chemical vapor infiltration of Glenn designed BN fiber coatings and conventional SiC matrices. Composite panels with system B were heat treated at Glenn, and the pores that remained open were filled by silicon melt infiltration (MI). Panels with system A and the other SiC/SiC systems were not heat treated, and remaining open pores in these systems were filled with SiC slurry and silicon MI.

Tensile properties of V-Cr-Ti alloys after exposure in oxygen-containing environments

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

Natesan, K.; Soppet, W.K.

A systematic study was conducted to evaluate the oxidation kinetics of V-4Cr-4Ti (44 alloy) and V-5Cr-5Ti alloys (55 alloy) and to establish the role of oxygen ingress on the tensile behavior of the alloys at room temperature and at 500 C. The oxidation rate of the 44 alloy is slightly higher than that of the 55 alloy. The oxidation process followed parabolic kinetics. Maximum engineering stress for 55 alloy increased with an increase in oxidation time at 500 C. The maximum stress values for 55 alloy were higher at room temperature than ta 500 C for the same oxidation treatment.more » Maximum engineering stresses for 44 alloy were substantially lower than those for 55 alloy in the same oxidation {approx}500 h exposure in air at 500 C; the same values were 4.8 and 6.1%, respectively, at 500 C after {approx}2060 h oxidation in air at 500 C. Maximum engineering stress for 44 alloy at room temperature was 421.6--440.6 MPa after {approx}250 h exposure at 500 C in environments with a pO{sub 2} range of 1 {times} 10{sup {minus}6} to 760 torr. The corresponding uniform and total elongation values were 11--14.4% and 14.5--21.7%, respectively. Measurements of crack depths in various specimens showed that depth is independent of pO{sub 2} in the preexposure environment and was of 70--95 {micro}m after 250--275 h exposure at 500 C.« less

Transforming Systems Engineering through Model Centric Engineering

DTIC Science & Technology

2017-08-08

12 Figure 5. Semantic Web Technologies related to Layers of Abstraction ................................. 23 Figure 6. NASA /JPL Instantiation...of OpenMBEE (circa 2014) ................................................. 24 Figure 7. NASA /JPL Foundational Ontology for Systems Engineering...Engineering (DE) Transformation initiative, and our relationship that we have fostered with National Aeronautics and Space Administration ( NASA ) Jet

Development of a Twin-Spool Turbofan Engine Simulation Using the Toolbox for the Modeling and Analysis of Thermodynamic Systems (T-MATS)

NASA Technical Reports Server (NTRS)

Zinnecker, Alicia M.; Chapman, Jeffryes W.; Lavelle, Thomas M.; Litt, Jonathan S.

2014-01-01

The Toolbox for the Modeling and Analysis of Thermodynamic Systems (T-MATS) is a tool that has been developed to allow a user to build custom models of systems governed by thermodynamic principles using a template to model each basic process. Validation of this tool in an engine model application was performed through reconstruction of the Commercial Modular Aero-Propulsion System Simulation (C-MAPSS) (v2) using the building blocks from the T-MATS (v1) library. In order to match the two engine models, it was necessary to address differences in several assumptions made in the two modeling approaches. After these modifications were made, validation of the engine model continued by integrating both a steady-state and dynamic iterative solver with the engine plant and comparing results from steady-state and transient simulation of the T-MATS and C-MAPSS models. The results show that the T-MATS engine model was accurate within 3% of the C-MAPSS model, with inaccuracy attributed to the increased dimension of the iterative solver solution space required by the engine model constructed using the T-MATS library. This demonstrates that, given an understanding of the modeling assumptions made in T-MATS and a baseline model, the T-MATS tool provides a viable option for constructing a computational model of a twin-spool turbofan engine that may be used in simulation studies.

In-Space Engine (ISE-100) Development - Design Verification Test

NASA Technical Reports Server (NTRS)

Trinh, Huu P.; Popp, Chris; Bullard, Brad

2017-01-01

In the past decade, NASA has formulated science mission concepts with an anticipation of landing spacecraft on the lunar surface, meteoroids, and other planets. Advancing thruster technology for spacecraft propulsion systems has been considered for maximizing science payload. Starting in 2010, development of In-Space Engine (designated as ISE-100) has been carried out. ISE-100 thruster is designed based on heritage Missile Defense Agency (MDA) technology aimed for a lightweight and efficient system in terms volume and packaging. It runs with a hypergolic bi-propellant system: MON-25 (nitrogen tetroxide, N2O4, with 25% of nitric oxide, NO) and MMH (monomethylhydrazine, CH6N2) for NASA spacecraft applications. The utilization of this propellant system will provide a propulsion system capable of operating at wide range of temperatures, from 50 C (122 F) down to -30 C (-22 F) to drastically reduce heater power. The thruster is designed to deliver 100 lb(sub f) of thrust with the capability of a pulse mode operation for a wide range of mission duty cycles (MDCs). Two thrusters were fabricated. As part of the engine development, this test campaign is dedicated for the design verification of the thruster. This presentation will report the efforts of the design verification hot-fire test program of the ISE-100 thruster in collaboration between NASA Marshall Space Flight Center (MSFC) and Aerojet Rocketdyne (AR) test teams. The hot-fire tests were conducted at Advance Mobile Propulsion Test (AMPT) facility in Durango, Colorado, from May 13 to June 10, 2016. This presentation will also provide a summary of key points from the test results.

Military Jet Engine Acquisition: Technology Basics and Cost-Estimating Methodology

DTIC Science & Technology

2002-01-01

aircraft , rather than by these forms of jet engines . Like the turbofan or turbojet , these engines have a nozzle down- stream of the low-pressure...2.5 illustrates the process of turbine blade cooling. Figure 2.6 illustrates the steady and rapid increase in RIT for turbo - jets , turbofans , and...87 B. AN OVERVIEW OF MILITARY JET ENGINE HISTORY ... 97 C. AIRCRAFT TURBINE ENGINE DEVELOPMENT ...... 121 D.

Pre-Engineering Program: Science, Technology, Engineering and Mathematics (STEM)

DTIC Science & Technology

2013-08-29

educators in the Urbana-Champaign area. 15. SUBJECT TERMS STEM: science, technology , engineering, mathematics 16. SECURITY CLASSIFICATION OF: 19a. NAME...9132T-13-1-0002 4. TITLE AND SUBTITLE Pre-Engineering Program: Science, Technology , Engineering and Mathematics (STEM) 5c. PROGRAM ELEMENT NUMBER N...project was focused on underserved children in grades 1-6 who need, but have limited access to, out-of-school time STEM (science, technology

Engineering the intracellular metabolism of Escherichia coli to produce gamma-aminobutyric acid by co-localization of GABA shunt enzymes.

PubMed

Pham, Van Dung; Somasundaram, Sivachandiran; Lee, Seung Hwan; Park, Si Jae; Hong, Soon Ho

2016-02-01

To direct the carbon flux from Krebs cycle into the gamma-aminobutyric acid (GABA) shunt pathway for the production of GABA by protein scaffold introduction in Escherichia coli. Escherichia coli was engineered to produce GABA from glucose by the co-localization of enzymes succinate semialdehyde dehydrogenase (GadD), GABA aminotransferase (PuuE) and GABA transporter (GadC) by protein scaffold. 0.7 g GABA l(-1) was produced from 10 g glucose l(-1) while no GABA was produced in wild type E. coli. pH 6 and 30 °C were optimum for GABA production, and GABA concentration increased to 1.12 g GABA l(-1) when 20 g glucose l(-1) was used. When competing metabolic networks were inactivated, GABA increased by 24 % (0.87 g GABA l(-1)). The novel GABA production system was constructed by co-localization of GABA shunt enzymes.

6. DETAIL VIEW OF BRIDGE DATEPLATE WHICH READS '1930, WHITE ...

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

6. DETAIL VIEW OF BRIDGE DATEPLATE WHICH READS '1930, WHITE RIVER BRIDGE, ARKANSAS HIGHWAY COMMISSION, DWIGHT BLACKWOOD, CHAIRMAN, JUSTIN MATTHEWS, J. LAN WILLIAMS, J.S. PARKS, SAM J. WILSON, COMMISSIONERS, C.S. CHRISTIAN, STATE HIGHWAY ENGINEER, IRA HEDRICK, INC., CONSULTING ENGINEERS, PARHAM CONT. CO., CONTRACTOR' - Augusta Bridge, Spanning White River at Highway 64, Augusta, Woodruff County, AR

Analysis of the Perceived Adequacy of Air Force Civil Engineering Prime Beef Training

DTIC Science & Technology

1985-09-01

P.9 0); - I 6Q ANALYSIS OF THE PERCEIUED ADEOUACY OF AIR FORCE CIUIL ENGINEER!NG PRIME BEEF TRAINING THESIS William C. Morris Captain, USAF AFIT...Ohio TIWA docm=ent La 1;;, Ow psl• c relm’,-j and owme;d _! i8U0- ________IS____rft* 85 11 05 04 AFIT/SEM/DET/BE ANALYSIS OF THE PERCEIVED ADEQUACY...distribution unlimited L * The contents of the document are technically accurate, and 6 no sensitive items, detrimental ideas, or deleterious information are

Air Force Inspection System: An Application for System-of-Systems (SOS) Engineering

DTIC Science & Technology

2014-06-19

Program, 15 Dec 11 5. AFI 10-210, Prime Base Engineer Emergency Force ( BEEF ) Program, 6 Sep 12 6. AFI 10-245, Antiterrorism (AT), 21 Sep 12 AFI 10...Aircraft Carrying Hazardous Materials, 11 Nov 94 79. AFMAN 11-226 (I), US Standard for Terminal Instrument Procedures (TERPS) 92 80. AFMAN 10

Engine Tune-up Service. Unit 6: Emission Control Systems. Posttests. Automotive Mechanics Curriculum.

ERIC Educational Resources Information Center

Morse, David T.; May, Theodore R.

This book of posttests is designed to accompany the Engine Tune-Up Service Student Guide for Unit 6, Emission Control Systems, available separately as CE 031 220. Focus of the posttests is inspecting, testing, and servicing emission control systems. One multiple choice posttest is provided that covers the seven performance objectives contained in…

Metabolic engineering of Corynebacterium glutamicum to produce GDP-L-fucose from glucose and mannose.

PubMed

Chin, Young-Wook; Park, Jin-Byung; Park, Yong-Cheol; Kim, Kyoung Heon; Seo, Jin-Ho

2013-06-01

Wild-type Corynebacterium glutamicum was metabolically engineered to convert glucose and mannose into guanosine 5'-diphosphate (GDP)-L-fucose, a precursor of fucosyl-oligosaccharides, which are involved in various biological and pathological functions. This was done by introducing the gmd and wcaG genes of Escherichia coli encoding GDP-D-mannose-4,6-dehydratase and GDP-4-keto-6-deoxy-D-mannose-3,5-epimerase-4-reductase, respectively, which are known as key enzymes in the production of GDP-L-fucose from GDP-D-mannose. Coexpression of the genes allowed the recombinant C. glutamicum cells to produce GDP-L-fucose in a minimal medium containing glucose and mannose as carbon sources. The specific product formation rate was much higher during growth on mannose than on glucose. In addition, the specific product formation rate was further increased by coexpressing the endogenous phosphomanno-mutase gene (manB) and GTP-mannose-1-phosphate guanylyl-transferase gene (manC), which are involved in the conversion of mannose-6-phosphate into GDP-D-mannose. However, the overexpression of manA encoding mannose-6-phosphate isomerase, catalyzing interconversion of mannose-6-phosphate and fructose-6-phosphate showed a negative effect on formation of the target product. Overall, coexpression of gmd, wcaG, manB and manC in C. glutamicum enabled production of GDP-L-fucose at the specific rate of 0.11 mg g cell(-1) h(-1). The specific GDP-L-fucose content reached 5.5 mg g cell(-1), which is a 2.4-fold higher than that of the recombinant E. coli overexpressing gmd, wcaG, manB and manC under comparable conditions. Well-established metabolic engineering tools may permit optimization of the carbon and cofactor metabolisms of C. glutamicum to further improve their production capacity.

Lightweight Combat Vehicle S&T Initiatives

DTIC Science & Technology

2015-08-01

1 U.S. ARMY TANK AUTOMOTIVE RESEARCH, DEVELOPMENT AND ENGINEERING CENTER Lightweight Combat Vehicle S &T Initiatives Dr. Richard Gerth Ground Systems...00-00-2015 to 00-00-2015 4. TITLE AND SUBTITLE Lightweight Combat Vehicle S &T Initiatives Global Automotive Lightweight Materials 2015 - August...18-20 2015 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR( S ) Richard Gerth 5d. PROJECT NUMBER 5e. TASK NUMBER 5f

Test and Evaluation of Teleconferencing Video Codecs Transmitting at 1.5 Mbps.

DTIC Science & Technology

1985-08-01

video teleconferencing codecs on the market as of November 1984 to facilitate the choice of an appropriate frame format and data compression algorithm...Engineer, computer company, male 5. Chapter Officer, national civic organization, female Group Y: 6. Marketing Representative, communication systems...both mon:tors to C4ve t e evi uators an idea what kind of cictures they will have to ; ucge . Special suggestions were given regardinc the sequences witn

14 CFR 29.951 - General.

Code of Federal Regulations, 2014 CFR

2014-01-01

... STANDARDS: TRANSPORT CATEGORY ROTORCRAFT Powerplant Fuel System § 29.951 General. (a) Each fuel system must... permitted to be in operation. (b) Each fuel system must be arranged so that— (1) No engine or fuel pump can... system. (c) Each fuel system for a turbine engine must be capable of sustained operation throughout its...

14 CFR 29.951 - General.

Code of Federal Regulations, 2012 CFR

2012-01-01

... STANDARDS: TRANSPORT CATEGORY ROTORCRAFT Powerplant Fuel System § 29.951 General. (a) Each fuel system must... permitted to be in operation. (b) Each fuel system must be arranged so that— (1) No engine or fuel pump can... system. (c) Each fuel system for a turbine engine must be capable of sustained operation throughout its...

14 CFR 29.951 - General.

Code of Federal Regulations, 2013 CFR

2013-01-01

... STANDARDS: TRANSPORT CATEGORY ROTORCRAFT Powerplant Fuel System § 29.951 General. (a) Each fuel system must... permitted to be in operation. (b) Each fuel system must be arranged so that— (1) No engine or fuel pump can... system. (c) Each fuel system for a turbine engine must be capable of sustained operation throughout its...

14 CFR 29.951 - General.

Code of Federal Regulations, 2011 CFR

2011-01-01

... STANDARDS: TRANSPORT CATEGORY ROTORCRAFT Powerplant Fuel System § 29.951 General. (a) Each fuel system must... permitted to be in operation. (b) Each fuel system must be arranged so that— (1) No engine or fuel pump can... system. (c) Each fuel system for a turbine engine must be capable of sustained operation throughout its...

14 CFR 29.951 - General.

Code of Federal Regulations, 2010 CFR

2010-01-01

... STANDARDS: TRANSPORT CATEGORY ROTORCRAFT Powerplant Fuel System § 29.951 General. (a) Each fuel system must... permitted to be in operation. (b) Each fuel system must be arranged so that— (1) No engine or fuel pump can... system. (c) Each fuel system for a turbine engine must be capable of sustained operation throughout its...

Small Engine Technology (SET) - Task 13 ANOPP Noise Prediction for Small Engines: Jet Noise Prediction Module, Wing Shielding Module, and System Studies Results

NASA Technical Reports Server (NTRS)

Lieber, Lysbeth; Golub, Robert (Technical Monitor)

2000-01-01

This Final Report has been prepared by AlliedSignal Engines and Systems, Phoenix, Arizona, documenting work performed during the period May 1997 through June 1999, under the Small Engines Technology Program, Contract No. NAS3-27483, Task Order 13, ANOPP Noise Prediction for Small Engines. The report specifically covers the work performed under Subtasks 4, 5 and 6. Subtask 4 describes the application of a semi-empirical procedure for jet noise prediction, subtask 5 describes the development of a procedure to predict the effects of wing shielding, and subtask 6 describes the results of system studies of the benefits of the new noise technology on business and regional aircraft.

Effect of ethanol-gasoline blends on small engine generator energy efficiency and exhaust emission.

PubMed

Lin, Wen-Yinn; Chang, Yuan-Yi; Hsieh, You-Ru

2010-02-01

This study was focused on fuel energy efficiency and pollution analysis of different ratios of ethanol-gasoline blended fuels (E0, E3, E6, and E9) under different loadings. In this research, the experimental system consisted of a small engine generator, a particulate matter measurement system, and an exhaust gas analyzer system. Different fuels, unleaded gasoline, and ethanol-gasoline blends (E0, E3, E6, and E9) were used to study their effects on the exhaust gas emission and were expressed as thermal efficiency of the small engine generator energy efficiency. The results suggested that particle number concentration increased as the engine loading increased; however, it decreased as the ethanol content in the blend increased. While using E6 as fuel, the carbon monoxide (CO) concentration was less than other fuels (E0, E3, and E9) for each engine loading. The average of CO concentration reduction by using E3, E6, and E9 is 42, 86, and 83%, respectively. Using an ethanol-gasoline blend led to a significant reduction in exhaust emissions by approximately 78.7, 97.5, and 89.46% of the mean average values of hydrocarbons (HCs) with E3, E6, and E9 fuels, respectively, for all engine loadings. Using an ethanol-gasoline blend led to a significant reduction in exhaust emissions by approximately 35, 86, and 77% of the mean average values of nitrogen oxides (NOx) with E3, E6, and E9 fuels, respectively, at each engine loading. The E6 fuel gave the best results of the exhaust emissions, and the E9 fuel gave the best results of the particle emissions and engine performance. The thermal efficiency of the small engine generator increased as the ethanol content in the blend increased and as the engine loading increased.

Overview of Engineering Design and Analysis at the NASA John C. Stennis Space Center

NASA Technical Reports Server (NTRS)

Congiardo, Jared; Junell, Justin; Kirkpatrick, Richard; Ryan, Harry

2007-01-01

This viewgraph presentation gives a general overview of the design and analysis division of NASA John C. Stennis Space Center. This division develops and maintains propulsion test systems and facilities for engineering competencies.

Biotechnology Process Engineering Center at MIT Home

Science.gov Websites

, 2003 BPEC Director Doug Lauffenburger in C&EN's coverstory on Systems Biology C&EN May 19th March 2003 Tissue engineering: The beat goes on Nature Februray 27th 2003 Molecular biology: A fix for

Soil temperature of peatland landscapes as a factor in the development of exogenous processes of biogenic relief formation in engineering development of territory

NASA Astrophysics Data System (ADS)

Korkin, S.; Talyneva, O.; Kail, E.

2018-03-01

In the presented work we consider mire landscapes in the context of temperature monitoring. The mire landscapes in engineering development of the territory are very sensitive to anthropogenic impact that leads to a change in surface conditions, changes in natural succession and, as a rule, to changes in soil temperature and properties, which in turn may develop a complex of hostile geodynamic processes. For this study we used recording systems for field measurement of peat and subsoil temperatures. The measurements were made in two key areas: the territory of the north-taiga landscapes of Western Siberia (the Siberian Ridges), and the territory of the middle-taiga landscapes of Western Siberia (the Ob middle-river lowland). The paper analyses the data obtained from five observation sites (3, 5, 5a, 6 and 8) referred to hydromorphic landscapes. For the territory of the Siberian Ridges the 5-year average soil temperature was 3°C. For the Ob middle-river lowland the 6-year average soil temperature was 4.2°C. The annual soil temperature in the period 2015-2016 for Site 5a (man-disturbed area) was 8.3°C at all depths, which is 3.8°C higher than in a natural bog (Site 5 was a control area).

Spacecraft systems engineering: An introduction to the process at GSFC

NASA Technical Reports Server (NTRS)

Fragomeni, Tony; Ryschkewitsch, Michael G.

1993-01-01

The main objective in systems engineering is to devise a coherent total system design capable of achieving the stated requirements. Requirements should be rigid. However, they should be continuously challenged, rechallenged and/or validated. The systems engineer must specify every requirement in order to design, document, implement and conduct the mission. Each and every requirement must be logically considered, traceable and evaluated through various analysis and trade studies in a total systems design. Margins must be determined to be realistic as well as adequate. The systems engineer must also continuously close the loop and verify system performance against the requirements. The fundamental role of the systems engineer, however, is to engineer, not manage. Yet, in large, complex missions, where more than one systems engineer is required, someone needs to manage the systems engineers, and we call them 'systems managers.' Systems engineering management is an overview function which plans, guides, monitors and controls the technical execution of a project as implemented by the systems engineers. As the project moves on through Phases A and B into Phase C/D, the systems engineering tasks become a small portion of the total effort. The systems management role increases since discipline subsystem engineers are conducting analyses and reviewing test data for final review and acceptance by the systems managers.

48 CFR 48.103 - Processing value engineering change proposals.

Code of Federal Regulations, 2014 CFR

2014-10-01

... engineering change proposals. 48.103 Section 48.103 Federal Acquisition Regulations System FEDERAL ACQUISITION REGULATION CONTRACT MANAGEMENT VALUE ENGINEERING Policies and Procedures 48.103 Processing value engineering... Government are included in paragraphs (c) and (d) of the value engineering clauses prescribed in subpart 48.2...

48 CFR 48.103 - Processing value engineering change proposals.

Code of Federal Regulations, 2012 CFR

2012-10-01

... engineering change proposals. 48.103 Section 48.103 Federal Acquisition Regulations System FEDERAL ACQUISITION REGULATION CONTRACT MANAGEMENT VALUE ENGINEERING Policies and Procedures 48.103 Processing value engineering... Government are included in paragraphs (c) and (d) of the value engineering clauses prescribed in subpart 48.2...

48 CFR 48.103 - Processing value engineering change proposals.

Code of Federal Regulations, 2013 CFR

2013-10-01

... engineering change proposals. 48.103 Section 48.103 Federal Acquisition Regulations System FEDERAL ACQUISITION REGULATION CONTRACT MANAGEMENT VALUE ENGINEERING Policies and Procedures 48.103 Processing value engineering... Government are included in paragraphs (c) and (d) of the value engineering clauses prescribed in subpart 48.2...

48 CFR 48.103 - Processing value engineering change proposals.

Code of Federal Regulations, 2010 CFR

2010-10-01

... engineering change proposals. 48.103 Section 48.103 Federal Acquisition Regulations System FEDERAL ACQUISITION REGULATION CONTRACT MANAGEMENT VALUE ENGINEERING Policies and Procedures 48.103 Processing value engineering... Government are included in paragraphs (c) and (d) of the value engineering clauses prescribed in subpart 48.2...

48 CFR 48.103 - Processing value engineering change proposals.

Code of Federal Regulations, 2011 CFR

2011-10-01

... engineering change proposals. 48.103 Section 48.103 Federal Acquisition Regulations System FEDERAL ACQUISITION REGULATION CONTRACT MANAGEMENT VALUE ENGINEERING Policies and Procedures 48.103 Processing value engineering... Government are included in paragraphs (c) and (d) of the value engineering clauses prescribed in subpart 48.2...

48 CFR 736.605 - Government cost estimate for architect-engineer work.

Code of Federal Regulations, 2013 CFR

2013-10-01

... for architect-engineer work. 736.605 Section 736.605 Federal Acquisition Regulations System AGENCY FOR INTERNATIONAL DEVELOPMENT SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 736.605 Government cost estimate for architect-engineer work. See 736.602-3(c)(5). ...

48 CFR 736.605 - Government cost estimate for architect-engineer work.

Code of Federal Regulations, 2010 CFR

2010-10-01

... for architect-engineer work. 736.605 Section 736.605 Federal Acquisition Regulations System AGENCY FOR INTERNATIONAL DEVELOPMENT SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 736.605 Government cost estimate for architect-engineer work. See 736.602-3(c)(5). ...

48 CFR 736.605 - Government cost estimate for architect-engineer work.

Code of Federal Regulations, 2014 CFR

2014-10-01

... for architect-engineer work. 736.605 Section 736.605 Federal Acquisition Regulations System AGENCY FOR INTERNATIONAL DEVELOPMENT SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 736.605 Government cost estimate for architect-engineer work. See 736.602-3(c)(5). ...

48 CFR 736.605 - Government cost estimate for architect-engineer work.

Code of Federal Regulations, 2012 CFR

2012-10-01

... for architect-engineer work. 736.605 Section 736.605 Federal Acquisition Regulations System AGENCY FOR INTERNATIONAL DEVELOPMENT SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 736.605 Government cost estimate for architect-engineer work. See 736.602-3(c)(5). ...

48 CFR 736.605 - Government cost estimate for architect-engineer work.

Code of Federal Regulations, 2011 CFR

2011-10-01

... for architect-engineer work. 736.605 Section 736.605 Federal Acquisition Regulations System AGENCY FOR INTERNATIONAL DEVELOPMENT SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 736.605 Government cost estimate for architect-engineer work. See 736.602-3(c)(5). ...

Calcium-Magnesium-Alumino-Silicates (CMAS) Reaction Mechanisms and Resistance of Advanced Turbine Environmental Barrier Coatings for SiC/SiC Ceramic Matrix Composites

NASA Technical Reports Server (NTRS)

Zhu, Dongming; Costa, Gustavo; Harder, Bryan J.; Wiesner, Valerie L.; Hurst, Janet B.; Puleo, Bernadette J.

2017-01-01

Environmental barrier coatings (EBCs) and SiC/SiC ceramic matrix composites (CMCs) systems will play a crucial role in future turbine engines for hot-section component applications because of their ability to significantly increase engine operating temperatures, reduce engine weight and cooling requirements. The development of prime-reliant environmental barrier coatings is an essential requirement to enable the applications of the 2700-3000 F EBC - CMC systems. This presentation primarily focuses on the reaction mechanisms of advanced NASA environmental barrier coating systems, when in contact with Calcium-Magnesium Alumino-Silicates (CMAS) at high temperatures. Advanced oxide-silicate defect cluster environmental barrier coatings are being designed for ultimate balanced controls of the EBC temperature capability and CMAS reactivity, thus improving the CMAS resistance. Further CMAS mitigation strategies are also discussed.

Simulator Evaluation of Simplified Propulsion-Only Emergency Flight Control Systems on Transport Aircraft

NASA Technical Reports Server (NTRS)

Burcham, Frank W., Jr.; Kaneshige, John; Bull, John; Maine, Trindel A.

1999-01-01

With the advent of digital engine control systems, considering the use of engine thrust for emergency flight control has become feasible. Many incidents have occurred in which engine thrust supplemented or replaced normal aircraft flight controls. In most of these cases, a crash has resulted, and more than 1100 lives have been lost. The NASA Dryden Flight Research Center has developed a propulsion-controlled aircraft (PCA) system in which computer-controlled engine thrust provides emergency flight control capability. Using this PCA system, an F-15 and an MD-11 airplane have been landed without using any flight controls. In simulations, C-17, B-757, and B-747 PCA systems have also been evaluated successfully. These tests used full-authority digital electronic control systems on the engines. Developing simpler PCA systems that can operate without full-authority engine control, thus allowing PCA technology to be installed on less capable airplanes or at lower cost, is also a desire. Studies have examined simplified ?PCA Ultralite? concepts in which thrust control is provided using an autothrottle system supplemented by manual differential throttle control. Some of these concepts have worked well. The PCA Ultralite study results are presented for simulation tests of MD-11, B-757, C-17, and B-747 aircraft.

Rapid Response Research and Development (R&D) for the Aerospace Systems Directorate. Delivery Order 0021: Engineering Research and Technical Analyses of Advanced Airbreathing Propulsion Fuels, Subtask: Engine and Pump Studies Utilizing JP-8 and Alcohol-to-Jet (ATJ) Blends

DTIC Science & Technology

2014-08-01

41 Figure A-21. Lubricant Soot Accumulation...ASTM D4739 Total Base Number ASTM D664 Total Acid Number ASTM D445 Kinematic Viscosity @ 100°C ASTM D4052 Density ASTM TGA SOOT TGA Soot ASTM E168...118.85 134.01 145.47 169.22 187.43 342.42 Nitration (Abs./cm) E168 FTIR 0 6.67 10.91 16.54 19.04 25.79 35.12 24.03 23.75 52.31 93.9 Soot (%) Soot TGA

Magnetohydrodynamics (MHD) Engineering Test Facility (ETF) 200 MWe power plant. Conceptual Design Engineering Report (CDER) supplement. Magnet system special investigations

NASA Technical Reports Server (NTRS)

1981-01-01

The results of magnet system special investigations listed below are summarized: 4 Tesla Magnet Alternate Design Study; 6 Tesla Magnet Manufacturability Study. The conceptual design for a 4 Tesla superconducting magnet system for use with an alternate (supersonic) ETF power train is described, and estimated schedule and cost are identified. The magnet design is scaled from the ETF 6 T Tesla design. Results of a manufacturability study and a revised schedule and cost estimate for the ETF 6 T magnet are reported. Both investigations are extensions of the conceptual design of a 6 T magnet system performed earlier as a part of the overall MED-ETF conceptual design described in Conceptual Design Engineering Report (CDER) Vol. V, System Design Description (SDD) 503 dated September, 1981, DOE/NASA/0224-1; NASA CR-165/52.

Long-Term Characterization of 6H-SiC Transistor Integrated Circuit Technology Operating at 500 C

NASA Technical Reports Server (NTRS)

Neudeck, Philip G.; Spry, David J.; Chen, Liang-Yu; Chang, Carl W.; Beheim, Glenn M.; Okojie, Robert S.; Evans, Laura J.; Meredith Roger D.; Ferrier, Terry L.; Krasowski, Michael J.;

Aircraft Engine Emissions Estimator

DTIC Science & Technology

1985-11-01

GE) 4 A-4 C-9A JT8D-9 (P&W) 2 A-5 C-12A PT6A-41 (P&W) 2 C-21A TFE731 -2 (GARRETT) 2 C-130A T 56-9 (ALLISON) 4 A-6 C-130B T 56-7 (ALLISON) 4 A-6 C-130...OA 0.52N MILITARY 1.06A 8.42A I.SA 0.2A 21.OA 0.67N TFE731 -2 IDLE (CA) APPROACH NO DATA AVAILABLE :NTERMED MILITARY * A-X represents the reference

Fuel Property Effects on the Cold Startability of Navy High-Speed Diesel Engines.

DTIC Science & Technology

1985-12-01

0C D 93 77 64.4 85.0 40.6 Cloud Point, 0C D 2500 -13 -18 +16 -5 Pour Point, 0C D 97 -17 <-50 -17 <-50 K . Vis at 400C, m2 /sec D 445 2.75 1.43 2.97...0.75 X 10- 6 X 10-6 X 10-6 X 10-6 K . Vis at 50C, m2/sec D 445 6.65 2.78 8.44 1.17 X 10-6 X 10-6 X 10-6 X 10-6 Distillation, 0C D 2887 IBP 133.2 138.1...volumes, and k is the rate of molal specific heats Cp/Cv. This process is independent of time. However, as the gas temperature is increased, the gas

Subjective Mapping of Dust Emission Sources by Using MODIS Imagery: Reproducibility Assessment

DTIC Science & Technology

2017-05-31

ER D C/ CR RE L TR -1 7- 8 ERDC 6.2 Geospatial Research and Engineering (GRE) ARTEMIS STO-R DUST-CLOUD Subjective Mapping of Dust...N. Sinclair and Sandra L. Jones May 2017 Approved for public release; distribution is unlimited. The U.S. Army Engineer Research and...library at http://acwc.sdp.sirsi.net/client/default. ERDC 6.2 Geospatial Research and Engineering (GRE) ARTEMIS STO-R DUST-CLOUD ERDC/CRREL TR-17-8

Development and Testing of Carbon-Carbon Nozzle Extensions for Upper Stage Liquid Rocket Engines

NASA Technical Reports Server (NTRS)

Valentine, Peter G.; Gradl, Paul R.; Greene, Sandra E.

2017-01-01

Carbon-carbon (C-C) composite nozzle extensions are of interest for use on a variety of launch vehicle upper stage engines and in-space propulsion systems. The C-C nozzle extension technology and test capabilities being developed are intended to support National Aeronautics and Space Administration (NASA) and Department of Defense (DOD) requirements, as well as those of the broader Commercial Space industry. For NASA, C-C nozzle extension technology development primarily supports the NASA Space Launch System (SLS) and NASA's Commercial Space partners. Marshall Space Flight Center (MSFC) efforts are aimed at both (a) further developing the technology and databases needed to enable the use of composite nozzle extensions on cryogenic upper stage engines, and (b) developing and demonstrating low-cost capabilities for testing and qualifying composite nozzle extensions. Recent, on-going, and potential future work supporting NASA, DOD, and Commercial Space needs will be discussed. Information to be presented will include (a) recent and on-going mechanical, thermal, and hot-fire testing, as well as (b) potential future efforts to further develop and qualify domestic C-C nozzle extension solutions for the various upper stage engines under development.

Development Status and Performance Comparisons of Environmental Barrier Coating Systems for SiCSiC Ceramic Matrix Composites

NASA Technical Reports Server (NTRS)

Zhu, Dongming; Harder, Bryan

2016-01-01

Environmental barrier coatings (EBC) and SiCSiC ceramic matrix composites (CMCs) will play a crucial role in future aircraft turbine engine systems, because of their ability to significantly increase engine operating temperatures, reduce engine weight and cooling requirements. This paper presents current NASA EBC-CMC development emphases including: the coating composition and processing improvements, laser high heat flux-thermal gradient thermo-mechanical fatigue - environmental testing methodology development, and property evaluations for next generation EBC-CMC systems. EBCs processed with various deposition techniques including Plasma Spray, Electron Beam - Physical Vapor Deposition, and Plasma Spray Physical Vapor Deposition (PS-PVD) will be particularly discussed. The testing results and demonstrations of advanced EBCs-CMCs in complex simulated engine thermal gradient cyclic fatigue, oxidizing-steam and CMAS environments will help provide insights into the coating development strategies to meet long-term engine component durability goals.

14 CFR 21.6 - Manufacture of new aircraft, aircraft engines, and propellers.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Manufacture of new aircraft, aircraft... Manufacture of new aircraft, aircraft engines, and propellers. (a) Except as specified in paragraphs (b) and (c) of this section, no person may manufacture a new aircraft, aircraft engine, or propeller based on...

The Genome-Based Metabolic Systems Engineering to Boost Levan Production in a Halophilic Bacterial Model.

PubMed

Aydin, Busra; Ozer, Tugba; Oner, Ebru Toksoy; Arga, Kazim Yalcin

2018-03-01

Metabolic systems engineering is being used to redirect microbial metabolism for the overproduction of chemicals of interest with the aim of transforming microbial hosts into cellular factories. In this study, a genome-based metabolic systems engineering approach was designed and performed to improve biopolymer biosynthesis capability of a moderately halophilic bacterium Halomonas smyrnensis AAD6 T producing levan, which is a fructose homopolymer with many potential uses in various industries and medicine. For this purpose, the genome-scale metabolic model for AAD6 T was used to characterize the metabolic resource allocation, specifically to design metabolic engineering strategies for engineered bacteria with enhanced levan production capability. Simulations were performed in silico to determine optimal gene knockout strategies to develop new strains with enhanced levan production capability. The majority of the gene knockout strategies emphasized the vital role of the fructose uptake mechanism, and pointed out the fructose-specific phosphotransferase system (PTS fru ) as the most promising target for further metabolic engineering studies. Therefore, the PTS fru of AAD6 T was restructured with insertional mutagenesis and triparental mating techniques to construct a novel, engineered H. smyrnensis strain, BMA14. Fermentation experiments were carried out to demonstrate the high efficiency of the mutant strain BMA14 in terms of final levan concentration, sucrose consumption rate, and sucrose conversion efficiency, when compared to the AAD6 T . The genome-based metabolic systems engineering approach presented in this study might be considered an efficient framework to redirect microbial metabolism for the overproduction of chemicals of interest, and the novel strain BMA14 might be considered a potential microbial cell factory for further studies aimed to design levan production processes with lower production costs.

Software System User’s Manual, Reference Manual, and Installation Guide for the Test Engineer’s Assistant System.

DTIC Science & Technology

1989-02-28

AD-A259 245 RESEARCH TRIANGLE INSTITUTE I SOFTWARE SYSTEM USER’S MANUAL, REFERENCE MANUAL, AND INSTALLATION GUIDE FOR THE TEST ENGINEER’S ASSISTANT...SYSTEM U. yD"VxC - February 28, 1989 Iŕ 5 G3 ’Contract No. DAAL01-86-C-0039 W Prepared for: Department of the Army Electronics Research and...Development Command Fort Monmouth, New Jersey 07703 I Prepared by: Center for Digital Systems ResearchI Research Triangle Institute Research Triangle Park, NC

Engine Tune-up Service. Unit 6: Emission Control Systems. Review Exercise Book. Automotive Mechanics Curriculum.

ERIC Educational Resources Information Center

Bacon, E. Miles

This book of pretests and review exercises is designed to accompany the Engine Tune-Up Service Student Guide for Unit 6, Emission Control Systems, available separately as CE 031 220. Focus of the exercises and pretests is inspecting, testing, and servicing emission control systems. Pretests and performance checklists are provided for each of the…

Engine Tune-up Service. Unit 6: Emission Control Systems. Student Guide. Automotive Mechanics Curriculum.

ERIC Educational Resources Information Center

Bacon, E. Miles

This student guide is for Unit 6, Emission Control Systems, in the Engine Tune-Up Service portion of the Automotive Mechanics Curriculum. It deals with inspecting, testing, and servicing an emission control system. A companion review exercise book and posttests are available separately as CE 031 221-222. An introduction tells how this unit fits…

Development and Evaluation of the Stingray, an Amphibious Maritime Interdiction Operations Unmanned Ground Vehicle

DTIC Science & Technology

2014-05-01

of Ships], Charles Griffin and Company, London, 246-261 (1908). [6] Volpich, H. & Bridge, I . C., “Paddle Wheels Pt 1: Preliminary Model Experiments...Transactions of the Institution of Engineers and Shipbuilders in Scotland, 327-380 (1955). [7] Volpich, H. & Bridge, I . C., “Paddle Wheels...Bridge, I . C., “Paddle Wheels Pt III: Ship/Model Correlation,” Transactions of the Institution of Engineers and Shipbuilders in Scotland, 512-550

76 FR 70382 - Airworthiness Directives; General Electric Company (GE) CF6-80C2B Series Turbofan Engines

Federal Register 2010, 2011, 2012, 2013, 2014

2011-11-14

... installing software version 8.2.Q1 to the engine electronic control unit (ECU), which increases the engine's... proposed AD would require the removal of the affected ECUs from service. We are proposing this AD to... software version 8.2.Q1 to the ECU, which increases the engine's margin to flameout. That AD was prompted...

Analysis of Ten Reverse Engineering Tools

NASA Astrophysics Data System (ADS)

Koskinen, Jussi; Lehmonen, Tero

Reverse engineering tools can be used in satisfying the information needs of software maintainers. Especially in case of maintaining large-scale legacy systems tool support is essential. Reverse engineering tools provide various kinds of capabilities to provide the needed information to the tool user. In this paper we analyze the provided capabilities in terms of four aspects: provided data structures, visualization mechanisms, information request specification mechanisms, and navigation features. We provide a compact analysis of ten representative reverse engineering tools for supporting C, C++ or Java: Eclipse Java Development Tools, Wind River Workbench (for C and C++), Understand (for C++), Imagix 4D, Creole, Javadoc, Javasrc, Source Navigator, Doxygen, and HyperSoft. The results of the study supplement the earlier findings in this important area.

Bibliography of Books and Published Reports on Gas Turbines, Jet Propulsion, and Rocket Power Plants, January 1950 through December 1953

DTIC Science & Technology

1953-12-01

Vt. J. V. Casamassa, Jet aircraft power systems . McGraw-Hill, New York. C. C. Chapel, Jet aircraft simplified. Aero Pubs. Inc., Los Angeles. V. C...combination. NACA Tech. Note No. 1951 (Sept.). A. F. Lietzke and H. M. Henneberry, Evaluation of piston-type gas- generator engine for subsonic transport...Dynamics of a turbojet engine considered as a quasi-static system . NACA Tech. Note No. 2091 (May). A. E. Puckett, Optimum performance of rocket- powered

Electric propulsion options for 10 kW class earth space missions

NASA Technical Reports Server (NTRS)

Patterson, M. J.; Curran, Francis M.

1989-01-01

Five and 10 kW ion and arcjet propulsion system options for a near-term space demonstration experiment have been evaluated. Analyses were conducted to determine first-order propulsion system performance and system component mass estimates. Overall mission performance of the electric propulsion systems was quantified in terms of the maximum thrusting time, total impulse, and velocity increment capability available when integrated onto a generic spacecraft under fixed mission model assumptions. Maximum available thrusting times for the ion-propelled spacecraft options, launched on a DELTA II 6920 vehicle, range from approximately 8,600 hours for a 4-engine 10 kW system to more than 29,600 hours for a single-engine 5 kW system. Maximum total impulse values and maximum delta-v's range from 1.2x10(7) to 2.1x10(7) N-s, and 3550 to 6200 m/s, respectively. Maximum available thrusting times for the arcjet propelled spacecraft launched on the DELTA II 6920 vehicle range from approximately 528 hours for the 6-engine 10 kW hydrazine system to 2328 hours for the single-engine 5 kW system. Maximum total impulse values and maximum delta-v's range from 2.2x10(6) to 3.6x10(6) N-s, and approximately 662 to 1072 m/s, respectively.

Economic Impact Forecast System (EIFS). Version 2.0. Users Manual. Supplement II. European Economic Impact Forecast System (EEIFS), Phase 1, (FRG/EIFS Pilot Model).

DTIC Science & Technology

1982-05-01

Chmpip. tL : Construction engineering Research Laboratory ; available from NTIS. 1982. 71 p. (Technical report / Construction Engineering Researsh ...AD-Al17 661 CONSTRUCTION ENGINEERING RESEARCH LAB (ARMY) CHAMPAIGN IL F/G 5/3 ECONOMIC IMPACT FORECAST SYSTEM (EIFS). VERSION 2.0. USERS MANU--ETC(u...CONSTRUCTION ENGINEERING RESEARCH LABORATORY 4A762720A896-C-004 P.O. BOX 4005, CHAMPAIGN, IL 61820 I. CONTROLLING OFFICE NAME AND ADDRESS It. REPORT

The Effect of Rotor Cruise Tip Speed, Engine Technology and Engine/Drive System RPM on the NASA Large Civil Tiltrotor (LCTR2) Size and Performance

NASA Technical Reports Server (NTRS)

Robuck, Mark; Wilkerson, Joseph; Maciolek, Robert; Vonderwell, Dan

2012-01-01

A multi-year study was conducted under NASA NNA06BC41C Task Order 10 and NASA NNA09DA56C task orders 2, 4, and 5 to identify the most promising propulsion system concepts that enable rotor cruise tip speeds down to 54% of the hover tip speed for a civil tiltrotor aircraft. Combinations of engine RPM reduction and 2-speed drive systems were evaluated. Three levels of engine and the drive system advanced technology were assessed; 2015, 2025 and 2035. Propulsion and drive system configurations that resulted in minimum vehicle gross weight were identified. Design variables included engine speed reduction, drive system speed reduction, technology, and rotor cruise propulsion efficiency. The NASA Large Civil Tiltrotor, LCTR, aircraft served as the base vehicle concept for this study and was resized for over thirty combinations of operating cruise RPM and technology level, quantifying LCTR2 Gross Weight, size, and mission fuel. Additional studies show design sensitivity to other mission ranges and design airspeeds, with corresponding relative estimated operational cost. The lightest vehicle gross weight solution consistently came from rotor cruise tip speeds between 422 fps and 500 fps. Nearly equivalent results were achieved with operating at reduced engine RPM with a single-speed drive system or with a two-speed drive system and 100% engine RPM. Projected performance for a 2025 engine technology provided improved fuel flow over a wide range of operating speeds relative to the 2015 technology, but increased engine weight nullified the improved fuel flow resulting in increased aircraft gross weights. The 2035 engine technology provided further fuel flow reduction and 25% lower engine weight, and the 2035 drive system technology provided a 12% reduction in drive system weight. In combination, the 2035 technologies reduced aircraft takeoff gross weight by 14% relative to the 2015 technologies.

Melt-infiltrated Sic Composites for Gas Turbine Engine Applications

NASA Technical Reports Server (NTRS)

Morscher, Gregory N.; Pujar, Vijay V.

2004-01-01

SiC-SiC ceramic matrix composites (CMCs) manufactured by the slurry -cast melt-infiltration (MI) process are leading candidates for many hot-section turbine engine components. A collaborative program between Goodrich Corporation and NASA-Glenn Research Center is aimed at determining and optimizing woven SiC/SiC CMC performance and reliability. A variety of composites with different fiber types, interphases and matrix compositions have been fabricated and evaluated. Particular focus of this program is on the development of interphase systems that will result in improved intermediate temperature stressed-oxidation properties of this composite system. The effect of the different composite variations on composite properties is discussed and, where appropriate, comparisons made to properties that have been generated under NASA's Ultra Efficient Engine Technology (UEET) Program.

23 CFR 940.11 - Project implementation.

Code of Federal Regulations, 2011 CFR

2011-04-01

... projects funded with highway trust funds shall be based on a systems engineering analysis. (b) The analysis should be on a scale commensurate with the project scope. (c) The systems engineering analysis shall... definitions; (4) Analysis of alternative system configurations and technology options to meet requirements; (5...

23 CFR 940.11 - Project implementation.

Code of Federal Regulations, 2014 CFR

2014-04-01

... projects funded with highway trust funds shall be based on a systems engineering analysis. (b) The analysis should be on a scale commensurate with the project scope. (c) The systems engineering analysis shall... definitions; (4) Analysis of alternative system configurations and technology options to meet requirements; (5...

23 CFR 940.11 - Project implementation.

Code of Federal Regulations, 2012 CFR

2012-04-01

... projects funded with highway trust funds shall be based on a systems engineering analysis. (b) The analysis should be on a scale commensurate with the project scope. (c) The systems engineering analysis shall... definitions; (4) Analysis of alternative system configurations and technology options to meet requirements; (5...

23 CFR 940.11 - Project implementation.

Code of Federal Regulations, 2013 CFR

2013-04-01

... projects funded with highway trust funds shall be based on a systems engineering analysis. (b) The analysis should be on a scale commensurate with the project scope. (c) The systems engineering analysis shall... definitions; (4) Analysis of alternative system configurations and technology options to meet requirements; (5...

23 CFR 940.11 - Project implementation.

Code of Federal Regulations, 2010 CFR

2010-04-01

... projects funded with highway trust funds shall be based on a systems engineering analysis. (b) The analysis should be on a scale commensurate with the project scope. (c) The systems engineering analysis shall... definitions; (4) Analysis of alternative system configurations and technology options to meet requirements; (5...

STV engine design considerations

NASA Technical Reports Server (NTRS)

1991-01-01

The topics covered include the following: (1) engine design criteria and issues; (2) design requirements for man rating; (3) test requirements for man rating; (4) design requirements for space basing; (5) engine operation requirements; (6) health monitoring; (7) lunar transfer vehicle (LTV) feed system; (8) lunar excursion vehicle (LEV) propellant system; (9) area ratio gimbal angle limits; (10) reaction control system; and (11) engine configuration and characteristics. This document is presented in viewgraph form.

Effects of Transient Power Extraction on an Integrated Hardware-in-the-Loop Aircraft/Propulsion/Power System

DTIC Science & Technology

2008-11-01

Simulations of an engine and its Full Authority Digital Engine Control ( FADEC ), along with a 6 degree-of-freedom (6DoF) airframe dynamics model and...as needed. In its current configuration, the generic turbine engine model’s FADEC is included in the same simulation and runs primarily on 2 a...back to the engine. As mentioned previously, the FADEC and engine are combined into one simulation and are collectively referred to as “the engine

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

Innovative technologies in course Electrical engineering and electronics

NASA Astrophysics Data System (ADS)

Kuznetsov, E. V.; Kiselev, V. I.; Kulikova, E. A.

2017-11-01

Department of Electrical Engineering and Nondestructive Testing, NRU “MPEI”, has been working on development Electronic Learning Resources (ELRs) in course Electrical Engineering and Electronics for several years. This work have been focused on education intensification and effectiveness while training bachelors in nonelectrical specializations including students from Thermal and Atomic Power Engineering Institute. The developed ELRs are united in a tutorial module consisting of three parts (Electrical Circuits, Electrical Machines, Basics of Electronics): electronic textbook and workbook (ETW); virtual laboratory sessions (VLS); training sessions (ETS); personal tasks (PT); testing system that contains electronic tests in all course subjects and built-in verification of a student’s work results in ETW, VLS, ETS, PT. The report presents samples of different ELRs in html format and MathCAD, MatLAB Simulink applications, copyrighted programs in Java2, Delphi, VB6, C++. The report also contains the experience description, advantages and disadvantages of the new technologies. It is mentioned that ELRs provide new opportunities in course studying.

Space and Missile Systems Center Standard: Test Requirements for Launch, Upper-Stage and Space Vehicles

DTIC Science & Technology

2014-09-05

adiabatic expansion of a perfect gas ; b. Contains a gas or liquid that would endanger personnel or equipment or create a mis- hap if released; or c...Guidelines for Liquid Rocket Engines 31. TOR-2013(3213)-6 Acoustic Testing on Production Space Vehicle (The Value of the Test and Deletion...materials used in space vehicles, interstages, payload adapters, payload fairings, motor cases, nozzles , propellant tanks, and over-wrapped pressure vessels

Technical and Regulatory Guidance for Surfactant/Cosolvent Flushing of DNAPL Source Zones

DTIC Science & Technology

2003-04-01

industry and public institutions who contributed to this document: George J . Hall – ITRC Program Advisor Doug Beal – BEM Systems Susan Gawarecki...these tests are also used during the design process to estimate hydraulic properties based on empirical correlations ( Vukovic and Soro, 1992). Samples...Journal of Environmental Engineering, 124(6): 498–503. Bear, J . 1972. Flow Through Porous Media. Elsevier, N.Y. Bedient, P.B., A.W. Holder, C.G

Airborne Navigation Remote Map Reader Evaluation.

DTIC Science & Technology

1986-03-01

EVALUATION ( James C. Byrd Intergrated Controls/Displays Branch SAvionics Systems Division Directorate of Avionics Engineering SMarch 1986 Final Report...Resolution 15 3.2 Accuracy 15 3.3 Symbology 15 3.4 Video Standard 18 3.5 Simulator Control Box 18 3.6 Software 18 3.7 Display Performance 21 3.8 Reliability 24...can be selected depending on the detail required and will automatically be presented at his present position. .The French RMR uses a Flying Spot Scanner

An Intelligent Tutoring System for Introductory C Language Course.

ERIC Educational Resources Information Center

Song, J. S.; And Others

1997-01-01

This discussion of intelligent tutoring systems (ITS) focuses on a description of C-Tutor, a knowledge-based ITS for novice C programmers. The program analyzer, which is a compound of a reverse engineering system and a didactic system, is explained, and implementation and evaluation is discussed. (LRW)

Academic satisfaction among Latino/a and White men and women engineering students.

PubMed

Flores, Lisa Y; Navarro, Rachel L; Lee, Hang Shim; Addae, Dorothy A; Gonzalez, Rebecca; Luna, Laura L; Jacquez, Ricardo; Cooper, Sonya; Mitchell, Martha

2014-01-01

The current study tests a model of academic satisfaction in engineering based on Lent, Brown, and Hackett's (1994, 2000) social cognitive career theory among a sample of 527 engineering majors attending a Hispanic serving institution. The findings indicated that (a) an alternative bidirectional model fit the data for the full sample; (b) all of the hypothesized relations were significant for the full sample, except the path from engineering interests to goals; (c) social cognitive career theory predictors accounted for a significant amount of variance in engineering goals (26.6%) and academic satisfaction (45.1%); and (d) the model parameters did not vary across men and women or across Latino/a and White engineering undergraduate students. Implications for research and practice are discussed in relation to persistence in engineering among women and Latinos/as. (c) 2014 APA, all rights reserved.

Engineering Graphene Mechanical Systems

DTIC Science & Technology

2012-07-05

strength material. On the basis of chemical /defect manipulation and recrystallization this technique allows wide-range engineering of mechanical... Engineering Graphene Mechanical Systems Maxim K. Zalalutdinov,† Jeremy T. Robinson,*,† Chad E. Junkermeier,‡ James C. Culbertson, Thomas L. Reinecke...Information ABSTRACT: We report a method to introduce direct bonding between graphene platelets that enables the transformation of a multilayer chemically

14 CFR Appendix K to Part 25 - Extended Operations (ETOPS)

Code of Federal Regulations, 2014 CFR

2014-01-01

... that is time-limited. K25.1.4Propulsion systems. (a) Fuel system design. Fuel necessary to complete an... does not apply to airplanes with a required flight engineer. (b) APU design. If an APU is needed to..., whichever is lower, and run for the remainder of any flight . (c) Engine oil tank design. The engine oil...

14 CFR Appendix K to Part 25 - Extended Operations (ETOPS)

Code of Federal Regulations, 2010 CFR

2010-01-01

... that is time-limited. K25.1.4Propulsion systems. (a) Fuel system design. Fuel necessary to complete an... does not apply to airplanes with a required flight engineer. (b) APU design. If an APU is needed to..., whichever is lower, and run for the remainder of any flight . (c) Engine oil tank design. The engine oil...

14 CFR Appendix K to Part 25 - Extended Operations (ETOPS)

Code of Federal Regulations, 2013 CFR

2013-01-01

... that is time-limited. K25.1.4Propulsion systems. (a) Fuel system design. Fuel necessary to complete an... does not apply to airplanes with a required flight engineer. (b) APU design. If an APU is needed to..., whichever is lower, and run for the remainder of any flight . (c) Engine oil tank design. The engine oil...

14 CFR Appendix K to Part 25 - Extended Operations (ETOPS)

Code of Federal Regulations, 2012 CFR

2012-01-01

... that is time-limited. K25.1.4Propulsion systems. (a) Fuel system design. Fuel necessary to complete an... does not apply to airplanes with a required flight engineer. (b) APU design. If an APU is needed to..., whichever is lower, and run for the remainder of any flight . (c) Engine oil tank design. The engine oil...

46 CFR 58.10-10 - Diesel engine installations.

Code of Federal Regulations, 2011 CFR

2011-10-01

... 46 Shipping 2 2011-10-01 2011-10-01 false Diesel engine installations. 58.10-10 Section 58.10-10... MACHINERY AND RELATED SYSTEMS Internal Combustion Engine Installations § 58.10-10 Diesel engine installations. (a) The requirements of § 58.10-5 (a), (c), and (d) shall apply to diesel engine installations...

46 CFR 58.10-10 - Diesel engine installations.

Code of Federal Regulations, 2010 CFR

2010-10-01

... 46 Shipping 2 2010-10-01 2010-10-01 false Diesel engine installations. 58.10-10 Section 58.10-10... MACHINERY AND RELATED SYSTEMS Internal Combustion Engine Installations § 58.10-10 Diesel engine installations. (a) The requirements of § 58.10-5 (a), (c), and (d) shall apply to diesel engine installations...

46 CFR 58.10-10 - Diesel engine installations.

Code of Federal Regulations, 2014 CFR

2014-10-01

... 46 Shipping 2 2014-10-01 2014-10-01 false Diesel engine installations. 58.10-10 Section 58.10-10... MACHINERY AND RELATED SYSTEMS Internal Combustion Engine Installations § 58.10-10 Diesel engine installations. (a) The requirements of § 58.10-5 (a), (c), and (d) shall apply to diesel engine installations...

46 CFR 58.10-10 - Diesel engine installations.

Code of Federal Regulations, 2012 CFR

2012-10-01

... 46 Shipping 2 2012-10-01 2012-10-01 false Diesel engine installations. 58.10-10 Section 58.10-10... MACHINERY AND RELATED SYSTEMS Internal Combustion Engine Installations § 58.10-10 Diesel engine installations. (a) The requirements of § 58.10-5 (a), (c), and (d) shall apply to diesel engine installations...

Effects of micro-water on decomposition of the environment-friendly insulating medium C5F10O

NASA Astrophysics Data System (ADS)

Xiao, Song; Li, Yi; Zhang, Xiaoxing; Tian, Shuangshuang; Deng, Zaitao; Tang, Ju

2017-06-01

SF6 is widely used in all kinds of high-voltage electrical equipment because of its excellent insulation and arc-extinguishing performance. However, this compound leads to serious greenhouse effect, which harms the environment. Many research institutions are now actively in search of SF6 alternative gas. C5F10O has attracted much attention as an alternative gas with low global warming potential (GWP) and excellent dielectric strength. In this paper, we analyzed the possible decomposition paths of C5F10O under micro-water environment through density functional theory. We also evaluated the ionization parameters and toxicity of the decomposition products. The results show that OH• and H• produced by H2O exhibited a catalytic effect on the decomposition of C5F10O. CF4, C2F6, C3F6, C3F8, C4F10, C5F12, C6F14, C3F7COH, C3F7OH, CF3COH, C3F7H, and CF3OH were produced in the micro-water environment. Based on molecular configuration calculation, the ionization parameters of these products were inferior to perfluorocarbons, such as C3F8, leading to reduced insulation performance of the system. Moreover, CF2O and HF are hazardous to human health and equipment safety. Results will provide a basis for further study of the insulation characteristic of the C5F10O gas mixture under micro-water condition to guide the formulation of their relevant international standards prior to engineering applications.

EOD and Engineers Close the Gap

DTIC Science & Technology

2005-03-01

Engineers ’ Close the Gap ’ 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e. TASK NUMBER 5f. WORK UNIT...action to accomplish missions effectively in the COE. However, tomorrow’s construct will not only “ close the gap ” between EOD and engineers, it will close

Engineering of new-to-nature halogenated indigo precursors in plants.

PubMed

Fräbel, Sabine; Wagner, Bastian; Krischke, Markus; Schmidts, Volker; Thiele, Christina M; Staniek, Agata; Warzecha, Heribert

2018-03-01

Plants are versatile chemists producing a tremendous variety of specialized compounds. Here, we describe the engineering of entirely novel metabolic pathways in planta enabling generation of halogenated indigo precursors as non-natural plant products. Indican (indolyl-β-D-glucopyranoside) is a secondary metabolite characteristic of a number of dyers plants. Its deglucosylation and subsequent oxidative dimerization leads to the blue dye, indigo. Halogenated indican derivatives are commonly used as detection reagents in histochemical and molecular biology applications; their production, however, relies largely on chemical synthesis. To attain the de novo biosynthesis in a plant-based system devoid of indican, we employed a sequence of enzymes from diverse sources, including three microbial tryptophan halogenases substituting the amino acid at either C5, C6, or C7 of the indole moiety. Subsequent processing of the halotryptophan by bacterial tryptophanase TnaA in concert with a mutant of the human cytochrome P450 monooxygenase 2A6 and glycosylation of the resulting indoxyl derivatives by an endogenous tobacco glucosyltransferase yielded corresponding haloindican variants in transiently transformed Nicotiana benthamiana plants. Accumulation levels were highest when the 5-halogenase PyrH was utilized, reaching 0.93 ± 0.089 mg/g dry weight of 5-chloroindican. The identity of the latter was unambiguously confirmed by NMR analysis. Moreover, our combinatorial approach, facilitated by the modular assembly capabilities of the GoldenBraid cloning system and inspired by the unique compartmentation of plant cells, afforded testing a number of alternative subcellular localizations for pathway design. In consequence, chloroplasts were validated as functional biosynthetic venues for haloindican, with the requisite reducing augmentation of the halogenases as well as the cytochrome P450 monooxygenase fulfilled by catalytic systems native to the organelle. Thus, our study puts forward a viable alternative production platform for halogenated fine chemicals, eschewing reliance on fossil fuel resources and toxic chemicals. We further contend that in planta generation of halogenated indigoid precursors previously unknown to nature offers an extended view on and, indeed, pushes forward the established frontiers of biosynthetic capacity of plants. Copyright © 2018 International Metabolic Engineering Society. Published by Elsevier Inc. All rights reserved.

Multilayer Network Modeling of Change Propagation for Engineering Change Management

DTIC Science & Technology

2010-06-01

generalization, rather than statistical generalization. As such, a single case can be used to advance a theory, similarly to how scientific experiments are...ation 411 PNC C ac 2 C PC Not Predicted & Propagated wI Comunication ENot Predicted & Not Propagated w ConPnCcation 04 PPC 5CPredicted & Propagated w...Engineering Management 48(3): 292-306. 5. Clark, J. and Holton, D.A. (2005). A First Look at Graph Theory. World Scientific . 6. Clarkson P.J., Simons, C

Experimental investigation of a thermoacoustic-Stirling refrigerator driven by a thermoacoustic-Stirling heat engine.

PubMed

Luo, E C; Dai, W; Zhang, Y; Ling, H

2006-12-22

In this paper, a thermally-driven thermoacoustic refrigerator system without any moving part is reported. This refrigeration system consists of a thermoacoustic-Stirling heat engine and a thermoacoustic-Stirling refrigerator; that is, the former is the driving source for the latter. Both the subsystems are designed to operate on traveling-wave mode. In the experiment, it was found that the DC-flows had significant negative effect on the heat engine and the refrigerator. To suppress these DC-flows, two flexible membranes were inserted into the two subsystems and worked very well. Then extensive experiments were made to test the influence of different parameters on refrigeration performance of the whole system. The system has so far achieved a no-load temperature of -65 degrees C, a cooling capacity of about 270 W at -20 degrees C and 405 W at 0 degrees C; in fact, the result showed a good prospect of the refrigeration system in room-temperature cooling such as food refrigeration and air-conditioning.

46 CFR 27.205 - What are the requirements for internal communication systems on towing vessels?

Code of Federal Regulations, 2010 CFR

2010-10-01

... systems on towing vessels? 27.205 Section 27.205 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY... fitted with a communication system between the engine room and the operating station that— (1) Consists... required to have internal communication systems. (c) When the operating-station's engine controls and the...

Engineering Irisin for Understanding Its Benefits to Obesity

DTIC Science & Technology

2016-08-01

1 AWARD NUMBER: W81XWH-15-1-0196 TITLE: Engineering Irisin for Understanding Its Benefits to Obesity PRINCIPAL INVESTIGATOR: Yousong Ding...Engineering Irisin for Understanding Its Benefits to Obesity 5a. CONTRACT NUMBER 5b. GRANT NUMBER W81XWH-15-1-0196 5c. PROGRAM ELEMENT NUMBER 6...increasing energy expenditure. The overall objective of the proposed project is to engineer irisin for uncovering its signaling in obesity , with

Improved Real-Time Monitoring Using Multiple Expert Systems

NASA Technical Reports Server (NTRS)

Schwuttke, Ursula M.; Angelino, Robert; Quan, Alan G.; Veregge, John; Childs, Cynthia

1993-01-01

Monitor/Analyzer of Real-Time Voyager Engineering Link (MARVEL) computer program implements combination of techniques of both conventional automation and artificial intelligence to improve monitoring of complicated engineering system. Designed to support ground-based operations of Voyager spacecraft, also adapted to other systems. Enables more-accurate monitoring and analysis of telemetry, enhances productivity of monitoring personnel, reduces required number of such personnel by performing routine monitoring tasks, and helps ensure consistency in face of turnover of personnel. Programmed in C language and includes commercial expert-system software shell also written in C.

Film Cooled Recession of SiC/SiC Ceramic Matrix Composites: Test Development, CFD Modeling and Experimental Observations

NASA Technical Reports Server (NTRS)

Zhu, Dongming; Sakowski, Barbara A.; Fisher, Caleb

2014-01-01

SiCSiC ceramic matrix composites (CMCs) systems will play a crucial role in next generation turbine engines for hot-section component applications because of their ability to significantly increase engine operating temperatures, reduce engine weight and cooling requirements. However, the environmental stability of Si-based ceramics in high pressure, high velocity turbine engine combustion environment is of major concern. The water vapor containing combustion gas leads to accelerated oxidation and corrosion of the SiC based ceramics due to the water vapor reactions with silica (SiO2) scales forming non-protective volatile hydroxide species, resulting in recession of the ceramic components. Although environmental barrier coatings are being developed to help protect the CMC components, there is a need to better understand the fundamental recession behavior of in more realistic cooled engine component environments.In this paper, we describe a comprehensive film cooled high pressure burner rig based testing approach, by using standardized film cooled SiCSiC disc test specimen configurations. The SiCSiC specimens were designed for implementing the burner rig testing in turbine engine relevant combustion environments, obtaining generic film cooled recession rate data under the combustion water vapor conditions, and helping developing the Computational Fluid Dynamics (CFD) film cooled models and performing model validation. Factors affecting the film cooled recession such as temperature, water vapor concentration, combustion gas velocity, and pressure are particularly investigated and modeled, and compared with impingement cooling only recession data in similar combustion flow environments. The experimental and modeling work will help predict the SiCSiC CMC recession behavior, and developing durable CMC systems in complex turbine engine operating conditions.

Post-exposure treatment of VX poisoned guinea pigs with the engineered phosphotriesterase mutant C23: a proof-of-concept study.

PubMed

Worek, Franz; Seeger, Thomas; Reiter, Georg; Goldsmith, Moshe; Ashani, Yacov; Leader, Haim; Sussman, Joel L; Aggarwal, Nidhi; Thiermann, Horst; Tawfik, Dan S

2014-11-18

The highly toxic organophosphorus (OP) nerve agent VX is characterized by a remarkable biological persistence which limits the effectiveness of standard treatment with atropine and oximes. Existing OP hydrolyzing enzymes show low activity against VX and hydrolyze preferentially the less toxic P(+)-VX enantiomer. Recently, a phosphotriesterase (PTE) mutant, C23, was engineered towards the hydrolysis of the toxic P(-) isomers of VX and other V-type agents with relatively high in vitro catalytic efficiency (kcat/KM=5×10(6)M(-1)min(-1)). To investigate the suitability of the PTE mutant C23 as a catalytic scavenger, an in vivo guinea pig model was established to determine the efficacy of post-exposure treatment with C23 alone against VX intoxication. Injection of C23 (5mgkg(-1) i.v.) 5min after s.c. challenge with VX (∼2LD50) prevented systemic toxicity. A lower C23 dose (2mgkg(-1)) reduced systemic toxicity and prevented mortality. Delayed treatment (i.e., 15min post VX) with 5mgkg(-1) C23 resulted in survival of all animals and only in moderate systemic toxicity. Although C23 did not prevent inhibition of erythrocyte acetylcholinesterase (AChE) activity, it partially preserved brain AChE activity. C23 therapy resulted in a rapid decrease of racemic VX blood concentration which was mainly due to the rate of degradation of the toxic P(-)-VX enantiomer that correlates with the C23 blood levels and its kcat/KM value. Although performed under anesthesia, this proof-of-concept study demonstrated for the first time the ability of a catalytic bioscavenger to prevent systemic VX toxicity when given alone as a single post-exposure treatment, and enables an initial assessment of a time window for this approach. In conclusion, the PTE mutant C23 may be considered as a promising starting point for the development of highly effective catalytic bioscavengers for post-exposure treatment of V-agents intoxication. Copyright © 2014 Elsevier Ireland Ltd. All rights reserved.

Boiler Control Systems Oxygen Trim Systems Manual.

DTIC Science & Technology

1983-02-01

F/ G 5/9 N EhhhhhhhmonsoI smhhhEmhhhhhh smhhhhhhhhhhh Ehh0h0010I-E1E FEmhhhhEmmhhhhhhI LL+4 -.Lm(m~mkl~~d - - ." " - , -, - - ’ - °. ,,_ ". . . b...PAGIES Ik NNITrG A9NC ORS7 Ir- e, 0) 1 SECURITY CLASS. (of K4* MPMf) Office, g &, Washington, DC 20360 Unclassified Naval Facilities Engineering Coand...1NPLJT SoNAI . S141NAL. f* FIR4GIb[CTIQNAL SCkEMIATC DICIAN A’ RLfL FOSITIOWINC- SY<STEM1 (FUUMArIC) PRESSURE PROC.ESS PIIN42 ATI 6 C~rEMASTERO F13UE

Vehicle Systems Engineering and Integration Activities - Phase 5

DTIC Science & Technology

2012-08-31

and Engineering. Its objective is to fundamentally change the capabilities for the design, adaptation, and manufacture of defense systems. Recent...package. The standard RISE package includes an upgraded propulsion system ( turbocharged engine and new transmission), greatly improved driver...original M113A3 and M730A2 vehicles is the turbocharged 275 hp 6V53T engine from Detroit Diesel Corporation. Replacing the earlier 212 hp M113A2

Ammonia Generation and Utilization in a Passive SCR (TWC+SCR) System on Lean Gasoline Engine

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

Prikhodko, Vitaly Y.; James E. Parks, II; Pihl, Josh A.

Lean gasoline engines offer greater fuel economy than the common stoichiometric gasoline engine, but the current three way catalyst (TWC) on stoichiometric engines is unable to control nitrogen oxide (NOX) emissions in oxidizing exhaust. For these lean gasoline engines, lean NOX emission control is required to meet existing Tier 2 and upcoming Tier 3 emission regulations set by the U.S. Environmental Protection Agency (EPA). While urea-based selective catalytic reduction (SCR) has proven effective in controlling NOX from diesel engines, the urea storage and delivery components can add significant size and cost. As such, onboard NH 3 production via a passivemore » SCR approach is of interest. In a passive SCR system, NH 3 is generated over a close-coupled TWC during periodic slightly rich engine operation and subsequently stored on an underfloor SCR catalyst. Upon switching to lean operation, NOX passes through the TWC and is reduced by the stored NH 3 on the SCR catalyst. In this work, a passive SCR system was evaluated on a 2.0-liter BMW lean burn gasoline direct injection engine to assess NH 3 generation over a Pd-only TWC and utilization over a Cu-based SCR catalyst. System NOX reduction efficiency and fuel efficiency improvement compared to stoichiometric engine operation were measured. A feedback control strategy based on cumulative NH 3 produced by the TWC during rich operation and NOX emissions during lean operation was implemented on the engine to control lean/rich cycle timing. At an SCR average inlet temperature of 350 °C, an NH 3:NOX ratio of 1.15:1 (achieved through longer rich cycle timing) resulted in 99.7 % NOX conversion. Increasing NH 3 generation further resulted in even higher NOX conversion; however, tailpipe NH 3 emissions resulted. At higher underfloor temperatures, NH 3 oxidation over the SCR limited NH 3 availability for NOX reduction. At the engine conditions studied, greater than 99 % NOX conversion was achieved with passive SCR while delivering fuel efficiency benefits ranging between 6-11 % compared with stoichiometric operation.« less

Ammonia Generation and Utilization in a Passive SCR (TWC+SCR) System on Lean Gasoline Engine

DOE PAGES

Prikhodko, Vitaly Y.; James E. Parks, II; Pihl, Josh A.; ...

2016-04-05

Lean gasoline engines offer greater fuel economy than the common stoichiometric gasoline engine, but the current three way catalyst (TWC) on stoichiometric engines is unable to control nitrogen oxide (NOX) emissions in oxidizing exhaust. For these lean gasoline engines, lean NOX emission control is required to meet existing Tier 2 and upcoming Tier 3 emission regulations set by the U.S. Environmental Protection Agency (EPA). While urea-based selective catalytic reduction (SCR) has proven effective in controlling NOX from diesel engines, the urea storage and delivery components can add significant size and cost. As such, onboard NH 3 production via a passivemore » SCR approach is of interest. In a passive SCR system, NH 3 is generated over a close-coupled TWC during periodic slightly rich engine operation and subsequently stored on an underfloor SCR catalyst. Upon switching to lean operation, NOX passes through the TWC and is reduced by the stored NH 3 on the SCR catalyst. In this work, a passive SCR system was evaluated on a 2.0-liter BMW lean burn gasoline direct injection engine to assess NH 3 generation over a Pd-only TWC and utilization over a Cu-based SCR catalyst. System NOX reduction efficiency and fuel efficiency improvement compared to stoichiometric engine operation were measured. A feedback control strategy based on cumulative NH 3 produced by the TWC during rich operation and NOX emissions during lean operation was implemented on the engine to control lean/rich cycle timing. At an SCR average inlet temperature of 350 °C, an NH 3:NOX ratio of 1.15:1 (achieved through longer rich cycle timing) resulted in 99.7 % NOX conversion. Increasing NH 3 generation further resulted in even higher NOX conversion; however, tailpipe NH 3 emissions resulted. At higher underfloor temperatures, NH 3 oxidation over the SCR limited NH 3 availability for NOX reduction. At the engine conditions studied, greater than 99 % NOX conversion was achieved with passive SCR while delivering fuel efficiency benefits ranging between 6-11 % compared with stoichiometric operation.« less

BCAT-C1 Session in the JPM

NASA Image and Video Library

2012-08-08

ISS032-E-014593 (6 Aug. 2012) --- NASA astronaut Joe Acaba, Expedition 32 flight engineer, conducts a session with the Binary Colloidal Alloy Test-6 (BCAT-6) experiment in the Kibo laboratory of the International Space Station.

Simulating Operation of a Large Turbofan Engine

NASA Technical Reports Server (NTRS)

Litt, Jonathan S.; Frederick, Dean K.; DeCastro, Jonathan

2008-01-01

The Commercial Modular Aero- Propulsion System Simulation (C-MAPSS) is a computer program for simulating transient operation of a commercial turbofan engine that can generate as much as 90,000 lb (.0.4 MN) of thrust. It includes a power-management system that enables simulation of open- or closed-loop engine operation over a wide range of thrust levels throughout the full range of flight conditions. C-MAPSS provides the user with a set of tools for performing open- and closed-loop transient simulations and comparison of linear and non-linear models throughout its operating envelope, in an easy-to-use graphical environment.

40 CFR Appendix I to Part 92 - Emission Related Locomotive and Engine Parameters and Specifications

Code of Federal Regulations, 2010 CFR

2010-07-01

.... b. Idle mixture. c. Transient enrichment system calibration. d. Starting enrichment system... shutoff system calibration. d. Starting enrichment system calibration. e. Transient enrichment system... parameters and calibrations. b. Transient enrichment system calibration. c. Air-fuel flow calibration. d...

USAF Evaluation of an Automated Adaptive Flight Training System

DTIC Science & Technology

1975-10-01

system. C. What is the most effective wav to utilize the system in ^jierational training’ Student opinion for this question JS equally divided...None Utility hydraulic failure Flap failure left engine failure Right engine failure Stah 2 aug failure No g\\ ro approach procedure, no MIDI

Signal-chip microcomputer control system for a diffraction grating ruling engine

NASA Astrophysics Data System (ADS)

Wang, Xiaolin; Zhang, Yuhua; Yang, Houmin; Guo, Du

1998-08-01

A control system with a chip of 8031 single-chip microcomputer as its nucleus for a diffraction grating ruling engine has been developed, its hardware and software are presented in this paper. A series of techniques such as program-controlled amplifier and interference fringes subdivision as well as motor velocity step governing are adopted to improve the control accuracy. With this control system, 8 kinds of gratings of different spacings can be ruled, the positioning precision of the diffraction grating ruling engine (sigma) equals 3.6 nm, and the maximum positioning error is less than 14.6 nm.

Small Engines Care, Operation, Maintenance and Repair. Volume II.

ERIC Educational Resources Information Center

Turner, J. Howard

Developed by teacher educators and agricultural engineers, this teacher and student reference is for use in a course in small engine operation and maintenance. Content includes: (1) Principles of Good Workmanship, (2) Repairing Starters, (3) Maintaining and Repairing Ignition Systems, (4) Repairing Fuel Systems, (5) Repairing Governors, (6)…

Application of powder metallurgy technique to produce improved bearing elements for cryogenic aerospace engine turbopumps

NASA Technical Reports Server (NTRS)

Moxson, V. S.; Moracz, D. J.; Bhat, B. N.; Dolan, F. J.; Thom, R.

1987-01-01

Traditionally, vacuum melted 440C stainless steel is used for high performance bearings for aerospace cryogenic systems where corrosion due to condensation is a major concern. For the Space Shuttle Main Engine (SSME), however, 440C performance in the high-pressure turbopumps has been marginal. A basic assumption of this study was that powder metallurgy, rather than cast/wrought, processing would provide the finest, most homogeneous bearing alloy structure. Preliminary testing of P/M alloys (hardness, corrosion resistance, wear resistance, fatigue resistance, and fracture toughness) was used to 'de-select' alloys which did perform as well as baseline 440C. Five out of eleven candidate materials (14-4/6V, X-405, MRC-2001, T-440V, and D-5) based on preliminary screening were selected for the actual rolling-sliding five-ball testing. The results of this test were compared with high-performance vacuum-melted M50 bearing steel. The results of the testing indicated outstanding performance of two P/M alloys, X-405 and MRC-2001, which eventually will be further evaluated by full-scale bearing testing.

Aerospace Ceramic Materials: Thermal, Environmental Barrier Coatings and SiC/SiC Ceramic Matrix Composites for Turbine Engine Applications

NASA Technical Reports Server (NTRS)

Zhu, Dongming

2018-01-01

Ceramic materials play increasingly important roles in aerospace applications because ceramics have unique properties, including high temperature capability, high stiffness and strengths, excellent oxidation and corrosion resistance. Ceramic materials also generally have lower densities as compared to metallic materials, making them excellent candidates for light-weight hot-section components of aircraft turbine engines, rocket exhaust nozzles, and thermal protection systems for space vehicles when they are being used for high-temperature and ultra-high temperature ceramics applications. Ceramic matrix composites (CMCs), including non-oxide and oxide CMCs, are also recently being incorporated in gas turbine engines for high pressure and high temperature section components and exhaust nozzles. However, the complexity and variability of aerospace ceramic processing methods, compositions and microstructures, the relatively low fracture toughness of the ceramic materials, still remain the challenging factors for ceramic component design, validation, life prediction, and thus broader applications. This ceramic material section paper presents an overview of aerospace ceramic materials and their characteristics. A particular emphasis has been placed on high technology level (TRL) enabling ceramic systems, that is, turbine engine thermal and environmental barrier coating systems and non-oxide type SiC/SiC CMCs. The current status and future trend of thermal and environmental barrier coatings and SiC/SiC CMC development and applications are described.

48 CFR 52.232-10 - Payments Under Fixed-Price Architect-Engineer Contracts.

Code of Federal Regulations, 2012 CFR

2012-10-01

... Architect-Engineer Contracts. 52.232-10 Section 52.232-10 Federal Acquisition Regulations System FEDERAL... Provisions and Clauses 52.232-10 Payments Under Fixed-Price Architect-Engineer Contracts. As prescribed in 32.111(c)(1), insert the following clause: Payments Under Fixed-Price Architect-Engineer Contracts (APR...

48 CFR 52.232-10 - Payments Under Fixed-Price Architect-Engineer Contracts.

Code of Federal Regulations, 2014 CFR

2014-10-01

... Architect-Engineer Contracts. 52.232-10 Section 52.232-10 Federal Acquisition Regulations System FEDERAL... Provisions and Clauses 52.232-10 Payments Under Fixed-Price Architect-Engineer Contracts. As prescribed in 32.111(c)(1), insert the following clause: Payments Under Fixed-Price Architect-Engineer Contracts (APR...

48 CFR 52.232-10 - Payments Under Fixed-Price Architect-Engineer Contracts.

Code of Federal Regulations, 2010 CFR

2010-10-01

... Architect-Engineer Contracts. 52.232-10 Section 52.232-10 Federal Acquisition Regulations System FEDERAL... Provisions and Clauses 52.232-10 Payments Under Fixed-Price Architect-Engineer Contracts. As prescribed in 32.111(c)(1), insert the following clause: Payments Under Fixed-Price Architect-Engineer Contracts (APR...

48 CFR 52.232-10 - Payments Under Fixed-Price Architect-Engineer Contracts.

Code of Federal Regulations, 2013 CFR

2013-10-01

... Architect-Engineer Contracts. 52.232-10 Section 52.232-10 Federal Acquisition Regulations System FEDERAL... Provisions and Clauses 52.232-10 Payments Under Fixed-Price Architect-Engineer Contracts. As prescribed in 32.111(c)(1), insert the following clause: Payments Under Fixed-Price Architect-Engineer Contracts (APR...

48 CFR 52.232-10 - Payments Under Fixed-Price Architect-Engineer Contracts.

Code of Federal Regulations, 2011 CFR

2011-10-01

... Architect-Engineer Contracts. 52.232-10 Section 52.232-10 Federal Acquisition Regulations System FEDERAL... Provisions and Clauses 52.232-10 Payments Under Fixed-Price Architect-Engineer Contracts. As prescribed in 32.111(c)(1), insert the following clause: Payments Under Fixed-Price Architect-Engineer Contracts (APR...

Non-Toxic Orbital Maneuvering System Engine Development

NASA Technical Reports Server (NTRS)

Green, Christopher; Claflin, Scott; Maeding, Chris; Butas, John

1999-01-01

Recent results using the Aestus engine operated with LOx/ethanol propellant are presented. An experimental program at Rocketdyne Propulsion and Power is underway to adapt this engine for the Boeing Reusable Space Systems Division non-toxic Orbital Maneuvering System/Reaction control System (OMS/RCS) system. Daimler-Chrysler Aerospace designed the Aestus as an nitrogen tetroxide/monomethyl hydrazine (NTO/MMH) upper-stage engine for the Ariane 5. The non-toxic OMS/RCS system's preliminary design requires a LOx/ethanol (O2/C2H5OH) engine that operates with a mixture ratio of 1.8, a specific impulse of 323 seconds, and fits within the original OMS design envelope. This paper describes current efforts to meet these requirements including, investigating engine performance using LOx/ethanol, developing the en-ine system sizing package, and meeting the vehicle operation parameters. Data from hot-fire testing are also presented and discussed.

Exploiting Expertise and Knowledge Sharing Online for the Benefit of NASA's GN&C Community of Practice

NASA Technical Reports Server (NTRS)

Topousis, Daria E.; Lebsock, Kenneth L.; Dennehy, Cornelius J.

2010-01-01

In 2004, NASA faced major knowledge sharing challenges due to geographically isolated field centers that inhibited engineers from sharing their experiences, expertise, ideas, and lessons learned. The necessity to collaborate on complex development projects and the reality of constrained project resources together drove the need for ensuring that personnel at all NASA centers had comparable skill sets and that engineers could find resources in a timely fashion. Mission failures and new directions for the Agency also demanded better collaborative tools for NASA's engineering workforce. In response to these needs, the online NASA Engineering Network (NEN) was formed by the NASA Office of the Chief Engineer to provide a multi-faceted system for overcoming geographic and cultural barriers. NEN integrates communities of practice with a cross-repository search and the Lessons Learned Information System. This paper describes the features of the GN&C engineering discipline CoP site which went live on NEN in May of 2008 as an online means of gathering input and guidance from practitioners. It allows GN&C discipline expertise captured at one field center to be shared in a collaborative way with the larger discipline CoP spread across the entire Agency. The site enables GN&C engineers to find the information they need quickly, to find solutions to questions from experienced engineers, and to connect with other practitioners regardless of geographic location, thus increasing the probability of project success.

Ceramic regenerator systems development program

NASA Technical Reports Server (NTRS)

Cook, J. A.; Fucinari, C. A.; Lingscheit, J. N.; Rahnke, C. J.; Rao, V. D.

1978-01-01

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 tests/in industrial gas turbine engines. A regenerator core made from aluminum silicate shows minimal evidence of chemical attack damage after 7804 hours of engine test at 800 C and another showed little distress after 4983 hours at 982 C. The results obtained in ceramic material screening tests, aerothermodynamic performance tests, stress analysis, cost studies, and material specifications are also included.

Electric Propulsion Options for 10 kW Class Earth-Space Missions

NASA Technical Reports Server (NTRS)

Patterson, M. J.; Curran, Francis M.

1989-01-01

Five and 10 kW ion and arcjet propulsion system options for a near-term space demonstration experiment were evaluated. Analyses were conducted to determine first-order propulsion system performance and system component mass estimates. Overall mission performance of the electric propulsion systems was quantified in terms of the maximum thrusting time, total impulse, and velocity increment capability available when integrated onto a generic spacecraft under fixed mission model assumptions. Maximum available thrusting times for the ion-propelled spacecraft options, launched on a DELTA 2 6920 vehicle, range from approximately 8,600 hours for a 4-engine 10 kW system to more than 29,600 hours for a single-engine 5 kW system. Maximum total impulse values and maximum delta-v's range from 1.2x10 (exp 7) to 2.1x10 (exp 7) N-s, and 3550 to 6200 m/s, respectively. Maximum available thrusting times for the arcjet propelled spacecraft launched on the DELTA 2 6920 vehicle range from approximately 528 hours for the 6-engine 10 kW hydrazine system to 2328 hours for the single-engine 5 kW system. Maximum total impulse values and maximum delta-v's range from 2.2x10 (exp 6) to 3.6x10 (exp 6) N-s, and approximately 662 to 1072 m/s, respectively.

CRISPR/Cas9-coupled recombineering for metabolic engineering of Corynebacterium glutamicum.

PubMed

Cho, Jae Sung; Choi, Kyeong Rok; Prabowo, Cindy Pricilia Surya; Shin, Jae Ho; Yang, Dongsoo; Jang, Jaedong; Lee, Sang Yup

2017-07-01

Genome engineering of Corynebacterium glutamicum, an important industrial microorganism for amino acids production, currently relies on random mutagenesis and inefficient double crossover events. Here we report a rapid genome engineering strategy to scarlessly knock out one or more genes in C. glutamicum in sequential and iterative manner. Recombinase RecT is used to incorporate synthetic single-stranded oligodeoxyribonucleotides into the genome and CRISPR/Cas9 to counter-select negative mutants. We completed the system by engineering the respective plasmids harboring CRISPR/Cas9 and RecT for efficient curing such that multiple gene targets can be done iteratively and final strains will be free of plasmids. To demonstrate the system, seven different mutants were constructed within two weeks to study the combinatorial deletion effects of three different genes on the production of γ-aminobutyric acid, an industrially relevant chemical of much interest. This genome engineering strategy will expedite metabolic engineering of C. glutamicum. Copyright © 2017 International Metabolic Engineering Society. Published by Elsevier Inc. All rights reserved.

Main propulsion system test requirements for the two-engine Shuttle-C

NASA Technical Reports Server (NTRS)

Lynn, E. E.; Platt, G. K.

1989-01-01

The Shuttle-C is an unmanned cargo carrying derivative of the space shuttle with optional two or three space shuttle main engines (SSME's), whereas the shuttle has three SSME's. Design and operational differences between the Shuttle-C and shuttle were assessed to determine requirements for additional main propulsion system (MPS) verification testing. Also, reviews were made of the shuttle main propulsion test program objectives and test results and shuttle flight experience. It was concluded that, if significant MPS modifications are not made beyond those currently planned, then main propulsion system verification can be concluded with an on-pad flight readiness firing.

Divergence and inheritance of neocortical heterotopia in inbred and genetically-engineered mice.

PubMed

Toia, Alyssa R; Cuoco, Joshua A; Esposito, Anthony W; Ahsan, Jawad; Joshi, Alok; Herron, Bruce J; Torres, German; Bolivar, Valerie J; Ramos, Raddy L

2017-01-18

Cortical function emerges from the intrinsic properties of neocortical neurons and their synaptic connections within and across lamina. Neurodevelopmental disorders affecting migration and lamination of the neocortex result in cognitive delay/disability and epilepsy. Molecular layer heterotopia (MLH), a dysplasia characterized by over-migration of neurons into layer I, are associated with cognitive deficits and neuronal hyperexcitability in humans and mice. The breadth of different inbred mouse strains that exhibit MLH and inheritance patterns of heterotopia remain unknown. A neuroanatomical survey of numerous different inbred mouse strains, 2 first filial generation (F1) hybrids, and one consomic strain (C57BL/6J-Chr 1 A/J /NaJ) revealed MLH only in C57BL/6 mice and the consomic strain. Heterotopia were observed in numerous genetically-engineered mouse lines on a congenic C57BL/6 background. These data indicate that heterotopia formation is a weakly penetrant trait requiring homozygosity of one or more C57BL/6 alleles outside of chromosome 1. These data are relevant toward understanding neocortical development and disorders affecting neocortical lamination. Copyright © 2016 Elsevier Ireland Ltd. All rights reserved.

Mazda's new V-6 gasoline engine and its innovative induction system

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

Hatamura, K.; Morishita, K.; Asanomi, K.

1987-01-01

Mazda succeeded in the development of a new V-type 6-cylinder engine series comprising 2-liter JF naturally aspirated and turbocharged units and also a 3-liter JE naturally aspirated unit. This engine is 60-degree-banked and has 18 valves: two intake valves and one exhaust valve per cylinder. Various techniques, such as High Rigidity Cylinder Block and HLA, are adopted to upgrade quietness and smoothness. The Dynamic Charge Effects system, a combination of inertia and resonance charge effects, is modeled on the principle of two-degree-of-freedom system. The application of this principle helped develop the Induction system that is compatible with the three enginemore » types. The turbocharger adopted on the JF engine is of a twin scroll type to considerably improve power response quality and increase torque at low speed. Triple Port Induction Control System is used to help improve fuel economy and running performance.« less

High Fidelity Simulation of Atomization in Diesel Engine Sprays

DTIC Science & Technology

2015-09-01

ARL-RP-0555 ● SEP 2015 US Army Research Laboratory High Fidelity Simulation of Atomization in Diesel Engine Sprays by L Bravo...ARL-RP-0555 ● SEP 2015 US Army Research Laboratory High Fidelity Simulation of Atomization in Diesel Engine Sprays by L...Simulation of Atomization in Diesel Engine Sprays 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) L Bravo, CB Ivey, D

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

Technical Digest. Detection Systems and Technology, September 1992

DTIC Science & Technology

1992-09-01

by Van Bladel 7,8 and Mo.9 One method is to c transform the fields in such a way that the (6) boundary "appears" to be at rest relative to the fields...Digest, September 1992 equation of motion from the spectrograph is an 8. Van Bladel, Jean, Relativity and Engineering, Springer- interesting application...many Sci., 2, 1980, pp. 131-148. valuable discussions and advice. 14. Van Bladel, Jean and De Zutter, Daniel, "Reflections from Linearly Vibrating

Exploring Capabilities of Electrical Capacitance Tomography Sensor and Velocity Analysis of Two-Phase R-134A Flow Through a Sudden Expansion

DTIC Science & Technology

2017-05-01

SUDDEN EXPANSION 5a. CONTRACT NUMBER In-house 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 62203F 6. AUTHOR(S) Joseph Michael Cronin 5d. PROJECT ...heat transfer in order to manage the ever-increasing airframe and engine heat loads. Two-phase liquid-vapor refrigerant systems are one solution for...were compared with pressure drop correlations. 15. SUBJECT TERMS thermal management , two-phase flow, flow visualization, electric capacitance

Protocol Standards and Implementation within the Digital Engineering Laboratory Computer Network (DELNET) Using the Universal Network Interface Device (UNID). Part 1.

DTIC Science & Technology

1983-12-01

Initializes the data tables shared by both the Local and Netowrk Operating Systems. 3. Invint: Written in Assembly Language. Initializes the Input/Output...connection with an appropriate type and grade of transport service and appropriate security authentication (Ref 6:38). Data Transfer within a session...V.; Kent, S. Security in oihr Level Protocolst Anorgaches. Alternatives and Recommendations, Draft Report ICST/HLNP-81-19, Wash ingt on,,D.C.: Dept

Basic EMC Technology Advancement for C(3) Systems - SHIELD. Volume IV B. A Digital Computer Program for Computing Crosstalk between Shielded Cables

DTIC Science & Technology

1982-11-01

your organization , please notify RADC OBCT) Griffiss AFB NY 13441. This will assist us in maintaining a current mailing list. Do not return copies of...RMING ORGANIZATION NAME r AND ADDRESS 10. PROGRAM ELEMENT. PROJECT. TASK Southeastern Center for Electrical AREA6WORKUNITNUMBERS Engineering Education...The program requires that the input data groups be organized as shown in Table 1 where the number of unshielded wires is U and the number of shielded

Gene engineering in yeast for biodegradation: Immunological cross-reactivity among cytochrome p-450 system proteins of saccharomyces cerevisiae and candida tropicalis

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

Loper, J.C.; Chen, C.; Dey, C.R.

1993-01-01

Yeasts are eukaryotic microorganisms whose cytochrome P-450 monooxygenase systems may be amenable to genetic engineering for the hydroxylation and detoxication of polychlorinated aromatic hydrocarbons. The molecular genetic properties of strains of bakers yeast, Saccharomyces cerevisiae, and an n-alkane utilizing yeast, Candida tropicalis ATCC750 are examined. Standard methods were used to purify cytochrome P-450 and NADPH-cytochrome c (P-450) reductase proteins from cells cultured by semi-anaerobic glucose fermentation (S. cerevisiae, C. tropicalis) and by growth on tetradecane (C. tropicalis). Polyvalent antisera prepared in rabbits to some of these proteins were used in tests of immunological relatedness among the purified proteins using sodiummore » dodecyl sulfate-polyacrylamide gel electrophoresis and nitrocellulose filter immunoblots. The results provide evidence for gene relationships which should prove useful in gene isolation and subsequent engineering of P-450 enzyme systems in yeast.« less

Donor specificity of YjiC glycosyltransferase determines the conjugation of cytosolic NDP-sugar in in vivo glycosylation reactions.

PubMed

Pandey, Ramesh Prasad; Parajuli, Prakash; Gurung, Rit Bahadur; Sohng, Jae Kyung

2016-09-01

Escherichia coli BL21 (DE3) was engineered by blocking glucose-1-phosphate utilizing glucose phosphate isomerase (pgi), glucose-6-phosphate dehydrogenase (zwf) and uridylyltransferase (galU) genes to produce pool of four different rare dTDP-sugars. The cytosolic pool of dTDP-l-rhamnose, dTDP-d-viosamine, dTDP-4-amino 4,6-dideoxy-d-galactose, and dTDP-3-amino 3,6-dideoxy-d-galactose was generated by overexpressing respective dTDP-sugars biosynthesis genes from various microbial sources. A flexible glycosyltransferase YjiC, from Bacillus licheniformis DSM 13 was also overexpressed to transfer sugar moieties to 3-hydroxyl group of 3-hydroxyflavone, a core unit of flavonoids. Among four rare dTDP-sugars generated in cytosol of engineered strains, YjiC solely transferred l-rhamnose from dTDP-l-rhamnose and tuned to rhamnosyltransferase. Copyright © 2016. Published by Elsevier Inc.

Creep-rupture behavior of candidate Stirling engine alloys after long-term aging at 760 deg C in low-pressure hydrogen

NASA Technical Reports Server (NTRS)

Titran, R. H.

1984-01-01

Nine candidate Stirling automotive engine alloys were aged at 760 C for 3500 hr in low pressure hydrogen or argon to determine the resulting effects on mechanical behavior. Candidate heater head tube alloys were CG-27, W545, 12RN72, INCONEL-718, and HS-188 while candidate cast cylinder-regenerator housing alloys were SA-F11, CRM-6D, XF-818, and HS-31. Aging per se is detrimental to the creep rupture and tensile strengths of the iron base alloys. The presence of hydrogen does not significantly contribute to strength degradation. Based percent highway driving cycle; CG-27 has adequate 3500 hr - 870 C creep rupture strength and SA-Fll, CRM-6D, and XF-818 have adequate 3500 hr - 775 C creep rupture strength.

47 CFR 27.1164 - The cost-sharing formula.

Code of Federal Regulations, 2010 CFR

2010-10-01

... control equipment; engineering costs (design/path survey); installation; systems testing; FCC filing costs; site acquisition and civil works; zoning costs; training; disposal of old equipment; test equipment... a replacement system, such as equipment and engineering expenses. C may not exceed $250,000 per...

Advanced Environmental Barrier Coating Development for SiC/SiC Ceramic Matrix Composites: NASA's Perspectives

NASA Technical Reports Server (NTRS)

Zhu, Dongming

2016-01-01

This presentation reviews NASA environmental barrier coating (EBC) system development programs and the coating materials evolutions for protecting the SiC/SiC Ceramic Matrix Composites in order to meet the next generation engine performance requirements. The presentation focuses on several generations of NASA EBC systems, EBC-CMC component system technologies for SiC/SiC ceramic matrix composite combustors and turbine airfoils, highlighting the temperature capability and durability improvements in simulated engine high heat flux, high pressure, high velocity, and with mechanical creep and fatigue loading conditions. The current EBC development emphasis is placed on advanced NASA 2700F candidate environmental barrier coating systems for SiC/SiC CMCs, their performance benefits and design limitations in long-term operation and combustion environments. Major technical barriers in developing environmental barrier coating systems, the coating integrations with next generation CMCs having the improved environmental stability, erosion-impact resistance, and long-term fatigue-environment system durability performance are described. The research and development opportunities for advanced turbine airfoil environmental barrier coating systems by utilizing improved compositions, state-of-the-art processing methods, and simulated environment testing and durability modeling are discussed.

A Feasibility Study for Advanced Technology Integration for General Aviation.

DTIC Science & Technology

1980-05-01

154 4.5.9.4 Stratified Charge Reciprocating Engine ..... .. 155 4.5.9.5 Advanced Diesel Engine . ... 158 4.5.9.6 Liquid Cooling ... ........ 159... diesel , rotary combustion engine, advanced reciprocating engine concepts. (7) Powerplant control - integrated controls, microprocessor- based controls...Research Center Topics. (1) GATE (2) Positive displacement engines (a) Advanced reciprocating engines. (b) Alternative engine systems Diesel engines

Response Characteristics of a Stable Mixed Potential Ammonia Sensor in Simulated Diesel Exhaust

DOE PAGES

Ramaiyan, Kannan P.; Pihl, Josh A.; Kreller, Cortney R.; ...

2017-07-15

A mixed potential sensor using Au and Pt dense wire electrodes embedded between tape-casted layers of 8 mol% yttria stabilized zirconia (YSZ) was tested for application toward NH 3, NO, NO 2, C 3H 6 and C 3H 8. In single-gas testing, the sensor exhibited the highest response toward NH 3, while still exhibiting reasonably high sensitivity toward other interferent gases. We tested the sensor in a high-flow reactor at the National Transportation Research Center (NTRC) in order to simulate exhaust gas constituents and flow rates produced by lean-burn vehicles powered by Compression-Ignition Direct-Injection (CIDI), diesel engines. The sensor wasmore » characterized at 525 and 625°C for NH 3, CO, C 3H 6, C 3H 8, and NO x in a base gas composition of 10% O 2, 5% H 2O, and 5% CO 2 flowing at 15 slpm. The sensor exhibited fast response time equal to the response time of the system's switching valve (T90<0.6s). Furthermore, in simulations of overdosing a selective catalytic reduction (SCR) system, the sensor was able to selectively respond to 20ppm injections of NH 3 slip despite the presence of the interferent gas species at combined concentrations ten times higher than that of the NH 3. The laboratory sensor construct was transitioned to a pre-commercial, automotive stick sensor configuration that was demonstrated to retain the advantageous characteristics of the tape-cast device.« less

Response Characteristics of a Stable Mixed Potential Ammonia Sensor in Simulated Diesel Exhaust

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

Ramaiyan, Kannan P.; Pihl, Josh A.; Kreller, Cortney R.

A mixed potential sensor using Au and Pt dense wire electrodes embedded between tape-casted layers of 8 mol% yttria stabilized zirconia (YSZ) was tested for application toward NH 3, NO, NO 2, C 3H 6 and C 3H 8. In single-gas testing, the sensor exhibited the highest response toward NH 3, while still exhibiting reasonably high sensitivity toward other interferent gases. We tested the sensor in a high-flow reactor at the National Transportation Research Center (NTRC) in order to simulate exhaust gas constituents and flow rates produced by lean-burn vehicles powered by Compression-Ignition Direct-Injection (CIDI), diesel engines. The sensor wasmore » characterized at 525 and 625°C for NH 3, CO, C 3H 6, C 3H 8, and NO x in a base gas composition of 10% O 2, 5% H 2O, and 5% CO 2 flowing at 15 slpm. The sensor exhibited fast response time equal to the response time of the system's switching valve (T90<0.6s). Furthermore, in simulations of overdosing a selective catalytic reduction (SCR) system, the sensor was able to selectively respond to 20ppm injections of NH 3 slip despite the presence of the interferent gas species at combined concentrations ten times higher than that of the NH 3. The laboratory sensor construct was transitioned to a pre-commercial, automotive stick sensor configuration that was demonstrated to retain the advantageous characteristics of the tape-cast device.« less

Ammonia Generation and Utilization in a Passive SCR (TWC+SCR) System on Lean Gasoline Engine

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

Prikhodko, Vitaly Y; Parks, II, James E; Pihl, Josh A

Lean gasoline engines offer greater fuel economy than the common stoichiometric gasoline engine, but the current three-way catalyst (TWC) on stoichiometric engines is unable to control nitrogen oxide (NOX) emissions in the oxygen-rich exhaust. Thus, lean NOX emission control is required to meet existing Tier 2 and upcoming Tier 3 emission regulations set by the U.S. Environmental Protection Agency (EPA). While urea-based selective catalytic reduction (SCR) has proven effective in controlling NOX from diesel engines, the urea storage and delivery components can add significant size and cost. As such, onboard NH3 production via a passive SCR approach is of interest.more » In a passive SCR system, NH3 is generated over a close-coupled TWC during periodic slightly rich engine operation and subsequently stored on an underfloor SCR catalyst. Upon switching to lean operation, NOX passes through the TWC and is reduced by the stored NH3 on the SCR catalyst. In this work, a passive SCR system was evaluated on a 2.0-liter BMW lean burn gasoline direct injection engine to assess NH3 generation over a Pd-only TWC and utilization over a Cu-based SCR catalyst. System NOX reduction efficiency and fuel efficiency improvement compared to stoichiometric engine operation were measured. A feedback control strategy based on cumulative NH3 produced by the TWC during rich operation and NOX emissions during lean operation was implemented on the engine to control lean/rich cycle timing. 15% excess NH3 production over a 1:1 NH3:NOX ratio was required (via longer rich cycle timing) to achieve 99.7% NOX conversion at an SCR average inlet temperature of 350 C. Increasing NH3 generation further resulted in even higher NOX conversion; however, tailpipe NH3 emissions resulted. At higher temperatures, NH3 oxidation becomes important and limits NH3 availability for NOX reduction. At the engine conditions studied here, greater than 99% NOX conversion was achieved with passive SCR while delivering fuel efficiency benefits ranging between 6-11% compared with stoichiometric operation.« less

Study of solid rocket motor for space shuttle booster, volume 2, book 1

NASA Technical Reports Server (NTRS)

1972-01-01

The technical requirements for the solid propellant rocket engine to be used with the space shuttle orbiter are presented. The subjects discussed are: (1) propulsion system definition, (2) solid rocket engine stage design, (3) solid rocket engine stage recovery, (4) environmental effects, (5) manrating of the solid rocket engine stage, (6) system safety analysis, and (7) ground support equipment.

Guidance, Navigation and Control (GN&C): Best Practices for Human-Rated Spacecraft Systems

NASA Technical Reports Server (NTRS)

Lebsock, Ken; West, John

2008-01-01

In 2007 the NESC completed an in-depth assessment to identify, define and document engineering considerations for the Design Development Test and Evaluation (DDT&E) of human-rated spacecraft systems. This study had been requested by the Astronaut Office at JSC to help them to better understand what is required to ensure safe, robust, and reliable human-rated spacecraft systems. The 22 GN&C engineering Best Practices described in this paper are a condensed version of what appears in the NESC Technical Report. These Best Practices cover a broad range from fundamental system architectural considerations to more specific aspects (e.g., stability margin recommendations) of GN&C system design and development. 15 of the Best Practices address the early phases of a GN&C System development project and the remaining 7 deal with the later phases. Some of these Best Practices will cross-over between both phases. We recognize that this set of GN&C Best Practices will not be universally applicable to all projects and mission applications.

RS-25D engine

NASA Image and Video Library

2012-01-17

Employees unload a RS25D rocket engine at NASA's John C. Stennis Space Center on Jan. 17. The engine - and 14 others - will be stored at the facility for future testing and use on NASA's new Space Launch System (SLS). The SLS is a new heavy-lift launch vehicle that will expand human presence beyond low-Earth orbit and enable new missions of exploration across the solar system. NASA's Marshall Space Flight Center in Huntsville, Ala., is leading the design and development of the Space Launch System for NASA, including the engine testing program. Delivery of the 15 RS-25 engines will continue throughout the next few months

DoD Housing Management

DTIC Science & Technology

1993-09-01

E, below. The forms are approved for electronic generation and distribution. * 1-7 0 C~L0 _ 0 C 0I U)2 Ea 0 0 0 U! 0 3: X 9 0 V~ 0 CD co L. 8p 6 V- I...and inspection by installation personnel. e. Costs above installation level, such as costs attributable to Engineer Districts, Public Works Offices...the major command or engineering field dMsion ’). For DoD Component area summary reports, leave bla’*. C-1 Go %a M -ý - f N 4I- -t C-4.𔃻-1 .7 %10O O

Cook/chill foodservice system with a microwave oven: aerobic plate counts from beef loaf, potatoes and frozen green beans.

PubMed

Dahl, C A; Matthews, M E; Marth, E H

1980-06-01

The purpose was to evaluate microbiological quality and end temperature (ET) of portioned food after heating in a microwave oven as used in a hospital cook/chill foodservice system. Beef loaf (15 kg), potatoes (6 kg), and green beans (5 kg) were prepared in a laboratory. After initial cooking to 60 degrees C, and storage (7 degrees C for 24 h), beef loaf (100 g) was microwave heated: 20, 50, 80 or 110 s. Potatoes were reconstituted, stored (7 degrees C for 24 h), portioned (100 g/portion), and microwave-heated: 25, 45, 65 or 84 s. Beans were thawed (7 degrees C for 24 h), portioned (100 g/portion), and microwave-heated: 20, 50, 80 or 110 s. Aerobic plate counts (APC) for foods were obtained throughout product flow. Wide ranges of Et and of APC in foods indicates that research is needed, for greater control of microwave-heating through advanced microwave engineering and food technology, to produce food with constant microbiological quality.

Engineering proximal vs. distal heme-NO coordination via dinitrosyl dynamics: implications for NO sensor design.

PubMed

Kekilli, Demet; Petersen, Christine A; Pixton, David A; Ghafoor, Dlzar D; Abdullah, Gaylany H; Dworkowski, Florian S N; Wilson, Michael T; Heyes, Derren J; Hardman, Samantha J O; Murphy, Loretta M; Strange, Richard W; Scrutton, Nigel S; Andrew, Colin R; Hough, Michael A

2017-03-01

Proximal vs. distal heme-NO coordination is a novel strategy for selective gas response in heme-based NO-sensors. In the case of Alcaligenes xylosoxidans cytochrome c' (AXCP), formation of a transient distal 6cNO complex is followed by scission of the trans Fe-His bond and conversion to a proximal 5cNO product via a putative dinitrosyl species. Here we show that replacement of the AXCP distal Leu16 residue with smaller or similar sized residues (Ala, Val or Ile) traps the distal 6cNO complex, whereas Leu or Phe residues lead to a proximal 5cNO product with a transient or non-detectable distal 6cNO precursor. Crystallographic, spectroscopic, and kinetic measurements of 6cNO AXCP complexes show that increased distal steric hindrance leads to distortion of the Fe-N-O angle and flipping of the heme 7-propionate. However, it is the kinetic parameters of the distal NO ligand that determine whether 6cNO or proximal 5cNO end products are formed. Our data support a 'balance of affinities' mechanism in which proximal 5cNO coordination depends on relatively rapid release of the distal NO from the dinitrosyl precursor. This mechanism, which is applicable to other proteins that form transient dinitrosyls, represents a novel strategy for 5cNO formation that does not rely on an inherently weak Fe-His bond. Our data suggest a general means of engineering selective gas response into biologically-derived gas sensors in synthetic biology.

33 CFR 326.6 - Class I administrative penalties.

Code of Federal Regulations, 2010 CFR

2010-07-01

.... 326.6 Section 326.6 Navigation and Navigable Waters CORPS OF ENGINEERS, DEPARTMENT OF THE ARMY, DEPARTMENT OF DEFENSE ENFORCEMENT § 326.6 Class I administrative penalties. (a) Introduction. (1) This... giving public notice and providing the opportunity for public comment are contained in § 326.6(c). (4) At...

Holocene morphogenesis of Alexander the Great's isthmus at Tyre in Lebanon

PubMed Central

Marriner, Nick; Morhange, Christophe; Meulé, Samuel

2007-01-01

In 332 B.C., Alexander the Great constructed an ≈1,000-m-long causeway to seize the offshore island of Tyre. The logistics behind this engineering feat have long troubled archaeologists. Using the Holocene sedimentary record, we demonstrate that Alexander's engineers cleverly exploited a shallow proto-tombolo, or sublittoral sand spit, to breach the offshore city's defensive impregnability. We elucidate a three-phase geomorphological model for the spit's evolution. Settled since the Bronze Age, the area's geological record manifests a long history of natural and anthropogenic forcings. (i) Leeward of the island breakwater, the maximum flooding surface (e.g., drowning of the subaerial land surfaces by seawater) is dated ≈8000 B.P. Fine-grained sediments and brackish and marine-lagoonal faunas translate shallow, low-energy water bodies at this time. Shelter was afforded by Tyre's elongated sandstone reefs, which acted as a 6-km natural breakwater. (ii) By 6000 B.P., sea-level rise had reduced the dimensions of the island from 6 to 4 km. The leeward wave shadow generated by this island, allied with high sediment supply after 3000 B.P., culminated in a natural wave-dominated proto-tombolo within 1–2 m of mean sea level by the time of Alexander the Great (4th century B.C.). (iii) After 332 B.C., construction of Alexander's causeway entrained a complete anthropogenic metamorphosis of the Tyrian coastal system. PMID:17517668

Holocene morphogenesis of Alexander the Great's isthmus at Tyre in Lebanon.

PubMed

Marriner, Nick; Morhange, Christophe; Meulé, Samuel

2007-05-29

In 332 B.C., Alexander the Great constructed an approximately 1,000-m-long causeway to seize the offshore island of Tyre. The logistics behind this engineering feat have long troubled archaeologists. Using the Holocene sedimentary record, we demonstrate that Alexander's engineers cleverly exploited a shallow proto-tombolo, or sublittoral sand spit, to breach the offshore city's defensive impregnability. We elucidate a three-phase geomorphological model for the spit's evolution. Settled since the Bronze Age, the area's geological record manifests a long history of natural and anthropogenic forcings. (i) Leeward of the island breakwater, the maximum flooding surface (e.g., drowning of the subaerial land surfaces by seawater) is dated approximately 8000 B.P. Fine-grained sediments and brackish and marine-lagoonal faunas translate shallow, low-energy water bodies at this time. Shelter was afforded by Tyre's elongated sandstone reefs, which acted as a 6-km natural breakwater. (ii) By 6000 B.P., sea-level rise had reduced the dimensions of the island from 6 to 4 km. The leeward wave shadow generated by this island, allied with high sediment supply after 3000 B.P., culminated in a natural wave-dominated proto-tombolo within 1-2 m of mean sea level by the time of Alexander the Great (4th century B.C.). (iii) After 332 B.C., construction of Alexander's causeway entrained a complete anthropogenic metamorphosis of the Tyrian coastal system.

Emissions characteristics of Military Helicopter Engines Fueled with JP-8 and a Fischer-Tropsch Fuel

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

Corporan, E.; DeWitt, M.; Klingshirn, Christopher D

2010-01-01

The rapid growth in aviation activities and more stringent U.S. Environmental Protection Agency regulations have increased concerns regarding aircraft emissions, due to their harmful health and environmental impacts, especially in the vicinity of airports and military bases. In this study, the gaseous and particulate-matter emissions of two General Electric T701C engines and one T700 engine were evaluated. The T700 series engines power the U.S. Army's Black Hawk and Apache helicopters. The engines were fueled with standard military JP-8 fuel and were tested at three power settings. In addition, one of the T701C engines was operated on a natural-gas-derived Fischer-Tropsch syntheticmore » paraffinic kerosene jet fuel. Test results show that the T701C engine emits significantly lower particulate-matter emissions than the T700 for all conditions tested. Particulate-matter mass emission indices ranged from 0.2-1.4 g/kg fuel for the T700 and 0.2-0.6 g/kg fuel for the T701C. Slightly higher NOx and lower CO emissions were observed for the T701C compared with the T700. Operation of the T701C with the Fischer-Tropsch fuel rendered dramatic reductions in soot emissions relative to operation on JP-8, due primarily to the lack of aromatic compounds in the alternative fuel. The Fischer-Tropsch fuel also produced smaller particles and slight reductions in CO emissions.« less

40 CFR Appendix I to Part 92 - Emission Related Locomotive and Engine Parameters and Specifications

Code of Federal Regulations, 2011 CFR

2011-07-01

... injection—non-compression ignition engines. a. Control parameters and calibrations. b. Idle mixture. c. Fuel...(s). i. Injector timing calibration. 4. Fuel injection—compression ignition engines. a. Control... restriction. III. Fuel System. 1. General. a. Engine idle speed. 2. Carburetion. a. Air-fuel flow calibration...

40 CFR Appendix I to Part 92 - Emission Related Locomotive and Engine Parameters and Specifications

Code of Federal Regulations, 2014 CFR

2014-07-01

... injection—non-compression ignition engines. a. Control parameters and calibrations. b. Idle mixture. c. Fuel...(s). i. Injector timing calibration. 4. Fuel injection—compression ignition engines. a. Control... restriction. III. Fuel System. 1. General. a. Engine idle speed. 2. Carburetion. a. Air-fuel flow calibration...

40 CFR Appendix I to Part 92 - Emission Related Locomotive and Engine Parameters and Specifications

Code of Federal Regulations, 2013 CFR

2013-07-01

... injection—non-compression ignition engines. a. Control parameters and calibrations. b. Idle mixture. c. Fuel...(s). i. Injector timing calibration. 4. Fuel injection—compression ignition engines. a. Control... restriction. III. Fuel System. 1. General. a. Engine idle speed. 2. Carburetion. a. Air-fuel flow calibration...

40 CFR Appendix I to Part 92 - Emission Related Locomotive and Engine Parameters and Specifications

Code of Federal Regulations, 2012 CFR

2012-07-01

... injection—non-compression ignition engines. a. Control parameters and calibrations. b. Idle mixture. c. Fuel...(s). i. Injector timing calibration. 4. Fuel injection—compression ignition engines. a. Control... restriction. III. Fuel System. 1. General. a. Engine idle speed. 2. Carburetion. a. Air-fuel flow calibration...

Orbit transfer rocket engine technology program

NASA Technical Reports Server (NTRS)

Gustafson, N. B.; Harmon, T. J.

1993-01-01

An advanced near term (1990's) space-based Orbit Transfer Vehicle Engine (OTVE) system was designed, and the technologies applicable to its construction, maintenance, and operations were developed under Tasks A through F of the Orbit Transfer Rocket Engine Technology Program. Task A was a reporting task. In Task B, promising OTV turbomachinery technologies were explored: two stage partial admission turbines, high velocity ratio diffusing crossovers, soft wear ring seals, advanced bearing concepts, and a rotordynamic analysis. In Task C, a ribbed combustor design was developed. Possible rib and channel geometries were chosen analytically. Rib candidates were hot air tested and laser velocimeter boundary layer analyses were conducted. A channel geometry was also chosen on the basis of laser velocimeter data. To verify the predicted heat enhancement effects, a ribbed calorimeter spool was hot fire tested. Under Task D, the optimum expander cycle engine thrust, performance and envelope were established for a set of OTV missions. Optimal nozzle contours and quick disconnects for modularity were developed. Failure Modes and Effects Analyses, maintenance and reliability studies and component study results were incorporated into the engine system. Parametric trades on engine thrust, mixture ratio, and area ratio were also generated. A control system and the health monitoring and maintenance operations necessary for a space-based engine were outlined in Task E. In addition, combustor wall thickness measuring devices and a fiberoptic shaft monitor were developed. These monitoring devices were incorporated into preflight engine readiness checkout procedures. In Task F, the Integrated Component Evaluator (I.C.E.) was used to demonstrate performance and operational characteristics of an advanced expander cycle engine system and its component technologies. Sub-system checkouts and a system blowdown were performed. Short transitions were then made into main combustor ignition and main stage operation.

REDIR: Automated Static Detection of Obfuscated Anti-Debugging Techniques

DTIC Science & Technology

2014-03-27

analyzing code samples that resist other forms of analysis. 2.5.6 RODS and HASTI: Software Engineering Cognitive Support Software Engineering (SE) is another...and (c) this method is resistant to common obfuscation techniques. To achieve this goal, the Data/Frame sensemaking theory guides the process of...No Starch Press, 2012. [46] C.-W. Hsu, S. W. Shieh et al., “Divergence Detector: A Fine-Grained Approach to Detecting VM-Awareness Malware,” in

CrossTalk: The Journal of Defense Software Engineering. Volume 19, Number 3

DTIC Science & Technology

2006-03-01

Humphreys & Associates, Inc., 2002. 3. Humphrey , Watts S . PSP : A Self- Improvement Process for...sanderfer.html>. 5. Humphrey , Watts S . A Discipline for Software Engineering. Addison- Wesley, 1995. 6. Tuma, David, and David R. Webb. “Personal Earned Value: Why...o u r c e li n e s o f c o d e ) Figure 3: Differences for Highest Degree Attained PSP /TSP 12 CROSSTALK The Journal of Defense Software

Stennis Space Center goes to Washington Folklife Festival

NASA Image and Video Library

2008-07-03

Bryon Maynard (left), an aerospace technologist for Propulsion Systems & Tech in Stennis' Engineering and Science Directorate, uses a 'pocket rocket' to demonstrate the concept of rocket propulsion as part of NASA's exhibit at the Smithsonian Folklife Festival in Washington, D.C. Maynard is joined by Bradley Messer (right), chief of the Systems Engineering & Integration Division in Stennis' Engineering and Science Directorate, and a pair of exhibit visitors.

Stennis Space Center goes to Washington Folklife Festival

NASA Technical Reports Server (NTRS)

2008-01-01

Bryon Maynard (left), an aerospace technologist for Propulsion Systems & Tech in Stennis' Engineering and Science Directorate, uses a 'pocket rocket' to demonstrate the concept of rocket propulsion as part of NASA's exhibit at the Smithsonian Folklife Festival in Washington, D.C. Maynard is joined by Bradley Messer (right), chief of the Systems Engineering & Integration Division in Stennis' Engineering and Science Directorate, and a pair of exhibit visitors.

14 CFR 33.69 - Ignitions system.

Code of Federal Regulations, 2013 CFR

2013-01-01

... STANDARDS: AIRCRAFT ENGINES Design and Construction; Turbine Aircraft Engines § 33.69 Ignitions system. Each..., except that only one igniter is required for fuel burning augmentation systems. [Amdt. 33-6, 39 FR 35466... 14 Aeronautics and Space 1 2013-01-01 2013-01-01 false Ignitions system. 33.69 Section 33.69...

14 CFR 33.69 - Ignitions system.

Code of Federal Regulations, 2014 CFR

2014-01-01

... STANDARDS: AIRCRAFT ENGINES Design and Construction; Turbine Aircraft Engines § 33.69 Ignitions system. Each..., except that only one igniter is required for fuel burning augmentation systems. [Amdt. 33-6, 39 FR 35466... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false Ignitions system. 33.69 Section 33.69...

14 CFR 33.69 - Ignitions system.

Code of Federal Regulations, 2012 CFR

2012-01-01

... STANDARDS: AIRCRAFT ENGINES Design and Construction; Turbine Aircraft Engines § 33.69 Ignitions system. Each..., except that only one igniter is required for fuel burning augmentation systems. [Amdt. 33-6, 39 FR 35466... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false Ignitions system. 33.69 Section 33.69...

Thermal and Environmental Barrier Coatings for Advanced Turbine Engine Applications

NASA Technical Reports Server (NTRS)

Zhu, Dong-Ming; Miller, Robert A.

2005-01-01

Ceramic thermal and environmental barrier coatings (T/EBCs) will play a crucial role in advanced gas turbine engine systems because of their ability to significantly increase engine operating temperatures and reduce cooling requirements, thus help achieve engine low emission and high efficiency goals. Advanced T/EBCs are being developed for the low emission SiC/SiC ceramic matrix composite (CMC) combustor applications by extending the CMC liner and vane temperature capability to 1650 C (3000 F) in oxidizing and water vapor containing combustion environments. Low conductivity thermal barrier coatings (TBCs) are also being developed for metallic turbine airfoil and combustor applications, providing the component temperature capability up to 1650 C (3000 F). In this paper, ceramic coating development considerations and requirements for both the ceramic and metallic components will be described for engine high temperature and high-heat-flux applications. The underlying coating failure mechanisms and life prediction approaches will be discussed based on the simulated engine tests and fracture mechanics modeling results.

Aircraft Control Using Engine Thrust: A History of Learning TOC Real-Time

NASA Technical Reports Server (NTRS)

Cole, Jennifer H.; Batteas, Frank; Fullerton, Gordon

2006-01-01

A history of learning the operation of Throttles Only Control (TOC) to control an aircraft in real time using engine thrust is shown. The topics include: 1) Past TOC Accidents/Incidents; 2) 1972: DC-10 American Airlines; 3) May 1974: USAF B-52H; 4) April 1975: USAF C-5A; 5) April 1975: USAF C-5A; 6) 1981: USAF B-52G; 7) August 1985: JAL 123 B-747; 8) JAL 123 Survivor Story; 9) JAL 123 Investigation Findings; 10) July 1989: UAL 232 DC-10; 11) UAL 232 DC-10; 12) Eastwind 517 B-737; 13) November 2003: DHL A-300; 14) Historically, TOC has saved lives; 15) Automated Throttles-Only Control; 16) PCA Project; 17) Propulsion-Controlled Aircraft; 18) MD-11 PCA System and Flight Test Envelope; 19) MD-11 Simulation, PCA ILS-Soupled Landing Dispersion; 20) Throttles-Only Pitch and Roll Control Power; 21) PCA in Commercial Fleet; 22) Fall 2005: PCAR Project; 23) PCAR Background - TOC; and 24) PCAR Background - TOC.

Advanced Environmental Barrier Coating and SA Tyrannohex SiC Composites Integration for Improved Thermomechanical and Environmental Durability

NASA Technical Reports Server (NTRS)

Zhu, Dongming; Halbig, Michael; Singh, Mrityunjay

2018-01-01

The development of 2700 degF capable environmental barrier coating (EBC) systems, particularly, the Rare Earth "Hafnium" Silicon bond coat systems, have significantly improved the temperature capability and environmental stability of SiC/SiC Ceramic Matrix Composite Systems. We have specifically developed the advanced 2700 degF EBC systems, integrating the EBC to the high temperature SA Tyrannohex SiC fiber composites, for comprehensive performance and durability evaluations for potential turbine engine airfoil component applications. The fundamental mechanical properties, environmental stability and thermal gradient cyclic durability performance of the EBC - SA Tyrannohex composites were investigated. The paper will particularly emphasize the high pressure combustion rig recession, cyclic thermal stress resistance and thermomechanical low cycle fatigue testing of uncoated and environmental barrier coated Tyrannohex SiC SA composites in these simulated turbine engine combustion water vapor, thermal gradients, and mechanical loading conditions. We have also investigated high heat flux and flexural fatigue degradation mechanisms, determined the upper limits of operating temperature conditions for the coated SA composite material systems in thermomechanical fatigue conditions. Recent progress has also been made by using the self-healing rare earth-silicon based EBCs, thus enhancing the SA composite hexagonal fiber columns bonding for improved thermomechanical and environmental durability in turbine engine operation environments. More advanced EBC- composite systems based on the new EBC-Fiber Interphases will also be discussed.

NASA C-17 Usage Overview

NASA Technical Reports Server (NTRS)

Miller, Christopher R.

2008-01-01

The usage and integrated vehicle health management of the NASA C-17. Propulsion health management flight objectives for the aircraft include mapping of the High Pressure Compressor in order to calibrate a Pratt and Whitney engine model and the fusion of data collected from existing sensors and signals to develop models, analysis methods and information fusion algorithms. An additional health manage flight objective is to demonstrate that the Commercial Modular Aero-Propulsion Systems Simulation engine model can successfully execute in real time onboard the C-17 T-1 aircraft using engine and aircraft flight data as inputs. Future work will address aircraft durability and aging, airframe health management, and propulsion health management research in the areas of gas path and engine vibration.

Engineering C4 photosynthesis into C3 chassis in the synthetic biology age.

PubMed

Schuler, Mara L; Mantegazza, Otho; Weber, Andreas P M

2016-07-01

C4 photosynthetic plants outperform C3 plants in hot and arid climates. By concentrating carbon dioxide around Rubisco C4 plants drastically reduce photorespiration. The frequency with which plants evolved C4 photosynthesis independently challenges researchers to unravel the genetic mechanisms underlying this convergent evolutionary switch. The conversion of C3 crops, such as rice, towards C4 photosynthesis is a long-standing goal. Nevertheless, at the present time, in the age of synthetic biology, this still remains a monumental task, partially because the C4 carbon-concentrating biochemical cycle spans two cell types and thus requires specialized anatomy. Here we review the advances in understanding the molecular basis and the evolution of the C4 trait, advances in the last decades that were driven by systems biology methods. In this review we emphasise essential genetic engineering tools needed to translate our theoretical knowledge into engineering approaches. With our current molecular understanding of the biochemical C4 pathway, we propose a simplified rational engineering model exclusively built with known C4 metabolic components. Moreover, we discuss an alternative approach to the progressing international engineering attempts that would combine targeted mutagenesis and directed evolution. © 2016 The Authors The Plant Journal © 2016 John Wiley & Sons Ltd.

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

DTIC Science & Technology

2017-03-06

WP-201317) Demonstration of Novel Sampling Techniques for Measurement of Turbine Engine Volatile and Non -volatile Particulate Matter (PM...Engine Volatile and Non -Volatile Particulate Matter (PM) Emissions 6. AUTHOR(S) E. Corporan, M. DeWitt, C. Klingshirn, M.D. Cheng, R. Miake-Lye, J. Peck...the performance and viability of two devices to condition aircraft turbine engine exhaust to allow the accurate measurement of total (volatile and non

Appendix C: Rapid development approaches for system engineering and design

NASA Technical Reports Server (NTRS)

1993-01-01

Conventional system architectures, development processes, and tool environments often produce systems which exceed cost expectations and are obsolete before they are fielded. This paper explores some of the reasons for this and provides recommendations for how we can do better. These recommendations are based on DoD and NASA system developments and on our exploration and development of system/software engineering tools.

Entry Atmospheric Flight Control Authority Impacts on GN and C and Trajectory Performance for Orion Exploration Flight Test 1

NASA Technical Reports Server (NTRS)

McNamara, Luke W.

2012-01-01

One of the key design objectives of NASA's Orion Exploration Flight Test 1 (EFT-1) is to execute a guided entry trajectory demonstrating GN&C capability. The focus of this paper is the ight control authority of the vehicle throughout the atmospheric entry ight to the target landing site and its impacts on GN&C, parachute deployment, and integrated performance. The vehicle's attitude control authority is obtained from thrusting 12 Re- action Control System (RCS) engines, with four engines to control yaw, four engines to control pitch, and four engines to control roll. The static and dynamic stability derivatives of the vehicle are determined to assess the inherent aerodynamic stability. The aerodynamic moments at various locations in the entry trajectory are calculated and compared to the available torque provided by the RCS system. Interaction between the vehicle's RCS engine plumes and the aerodynamic conditions are considered to assess thruster effectiveness. This document presents an assessment of Orion's ight control authority and its effectiveness in controlling the vehicle during critical events in the atmospheric entry trajectory.

NASA Orbit Transfer Rocket Engine Technology Program

NASA Technical Reports Server (NTRS)

1984-01-01

The advanced expander cycle engine with a 15,000 lb thrust level and a 6:1 mixture ratio and optimized performance was used as the baseline for a design study of the hydrogen/oxgyen propulsion system for the orbit transfer vehicle. The critical components of this engine are the thrust chamber, the turbomachinery, the extendible nozzle system, and the engine throttling system. Turbomachinery technology is examined for gears, bearing, seals, and rapid solidification rate turbopump shafts. Continuous throttling concepts are discussed. Components of the OTV engine described include the thrust chamber/nozzle assembly design, nozzles, the hydrogen regenerator, the gaseous oxygen heat exchanger, turbopumps, and the engine control valves.

V&V Plan for FPGA-based ESF-CCS Using System Engineering Approach.

NASA Astrophysics Data System (ADS)

Maerani, Restu; Mayaka, Joyce; El Akrat, Mohamed; Cheon, Jung Jae

2018-02-01

Instrumentation and Control (I&C) systems play an important role in maintaining the safety of Nuclear Power Plant (NPP) operation. However, most current I&C safety systems are based on Programmable Logic Controller (PLC) hardware, which is difficult to verify and validate, and is susceptible to software common cause failure. Therefore, a plan for the replacement of the PLC-based safety systems, such as the Engineered Safety Feature - Component Control System (ESF-CCS), with Field Programmable Gate Arrays (FPGA) is needed. By using a systems engineering approach, which ensures traceability in every phase of the life cycle, from system requirements, design implementation to verification and validation, the system development is guaranteed to be in line with the regulatory requirements. The Verification process will ensure that the customer and stakeholder’s needs are satisfied in a high quality, trustworthy, cost efficient and schedule compliant manner throughout a system’s entire life cycle. The benefit of the V&V plan is to ensure that the FPGA based ESF-CCS is correctly built, and to ensure that the measurement of performance indicators has positive feedback that “do we do the right thing” during the re-engineering process of the FPGA based ESF-CCS.

Knowledge Acquisition for Expert Systems in Construction.

DTIC Science & Technology

1988-02-01

Trmble R J Aliwood A E Bryman C N Cooper -. Sixth interim report 4r " -Contract DAJA 45-85-C-0033 February 1988 i i 88 3 09 124 "I...Wheeler, has developed a experienced knowlae engineer Successful applications of expert sys- system for material selection of boier researching at...wanted to try engineer who may suddexiy become very also benefitted from application of artifi- the technology for some time, and his busy on a

Combustion engine system

NASA Technical Reports Server (NTRS)

Houseman, John (Inventor); Voecks, Gerald E. (Inventor)

1986-01-01

A flow through catalytic reactor which selectively catalytically decomposes methanol into a soot free hydrogen rich product gas utilizing engine exhaust at temperatures of 200 to 650 C to provide the heat for vaporizing and decomposing the methanol is described. The reactor is combined with either a spark ignited or compression ignited internal combustion engine or a gas turbine to provide a combustion engine system. The system may be fueled entirely by the hydrogen rich gas produced in the methanol decomposition reactor or the system may be operated on mixed fuels for transient power gain and for cold start of the engine system. The reactor includes a decomposition zone formed by a plurality of elongated cylinders which contain a body of vapor permeable, methanol decomposition catalyst preferably a shift catalyst such as copper-zinc.

Advanced SiC/SiC Ceramic Composites For Gas-Turbine Engine Components

NASA Technical Reports Server (NTRS)

Yun, H. M.; DiCarlo, J. A.; Easler, T. E.

2004-01-01

NASA Glenn Research Center (GRC) is developing a variety of advanced SiC/SiC ceramic composite (ASC) systems that allow these materials to operate for hundreds of hours under stress in air at temperatures approaching 2700 F. These SiC/SiC composite systems are lightweight (approximately 30% metal density) and, in comparison to monolithic ceramics and carbon fiber-reinforced ceramic composites, are able to reliably retain their structural properties for long times under aggressive gas-turbine engine environments. The key for the ASC systems is related first to the NASA development of the Sylramic-iBN Sic fiber, which displays higher thermal stability than any other SiC- based ceramic fibers and possesses an in-situ grown BN surface layer for higher environmental durability. This fiber is simply derived from Sylramic Sic fiber type that is currently produced at ATK COI Ceramics (COIC). Further capability is then derived by using chemical vapor infiltration (CVI) and/or polymer infiltration and pyrolysis (PIP) to form a Sic-based matrix with high creep and rupture resistance as well as high thermal conductivity. The objectives of this study were (1) to optimize the constituents and processing parameters for a Sylramic-iBN fiber reinforced ceramic composite system in which the Sic-based matrix is formed at COIC almost entirely by PIP (full PIP approach), (2) to evaluate the properties of this system in comparison to other 2700 F Sylramic-iBN systems in which the matrix is formed by full CVI and CVI + PIP, and (3) to examine the pros and cons of the full PIP approach for fabricating hot-section engine components. A key goal is the development of a composite system with low porosity, thereby providing high modulus, high matrix cracking strength, high interlaminar strength, and high thermal conductivity, a major property requirement for engine components that will experience high thermal gradients during service. Other key composite property goals are demonstration at high temperatures of high environmental resistance and high creep resistance, which in turn will result in long component life. Data are presented from a variety of laboratory tests on simple two-dimensional panels that examine these properties and compare the performance of the optimized full PIP system with those of the full CVI and CVI + PIP hybrid systems. Underlying mechanisms for performance differences in the various systems are discussed. Remaining issues for further property enhancement and for application of the full PIP approach for engine components are also discussed, as well as on-going approaches at NASA to solve these issues.

Center for Urban Transportation Studies | College of Engineering & Applied

Science.gov Websites

Engineering of the College of Engineering and Applied Science as well as with the faculty at UW-Madison, UW Science A B C D E F G H I J K L M N O P Q R S T U V W X Y Z D2L PAWS Email My UW-System About UWM Jobs D2L PAWS Email My UW-System University of Wisconsin-Milwaukee College ofEngineering &

40 CFR 86.1335-90 - Cool-down procedure.

Code of Federal Regulations, 2010 CFR

2010-07-01

...'s internal or external surfaces except for water and air as prescribed in paragraphs (c) and (d) of this section. (c) For water-cooled engines, two types of cooling are permitted: (1) Water may be circulated through the engine's water coolant system. (i) The coolant may be flowed in either direction and...

Experimental Studies of Radial Wave Thermoacoustic Engines. Navy Environmentally Safe Ships Program.

DTIC Science & Technology

1995-07-15

4 B. Pressure and specific acoustic impedance differer.: hd equation. .... ................ 6...the engine, Arf Sr) the resonator cross-see:iona! area at r. Ap(r) the cross-sectional area of" a porn at r, V; >h :c .... ,Ar tk. resonator at r

Engineering E. coli strain for conversion of short chain fatty acids to bioalcohols

PubMed Central

2013-01-01

Background Recent progress in production of various biofuel precursors and molecules, such as fatty acids, alcohols and alka(e)nes, is a significant step forward for replacing the fossil fuels with renewable fuels. A two-step process, where fatty acids from sugars are produced in the first step and then converted to corresponding biofuel molecules in the second step, seems more viable and attractive at this stage. We have engineered an Escherichia coli strain to take care of the second step for converting short chain fatty acids into corresponding alcohols by using butyrate kinase (Buk), phosphotransbutyrylase (Ptb) and aldehyde/alcohol dehydrogenase (AdhE2) from Clostridium acetobutylicum. Results The engineered E. coli was able to convert butyric acid and other short chain fatty acids of chain length C3 to C7 into corresponding alcohols and the efficiency of conversion varied with different E. coli strain type. Glycerol proved to be a better donor of ATP and electron as compared to glucose for converting butyric acid to butanol. The engineered E. coli was able to tolerate up to 100 mM butyric acid and produced butanol with the conversion rate close to 100% under anaerobic condition. Deletion of native genes, such as fumarate reductase (frdA) and alcohol dehydrogenase (adhE), responsible for side products succinate and ethanol, which act as electron sink and could compete with butyric acid uptake, did not improve the butanol production efficiency. Indigenous acyl-CoA synthetase (fadD) was found to play no role in the conversion of butyric acid to butanol. Engineered E. coli was cultivated in a bioreactor under controlled condition where 60 mM butanol was produced within 24 h of cultivation. A continuous bioreactor with the provision of cell recycling allowed the continuous production of butanol at the average productivity of 7.6 mmol/l/h until 240 h. Conclusions E. coli engineered with the pathway from C. acetobutylicum could efficiently convert butyric acid to butanol. Other short chain fatty acids with the chain length of C3 to C7 were also converted to the corresponding alcohols. The ability of engineered strain to convert butyric acid to butanol continuously demonstrates commercial significance of the system. PMID:24020887

Biodegradable Microfluidic Scaffolds for Vascular Tissue Engineering

DTIC Science & Technology

2005-01-01

Engineering DISTRIBUTION: Approved for public release, distribution unlimited This paper is part of the following report: TITLE: Materials Research...Society Symposium Proceedings. Volume 845, 2005. Nanoscale Materials Science in Biology and Medicine, Held in Boston, MA on 28 November-2 December 2004...Symp. Proc. Vol. 845 © 2005 Materials Research Society AA1.6 Biodegradable Microfluidic Scaffolds for Vascular Tissue Engineering C. J. Bettinger" 3

A Preliminary Study on Designing and Testing of an Absorption Refrigeration Cycle Powered by Exhaust Gas of Combustion Engine

NASA Astrophysics Data System (ADS)

Napitupulu, F. H.; Daulay, F. A.; Dedy, P. M.; Denis; Jecson

2017-03-01

In order to recover the waste heat from the exhaust gas of a combustion engine, an adsorption refrigeration cycle is proposed. This is a preliminary study on design and testing of a prototype of absorption refrigeration cycle powered by an internal combustion engine. The heat source of the cycle is a compression ignition engine which generates 122.36 W of heat in generator of the cycle. The pairs of absorbent and refrigerant are water and ammonia. Here the generator is made of a shell and tube heat exchanger with number of tube and its length are 20 and 0.69 m, respectively. In the experiments the exhaust gas, with a mass flow rate of 0.00016 kg/s, enters the generator at 110°C and leaves it at 72°C. Here, the solution is heated from 30°C to 90°C. In the evaporator, the lowest temperature can be reached is 17.9°C and COP of the system is 0.45. The main conclusion can be drawn here is that the proposed system can be used to recycle the waste heat and produced cooling. However, the COP is still low.

Vehicle Systems Engineering and Integration Activities

DTIC Science & Technology

2012-08-31

of the Assistant Secretary of Defense for Research and Engineering. Its objective is to fundamentally change the capabilities for the design...Reliability Improvements for Selected Equipment) package. The standard RISE package includes an upgraded propulsion system ( turbocharged engine and...component of the RISE powertrain incorporated into the original M113A3 and M730A2 vehicles is the turbocharged 275 hp 6V53T engine from Detroit Diesel

Computer-aided system design

NASA Technical Reports Server (NTRS)

Walker, Carrie K.

1991-01-01

A technique has been developed for combining features of a systems architecture design and assessment tool and a software development tool. This technique reduces simulation development time and expands simulation detail. The Architecture Design and Assessment System (ADAS), developed at the Research Triangle Institute, is a set of computer-assisted engineering tools for the design and analysis of computer systems. The ADAS system is based on directed graph concepts and supports the synthesis and analysis of software algorithms mapped to candidate hardware implementations. Greater simulation detail is provided by the ADAS functional simulator. With the functional simulator, programs written in either Ada or C can be used to provide a detailed description of graph nodes. A Computer-Aided Software Engineering tool developed at the Charles Stark Draper Laboratory (CSDL CASE) automatically generates Ada or C code from engineering block diagram specifications designed with an interactive graphical interface. A technique to use the tools together has been developed, which further automates the design process.

ENGINEERING DESIGN CRITERIA FOR SUB-SLAB DEPRESSURIZATION SYSTEMS IN LOW-PERMEABILTY SOLIDS

EPA Science Inventory

The report describes the development of engineering design criteria for the successful design, installation, and operation of sub-slab depressurization systems, based on radon (Rn) mitigation experience on 14 slab-on-grade houses in South Central Florida. The Florida houses are c...

An adaptable multiple power source for mass spectrometry and other scientific instruments.

PubMed

Lin, T-Y; Anderson, G A; Norheim, R V; Prost, S A; LaMarche, B L; Leach, F E; Auberry, K J; Smith, R D; Koppenaal, D W; Robinson, E W; Paša-Tolić, L

2015-09-01

An Adaptable Multiple Power Source (AMPS) system has been designed and constructed. The AMPS system can provide up to 16 direct current (DC) (±400 V; 5 mA), 4 radio frequency (RF) (two 500 VPP sinusoidal signals each, 0.5-5 MHz) channels, 2 high voltage sources (±6 kV), and one ∼40 W, 250 °C temperature-regulated heater. The system is controlled by a microcontroller, capable of communicating with its front panel or a computer. It can assign not only pre-saved fixed DC and RF signals but also profiled DC voltages. The AMPS system is capable of driving many mass spectrometry components and ancillary devices and can be adapted to other instrumentation/engineering projects.

Energy Efficient Engine (E3) controls and accessories detail design report

NASA Technical Reports Server (NTRS)

Beitler, R. S.; Lavash, J. P.

1982-01-01

An Energy Efficient Engine program has been established by NASA to develop technology for improving the energy efficiency of future commercial transport aircraft engines. As part of this program, a new turbofan engine was designed. This report describes the fuel and control system for this engine. The system design is based on many of the proven concepts and component designs used on the General Electric CF6 family of engines. One significant difference is the incorporation of digital electronic computation in place of the hydromechanical computation currently used.

Environmental Barrier Coatings for Turbine Engines: A Design and Performance Perspective

NASA Technical Reports Server (NTRS)

Zhu, Dongming; Fox, Dennis S.; Ghosn, Louis; Smialek, James L.; Miller, Robert A.

2009-01-01

Ceramic thermal and environmental barrier coatings (TEBC) for SiC-based ceramics will play an increasingly important role in future gas turbine engines because of their ability to effectively protect the engine components and further raise engine temperatures. However, the coating long-term durability remains a major concern with the ever-increasing temperature, strength and stability requirements in engine high heat-flux combustion environments, especially for highly-loaded rotating turbine components. Advanced TEBC systems, including nano-composite based HfO2-aluminosilicate and rare earth silicate coatings are being developed and tested for higher temperature capable SiC/SiC ceramic matrix composite (CMC) turbine blade applications. This paper will emphasize coating composite and multilayer design approach and the resulting performance and durability in simulated engine high heat-flux, high stress and high pressure combustion environments. The advances in the environmental barrier coating development showed promise for future rotating CMC blade applications.

Metabolic engineering of Clostridium acetobutylicum for enhanced production of butyric acid.

PubMed

Jang, Yu-Sin; Woo, Hee Moon; Im, Jung Ae; Kim, In Ho; Lee, Sang Yup

2013-11-01

Clostridium acetobutylicum has been considered as an attractive platform host for biorefinery due to its metabolic diversity. Considering its capability to overproduce butanol through butyrate, it was thought that butyric acid can also be efficiently produced by this bacterium through metabolic engineering. The pta-ctfB-deficient C. acetobutylicum CEKW, in which genes encoding phosphotransacetylase and CoA-transferase were knocked out, was assessed for its potential as a butyric acid producer in fermentations with four controlled pH values at 5.0, 5.5, 6.0, and 6.4. Butyric acid could be best produced by fermentation of the CEKW at pH 6.0, resulting in the highest titer of 26.6 g/l, which is 6.4 times higher than that obtained with the wild type. However, due to the remaining solventogenic ability of the CEKW, 3.6 g/l solvents were also produced. Thus, the CEKW was further engineered by knocking out the adhE1-encoding aldehyde/alcohol dehydrogenase to prevent solvent production. Batch fermentation of the resulting C. acetobutylicum HCEKW at pH 6.0 showed increased butyric acid production to 30.8 g/l with a ratio of butyric-to-acetic acid (BA/AA) of 6.6 g/g and a productivity of 0.72 g/l/h from 86.9 g/l glucose, while negligible solvent (0.8 g/l ethanol only) was produced. The butyric acid titer, BA/AA ratio, and productivity obtained in this study were the highest values reported for C. acetobutylicum, and the BA/AA ratio and productivity were also comparable to those of native butyric acid producer Clostridium tyrobutyricum. These results suggested that the simultaneous deletion of the pta-ctfB-adhE1 in C. acetobutylicum resulted in metabolic switch from biphasic to acidogenic fermentation, which enhanced butyric acid production.

Engine Performance (Section C: Emission Control Systems). Auto Mechanics Curriculum Guide. Module 3. Instructor's Guide.

ERIC Educational Resources Information Center

Rains, Larry

This engine performance (emission control systems) module is one of a series of competency-based modules in the Missouri Auto Mechanics Curriculum Guide. Topics of this module's five units are: positive crankcase ventilation (PCV) and evaporative emission control systems; exhaust gas recirculation (EGR); air injection and catalytic converters;…

Intelligence Decision Support System for the Republic of Korea Army Engineer Operation.

DTIC Science & Technology

1987-06-01

34.:L;’:Ce mnechanism and prUnin2 -must be collected in a computer program for it to -’’, nroerlx escribed as possessing Artificial Intelligence (AI). [Ref...At84 128 INTELLIGENCE DECISION SUPPORT SYSTEM FOR THE REPUBLIC I/i OF KOREA ARMY ENGINEER OPERATION(U) NAVAL POSTGRADUATE SCHOOL MONTEREY CA C K...POSTGRADUATE SCHOOL q~J.00 ’Monterey, California THESIS INTELLIGENCE DECISION SUPPORT SYSTEM FOR THE REPUBLIC OF KOREA ARMY ENGINEER OPERATION by Jang

Advanced Expander Test Bed Program

DTIC Science & Technology

1991-04-01

CHAMBER COOLANT DP 503. CHAMBER COOLANT DT 896. ETA C* 0.993 CHAMBER Q 12371. ENGINE STATION CONDITIONS FUEL SYSTEM CONDITIONS STATION PRESS TEMP FLOW...1597.3 452.5 7.44 1507.1 0.62 CHAMBER 1500.0 * OXYGEN SYSTEM CONDITIONS STATION PRESS TEMP FLOW ENTHALPY DENSITY ENGINE INLET 70.0 163.0- 44.64 61.2...FUEL SYSTEM CONOITIONS PRESS TEMP FLOM ENTHALPY OENSITY STATION (PSIA) (DEG R) (LB/SEC) [(BTU/LB) (LB/FT31 ENGINE INLET 73.0 38.0 7.440 -104.8 4.389

Launch Deployment Assembly Human Engineering Analysis

NASA Technical Reports Server (NTRS)

Loughead, T.

1996-01-01

This report documents the human engineering analysis performed by the Systems Branch in support of the 6A cargo element design. The human engineering analysis is limited to the extra vehicular activities (EVA) which are involved in removal of various cargo items from the LDA and specific activities concerning deployment of the Space Station Remote Manipulator System (SSRMS).

6. Photographic copy of a photograph taken from pasteup negatives ...

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

6. Photographic copy of a photograph taken from paste-up negatives for U.S. Army Corps of Engineers document GF-500-MCP, entitled "Grand Forks Site RLS Army Operating Drawings, Master Composite Photographs for SAFEGUARD TSE Systems and Equipment," Page 9, dated 1 September 1974 (original document and negatives in possession of U.S. Army Corps of Engineers, Huntsville, AL). Photographer unknown. View of remote launch operations building, power generation room #124, showing no-break units NB-1002 (A) and NB-1001 (B). This equipment consisted of a 150 horsepower, d.c. operational motor which drove, on each end of the extended shaft, a 70 kw generator and a 30 kw generator unit. It was designed to provide continuous power service for launch equipment. In particular, the photo is an excellent representation of the shock isolation scheme, as evidenced by the supporting air springs and equipment platform - Stanley R. Mickelsen Safeguard Complex, Remote Launch Operations Building, Near Service Road exit from Patrol Road, Nekoma, Cavalier County, ND

Processing Of Neem And Jatropha Methyl Esters -Alternative Fuels From Vegetable Oil

NASA Astrophysics Data System (ADS)

Ramasubramanian, S.; Manavalan, S.; Gnanavel, C.; Balakrishnan, G.

2017-03-01

Biodiesel is an alternative fuel for diesel engine. The methyl esters of vegetable oils, known as biodiesel are becoming increasingly popular because of their low environmental impact and potential as a green alternative fuel for diesel engine. This paper deals with the manufacturing process of Biodiesel from jatropha and neem oil. Biodiesel was prepared from neem oil and jatropha oil, the transestrified having kinematic viscosity of 3 & 2.6 centistokes, methanol ratio is 6:1 & 5.1respectively. The secondary solution is preheated at 65 C & 60 C and reaction temperature is maintained at 60C & 55 C and reaction time is 60 minutes approximately with NaOH catalyst and low viscosity oil is allowed to settle 24 hours. The average yield of neem and jatropha methyl esters was about 85%. These methyl esters shows excellent alternative under optimum condition for fossil fuels.

77 FR 25781 - Twenty-First Meeting: RTCA Special Committee 203, Unmanned Aircraft Systems

Federal Register 2010, 2011, 2012, 2013, 2014

2012-05-01

.... The agenda will include the following: May 22, 2012 Opening Plenary Session Welcome/Introductions... Breakout Sessions Systems Engineering Workgroup C&C Workgroup S&A Workgroup Safety Workgroup Wednesday, May...

Numerical Modeling of Pulse Detonation Rocket Engine Gasdynamics and Performance

NASA Technical Reports Server (NTRS)

2003-01-01

This paper presents viewgraphs on the numerical modeling of pulse detonation rocket engines (PDRE), with an emphasis on the Gasdynamics and performance analysis of these engines. The topics include: 1) Performance Analysis of PDREs; 2) Simplified PDRE Cycle; 3) Comparison of PDRE and Steady-State Rocket Engines (SSRE) Performance; 4) Numerical Modeling of Quasi 1-D Rocket Flows; 5) Specific PDRE Geometries Studied; 6) Time-Accurate Thrust Calculations; 7) PDRE Performance (Geometries A B C and D); 8) PDRE Blowdown Gasdynamics (Geom. A B C and D); 9) PDRE Geometry Performance Comparison; 10) PDRE Blowdown Time (Geom. A B C and D); 11) Specific SSRE Geometry Studied; 12) Effect of F-R Chemistry on SSRE Performance; 13) PDRE/SSRE Performance Comparison; 14) PDRE Performance Study; 15) Grid Resolution Study; and 16) Effect of F-R Chemistry on SSRE Exit Species Mole Fractions.

Electro-impulse de-icing of a turbofan engine inlet

NASA Technical Reports Server (NTRS)

Zumwalt, G. W.

1985-01-01

The application of electromagnetic impulse deicing (EIDI) systems to turbofan engine inlets on business aircraft has been investigated experimentally. The tests were performed in the Icing Research Tunnel at NASA's Lewis Research Center. The deicing system testbed was a Falcon Fanjet 20 engine nacelle. The effectiveness of various deicing coil configurations and mount designs were compared, and design parameters were developed specifically for EIDI systems in turbofan engines. Flight tests were also carried out at altitudes in the range 3000-6000 ft corresponding to a temperature range of -3 to -8 C. It is shown that the ice particles removed from the engine inlet by the deicing system were small enough for the engine to ingest. Tentative design specifications are given with respect to the optimum coil configuration, and operating power of a EIDI production candidate.

Measurements of C V flows from thermal charge-exchange excitation in divertor plasmas

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

Zaniol, B.; Isler, R. C.; Brooks, N. H.

2001-10-01

Certain transitions of C IV (C{sup 3+}) from n=7 to n=6 ({approx}7226 {angstrom}) and from n=6 to n=5 ({approx}4660 {angstrom}) sometimes appear much brighter in tokamak divertors than expected for electron-impact excitation from the ground state. This situation occurs because of charge exchange between C V (C{sup 4+}) and recycling thermal deuterium atoms in the n=2 level. As a result, it is possible to extend parallel flow measurements of carbon, which have previously been performed on C II--C IV ions using Doppler shift spectroscopy, to include flows of the He-like C V ions. The work described here includes modeling ofmore » the spectral features, correlation of state populations with classical Monte Carlo trajectory (CTMC) predictions, and applications to flow measurements in the DIII-D divertor [Plasma Physics Controlled Nuclear Fusion Research 1986 (International Atomic Energy Agency, Vienna, 1987), Vol. I, p. 159; Proceedings of the 18th IEEE/NPSS Symposium on Fusion Engineering, Albuquerque (Institute of Electrical and Electronic Engineers, Piscataway, 1999), p. 515].« less

Measurements of C V flows from thermal charge-exchange excitation in divertor plasmas

NASA Astrophysics Data System (ADS)

Zaniol, B.; Isler, R. C.; Brooks, N. H.; West, W. P.; Olson, R. E.

2001-10-01

Certain transitions of C IV (C3+) from n=7 to n=6 (≈7226 Å) and from n=6 to n=5 (≈4660 Å) sometimes appear much brighter in tokamak divertors than expected for electron-impact excitation from the ground state. This situation occurs because of charge exchange between C V (C4+) and recycling thermal deuterium atoms in the n=2 level. As a result, it is possible to extend parallel flow measurements of carbon, which have previously been performed on C II-C IV ions using Doppler shift spectroscopy, to include flows of the He-like C V ions. The work described here includes modeling of the spectral features, correlation of state populations with classical Monte Carlo trajectory (CTMC) predictions, and applications to flow measurements in the DIII-D divertor [Plasma Physics Controlled Nuclear Fusion Research 1986 (International Atomic Energy Agency, Vienna, 1987), Vol. I, p. 159; Proceedings of the 18th IEEE/NPSS Symposium on Fusion Engineering, Albuquerque (Institute of Electrical and Electronic Engineers, Piscataway, 1999), p. 515].

Optimization of fatty alcohol biosynthesis pathway for selectively enhanced production of C12/14 and C16/18 fatty alcohols in engineered Escherichia coli

PubMed Central

2012-01-01

Background With the increasing stress from oil price and environmental pollution, aroused attention has been paid to the microbial production of chemicals from renewable sources. The C12/14 and C16/18 alcohols are important feedstocks for the production of surfactants and detergents, which are widely used in the most respected consumer detergents, cleaning products and personal care products worldwide. Though bioproduction of fatty alcohols has been carried out in engineered E. coli, several key problems have not been solved in earlier studies, such as the quite low production of C16/18 alcohol, the lack of optimization of the fatty alcohol biosynthesis pathway, and the uncharacterized performance of the engineered strains in scaled-up system. Results We improved the fatty alcohol production by systematically optimizing the fatty alcohol biosynthesis pathway, mainly targeting three key steps from fatty acyl-acyl carrier proteins (ACPs) to fatty alcohols, which are sequentially catalyzed by thioesterase, acyl-coenzyme A (CoA) synthase and fatty acyl-CoA reductase. By coexpression of thioesterase gene BTE, acyl-CoA synthase gene fadD and fatty acyl-CoA reductase gene acr1, 210.1 mg/L C12/14 alcohol was obtained. A further optimization of expression level of BTE, fadD and acr1 increased the C12/14 alcohol production to 449.2 mg/L, accounting for 75.0% of the total fatty alcohol production (598.6 mg/L). In addition, by coexpression of thioesterase gene ‘tesA, acyl-CoA synthase gene fadD and fatty acyl-CoA reductase gene FAR, 101.5 mg/L C16/18 alcohol was obtained, with C16/18 alcohol accounting for 89.2% of the total fatty alcohol production. Conclusions To our knowledge, this is the first report on selective production of C12/14 and C16/18 alcohols by microbial fermentation. This work achieved high-specificity production of both C12/14 and C16/18 alcohols. The encouraging 598.6 mg/L of fatty alcohols represents the highest titer reported so far. In addition, the 101.5 mg/L 89.2% C16/18 alcohol suggests an important breakthrough in C16/18 alcohol production. A more detailed optimization of the expression level of fatty alcohol biosynthesis pathway may contribute to a further improvement of fatty alcohol production. PMID:22607313

Deep Seafloor Acoustic Backscattering Measurements Using Sea Beam

DTIC Science & Technology

1985-12-01

Am. Soc. Mech. Eng. Ocean engineering Symposium (submitted). C. de Moustier, "A Sea Beam acoustic data acquisition system" , MPL TM-379 Marine...paper submitted to the American Society of Mechanical Engineers for its symposium on Ocean Engineering. As such, it also reviews the approaches...seafloor down to maximum ocean depth (11 km). Since 1977 when the first system became operational aboard the French R/V Jean Charcot, nine other

Efficient Parallel Engineering Computing on Linux Workstations

NASA Technical Reports Server (NTRS)

Lou, John Z.

2010-01-01

A C software module has been developed that creates lightweight processes (LWPs) dynamically to achieve parallel computing performance in a variety of engineering simulation and analysis applications to support NASA and DoD project tasks. The required interface between the module and the application it supports is simple, minimal and almost completely transparent to the user applications, and it can achieve nearly ideal computing speed-up on multi-CPU engineering workstations of all operating system platforms. The module can be integrated into an existing application (C, C++, Fortran and others) either as part of a compiled module or as a dynamically linked library (DLL).

Shuttle Radar Topography Mission (SRTM) Flight System Design and Operations Overview

NASA Technical Reports Server (NTRS)

Shen, Yuhsyen; Shaffer, Scott J.; Jordan, Rolando L.

2000-01-01

This paper provides an overview of the Shuttle Radar Topography Mission (SRTM), with emphasis on flight system implementation and mission operations from systems engineering perspective. Successfully flown in February, 2000, the SRTM's primary payload consists of several subsystems to form the first spaceborne dual-frequency (C-band and X-band) fixed baseline interferometric synthetic aperture radar (InSAR) system, with the mission objective to acquire data sets over 80% of Earth's landmass for height reconstruction. The paper provides system architecture, unique design features, engineering budgets, design verification, in-flight checkout and data acquisition of the SRTM payload, in particular for the C-band system. Mission operation and post-mission data processing activities are also presented. The complexity of the SRTM as a system, the ambitious mission objective, the demanding requirements and the high interdependency between multi-disciplined subsystems posed many challenges. The engineering experience and the insight thus gained have important implications for future spaceborne interferometric SAR mission design and implementation.

14 CFR 35.22 - Feathering propellers.

Code of Federal Regulations, 2010 CFR

2010-01-01

... control systems that use engine oil to feather must incorporate a method to allow the propeller to feather if the engine oil system fails. (c) Feathering propellers must be designed to be capable of... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Feathering propellers. 35.22 Section 35.22...

14 CFR 35.22 - Feathering propellers.

Code of Federal Regulations, 2012 CFR

2012-01-01

... control systems that use engine oil to feather must incorporate a method to allow the propeller to feather if the engine oil system fails. (c) Feathering propellers must be designed to be capable of... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false Feathering propellers. 35.22 Section 35.22...

14 CFR 35.22 - Feathering propellers.

Code of Federal Regulations, 2014 CFR

2014-01-01

... control systems that use engine oil to feather must incorporate a method to allow the propeller to feather if the engine oil system fails. (c) Feathering propellers must be designed to be capable of... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false Feathering propellers. 35.22 Section 35.22...

14 CFR 35.22 - Feathering propellers.

Code of Federal Regulations, 2013 CFR

2013-01-01

... control systems that use engine oil to feather must incorporate a method to allow the propeller to feather if the engine oil system fails. (c) Feathering propellers must be designed to be capable of... 14 Aeronautics and Space 1 2013-01-01 2013-01-01 false Feathering propellers. 35.22 Section 35.22...

14 CFR 35.22 - Feathering propellers.

Code of Federal Regulations, 2011 CFR

2011-01-01

... control systems that use engine oil to feather must incorporate a method to allow the propeller to feather if the engine oil system fails. (c) Feathering propellers must be designed to be capable of... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false Feathering propellers. 35.22 Section 35.22...

Evidence for entanglement at high temperatures in an engineered molecular magnet

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

Reis, Mario S; Soriano, Stephane; Moreira Dos Santos, Antonio F

The molecular compound [Fe-2(mu(2)-oxo)(C3H4N2)(6)(C2O4)(2)] was designed and synthesized for the first time and its structure was determined using single-crystal X-ray diffraction. The magnetic susceptibility of this compound was measured from 2 to 300 K. The analysis of the susceptibility data using protocols developed for other spin singlet ground-state systems indicates that the quantum entanglement would remain at temperatures up to 732 K, significantly above the highest entanglement temperature reported to date. The large gap between the ground state and the first-excited state (282 K) suggests that the spin system may be somewhat immune to decohering mechanisms. Our measurements strongly suggestmore » that molecular magnets are promising candidate platforms for quantum information processing.« less

Profiles of Successful and Unsuccessful Graduate Engineering Management Students.

DTIC Science & Technology

1983-09-01

AFIT GPA 24. AFIT GPA in the following categories: a. Applied engineering b. Socio-humanistic c. Analytical The next chapter is a review of the...Deficiency (1- None, 2- GPA, 3- Class(s), 4- Thesis, AI G5- 2&3, 6- 2,3,&4, 7- 3&4, 8- 2&4) ______AFIT GPA 1-___GPA for Applied Engineering Courses GPA...50 AFIT Cumulative GPA 51 - 54 Applied Engineering GPA -J 55 - 58 Socio-Humanistic GPA 59 - 62 Analytical GPA 107 361173320500620

14 CFR 27.1121 - General.

Code of Federal Regulations, 2013 CFR

2013-01-01

... prevent local hot spots; (c) Exhaust gases must discharge clear of the engine air intake, fuel system... after the failure of an attempted engine start; (g) Each exhaust heat exchanger must incorporate means...

14 CFR 27.1121 - General.

Code of Federal Regulations, 2012 CFR

2012-01-01

... prevent local hot spots; (c) Exhaust gases must discharge clear of the engine air intake, fuel system... after the failure of an attempted engine start; (g) Each exhaust heat exchanger must incorporate means...

14 CFR 27.1121 - General.

Code of Federal Regulations, 2014 CFR

2014-01-01

... prevent local hot spots; (c) Exhaust gases must discharge clear of the engine air intake, fuel system... after the failure of an attempted engine start; (g) Each exhaust heat exchanger must incorporate means...

14 CFR 27.1121 - General.

Code of Federal Regulations, 2010 CFR

2010-01-01

... prevent local hot spots; (c) Exhaust gases must discharge clear of the engine air intake, fuel system... after the failure of an attempted engine start; (g) Each exhaust heat exchanger must incorporate means...

14 CFR 27.1121 - General.

Code of Federal Regulations, 2011 CFR

2011-01-01

... prevent local hot spots; (c) Exhaust gases must discharge clear of the engine air intake, fuel system... after the failure of an attempted engine start; (g) Each exhaust heat exchanger must incorporate means...

48 CFR 1852.243-70 - Engineering change proposals.

Code of Federal Regulations, 2011 CFR

2011-10-01

... 48 Federal Acquisition Regulations System 6 2011-10-01 2011-10-01 false Engineering change... and Clauses 1852.243-70 Engineering change proposals. As prescribed in 1843.205-70(a)(1), insert the following clause, modified to suit contract type: Engineering Change Proposals (FEB 1998) (a) Definitions...

48 CFR 1852.243-70 - Engineering change proposals.

Code of Federal Regulations, 2013 CFR

2013-10-01

... 48 Federal Acquisition Regulations System 6 2013-10-01 2013-10-01 false Engineering change... and Clauses 1852.243-70 Engineering change proposals. As prescribed in 1843.205-70(a)(1), insert the following clause, modified to suit contract type: Engineering Change Proposals (FEB 1998) (a) Definitions...

48 CFR 1852.243-70 - Engineering change proposals.

Code of Federal Regulations, 2010 CFR

2010-10-01

... 48 Federal Acquisition Regulations System 6 2010-10-01 2010-10-01 true Engineering change... and Clauses 1852.243-70 Engineering change proposals. As prescribed in 1843.205-70(a)(1), insert the following clause, modified to suit contract type: Engineering Change Proposals (FEB 1998) (a) Definitions...

48 CFR 1852.243-70 - Engineering change proposals.

Code of Federal Regulations, 2014 CFR

2014-10-01

... 48 Federal Acquisition Regulations System 6 2014-10-01 2014-10-01 false Engineering change... and Clauses 1852.243-70 Engineering change proposals. As prescribed in 1843.205-70(a)(1), insert the following clause, modified to suit contract type: Engineering Change Proposals (FEB 1998) (a) Definitions...

48 CFR 1852.243-70 - Engineering change proposals.

Code of Federal Regulations, 2012 CFR

2012-10-01

... 48 Federal Acquisition Regulations System 6 2012-10-01 2012-10-01 false Engineering change... and Clauses 1852.243-70 Engineering change proposals. As prescribed in 1843.205-70(a)(1), insert the following clause, modified to suit contract type: Engineering Change Proposals (FEB 1998) (a) Definitions...

Stationary Engineering. Science Manual--2.

ERIC Educational Resources Information Center

Frost, Harold J.; Steingress, Frederick M.

This second-year student manual contains 140 brief related science lessons applying science and math to trade activities in the field of stationary engineering. The lessons are organized into 16 units: (1) Introduction to Stationary Engineering, (2) Engineering Fundamentals, (3) Steam Boilers, (4) Boiler Fittings, (5) Boilerroom System, (6)…

The System of Systems Architecture Feasibility Assessment Model

DTIC Science & Technology

2016-06-01

OF SYSTEMS ARCHITECTURE FEASIBILITY ASSESSMENT MODEL by Stephen E. Gillespie June 2016 Dissertation Supervisor Eugene Paulo THIS PAGE...Dissertation 4. TITLE AND SUBTITLE THE SYSTEM OF SYSTEMS ARCHITECTURE FEASIBILITY ASSESSMENT MODEL 5. FUNDING NUMBERS 6. AUTHOR(S) Stephen E...SoS architecture feasibility assessment model (SoS-AFAM). Together, these extend current model- based systems engineering (MBSE) and SoS engineering

Advanced Environmental Barrier Coating Development for SiC-SiC Ceramic Matrix Composite Components

NASA Technical Reports Server (NTRS)

Zhu, Dongming; Harder, Bryan; Hurst, Janet B.; Halbig, Michael Charles; Puleo, Bernadette J.; Costa, Gustavo; Mccue, Terry R.

2017-01-01

This presentation reviews the NASA advanced environmental barrier coating (EBC) system development for SiC-SiC Ceramic Matrix Composite (CMC) combustors particularly under the NASA Environmentally Responsible Aviation, Fundamental Aeronautics and Transformative Aeronautics Concepts Programs. The emphases have been placed on the current design challenges of the 2700-3000F capable environmental barrier coatings for low NOX emission combustors for next generation turbine engines by using advanced plasma spray based processes, and the coating processing and integration with SiC-SiC CMCs and component systems. The developments also have included candidate coating composition system designs, degradation mechanisms, performance evaluation and down-selects; the processing optimizations using TriplexPro Air Plasma Spray Low Pressure Plasma Spray (LPPS), Plasma Spray Physical Vapor Deposition and demonstration of EBC-CMC systems. This presentation also highlights the EBC-CMC system temperature capability and durability improvements under the NASA development programs, as demonstrated in the simulated engine high heat flux, combustion environments, in conjunction with high heat flux, mechanical creep and fatigue loading testing conditions.

Improvements to Filter Debris Analysis in Aviation Propulsion Systems

DTIC Science & Technology

2012-12-01

been applied to the external scavenge filter fitted to the T56 -A-14 and T-56-A-15 engines (powering the P3C and C130-H aircraft respectively...15 3. AUTOMATED ANALYSIS OF T56 ENGINE OIL FILTER DEBRIS...................... 15 3.1 Historical Practices...for T56 .................................................................................... 15 3.2 FilterCHECK 290

Experimental temperature analysis of simple & hybrid earth air tunnel heat exchanger in series connection at Bikaner Rajasthan India

NASA Astrophysics Data System (ADS)

Jakhar, O. P.; Sharma, Chandra Shekhar; Kukana, Rajendra

2018-05-01

The Earth Air Tunnel Heat Exchanger System is a passive air-conditioning system which has no side effect on earth climate and produces better cooling effect and heating effect comfortable to human body. It produces heating effect in winter and cooling effect in summer with the minimum power consumption of energy as compare to other air-conditioning devices. In this research paper Temperature Analysis was done on the two systems of Earth Air Tunnel Heat Exchanger experimentally for summer cooling purpose. Both the system was installed at Mechanical Engineering Department Government Engineering College Bikaner Rajasthan India. Experimental results concludes that the Average Air Temperature Difference was found as 11.00° C and 16.27° C for the Simple and Hybrid Earth Air Tunnel Heat Exchanger in Series Connection System respectively. The Maximum Air Temperature Difference was found as 18.10° C and 23.70° C for the Simple and Hybrid Earth Air Tunnel Heat Exchanger in Series Connection System respectively. The Minimum Air Temperature Difference was found as 5.20° C and 11.70° C for the Simple and Hybrid Earth Air Tunnel Heat Exchanger in Series Connection System respectively.

Training Extract, AFSC 113X0B, Flight Engineer, Helicopter Qualified.

DTIC Science & Technology

1982-12-01

TRAINING .................................................................. 1I0 SE. GENERAL rLIGHT RULES A 9 C t | 7. PeRFORM INSPECIIOIS 12 7A... TRAINING .................................................................. lIC 6E. GENERAL FLIGHT RULES A a C...ME"BERS PERFORMING I-A I PROGRAM GENERATED VECTOR IMEMBERS/ NO TYPE VECTOR MEAN - SC DESCRIPTION I TN. SEP J.6 2.J TRAINING EMPHASIS RATINSS I IIOS

The CF6 Jet Engine Performance Improvement - Low Pressure Turbine Active Clearance Control

NASA Technical Reports Server (NTRS)

Beck, B. D.; Fasching, W. A.

1982-01-01

A low pressure turbine (LPT) active clearance control (ACC) cooling system was developed to reduce the fuel consumption of current CF6-50 turbofan engines for wide bodied commercial aircraft. The program performance improvement goal of 0.3% delta sfc was determined to be achievable with an improved impingement cooling system. The technology enables the design of an optimized manifold and piping system which is capable of a performance gain of 0.45% delta sfc.

Performance Evaluation of the NEXT Ion Engine

NASA Technical Reports Server (NTRS)

Soulas, George C.; Domonkos, Matthew T.; Patterson, Michael J.

2003-01-01

The performance test results of three NEXT ion engines are presented. These ion engines exhibited peak specific impulse and thrust efficiency ranges of 4060 4090 s and 0.68 0.69, respectively, at the full power point of the NEXT throttle table. The performance of the ion engines satisfied all project requirements. Beam flatness parameters were significantly improved over the NSTAR ion engine, which is expected to improve accelerator grid service life. The results of engine inlet pressure and temperature measurements are also presented. Maximum main plenum, cathode, and neutralizer pressures were 12,000 Pa, 3110 Pa, and 8540 Pa, respectively, at the full power point of the NEXT throttle table. Main plenum and cathode inlet pressures required about 6 hours to increase to steady-state, while the neutralizer required only about 0.5 hour. Steady-state engine operating temperature ranges throughout the power throttling range examined were 179 303 C for the discharge chamber magnet rings and 132 213 C for the ion optics mounting ring.

Mechanical evaluation of nHAp scaffold coated with poly-3-hydroxybutyrate for bone tissue engineering.

PubMed

Foroughi, Mohammad Reza; Karbasi, Saeed; Ebrahimi-Kahrizsangi, Reza

2013-02-01

Regeneration of bone, cartilage and osteochondral tissues by tissue engineering has attracted intense attention due to its potential advantages over the traditional replacement of tissues with synthetic implants. Nevertheless, there is still a dearth of ideal or suitable scaffolds based on porous biomaterials, and the present study was undertaken to develop and evaluate a useful porous composite scaffold system. In this study, nano hydroxyapatite (nHAp) powder made (about 35-45 nm) by heating at temperature of 900 degrees C and porous hydroxyapatite (40, 50 and 60 wt% solution) for making scaffold, by using Polyurethane sponge replication method. In order to increase the scaffolds mechanical properties, they coated with 2, 4 and 6 wt% Poly-3-hydroxybutyrate (P3HB) for 30 sec and 60 sec, respectively; after the scaffold coated by Polymer and survey results, this scaffold is nHAp/P3HB composite. Based on these results, this scaffold is an optimized one among three tested above mentioned composition and can be utilized in bone tissue engineering. In the result, the best of scaffold is with 50 wt% HAp and 6 wt% P3HB and porosity of present is between 80-90% with compressive strength and modulus 1.51 MPa and 22.73 MPa, respectively, that it can be application in bone tissue engineering.

Minimum Specific Fuel Consumption of a Liquid-Cooled Multicylinder Aircraft Engine as Affected by Compression Ratio and Engine Operating Conditions

NASA Technical Reports Server (NTRS)

Brun, Rinaldo J.; Feder, Melvin S.; Harries, Myron L.

1947-01-01

An investigation was conducted on a 12-cylinder V-type liquid-cooled aircraft engine of 1710-cubic-inch displacement to determine the minimum specific fuel consumption at constant cruising engine speed and compression ratios of 6.65, 7.93, and 9.68. At each compression ratio, the effect.of the following variables was investigated at manifold pressures of 28, 34, 40, and 50 inches of mercury absolute: temperature of the inlet-air to the auxiliary-stage supercharger, fuel-air ratio, and spark advance. Standard sea-level atmospheric pressure was maintained at the auxiliary-stage supercharger inlet and the exhaust pressure was atmospheric. Advancing the spark timing from 34 deg and 28 deg B.T.C. (exhaust and intake, respectively) to 42 deg and 36 deg B.T.C. at a compression ratio of 6.65 resulted in a decrease of approximately 3 percent in brake specific fuel consumption. Further decreases in brake specific fuel consumption of 10.5 to 14.1 percent (depending on power level) were observed as the compression ratio was increased from 6.65 to 9.68, maintaining at each compression ratio the spark advance required for maximum torque at a fuel-air ratio of 0.06. This increase in compression ratio with a power output of 0.585 horsepower per cubic inch required a change from . a fuel- lend of 6-percent triptane with 94-percent 68--R fuel at a compression ratio of 6.65 to a fuel blend of 58-percent, triptane with 42-percent 28-R fuel at a compression ratio of 9.68 to provide for knock-free engine operation. As an aid in the evaluation of engine mechanical endurance, peak cylinder pressures were measured on a single-cylinder engine at several operating conditions. Peak cylinder pressures of 1900 pounds per square inch can be expected at a compression ratio of 9.68 and an indicated mean effective pressure of 320 pounds per square inch. The engine durability was considerably reduced at these conditions.

Crawler Acquisition and Testing Demonstration Project Management Plan

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

DEFIGH-PRICE, C.

2000-10-23

If the crawler based retrieval system is selected, this project management plan identifies the path forward for acquiring a crawler/track pump waste retrieval system, and completing sufficient testing to support deploying the crawler for as part of a retrieval technology demonstration for Tank 241-C-104. In the balance of the document, these activities will be referred to as the Crawler Acquisition and Testing Demonstration. During recent Tri-Party Agreement negotiations, TPA milestones were proposed for a sludge/hard heel waste retrieval demonstration in tank C-104. Specifically one of the proposed milestones requires completion of a cold demonstration of sufficient scale to support finalmore » design and testing of the equipment (M-45-03G) by 6/30/2004. A crawler-based retrieval system was one of the two options evaluated during the pre-conceptual engineering for C-104 retrieval (RPP-6843 Rev. 0). The alternative technology procurement initiated by the Hanford Tanks Initiative (HTI) project, combined with the pre-conceptual engineering for C-104 retrieval provide an opportunity to achieve compliance with the proposed TPA milestone M-45-03H. This Crawler Acquisition and Testing Demonstration project management plan identifies the plans, organizational interfaces and responsibilities, management control systems, reporting systems, timeline and requirements for the acquisition and testing of the crawler based retrieval system. This project management plan is complimentary to and supportive of the Project Management Plan for Retrieval of C-104 (RPP-6557). This project management plan focuses on utilizing and completing the efforts initiated under the Hanford Tanks Initiative (HTI) to acquire and cold test a commercial crawler based retrieval system. The crawler-based retrieval system will be purchased on a schedule to support design of the waste retrieval from tank C-104 (project W-523) and to meet the requirement of proposed TPA milestone M-45-03H. This Crawler Acquisition and Testing Demonstration project management plan includes the following: (1) Identification of acquisition strategy and plan to obtain a crawler based retrieval system; (2) Plan for sufficient cold testing to make a decision for W-523 and to comply with TPA Milestone M-45-03H; (3) Cost and schedule for path forward; (4) Responsibilities of the participants; and (5) The plan is supported by updated Level 1 logics, a Relative Order of Magnitude cost estimate and preliminary project schedule.« less

Engine condition monitoring: CF6 family 60's through the 80's

NASA Technical Reports Server (NTRS)

Kent, H. J.; Dienger, G.

1981-01-01

The on condition program is described in terms of its effectiveness as a maintenance tool both at the line station as well as at home base by the early detection of engine faults, erroneous instrumentation signals and by verification of engine health. The system encompasses all known methods from manual procedures to the fully automated airborne integrated data system.

Software For Computer-Aided Design Of Control Systems

NASA Technical Reports Server (NTRS)

Wette, Matthew

1994-01-01

Computer Aided Engineering System (CAESY) software developed to provide means to evaluate methods for dealing with users' needs in computer-aided design of control systems. Interpreter program for performing engineering calculations. Incorporates features of both Ada and MATLAB. Designed to be flexible and powerful. Includes internally defined functions, procedures and provides for definition of functions and procedures by user. Written in C language.

A design support simulation of the augmentor wing jet STOL research aircraft

NASA Technical Reports Server (NTRS)

Rumsey, P. C.; Spitzer, R. E.; Glende, W. L. B.

1972-01-01

The modification of a C-8A (De Havilland Buffalo) aircraft to a STOL configuration is discussed. The modification consisted of the installation of an augmentor-wing jet flap system. System design requirements were investigated for the lateral and directional flight control systems, the lateral and directional axes stability augmentation systems, the engine and Pegasus nozzle control systems, and the hydraulic systems. Operational techniques for STOL landings, control of engine failures, and pilot techniques for improving engine-out go-around performance were examined. Design changes have been identified to correct deficiencies in areas of the airplane control sytems and to improve the airplane flying qualities.

Evaluation of some candidate materials for automobile thermal reactors in engine-dynamometer screening tests

NASA Technical Reports Server (NTRS)

Oldrieve, R. E.

1971-01-01

Fourteen materials were evaluated in engine screening tests on full-size thermal reactors for automobile engine pollution control systems. Cyclic test-stand engine operation provided 2 hours at 1040 C and a 20-minute air-cool to 70 C each test cycle. Each reactor material was exposed to 83 cycles in 200 hours of engine testing. On the basis of resistance to oxidation and distortion, the best materials included two ferritic iron alloys (Ge 1541 and Armco 18S/R), several commercial oxidation-resistant coatings on AlSl 651 (19-9 DL), and possibly uncoated AISI 310. The best commercial coatings were Cr-Al, Ni-Cr, and a glass ceramic.

Metabolic engineering of Clostridium acetobutylicum for butyric acid production with high butyric acid selectivity.

PubMed

Jang, Yu-Sin; Im, Jung Ae; Choi, So Young; Lee, Jung Im; Lee, Sang Yup

2014-05-01

A typical characteristic of the butyric acid-producing Clostridium is coproduction of both butyric and acetic acids. Increasing the butyric acid selectivity important for economical butyric acid production has been rather difficult in clostridia due to their complex metabolic pathways. In this work, Clostridium acetobutylicum was metabolically engineered for highly selective butyric acid production. For this purpose, the second butyrate kinase of C. acetobutylicum encoded by the bukII gene instead of butyrate kinase I encoded by the buk gene was employed. Furthermore, metabolic pathways were engineered to further enhance the NADH-driving force. Batch fermentation of the metabolically engineered C. acetobutylicum strain HCBEKW (pta(-), buk(-), ctfB(-) and adhE1(-)) at pH 6.0 resulted in the production of 32.5g/L of butyric acid with a butyric-to-acetic acid ratio (BA/AA ratio) of 31.3g/g from 83.3g/L of glucose. By further knocking out the hydA gene (encoding hydrogenase) in the HCBEKW strain, the butyric acid titer was not further improved in batch fermentation. However, the BA/AA ratio (28.5g/g) obtained with the HYCBEKW strain (pta(-), buk(-), ctfB(-), adhE1(-) and hydA(-)) was 1.6 times higher than that (18.2g/g) obtained with the HCBEKW strain at pH 5.0, while no improvement was observed at pH 6.0. These results suggested that the buk gene knockout was essential to get a high butyric acid selectivity to acetic acid in C. acetobutylicum. Copyright © 2014 International Metabolic Engineering Society. Published by Elsevier Inc. All rights reserved.

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...

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...

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...

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...

Combustion Stability of the Gas Generator Assembly from J-2X Engine E10001 and Powerpack Tests

NASA Technical Reports Server (NTRS)

Hulka, J. R.; Kenny, R. L.; Casiano, M. J.

2013-01-01

Testing of a powerpack configuration (turbomachinery and gas generator assembly) and the first complete engine system of the liquid oxygen/liquid hydrogen propellant J-2X rocket engine have been completed at the NASA Stennis Space Center. The combustion stability characteristics of the gas generator assemblies on these two systems are of interest for reporting since considerable effort was expended to eliminate combustion instability during early development of the gas generator assembly with workhorse hardware. Comparing the final workhorse gas generator assembly development test data to the powerpack and engine system test data provides an opportunity to investigate how the nearly identical configurations of gas generator assemblies operate with two very different propellant supply systems one the autonomous pressure-fed test configuration on the workhorse development test stand, the other the pump-fed configurations on the powerpack and engine systems. The development of the gas generator assembly and the elimination of the combustion instability on the pressure-fed workhorse test stand have been reported extensively in the two previous Liquid Propulsion Subcommittee meetings 1-7. The powerpack and engine system testing have been conducted from mid-2011 through 2012. All tests of the powerpack and engine system gas generator systems to date have been stable. However, measureable dynamic behavior, similar to that observed on the pressure-fed test stand and reported in Ref. [6] and attributed to an injection-coupled response, has appeared in both powerpack and engine system tests. As discussed in Ref. [6], these injection-coupled responses are influenced by the interaction of the combustion chamber with a branch pipe in the hot gas duct that supplies gaseous helium to pre-spin the turbine during the start transient. This paper presents the powerpack and engine system gas generator test data, compares these data to the development test data, and provides additional combustion stability analyses of the configurations.

An Application of Quality Control Theory to Vendor-Supplied Parts at an Aerospace Manufacturing Company.

DTIC Science & Technology

1985-08-01

presently used on the ATF3-6, TFE731 -2, -3, TPE331, GTCP660 and TSCP700 engines. Substantiation Metallurgical V Testing Tnstructions Control Part Name Part... TFE731 -2, -3 Fan 3072162 Ti-6-4 5001 C1.-2 L’$S52458 1st Stg.Comp. 3072193 Ti-6-4 5001 C1.-l AF5395 2nd Stg.Comp. 3072191 Ti-6-4 5001 CI.-I AF5395 W...Control Part Nam~e Part No. material (STIT~eouirernents Specification TFE731 -2, -3 4th Stg.Conp. 3072.93 Ti-6-4 5001 C1.-1 AF5395 HP Comp. 3072639 Ti-6-2

Systems of frequency distributions for water and environmental engineering

NASA Astrophysics Data System (ADS)

Singh, Vijay P.

2018-09-01

A wide spectrum of frequency distributions are used in hydrologic, hydraulic, environmental and water resources engineering. These distributions may have different origins, are based on different hypotheses, and belong to different generating systems. Review of literature suggests that different systems of frequency distributions employed in science and engineering in general and environmental and water engineering in particular have been derived using different approaches which include (1) differential equations, (2) distribution elasticity, (3) genetic theory, (4) generating functions, (5) transformations, (6) Bessel function, (7) expansions, and (8) entropy maximization. This paper revisits these systems of distributions and discusses the hypotheses that are used for deriving these systems. It also proposes, based on empirical evidence, another general system of distributions and derives a number of distributions from this general system that are used in environmental and water engineering.

Building Information Modeling (BIM): A Road Map for Implementation to Support MILCON Transformation and Civil Works Projects within the U.S. Army Corps of Engineers

DTIC Science & Technology

2006-10-01

benefit from BIM , but the data that can be gleaned from the BIM model will also feed many systems and users. What is Needed and What Must be...ER D C TR -0 6 -1 0 Building Information Modeling ( BIM ) A Road Map for Implementation To Support MILCON Transformation and Civil Works...compliant with National BIM Standard (NBIMS) 8 Centers of Standardization (COS) productive in BIM by 2008 All districts productive in NBIMS

Vulnerability Methodology and Protective Measures for Aircraft Fire and Explosion Hazards. Volume 2. Aircraft Engine Nacelle Fire Test Programs. Part 1. Fire Detection, Fire Extinguishment and Surface Ignition Studies

DTIC Science & Technology

1986-01-01

by sensors in the test cell and sampled, digitized, averaged, and calibrated by the facility computer system. The data included flowrates calculated ...before the next test could be started. This required about 2 minutes. 6.4 Combat Damage Testing Appendix C contains calculations and analysis...were comparable (Figure 7-5). Agent quantities required per MIL-E-22285 were again calculated using the equations noted in paragraph 7.1.1. The

Determination of two-stroke engine exhaust noise by the method of characteristics

NASA Technical Reports Server (NTRS)

Jones, A. D.; Brown, G. L.

1981-01-01

A computational technique was developed for the method of characteristics solution of a one-dimensional flow in a duct as applied to the wave action in an engine exhaust system. By using the method, it was possible to compute the unsteady flow in both straight pipe and tuned expansion chamber exhaust systems as matched to the flow from the cylinder of a small two-stroke engine. The radiated exhaust noise was then determined by assuming monopole radiation from the tailpipe outlet. Very good agreement with experiment on an operation engine was achieved in the calculation of both the third octave radiated noise and the associated pressure cycles at several locations in the different exhaust systems. Of particular interest is the significance of nonlinear behavior which results in wave steepening and shock wave formation. The method computes the precise paths on the x-t plane of a finite number of C(sub +), C(sub -) and P characteristics, thereby obtaining high accuracy in determining the tailpipe outlet velocity and the radiated noise.

Determination of two-stroke engine exhaust noise by the method of characteristics

NASA Astrophysics Data System (ADS)

Jones, A. D.; Brown, G. L.

1981-06-01

A computational technique was developed for the method of characteristics solution of a one-dimensional flow in a duct as applied to the wave action in an engine exhaust system. By using the method, it was possible to compute the unsteady flow in both straight pipe and tuned expansion chamber exhaust systems as matched to the flow from the cylinder of a small two-stroke engine. The radiated exhaust noise was then determined by assuming monopole radiation from the tailpipe outlet. Very good agreement with experiment on an operation engine was achieved in the calculation of both the third octave radiated noise and the associated pressure cycles at several locations in the different exhaust systems. Of particular interest is the significance of nonlinear behavior which results in wave steepening and shock wave formation. The method computes the precise paths on the x-t plane of a finite number of C(sub +), C(sub -) and P characteristics, thereby obtaining high accuracy in determining the tailpipe outlet velocity and the radiated noise.

Tripropellant engine study

NASA Technical Reports Server (NTRS)

Wheeler, D. B.

1977-01-01

Work conducted was devoted to three main tasks. Thermochemical equilibrium performance data were assembled to establish the expected performance calculations of the mode 1 engine propellant combinations and thermodynamic and transport data for the products of combustion. Turbine drive gas characteristics were also established. Thrust chamber and nozzle cooling studies were devoted to the evaluation of H2, C3H8, CH4, and RP-1 as coolants in the existing SSME cooling circuit geometry. It was found that all these candidate coolants are feasible without limiting the desired operating conditions with the exception of RP-1, which would limit the maximum P(c) to 2000 psia. RP-1 could be used, however, to cool the nozzle only without imposing the chamber pressure limit. A total of 15 candidate engine system cycles were selected and a preliminary engine system balance was conducted for 12 of these systems to establish component operating flowrates, pressures and temperatures. It was found that the staged combustion cycles employing fuel rich LOX/hydrocarbon turbine drive gases are power limited.

Department of Defense In-House RDT and E Activities Report for Fiscal Year 1990

DTIC Science & Technology

1990-01-01

equipment systems. Advanced personnel and cargo airdrop system. 1FUNCTIONS/EQUIPMENT!/FACI LITIES Biotechnology lab, materials characterization lab...4 Airworthines. Qualification Test Directorate ..... .................................... 5 Armament Rrsearch . Developaent & Eaguiecring Center...1), exploratory development (6.2), advanced development (6.3), engineering development (6.4), management support (6.5), operational systems support

14 CFR 33.7 - Engine ratings and operating limitations.

Code of Federal Regulations, 2010 CFR

2010-01-01

... turbine wheel inlet gas. (5) Pressure of— (i) Fuel at the fuel inlet; and (ii) Oil at the main oil gallery. (6) Accessory drive torque and overhang moment. (7) Component life. (8) Turbosupercharger turbine wheel r.p.m. (c) For turbine engines, ratings and operating limitations are established relating to the...

CRITERIA POLLUTANT EMISSIONS FROM INTERNAL COMBUSTION ENGINES IN THE NATURAL GAS INDUSTRY VOLUME II. APPENDICES A-I

EPA Science Inventory

The report summarizes emission factors for criteria pollutants (NOx, CO, CH4, C2H6, THC, NMHC, and NMEHC) from stationary internal combustion engines and gas turbines used in the natural gas industry. The emission factors were calculated from test results from five test campaigns...

CRITERIA POLLUTANT EMISSIONS FROM INTERNAL COMBUSTION ENGINES IN THE NATURAL GAS INDUSTRY VOLUME 1. TECHNICAL REPORT

EPA Science Inventory

The report summarizes emission factors for criteria pollutants (NOx, CO, CH4, C2H6, THC, NMHC, and NMEHC) from stationary internal combustion engines and gas turbines used in the natural gas industry. The emission factors were calculated from test results from five test campaigns...

76 FR 80406 - Notice Pursuant to the National Cooperative Research and Production Act of 1993-American Society...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-12-23

... DEPARTMENT OF JUSTICE Antitrust Division Notice Pursuant to the National Cooperative Research and Production Act of 1993--American Society of Mechanical Engineers Notice is hereby given that, on December 6....C. 4301 et seq. (``the Act''), American Society of Mechanical Engineers (``ASME'') has filed written...

A study on the dynamics of the zraP gene expression profile and its application to the construction of zinc adsorption bacteria.

PubMed

Ravikumar, Sambandam; Yoo, Ik-keun; Lee, Sang Yup; Hong, Soon Ho

2011-11-01

Zinc ion plays essential roles in biological chemistry. Bacteria acquire Zn(2+) from the environment, and cellular concentration levels are controlled by zinc homeostasis systems. In comparison with other homeostatic systems, the ZraSR two-component system was found to be more efficient in responding to exogenous zinc concentrations. To understand the dynamic response of the bacterium ZraSR two-component system with respect to exogenous zinc concentrations, the genetic circuit of the ZraSR system was integrated with a reporter protein. This study was helpful in the construction of an E. coli system that can display selective metal binding peptides on the surface of the cell in response to exogenous zinc. The engineered bacterial system for monitoring exogenous zinc was successfully employed to detect levels of zinc as low as 0.001 mM, which directly activates the expression of chimeric ompC(t)--zinc binding peptide gene to remove zinc by adsorbing a maximum of 163.6 μmol of zinc per gram of dry cell weight. These results indicate that the engineered bacterial strain developed in the present study can sense the specific heavy metal and activates a cell surface display system that acts to remove the metal.

Composite containment systems for jet engine fan blades

NASA Technical Reports Server (NTRS)

Smith, G. T.

1981-01-01

The use of composites in fan blade containment systems is investigated and the associated structural benefits of the composite system design are identified. Two basic types of containment structures were investigated. The short finned concept was evaluated using Kevlar/epoxy laminates for fins which were mounted in a 6061 T-6 aluminum ring. The long fin concept was evaluated with Kevlar/epoxy, 6Al4V titanium, and 2024 T-3 aluminum fins. The unfinned configurations consisted of the base-line steel sheet, a circumferentially oriented aluminum honeycomb, and a Kevlar cloth filled ring. Results obtained show that a substantial reduction in the fan blade containment system weight is possible. Minimization of damage within the engine arising from impact interaction between blade debris and the engine structure is also achieved.

14 CFR 33.67 - Fuel system.

Code of Federal Regulations, 2012 CFR

2012-01-01

... STANDARDS: AIRCRAFT ENGINES Design and Construction; Turbine Aircraft Engines § 33.67 Fuel system. (a) With... range with the fuel initially saturated with water at 80 °F (27 °C) and having 0.025 fluid ounces per gallon (0.20 milliliters per liter) of free water added and cooled to the most critical condition for...

A Modular Aero-Propulsion System Simulation of a Large Commercial Aircraft Engine

NASA Technical Reports Server (NTRS)

DeCastro, Jonathan A.; Litt, Jonathan S.; Frederick, Dean K.

2008-01-01

A simulation of a commercial engine has been developed in a graphical environment to meet the increasing need across the controls and health management community for a common research and development platform. This paper describes the Commercial Modular Aero Propulsion System Simulation (C-MAPSS), which is representative of a 90,000-lb thrust class two spool, high bypass ratio commercial turbofan engine. A control law resembling the state-of-the-art on board modern aircraft engines is included, consisting of a fan-speed control loop supplemented by relevant engine limit protection regulator loops. The objective of this paper is to provide a top-down overview of the complete engine simulation package.

CAR/FoxP3-engineered T regulatory cells target the CNS and suppress EAE upon intranasal delivery

PubMed Central

2012-01-01

Background Multiple sclerosis (MS) is an autoimmune disease of the central nervous system (CNS). In the murine experimental autoimmune encephalomyelitis (EAE) model of MS, T regulatory (Treg) cell therapy has proved to be beneficial, but generation of stable CNS-targeting Tregs needs further development. Here, we propose gene engineering to achieve CNS-targeting Tregs from naïve CD4 cells and demonstrate their efficacy in the EAE model. Methods CD4+ T cells were modified utilizing a lentiviral vector system to express a chimeric antigen receptor (CAR) targeting myelin oligodendrocyte glycoprotein (MOG) in trans with the murine FoxP3 gene that drives Treg differentiation. The cells were evaluated in vitro for suppressive capacity and in C57BL/6 mice to treat EAE. Cells were administered by intranasal (i.n.) cell delivery. Results The engineered Tregs demonstrated suppressive capacity in vitro and could efficiently access various regions in the brain via i.n cell delivery. Clinical score 3 EAE mice were treated and the engineered Tregs suppressed ongoing encephalomyelitis as demonstrated by reduced disease symptoms as well as decreased IL-12 and IFNgamma mRNAs in brain tissue. Immunohistochemical markers for myelination (MBP) and reactive astrogliosis (GFAP) confirmed recovery in mice treated with engineered Tregs compared to controls. Symptom-free mice were rechallenged with a second EAE-inducing inoculum but remained healthy, demonstrating the sustained effect of engineered Tregs. Conclusion CNS-targeting Tregs delivered i.n. localized to the CNS and efficiently suppressed ongoing inflammation leading to diminished disease symptoms. PMID:22647574

Durability and Design Issues of Thermal/environmental Barrier Coatings on Sic/sic Ceramic Matrix Composites Under 1650 C Test Conditions

NASA Technical Reports Server (NTRS)

Zhu, Dong-Ming; Choi, Sung R.; Ghosn, Louis J.; Miller, Robert A.

2004-01-01

Ceramic thermal/environmental barrier coatings for SiC-based ceramics will play an increasingly important role in future gas turbine engines because of their ability to effectively protect the engine components and further raise engine temperatures. However, the coating durability remains a major concern with the ever-increasing temperature requirements. Currently, advanced T/EBC systems, which typically include a high temperature capable zirconia- (or hahia-) based oxide top coat (thermal barrier) on a less temperature capable mullite/barium-strontium-aluminosilicate (BSAS)/Si inner coat (environmental barrier), are being developed and tested for higher temperature capability Sic combustor applications. In this paper, durability of several thermal/environmental barrier coating systems on SiC/SiC ceramic matrix composites was investigated under laser simulated engine thermal gradient cyclic, and 1650 C (3000 F) test conditions. The coating cracking and delamination processes were monitored and evaluated. The effects of temperature gradients and coating configurations on the ceramic coating crack initiation and propagation were analyzed using finite element analysis (FEA) models based on the observed failure mechanisms, in conjunction with mechanical testing results. The environmental effects on the coating durability will be discussed. The coating design approach will also be presented.

State Analysis: A Control Architecture View of Systems Engineering

NASA Technical Reports Server (NTRS)

Rasmussen, Robert D.

2005-01-01

A viewgraph presentation on the state analysis process is shown. The topics include: 1) Issues with growing complexity; 2) Limits of common practice; 3) Exploiting a control point of view; 4) A glimpse at the State Analysis process; 5) Synergy with model-based systems engineering; and 6) Bridging the systems to software gap.