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  • Other Sources  (256)
  • AIRCRAFT PROPULSION AND POWER  (255)
  • Correlation
  • 1980-1984  (256)
  • 1950-1954
  • 1980  (256)
  • 1
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    Engineering Applications of Correlation & Spectral Analysis (1980)
    John Wiley & Sons
    In:  Basel, 375 pp., John Wiley & Sons, vol. 96, pp. 225, (ISBN 3-7643-7011-4)
    Details
    Publication Date: 1980
    Keywords: Textbook of engineering ; Data analysis / ~ processing ; Textbook of geophysics ; Correlation ; Spectrum
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    Preparing aircraft propulsion for a new era in energy and the environment (1980)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Improving fuel efficiency, new sources of jet fuel, and noise and emission control are subjects of NASA's aeronautics program. Projects aimed at attaining a 5% fuel savings for existing engines and a 13-22% savings for the next generation of turbofan engines using advanced components, and establishing a basis for turboprop-powered commercial air transports with 30-40% savings over conventional turbofan aircraft at comparable speeds and altitudes, are discussed. Fuel sources are considered in terms of reduced hydrogen and higher aromatic contents and resultant higher liner temperatures, and attention is given to lean burning, improved fuel atomization, higher freezing-point fuel, and deriving jet fuel from shale oil or coal. Noise sources including the fan, turbine, combustion process, and flow over internal struts, and attenuation using acoustic treatment, are discussed, while near-term reduction of polluting gaseous emissions at both low and high power, and far-term defining of the minimum gaseous-pollutant levels possible from turbine engines are also under study.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Astronautics and Aeronautics; 18; Jan. 198
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    State-of-the-art SiAlON materials (1980)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The state of the art of SiAlONs is examined. The review includes work on phase relations, crystal structure, synthesis, fabrication, and properties of various SiAlONs. The essential features of compositions, fabrication methods, and microstructure are reviewed. High temperature flexure strength, creep, fracture toughness, oxidation, and thermal shock resistance are discussed. These data are compared to those for some currently produced silicon nitride ceramics to assess the potential of SiAlON materials for use in advanced gas turbine engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Ceram. for Turbine Eng. Appl.; 15 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Space shuttle main engine digital controller (1980)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The controller provides responsive control of engine thrust and mixture ratio through the digital computer in the controller, updating the instructions to the engine control elements 50 times per second (every 20 milliseconds). Additionally, precise engine performance is achieved through closed loop control, utilizing 16 bit computation, 10 bit input/output resolution, and self calibrating analog-to-digital conversion. Engine reliability is enhanced by a dual redundant control system that allows normal operation after the first failure and a fail-safe shutdown after a second failure. The digital computer is programmable, allowing modification of engine control equations and constants by change of the stored program (software). The controller is packaged in a sealed, pressurized chassis with cooling provided by convection heat transfer through pin fins as part of the main chassis. The electronics are distributed on functional modules having special provisions for thermal and vibrational protection.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Advan. Control Systems for Aircraft Powerplants; 11 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Design, evaluation and test of an electronic, multivariable control for the F100 turbofan engine (1980)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: A digital, multivariable control design procedure for the F100 turbofan engine is described. The controller is based on locally linear synthesis techniques using linear, quadratic regulator design methods. The control structure uses an explicit model reference form with proportional and integral feedback near a nominal trajectory. Modeling issues, design procedures for the control law and the estimation of poorly measured variables are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Advan. Control Systems for Aircraft Powerplants; 21 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Computerized systems analysis and optimization of aircraft engine performance, weight, and life cycle costs (1980)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The computational techniques are described which are utilized at Lewis Research Center to determine the optimum propulsion systems for future aircraft applications and to identify system tradeoffs and technology requirements. Cycle performance, and engine weight can be calculated along with costs and installation effects as opposed to fuel consumption alone. Almost any conceivable turbine engine cycle can be studied. These computer codes are: NNEP, WATE, LIFCYC, INSTAL, and POD DRG. Examples are given to illustrate how these computer techniques can be applied to analyze and optimize propulsion system fuel consumption, weight and cost for representative types of aircraft and missions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD The Use of Computers as a Design Tool; 15 p
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    NASA TECHNICAL REPORTS
  • 7
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    Performance seeking controls (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A performance logic algorithm (PSL) was developed to optimize the performance of propulsion systems for component and sensor degradations by monitoring the performance of the engine system and minimizing thrust specific fuel consumption (TSFC) while retaining a constant engine net thrust. Engine constraints such as surge margin, speed, pressure, and temperature are observed. The PSL algorithm was applied to the quiet, clean, short haul experimental engine. Engine control set points were modified for component degradations in order to restore the nominal net thrust. Results show convergence to the optimum value can be obtained within 60 to 90 seconds, which makes the program acceptable to on line operation with present state of the art minicomputers. Tests indicate that in most cases the PSL algorithm offers some improvement in thrust specific fuel consumption over the manual throttle.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Propulsion Controls, 1979; p 11-17
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Multivarable nyquist array method with application to turbofan engine control (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Extensions to the multivariable Nyquist array (MNA) method are used to design a feedback control system for the quiet clean shorthaul experimental engine. The results of this design are compared with those obtained from the deployment of an alternate control system design on a full scale nonlinear, real time digital simulation. The results clearly demonstrate the utility of the MNA synthesis procedures for highly nonlinear sophisticated design applications.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Propulsion Controls, 1979; p 105-110
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  • 9
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    Propulsion controls (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Increased system requirements and functional integration with the aircraft have placed an increased demand on control system capability and reliability. To provide these at an affordable cost and weight and because of the rapid advances in electronic technology, hydromechanical systems are being phased out in favor of digital electronic systems. The transition is expected to be orderly from electronic trimming of hydromechanical controls to full authority digital electronic control. Future propulsion system controls will be highly reliable full authority digital electronic with selected component and circuit redundancy to provide the required safety and reliability. Redundancy may include a complete backup control of a different technology for single engine applications. The propulsion control will be required to communicate rapidly with the various flight and fire control avionics as part of an integrated control concept.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Propulsion Controls, 1979; p 49-59
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  • 10
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    VCE test bed engine for supersonic cruise research (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Various design concepts for a variable cycle engine applicable to a supersonic, mixed mission propulsion system which would combine the merits of a turbofan at subsonic operating conditions with those of a turbojet for supersonic operating conditions are briefly examined. In particular the integration of the variable area bypass injector with the core driven (aft fan block) fan stage is discussed and the technical benefits of the configuration are summarized.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Supersonic Cruise Res. 1979, Pt. 1; p 347-356
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    NASA TECHNICAL REPORTS
  • 11
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    Fuel system technology overview (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Fuel system research and technology studies are being conducted to investigate the correlations and interactions of aircraft fuel system design and environment with applicable characteristics of the fuel. Topics include: (1) analysis of in-flight fuel temperatures; (2) fuel systems for high freezing point fuels; (3) experimental study of low temperature pumpability; (4) full scale fuel tank simulation; and (5) rapid freezing point measurement.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels; p 195-203
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    NASA TECHNICAL REPORTS
  • 12
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    Combustion technology overview (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An overview of combustor technology developments required for use of broadened property fuels in jet aircraft is presented. The intent of current investigations is to determine the extent to which fuel properties can be varied, to obtain a data base of combustion - fuel quality effects, and to determine the trade-offs associated with broadened property fuels. Subcomponents of in-service combustors such as fuel injectors and liners, as well as air distributions and stoichiometry, are being altered to determine the extent to which fuel flexibility can be extended. Finally, very advanced technology consisting of new combustor concepts is being evolved to optimize the fuel flexibility of gas turbine combustors.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels; p 67-73
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    NASA TECHNICAL REPORTS
  • 13
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    Fuels research: Fuel thermal stability overview (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Alternative fuels or crude supplies are examined with respect to satisfying aviation fuel needs for the next 50 years. The thermal stability of potential future fuels is discussed and the effects of these characteristics on aircraft fuel systems are examined. Advanced fuel system technology and design guidelines for future fuels with lower thermal stability are reported.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels; p 161-168
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    NASA TECHNICAL REPORTS
  • 14
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    Preliminary studies of combustor sensitivity to alternative fuels (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Combustion problems associated with using alternative fuels ground power and aeropropulsion applications were studied. Rectangular sections designed to simulate large annular combustor test conditions were examined. The effects of using alternative fuels with reduced hydrogen content, increased aromatic content, and a broad variation in fuel property characteristics were also studied. Data of special interest were collected which include: flame radiation characteristics in the various combustor zones; the correponding increase in liner temperature from increased radiant heat flux; the effect of fuel bound nitrogen on oxides of nitrogen (NO sub x) emissions; and the overall total effect of fuel variations on exhaust emissions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels; p 153-160
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    NASA TECHNICAL REPORTS
  • 15
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    Outlook for alternative energy sources (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Predictions are made concerning the development of alternative energy sources in the light of the present national energy situation. Particular emphasis is given to the impact of alternative fuels development on aviation fuels. The future outlook for aircraft fuels is that for the near term, there possibly will be no major fuel changes, but minor specification changes may be possible if supplies decrease. In the midterm, a broad cut fuel may be used if current development efforts are successful. As synfuel production levels increase beyond the 1990's there may be some mixtures of petroleum-based and synfuel products with the possibility of some shale distillate and indirect coal liquefaction products near the year 2000.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 5-9
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    NASA TECHNICAL REPORTS
  • 16
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    F100 exhaust nozzle area control (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The details of the F100 nozzle mechanism design are highlighted, placing particular emphasis upon the evolution of design constraints or drivers from initial concept through current operational deployment. A kinematic description of the area control mechanism is given, and several environmental constraints which complicate the normal mechanism design process are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center Proc. of the 14th Aerospace Mech. Symp.; p 211-223
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    NASA TECHNICAL REPORTS
  • 17
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    Positive displacement type general-aviation engines: Summary and concluding remarks (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The activities of programs investigating various aspects of aircraft internal combustion engines are briefly described including developments in fuel injection technology, cooling systems and drag reduction, turbocharger technology, and stratified-charge rotary engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 313-314
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    NASA TECHNICAL REPORTS
  • 18
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    Advanced rotary engine studies (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A review of rotary engine developments relevant to a stratified charge rotary aircraft engine is presented. Advantages in module size and weight, fuel efficiency, reliability, and multi-fuel capability are discussed along with developments in turbocharging, increased mean effective pressure, improved apex seal/trochoid wear surfacing materials, and high strength and temperature aluminum casting alloys. A carbureted prototype aircraft engine is also described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 287-311
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    NASA TECHNICAL REPORTS
  • 19
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    AiResearch QCGAT engine: Acoustic test results (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The noise levels of the quiet, general aviation turbofan (QCGAT) engine were measured in ground static noise tests. The static noise levels were found to be markedly lower than the demonstrably quiet AiResearch model TFE731 engine. The measured QCGAT noise levels were correlated with analytical noise source predictions to derive free-field component noise predictions. These component noise sources were used to predict the QCGAT flyover noise levels at FAR Part 36 conditions. The predicted flyover noise levels are about 10 decibels lower than the current quietest business jets.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 65-100
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    NASA TECHNICAL REPORTS
  • 20
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    High-freezing-point fuel studies (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Considerable progress in developing the experimental and analytical techniques needed to design airplanes to accommodate fuels with less stringent low temperature specifications is reported. A computer technique for calculating fuel temperature profiles in full tanks was developed. The computer program is being extended to include the case of partially empty tanks. Ultimately, the completed package is to be incorporated into an aircraft fuel tank thermal analyser code to permit the designer to fly various thermal exposure patterns, study fuel temperatures versus time, and determine holdup.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 205-219
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    NASA TECHNICAL REPORTS
  • 21
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    Fuel/engine/airframe tradeoff study, phase 1 (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The effects of broadening the specifications for JP-4 and JP-8 fueled on the performance and cost of all USAF aircraft presently using JP-4 as well as those expected to be introduced into the force structure by 1983 are investigated. Test results indicated that there was no impact on engine performance, turbine durability, and coking, however there was a small maintenance cost increase as a result of a small combustor life decrease. Using JP-4 as standard fuel will avoid the use of high demand middle distillate fuels and give producers flexibility. Extensive use of JP-8 in the United States will increase middle distillate demand and cause a slight increase in engine hot-section maintenance. It is also concluded that the maximum allowable freeze point of JP-4 or JP-8 cannot be increased without degrading system performance and safety as critical conditions are approached.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 41-47
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    NASA TECHNICAL REPORTS
  • 22
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    Current jet fuel trends (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Data concerning the properties of commercial jet fuels during the period between 1974 and 1979 are discussed. During this period the average aromatics content of fuels increased from 16% to 17.5%. It is evident that the arrival of Alaska North Slope crude in 1977 had a significant impact upon the aromatics content of jet fuel supply at West Coast points with less effect upon the entire United States domestic market. This increase in aromatics has not been accompanied by a corresponding reduction in burning quality as measured by smoke point. There has been a reduction of .6 smoke point on the average. Looking at hydrogen content as a measure of burning quality, the all refinery average calculated hydrogen for 1978 was approximately 13.7%. The relationship between hydrogen content and aromatics content shows a slope of .043% reduction in hydrogen for 1% increase in aromatics.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 11-14
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    NASA TECHNICAL REPORTS
  • 23
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    NASA/General Electric broad-specification fuels combustion technology program, phase 1 (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The use of broad specification fuels in aircraft turbine engine combustion systems was examined. Three different combustor design concepts were evaluated for their ability to use broad specification fuels while meeting several specific emissions, performance, and durability goals. These combustor concepts covered a range from those having limited complexity and relatively low technical risk to those having high potential for achieving all of the program goals at the expense of increased technical risk.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 109-113
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    NASA TECHNICAL REPORTS
  • 24
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    Air Force fuel mainburner/turbine effects programs (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A program for the determination of fuel property effects on aircraft gas turbine engine mainburners and turbines is discussed. The six engines selected as test candidates are the J79, J85, J57, TF30, TF39, and F100. Fuels election is the responsibility of the contractors with two fuels as exceptions. The petroleum JP-4 is to be used as a baseline in all tests. The shale JP-4 is to be used in nearly all tests. Fuel properties are to be correlated with combustion system performance paramters. In addition, life predictions are to be made for combustor and turbine hardware. These predictions are to be based on a typical mission for each system, measured metal temperatures and temperature gradients, and oxidation/corrosion effects.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 99-103
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  • 25
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    The broadened-specification fuels combustion technology program at Pratt and Whitney Aircraft (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The impact of the use of broadened specification fuels on combustor design was investigated. Particular emphasis was placed on establishing the viability of various combustor modifications to permit the use of broadened specification fuels while meeting exhaust emissions and performance specifications and maintaining acceptable combustor operational and durability characteristics. Three different combustor concepts will be evaluated. Various design modifications on the operating capability of each of the combustor concepts with experimental referee broadened specification Fuel. The modifications that were evaluated included perturbations of the combustor airflow schedules to alter local stoichiometry and residence time histories revisions to the fuel injectors, and variations in liner cooling including the use of thermal barrier coatings and/or advanced cooling concepts.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 105-108
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  • 26
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    An overview of NASA research on positive displacement general-aviation engines (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The research and technology program related to improved and advanced general aviation engines is described. Current research is directed at the near-term improvement of conventional air-cooled spark-ignition piston engines and at future alternative engine systems based on all-new spark-ignition piston engines, lightweight diesels, and rotary combustion engines that show potential for meeting program goals in the midterm and long-term future. The conventional piston engine activities involve efforts on applying existing technology to improve fuel economy, investigation of key processes to permit leaner operation and reduce drag, and the development of cost effective technology to permit flight at high-altitudes where fuel economy and safety are improved. The advanced engine concepts activities include engine conceptual design studies and enabling technology efforts on the critical or key technology items.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 227-229
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  • 27
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    Summary of NASA QCGAT program (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The application of large turbofan engine technology to small general aviation turbofan engines to achieve low noise, low emissions, and acceptable fuel consumption is described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 189-193
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  • 28
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    New opportunities for future, small, General-Aviation Turbine Engines (GATE) (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The results of four independent contracted studies to explore the opportunities for future small turbine engines are summarized in a composite overview. Candidate advanced technologies are screened, various cycles and staging arrangements are parametrically evaluated, and optimum conceptual engines are identified for a range of 300 to 600 horsepower applications. Engine improvements of 20 percent in specific fuel consumption and 40 percent in engine cost were forecast using high risk technologies that could be technically demonstrated by 1988. The ensuing economic benefits are in the neighborhood of 20 to 30 percent for twin-engine aircraft currently powered by piston engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 195-219
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  • 29
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    Avco Lycoming quiet clean general aviation turbofan engine (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A fan module was developed using an existing turboshaft engine. The fan was designed using the latest in large engine noise control technology. A mixer was added to reduce the already low exhaust gas velocity. A nacelle incorporating sound treatment was provided for the test engine. A noise prediction model was used through the design process to evaluate the various design alternatives. Acoustic tests were then made to verify the prediction and identify the noise characteristics of the fan, core, jet, and sound treatment. Analysis of the recorded data yielded close agreement with the expected results. Core noise, as was expected, was the predominant source of noise for the quiet clean general aviation turbofan (QCGAT) engine. Flyover noise predictions were made which indicated that the Avco Lycoming QCGAT engine would meet the goals set for the QCGAT program.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 155-187
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  • 30
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    Low speed propellers: Impact of advanced technologies (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Sensitivity studies performed to evaluate the potential of several advanced technological elements on propeller performance, noise, weight, and cost for general aviation aircraft are discussed. Studies indicate that the application of advanced technologies to general aviation propellers can reduce fuel consumption in future aircraft an average of ten percent, meeting current regulatory noise limits. Through the use of composite blade construction, up to 25 percent propeller weight reduction can be achieved. This weight reduction in addition to seven percent propeller efficiency improvements through application of advanced technologies result in four percent reduction in direct operating costs, ten percent reduction in aircraft acquisition cost, and seven percent lower gross weight for general aviation aircraft.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 327-343
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  • 31
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    NASA propeller noise research (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The research in propeller noise prediction, noise/performance optimization, and interior reduction is described. Selected results are presented to illustrate the status of the technology and the direction of future research.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 405-420
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  • 32
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    Advanced propeller aerodynamic analysis (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The analytical approaches as well as the capabilities of three advanced analyses for predicting propeller aerodynamic performance are presented. It is shown that two of these analyses use a lifting line representation for the propeller blades, and the third uses a lifting surface representation.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 375-385
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  • 33
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    NASA propeller technology program (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A program on propeller technology applicable to both low and high speed general aviation aircraft is summarized, and the overall program objectives and approach are outlined.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 315-325
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    Lightweight diesel aircraft engines for general aviation (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A methodical design study was conducted to arrive at new diesel engine configurations and applicable advanced technologies. Two engines are discussed and the description of each engine includes concept drawings. A performance analysis, stress and weight prediction, and a cost study were also conducted. This information was then applied to two airplane concepts, a six-place twin and a four-place single engine aircraft. The aircraft study consisted of installation drawings, computer generated performance data, aircraft operating costs and drawings of the resulting airplanes. The performance data shows a vast improvement over current gasoline-powered aircraft. At the completion of this basic study, the program was expanded to evaluate a third engine configuration. This third engine incorporates the best features of the original two, and its design is currently in progress. Preliminary information on this engine is presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 247-285
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  • 35
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    Avco Lycoming QCGAT program design cycle, demonstrated performance and emissions (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A high bypass ratio, twin spool turbofan engine of modular design which incorporates a front fan module driven by a modified LTS101 core engine was tested. The engine is housed in a nacelle incorporating full length fan ducting with sound treatment in both the inlet and fan discharge flow paths. Design goals of components and results of component tests are presented together with full engine test results. The rationale behind the combustor design selected for the engine is presented as well as the emissions test results. Total system (engine and nacelle) test results are included.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 135-154
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  • 36
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    Effect of fuel molecular structure on soot formation in gas turbine combustion (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The effect of fuel variations at the same hydrogen content on the formation of soot in a gas turbine combustor was studied. Six fuels were burned to a combustor over a matrix of about 50 test conditions with test conditions ranging over 500-1800 kPa (5-18 atm) pressure and 500-1000 K burner inlet temperature; fuel-air ratios were varied from 0.008-0.024. Flame radiation measurements were made through a sapphire window toward the end of the primary zone. The hydrogen content of the six test fuels ranged from 12.80 to 12.88%. Five fuels emphasized hydrocarbon types: (mono, di, and tricyclic), naphthenes (decalin) and partially hydrogenated aromatics (tetralin); the sixth fuel emphasized final boiling point.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 147-152
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  • 37
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    Fuel property effects in stirred combustors (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Soot formation in strongly backmixed combustion was investigated using the jet-stirred combustor (JSC). This device provided a combustion volume in which temperature and combustion were uniform. It simulated the recirculating characteristics of the gas turbine primary zone; it was in this zone where mixture conditions were sufficiently rich to produce soot. Results indicate that the JSC allows study of soot formation in an aerodynamic situation revelant to gas turbines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 139-146
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  • 38
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    Soot formation and burnout in flames (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The amount of soot formed when burning a benzene/hexane mixture in a turbulent combustor was examined. Soot concentration profiles in the same combustor for kerosene fuel are given. The chemistry of the formation of soot precursors, the nucleation, growth and subsequent burnout of soot particles, and the effect of mixing on the previous steps were considered.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 131-137
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  • 39
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    Antimisting kerosene (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The antimisting additive ((FM-9) was tested in terms of its propulsion systems performance. The effect of the additive on engine operation was evaluated, operating problems were identified, the adaptability of engines to antimisting kerosene was assessed, and the potential viability of this fuel for use in present and future fan jet engines was determined.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels Jul. 1980; p 125-130
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  • 40
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    Atomization of broad specification aircraft fuels (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The atomization properties of liquid fuels for the potential use in aircraft gas turbine engines are discussed. The significance of these properties are addressed with respect to the ignition and subsequent combustion behavior of the fuel spray/air mixture. It is shown that the fuel properties which affect the atomization behavior (viscosity, surface tension, and density) are less favorable for the broad specification fuels as compared to with those for conventional fuels.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels Jul. 1980; p 117-124
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  • 41
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    Fuels research: Combustion effects overview (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The effects of broadened property fuels on gas turbine combustors were assessed. Those physical and chemical properties of fuels that affect aviation gas turbine combustion were isolated and identified. Combustion sensitivity to variations in particular fuel properties were determined. Advanced combustion concepts and subcomponents that could lessen the effect of using broadened property fuels were also identified.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels; p 115-116
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  • 42
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    NASA broadened-specification fuels combustion technology program (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The broadened-Specification Fuels Combustion Technology program's purpose is to evolve and demonstrate the technology required to enable current and next generation high-thrust, high-bypass-ratio turbofan engines to use fuels with broadened properties and to verify the evolved technology in full scale engine tests. The three phases of the program are combustor concept screening, combustor optimization testing, and engine verification testing. Constraints for designing combustion systems are outlined and problems to be expected in the use of broadened properties fuels are listed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels p95-98 (SEE N80-29300 20-07)
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  • 43
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    Fuel character effects on the J79 and F101 engine combustion systems (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The effects of select fuel property variations on two major engine classifications are summarized. Thirteen refined and blended fuels were used which exhibited significant variations in hydrogen content, aromatic type, initial boiling point, final boiling point, and viscosity. Trends were very similar but the degree of fuel sensitivity was not constant. For both systems the dominant fuel property during high pressure operation was found to be fuel hydrogen content. For operation at low pressure test points the fuel volatility and viscosity became the dominant fuel properties for both systems. Aromatic type and final boiling point did not significantly affect combustion data. Correlations of other fuel properties with these and other performance parameters are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 83-93
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  • 44
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    Military jet fuel from shale oil (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Investigations leading to a specification for aviation turbine fuel produced from whole crude shale oil are described. Refining methods involving hydrocracking, hydrotreating, and extraction processes are briefly examined and their production capabilities are assessed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 49-57
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  • 45
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    Aviation fuels outlook (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Options for satisfying the future demand for commercial jet fuels are analyzed. It is concluded that the most effective means to this end are to attract more refiners to the jet fuel market and encourage development of processes to convert oil shale and coal to transportation fuels. Furthermore, changing the U.S. refineries fuel specification would not significantly alter jet fuel availability.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 15-24
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  • 46
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    AiResearch QCGAT engine, airplane, and nacelle design features (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The quiet, clean, general aviation turbofan engine and nacelle system was designed and tested. The engine utilized the core of the AiResearch model TFE731-3 engine and incorporated several unique noise- and emissions-reduction features. Components that were successfully adapted to this core include the fan, gearbox, combustor, low-pressure turbine, and associated structure. A highly versatile workhorse nacelle incorporating interchangeable acoustic and hardwall duct liners, showed that large-engine attenuation technology could be applied to small propulsion engines. The application of the mixer compound nozzle demonstrated both performance and noise advantages on the engine. Major performance, emissions, and noise goals were demonstrated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 11-43
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  • 47
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    High-speed-propeller wind-tunnel aeroacoustic results (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Some aerodynamic concepts are presented together with an explanation of how these concepts are applied to advanced propeller design. The unique features of this propulsion system are addressed with emphasis on the design concepts being considered for the high speed turboprop. More particular emphasis is given to the blade sweep, long blade chords, and the large number of blades.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 361-374
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  • 48
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    Determination of jet fuel thermal deposit rate using a modified JFTOT (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Three fuels having different breakpoint temperatures were studied in the modified jet fuel thermal oxidation tester. The lower stability fuel with a breakpoint of 240 C was first stressed at a constant temperature. After repeating this procedure at several different temperatures, an Arrehenius plot was drawn from the data. The correlation coefficient and the energy of activation were calculated to be 0.97 and 8 kcal/mole respectively. Two other fuels having breakpoint temperatures of 271 C and 285 C were also studied in a similar manner. A straight line was drawn through the data at a slope equivalent to the slope of the lower stability fuel. The deposit formation rates for the three fuels were determined at 260 C, and a relative deposit formation rate at this temperature was calculated and plotted as a function of the individual fuel's breakpoint temperatures.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 181-184
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    Experimental combustor study program (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Advanced combustor concepts are evaluated as a means of accommodating possible future broad specification fuels. The three advanced double annular combustor concepts consisted of (1) a concept employing high pressure drop fuel nozzles for improved atomization, (2) a concept with premixing tubes in the main stage, and (3) a concept with the pilot stage on the inside and the main stage on the sideout, which is the reverse of the other two concepts. All of the advanced concepts show promise for reduced sensitivity to fuel hydrogen content. Some hardware problems were encountered, but these problems could be quickly resolved if refinement tests were conducted. The design with the premixing main stage was selected for a parametric test because of its low NOx emissions level, carbon free dome, and very low dome temperatures which were essentially independent of fuel type. The other advanced designs also had low done temperatures. The premixing dome design liner temperatures exhibited less sensitivity to fuel type than did the base-line combustor, although more sensitivity than observed for concept 1. The inner liner hot spot and the observed smoke results for the premixing design suggest that the fuel-air mixture was not as uniform as desired.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 75-82
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    Fuels characterization studies (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Current analytical techniques used in the characterization of broadened properties fuels are briefly described. Included are liquid chromatography, gas chromatography, and nuclear magnetic resonance spectroscopy. High performance liquid chromatographic ground-type methods development is being approached from several directions, including aromatic fraction standards development and the elimination of standards through removal or partial removal of the alkene and aromatic fractions or through the use of whole fuel refractive index values. More sensitive methods for alkene determinations using an ultraviolet-visible detector are also being pursued. Some of the more successful gas chromatographic physical property determinations for petroleum derived fuels are the distillation curve (simulated distillation), heat of combustion, hydrogen content, API gravity, viscosity, flash point, and (to a lesser extent) freezing point.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels; p 59-65
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    Future aviation fuels overview (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The outlook for aviation fuels through the turn of the century is briefly discussed and the general objectives of the NASA Lewis Alternative Aviation Fuels Research Project are outlined. The NASA program involves the evaluation of potential characteristics of future jet aircraft fuels, the determination of the effects of those fuels on engine and fuel system components, and the development of a component technology to use those fuels.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels; p 1-4
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  • 52
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    Advanced turboprop potential for high speed (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A turboprop propulsion system for general aviation aircraft, allowing high speed flight (to 0.8 Mach) is discussed. Design methodologies for aerodynamic and acoustic considerations and the performance and cost advantages of a prop-fan aircraft are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 345-359
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  • 53
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    QCGAT aircraft/engine design for reduced noise and emissions (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The high bypass ratio QCGAT engine played an important role in shaping the aircraft design. The aircraft which evolved is a sleek, advanced design, six-place aircraft with 3538 kg (7,800 lb) maximum gross weight. It offers a 2778 kilometer (1500 nautical mile) range with cruise speed of 0.5 Mach number and will take-off and land on the vast majority of general aviation airfields. Advanced features include broad application of composite materials and a supercritical wing design with winglets. Full-span fowler flaps were introduced to improve landing capability. Engines are fuselage-mounted with inlets over the wing to provide shielding of fan noise by the wing surfaces. The design objectives, noise, and emission considerations, engine cycle and engine description are discussed as well as specific design features.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 101-133
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  • 54
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    AiResearch QCGAT engine performance and emissions tests (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Results of aerodynamic performance and emission tests, conducted on a specially designed QCGAT engine in the 17,793-N (4,000 lb) thrust class, are presented. Performance of the AiResearch QCGAT engine was excellent throughout all testing. No serious mechanical malfunctions were encountered, and no significant test time was lost due to engine-related problems. Emissions were drastically reduced over similar engines, and the engine exhibited good smoke performance.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 45-64
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  • 55
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    NASA Research in Aeropropulsion (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The role of the Lewis Research Center in aeronautical propulsion is described. The state of the art in engine systems and components are discussed and some of the problems that confront the civil and military aeronautic sectors are addressed. Some of the programs that are under way are summarized with emphasis on the future needs and opportunities in aeronautics.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Impact for the 80's: Proc. of a Conf. on Selected Technol. for Business and Ind.; p 11-26
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  • 56
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    Propulsion control and control theory: A new research focus (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Technological developments necessary for the implementation of advanced digital control concepts for aircraft propulsion are identified and discussed. Developments associated with the replacement analog controllers with digital control systems, sensors and actuators, and control modes and software are reported.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Propulsion Controls, 1979; p 89-95
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    Should we attempt global (inlet engine airframe) control design? (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The feasibility of multivariable design of the entire airplane control system is briefly addressed. An intermediate step in that direction is to design a control for an inlet engine augmentor system by using multivariable techniques. The supersonic cruise large scale inlet research program is described which will provide an opportunity to develop, integrate, and wind tunnel test a control for a mixed compression inlet and variable cycle engine. The integrated propulsion airframe control program is also discussed which will introduce the problem of implementing MVC within a distributed processing avionics architecture, requiring real time decomposition of the global design into independent modules in response to hardware communication failures.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Propulsion Controls, 1979; p 71-82
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    Design of a multivariable integrated control for a supersonic propulsion system (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An inlet/engine/nozzle integrated control mode for the propulsion system of an advanced supersonic commercial aircraft was studied. Results show that integration of these control functions can result in both operational and performance benefits for the propulsion system. For example, this integrated control mode may make it possible to minimize the use of inlet bypass doors for shock position control. This may be of benefit to the aircraft as a result of minimizing: (1) bypass bleed drag effects; (2) perturbations to the aircraft resulting from the side thrust effect of the bypass bleeds; and (3) potential unstarts of the inlet. A conceptual integrated control mode was developed which makes use of many cross coupling paths between inlet and engine control variables and inlet and engine sensed variables. A multivariable control design technique based upon linear quadratic regulator theory was applied to designing the feedback gains for this control to allow a simulation evaluation of the benefits of the integrated control mode.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Propulsion Controls, 1979; p 35-47
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    Sensor/actuator failure detection for turbofan engines (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A procedure for sensor/actuator failure detection using a generalized likelihood ratio (GLR) test is described. The GLR concept can provide a reliable evaluation of failure occurence when associated with a feedback control design which does not require sensor outputs to provide data estimates. A GLR detector was developed and tested.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Propulsion Controls, 1979; p 139-143
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  • 60
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    Multivariable synthesis with transfer functions (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A transfer function design theory for multivariable control synthesis is highlighted. The use of unique transfer function matrices and two simple, basic relationships - a synthesis equation and a design equation - are presented and illustrated. This multivariable transfer function approach provides the designer with a capability to specify directly desired dynamic relationships between command variables and controlled or response variables. At the same time, insight and influence over response, simplifications, and internal stability is afforded by the method. A general, comprehensive multivariable synthesis capability is indicated including nonminmum phase and unstable plants. Gas turbine engine examples are used to illustrate the ideas and method.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Propulsion Controls, 1979; p 111-127
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  • 61
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    Road map to adaptive optimal control (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A building block control structure leading toward adaptive, optimal control for jet engines is developed. This approach simplifies the addition of new features and allows for easier checkout of the control by providing a baseline system for comparison. Also, it is possible to eliminate certain features that do not have payoff by being selective in the addition of new building blocks to be added to the baseline system. The minimum risk approach specifically addresses the need for active identification of the plant to be controlled in real time and real time optimization of the control for the identified plant.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Propulsion Controls, 1979; p 83-87
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  • 62
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    Future Air Force aircraft propulsion control systems: The extended summary paper (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Hydromechanical control technology simply cannot compete against the performance benefits offered by electronics. Future military aircraft propulsion control systems will be full authority, digital electronic, microprocessor base systems. Anticipating the day when microprocessor technology will permit the integration and management of aircraft flight control, fire control and propulsion control systems, the Air Force Aero Propulsion Laboratory is developing control logic algorithms for a real time, adaptive control and diagnostic information system.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Propulsion Controls, 1979; p 63-67
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  • 63
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    F100 multivariable control synthesis program: A review of full scale engine altitude tests (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The benefits of linear quadratic regulator synthesis methods in designing a multivariable engine control capable of operating an engine throughout its flight envelope were demonstrated. The entire multivariable control synthesis program is reviewed with particular emphasis on engine tests conducted in the NASA Lewis propulsion systems laboratory altitude facility. The multivariable control has basically a proportional plus integral, model following structure with gains scheduled as functions of flight condition. The multivariable control logic design is described, along with control computer implementation aspects. Altitude tests demonstrated that the multivariable control logic could control an engine over a wide range of test conditions. Representative transient responses are presented to demonstrate engine behavior and the functioning of the control logic.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Propulsion Controls, 1979; p 20-34
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    Multivariable identification using centralized fixed modes (1980)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: A procedure to determine a state space model of a multivariable system (lambda inputs, m outputs) is presented. The model is suitable for control studies and uses single input, single output (SISO) system data in the identification procedure. The procedure can be defined in three distinct steps. First, the system's lambda x m SISO transfer functions are identified by using any standard or known identification technique for SISO systems. One objective of this step is to identify SISO transfer functions with as few distinct modes as possible between any two functions. Second, the time domain realization of each SISO transfer function is obtained in a straightforward manner and combined into a total multivariable realization. This total realization, in all probability, has more state variables than are required to define system response. In the third step, these excess or redundant states are removed by using minimal realization theory. The remaining states are related to system centralized fixed modes. Eigenvalue-eigenvector techniques were recently reported that yield a computationally feasible solution to the problem posed in step three. The procedure is applied to QCSEE data to demonstrate its feasibility.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Propulsion Controls, 1979; p 3-10
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    Noise and performance of the MIT and production propellers for a 150 HP single engine aircraft (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165729
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    Extended frequency turbofan model (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The fan model was developed using two dimensional modeling techniques to add dynamic radial coupling between the core stream and the bypass stream of the fan. When incorporated into a complete TF-30 engine simulation, the fan model greatly improved compression system frequency response to planar inlet pressure disturbances up to 100 Hz. The improved simulation also matched engine stability limits at 15 Hz, whereas the one dimensional fan model required twice the inlet pressure amplitude to stall the simulation. With verification of the two dimensional fan model, this program formulated a high frequency F-100(3) engine simulation using row by row compression system characteristics. In addition to the F-100(3) remote splitter fan, the program modified the model fan characteristics to simulate a proximate splitter version of the F-100(3) engine.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165261 , FR-13983
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    Propulsion system mathematical model for a lift/cruise fan V/STOL aircraft (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A propulsion system mathematical model is documented that allows calculation of internal engine parameters during transient operation. A non-realtime digital computer simulation of the model is presented. It is used to investigate thrust response and modulation requirements as well as the impact of duty cycle on engine life and design criteria. Comparison of simulation results with steady-state cycle deck calculations showed good agreement. The model was developed for a specific 3-fan subsonic V/STOL aircraft application, but it can be adapted for use with any similar lift/cruise V/STOL configuration.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-81663 , E-681
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    Evaluation of a bulk calorimeter and heat balance for determination of supersonic combustor efficiency (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results are presented from the shakedown and evaluation test of a bulk calorimeter. The calorimeter is designed to quench the combustion at the exit of a direct-connect, hydrogen fueled, scramjet combustor model, and to provide the measurements necessary to perform an analysis of combustion efficiency. Results indicate that the calorimeter quenches reaction, that reasonable response times are obtained, and that the calculated combustion efficiency is repeatable within + or -3 percent and varies in a regular way with combustor model parameters such as injected fuel equivalence ratio.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1739 , L-13943
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  • 69
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    Model aerodynamic test results for two variable cycle engine coannular exhaust systems at simulated takeoff and cruise conditions (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind tunnel tests were conducted to evaluate the aerodynamic performance of a coannular exhaust nozzle for a proposed variable stream control supersonic propulsion system. Tests were conducted with two simulated configurations differing primarily in the fan duct flowpaths: a short flap mechanism for fan stream control with an isentropic contoured flow splitter, and an iris fan nozzle with a conical flow splitter. Both designs feature a translating primary plug and an auxiliary inlet ejector. Tests were conducted at takeoff and simulated cruise conditions. Data were acquired at Mach numbers of 0, 0.36, 0.9, and 2.0 for a wide range of nozzle operating conditions. At simulated supersonic cruise, both configurations demonstrated good performance, comparable to levels assumed in earlier advanced supersonic propulsion studies. However, at subsonic cruise, both configurations exhibited performance that was 6 to 7.5 percent less than the study assumptions. At take off conditions, the iris configuration performance approached the assumed levels, while the short flap design was 4 to 6 percent less.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159818 , PWA-5550-37
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  • 70
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    Effect of ambient conditions on the emissions from a gas turbine combustor (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effect of variations in the ambient conditions of pressure, temperature, and relative humidity upon the emissions of a gas turbine combustion are investigated. A single combustor can from a Pratt and Whitney JT8D-17 engine was run at parametric inlet conditions bracketing the actual engine idle conditions. Data were correlated to determine the functional relationships between the emissions and ambient conditions. Mathematical modelling was used to determine the mechanism for the carbon monoxide and hydrocarbon emissions. Carbon monoxide emissions were modelled using finite rate chemical kinetics in a plug flow scheme. Hydrocarbon emissions were modelled by a vaporization scheme throughout the combustor.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-3355
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  • 71
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    Alternatives for jet engine control (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Alternatives to linear quadratic regulator theory in the linear case are examined along with nonlinear modelling and optimization approaches for global control. Context for the studies has been set by the DYNGEN digital simulator and by models generated for various phases of the F100 Multivariable Control Synthesis Program. With respect to the linear alternatives, the multivariable frequency domain is stressed. Progress is reported in both the direct algebraic approach to exact model matching, by means of stimulating work on the basic computational issues, and in the indirect generalized Nyquist approach. With respect to nonlinear modelling and optimization, the emphasis is twofold: the development of analytical nonlinear models of the jet engine and the use of these models in conjunction with techniques of mathematical programming in order to study global control over nonincremental portions of the flight envelope. The possibility of using tensor methods is explored.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Propulsion Controls, 1979; p 129-138
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  • 72
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    Engine identification for adaptive control (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An attempt to obtain a dynamic model for a turbofan gas turbine engine for the purpose of adaptive control is described. The requirements for adaptive control indicate that a dynamic model should be identified from data sampled during engine operation. The dynamic model identified was of the form of linear differential equations with time varying coefficients. A turbine engine is, however, a highly nonlinear system, so the identified model would be valid only over a small area near the operating point, thus requiring frequent updating of the coefficients in the model. Therefore it is necessary that the identifier use only recent information to perform its function. The identifier selected minimized the square of the equation errors. Known linear systems were used to test the characteristics of the identifier. It was found that the performance was dependent on the number of data points used in the computations and upon the time interval over which the data points were obtained. Preliminary results using an engine deck for the quiet, clean, shorthaul experimental engine indicate that the identified model predicts the engine motion well when there is sufficient dynamic information, that is when the engine is in transient operation.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Propulsion Controls, 1979; p 97-104
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  • 73
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    Effect of hole geometry and Electric-Discharge Machining (EDM) on airflow rates through small diameter holes in turbine blade material (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of two design parameters, electrode diameter and hole angle, and two machine parameters, electrode current and current-on time, on air flow rates through small-diameter (0.257 to 0.462 mm) electric-discharge-machined holes were measured. The holes were machined individually in rows of 14 each through 1.6 mm thick IN-100 strips. The data showed linear increase in air flow rate with increases in electrode cross sectional area and current-on time and little change with changes in hole angle and electrode current. The average flow-rate deviation (from the mean flow rate for a given row) decreased linearly with electrode diameter and increased with hole angle. Burn time and finished hole diameter were also measured.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1716 , E-417
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  • 74
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    Rotor redesign for a highly loaded 1800 ft/sec tip speed fan, 2 (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were conducted on a 0.5 hub/tip ratio single-stage fan designed to produce a pressure ratio of 2.280 at an efficiency of 83.8 percent with a rotor tip speed of 548.6 m/sec (1800 ft/sec). The rotor was designed utilizing a quasi three dimensional design system and four-part, multiple-circular-arc airfoil sections. The rotor is the third in a series of single-stage fans that have included a precompression airfoil design and a multiple-circular-arc airfoil design. The stage achieved a peak efficiency of 82.8 percent after performance had deteriorated by 0.6 of a point. The design mass flow was achieved at the peak efficiency point, and the stage total pressure ratio was 2.20, which is lower than the design goal of 2.28. The surge margin of 13% from the peak efficiency point exceeded the design goal of 7%.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159879 , PWA-5523-92
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  • 75
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    Core compressor exit stage study. Volume 3: Data and performance report for screening test configurations (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Rear stage blading designs that have lower losses in their endwall boundary layer regions were developed. Test data and performance results for rotor B, stator B, and stator C - blading designs that offer promise of reducing endwall losses relative to the baseline are given. A low speed research compressor was the principal investigative tool. The tests were conducted using four identical stages of blading so that the test data would be obtained in a true multistage environment.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159499 , R80AEG313-VOL-3
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  • 76
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    Engine diagnostics program: CF6-50 engine performance deterioration (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Cockpit cruise recordings and test cell data in conjunction with hardware inspection results from airline overhaul shops were analyzed to define the extent and magnitude of performance deterioration of the General Electric CF6-50 high bypass turbofan engine. The magnitude of short term deterioration was isolated from the long term, and the individual damage mechanisms that were the cause for the majority of the performance deterioration was identified. It was determined that the long term engine performance deterioration characteristics were different for the 3 aircraft types currently powered by the CF6-50 engine, but these differences were due to operational considerations (flight length and takeoff derate) and not to differences associated with the aircraft type. Unrestored losses, that is, performance deterioration which remains after engine refurbishment, represents over 70 percent of the total performance deterioration at engine shop visit. Superficial damage, such as, increased surface roughness, leading edge shape changes on airfoils, and increases in the average clearances between rotating and stationary components is the major contributor to these losses. Seventy one percent of the unrestored losses are cost effective to restore, and if implemented could reduce fuel consumed by CF6-50 engines by 26 million gallons in 1980.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159867
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  • 77
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    Surface pyrometry in presence of radiation from other sources with application to turbine blade temperature measurement (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Surface pyrometry is feasible even when the amount of surface radiation is exceeded by radiation from surrounding sources. To measure and correct for this interfering radiation, several methods that use multiple wavelength pyrometry were compared by an error analysis. For a specific application to turbine blade temperature measurement in a turbofan engine, a two wavelength method was best. Auxiliary measurements at the same wavelengths substantially improve the accuracy of the method.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1754 , E-396
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  • 78
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    Off-design performance loss model for radial turbines with pivoting, variable-area stators (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An off-design performance loss model was developed for variable stator (pivoted vane), radial turbines through analytical modeling and experimental data analysis. Stator loss is determined by a viscous loss model; stator vane end-clearance leakage effects are determined by a clearance flow model. Rotor loss coefficient were obtained by analyzing the experimental data from a turbine rotor previously tested with six stators having throat areas from 20 to 144 percent of design area and were correlated with stator-to-rotor throat area ratio. An incidence loss model was selected to obtain best agreement with experimental results. Predicted turbine performance is compared with experimental results for the design rotor as well as with results for extended and cutback versions of the rotor. Sample calculations were made to show the effects of stator vane end-clearance leakage.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1708 , AVRADCOM-TR-80-C-13 , E-455
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  • 79
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    Comparisons of four alternative powerplant types for future general aviation aircraft (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Recently completed NASA sponsored conceptual studies were culminated in the identification of promising new technologies for future spark ignition, diesel, rotary, and turbine engines. The results of a NASA in-house preliminary assessment study that compares these four powerplants types in several general aviation applications are reported. The evaluation consisted of installing each powerplant type in rubberized aircraft which are sized to accomplish fixed missions. The primary evaluation criteria include projected aircraft cost, total ownership cost, and mission fuel.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-81584 , E-561
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  • 80
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    Propulsion Study for Small Transport Aircraft Technology (STAT) (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Propulsion requirements were determined for 0.5 and 0.7 Mach aircraft. Sensitivity studies were conducted on both these aircraft to determine parametrically the influence of propulsion characteristics on aircraft size and direct operating cost (DOC). Candidate technology elements and design features were identified and parametric studies conducted to select the STAT advanced engine cycle. Trade off studies were conducted to determine those advanced technologies and design features that would offer a reduction in DOC for operation of the STAT engines. These features were incorporated in the two STAT engines. A benefit assessment was conducted comparing the STAT engines to current technology engines of the same power and to 1985 derivatives of the current technology engines. Research and development programs were recommended as part of an overall technology development plan to ensure that full commercial development of the STAT engines could be initiated in 1988.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165499 , DDA-EDR-10470
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  • 81
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    Supercritical fuel injection system (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: a fuel injection system for gas turbines is described including a pair of high pressure pumps. The pumps provide fuel and a carrier fluid such as air at pressures above the critical pressure of the fuel. A supercritical mixing chamber mixes the fuel and carrier fluid and the mixture is sprayed into a combustion chamber. The use of fuel and a carrier fluid at supercritical pressures promotes rapid mixing of the fuel in the combustion chamber so as to reduce the formation of pollutants and promote cleaner burning.
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 82
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    Performance and noise of a low pressure ratio variable pitch fan designed for general aviation applications (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A limited study has been conducted to establish the performance and noise characteristics of a low design tip speed (168 m/s, 550 ft/sec) low pressure ratio (1.04) variable pitch fan which was tested in the Langley 30 X 60 tunnel. This fan was designed for minimum noise when installed in the tail mount location of a twin engine aircraft which normally has both nose and tail mounted propulsors. Measurements showed the fan noise to be very close to predictions made during the design of the fan and extremely low in level (65 dBA at 1000 ft) with no acoustic treatment. This is about 8 dB lower than the unshrouded 2 blade propeller normally used in this installation. On the basis of tests conducted during this program, it appears that this level could be further reduced by 2 dBA if optimized acoustic treatments were installed in the fan duct. Even the best of the shrouded propellers tested previously were 7 dB higher in level than the Q-Fan without acoustic treatment. It was found that the cruise performance of this fan was within 5% of the predicted efficiency of 72%. Evaluation of the performance data indicated that disturbances in the inflow to the fan were the probable cause of the reduced performance.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159246
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  • 83
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    Energy efficient engine diffuser/combustor model technology (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A full scale, full annular diffuser/combustor model test rig was tested to investigate how configurational changes affect pressure loss and flow separation characteristics. The rig was characterized by five major modules: inlet; prediffuser; strut; simulated combustor; and full combustor. The prediffuser featured a short, curved wall dump design. Performance goals included: (1) a separation-free prediffuser flow field; (2) total pressure loss limited to 3.0 percent in the prediffuser and shrouds; and (3) an overall section pressure loss of 5.5 percent P sub T3 at the design airflow distribution. The results indicated that the prediffuser configurations operate well within the program goals for pressure loss and demonstrate separation free operation over a wide range of inlet conditions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165157 , PWA-5594-122
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  • 84
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    Experimental performance and analysis of 15.04-centimeter-tip-diameter, radial-inflow turbine with work factor of 1.126 and thick blading (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The aerodynamic design, the performance, and an internal loss breakdown were examined for a 15.04 cm tip diameter, radial-inflow turbine. The design application was to drive a two stage, 10 to 1 pressure ratio compressor with a mass flow of 0.952 kg/sec and a rotative speed of 70,000 rmp. The turbine inlet temperature was 1478 K, and the turbine was designed with blades thick enough for internal cooling passages. The rotor tip diameter was limited to 86 percent of optimum in order to obtain a reduced tip speed design. The turbine was fabricated with solid, uncooled blading and tested in air at nominal inlet pressure and temperature of 1.379 x 10000 N/sq m and 322.2 K, respectively. Results indicated the turbine total efficiency to be 5.3 points less than design. Analysis of these results has indicated the deficit in performance to be due to stator secondary flow losses, vaneless space surface friction losses, and trailing edge wake mixing losses.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1730 , E-391 , AVRADCOM-TR-80-09
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  • 85
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    A preliminary assessment of the impact of 2-D exhaust-nozzle geometry on the cruise range of a hypersonic aircraft with top-mounted ramjet propulsion (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A theoretical study of full length and shortened, two dimensional, isentropic, exhaust nozzles integrated with top mounted ramjet propulsion nacelles were conducted. Both symmetric and asymmetric contoured nozzles with a range of angular orientations were considered. Performance comparisons to determine optimum installations for a representative hypersonic vehicle at Mach 5 cruise conditions are presented on the basis of cruise range, propulsive specific impulse, inlet area requirements, and overall lift drag ratio. The effect of approximating the nozzle internal contours with planar surfaces and the determination of viscous and frozen flow effects are also presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-81841 , L-13518
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  • 86
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    Low-pressure performance of annular, high-pressure (40 atm) high-temperature (2480 K) combustion system (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental tests were conducted to develop a combustion system for a 40 atmosphere pressure, 2480 K exhaust gas temperature, turbine cooling facility. The tests were conducted in an existing facility with a maximum pressure capability of 10 atmospheres and where inlet air temperatures as high as 894 K could be attained. Exhaust gas temperatures were as high as 2365 K. Combustion efficiences were about 100 percent over a fuel air ratio range of 0.016 to 0.056. Combustion efficiency decreased at leaner and richer ratios when the inlet air temperature was 589 K. Data are presented that show the effect of fuel air ratio and inlet air temperature on liner metal temperature. Isothermal system pressure loss as a function of diffuser inlet Mach number is also presented. Data included exhaust gas pattern factors; unburned hydrocarbon, carbon monoxide, and oxides of nitrogen emission index values; and smoke numbers.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1713 , E-372
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  • 87
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    Aircraft engine nozzle (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A variable area exit nozzle arrangement for an aircraft engine was a substantially reduced length and weight which comprises a number of longitudinally movable radial vanes and a number of fixed radial vanes. The movable radial vanes are alternately disposed with respect to the fixed radial vanes. A means is provided for displacing the movable vanes along the longitudinal axis of the engine relative to the fixed radial vanes which extend across the main exhaust flow of the engine.
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 88
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    Cost analysis of composite fan blade manufacturing processes (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The relative manufacturing costs were estimated for large high technology fan blades prepared by advanced composite fabrication methods using seven candidate materials/process systems. These systems were identified as laminated resin matrix composite, filament wound resin matrix composite, superhybrid solid laminate, superhybrid spar/shell, metal matrix composite, metal matrix composite with a spar and shell, and hollow titanium. The costs were calculated utilizing analytical process models and all cost data are presented as normalized relative values where 100 was the cost of a conventionally forged solid titanium fan blade whose geometry corresponded to a size typical of 42 blades per disc. Four costs were calculated for each of the seven candidate systems to relate the variation of cost on blade size. Geometries typical of blade designs at 24, 30, 36 and 42 blades per disc were used. The impact of individual process yield factors on costs was also assessed as well as effects of process parameters, raw materials, labor rates and consumable items.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159876 , TRW-ER-8064
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  • 89
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    Reliability of ceramics for heat engine applications (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The advantages and disadvantages associated with the use of monolithic ceramics in heat engines are discussed. The principle gaps in the state of understanding of ceramic material, failure origins, nondestructive tests as well as life prediction are included.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-163435 , PB80-182678 , NMAB-357
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  • 90
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    Experimental Study of Turbine Fuel Thermal Stability in an Aircraft Fuel System Simulator (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The thermal stability of aircraft gas turbines fuels was investigated. The objectives were: (1) to design and build an aircraft fuel system simulator; (2) to establish criteria for quantitative assessment of fuel thermal degradation; and (3) to measure the thermal degradation of Jet A and an alternative fuel. Accordingly, an aircraft fuel system simulator was built and the coking tendencies of Jet A and a model alternative fuel (No. 2 heating oil) were measured over a range of temperatures, pressures, flows, and fuel inlet conditions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 169-179
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  • 91
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    CF6-6D engine performance deterioration (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Cruise cockpit recordings and test cell performance data in conjunction with hardware inspection data from airline overhaul shops were analyzed to define the extent and magnitude of performance deterioration of the General Electric CF6-6D model engine. These studies successfully isolated short-term deterioration from the longer term, and defined areas where a significant reduction in aircraft energy requirements for the 1980's can be realized. Unrestored losses which remain after engine refurbishment represent over 70% of the loss at engine shop visit. Sixty-three percent of the unrestored losses are cost-effective to restore which could reduce fuel consumed by CF6-6D engines in 1980 by 10.9 million gallons.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159786 , R80AEG218
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  • 92
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    CF6-6D engine short-term performance deterioration (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Studies conducted as part of the NASA-Lewis CF6 jet engine diagnostics program are summarized. An 82-engine sample of DC-10-10 aircraft engine checkout data that were gathered to define the extent and magnitude of CF6-6D short term performance deterioration were analyzed. These data are substantiated by the performance testing and analytical teardown of CF6-6D short term deterioration engine serial number (ESN) 451507.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159830 , R80AEG374
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  • 93
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    Preliminary study of advanced turboprop and turboshaft engines for light aircraft (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effects of engine configuration, advanced component technology, compressor pressure ratio and turbine rotor-inlet temperature on such figures of merit as vehicle gross weight, mission fuel, aircraft acquisition cost, operating, cost and life cycle cost are determined for three fixed- and two rotary-wing aircraft. Compared with a current production turboprop, an advanced technology (1988) engine results in a 23 percent decrease in specific fuel consumption. Depending on the figure of merit and the mission, turbine engine cost reductions required to achieve aircraft cost parity with a current spark ignition reciprocating (SIR) engine vary from 0 to 60 percent and from 6 to 74 percent with a hypothetical advanced SIR engine. Compared with a hypothetical turboshaft using currently available technology (1978), an advanced technology (1988) engine installed in a light twin-engine helicopter results in a 16 percent reduction in mission fuel and about 11 percent in most of the other figures of merit.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-81467 , E-397
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  • 94
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    Aerodynamic performances of three fan stator designs operating with rotor having tip speed of 337 meters per second and pressure ratio of 1.54. Relation of analytical code calculations to experimental performance (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A hub-to-shroud and a blade-to-blade internal-flow analysis code, both inviscid and basically subsonic, were used to calculate the flow parameters within four stator-blade rows. The produced ratios of maximum suction-surface velocity to trailing-edge velocity correlated well in the midspan region, with the measured total-parameters over the minimum-loss to near stall operating range for all stators and speeds studied. The potential benefits of a blade designed with the aid of these flow analysis codes are illustrated by a proposed redesign of one of the four stators studied. An overall efficiency improvement of 1.6 points above the peak measured for that stator is predicted for the redesign.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1614 , E-137
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 95
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    Expanded study of feasibility of measuring in-flight 747/JT9D loads, performance, clearance, and thermal data (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The JT9D jet engine exhibits a TSFC loss of about 1 percent in the initial 50 flight cycles of a new engine. These early losses are caused by seal-wear induced opening of running clearances in the engine gas path. The causes of this seal wear have been identified as flight induced loads which deflect the engine cases and rotors, causing the rotating blades to rub against the seal surfaces, producing permanent clearance changes. The real level of flight loads encountered during airplane acceptance testing and revenue service and the engine's response in the dynamic flight environment were investigated. The feasibility of direct measurement of these flight loads and their effects by concurrent measurement of 747/JT9D propulsion system aerodynamic and inertia loads and the critical engine clearance and performance changes during 747 flight and ground operations was evaluated. A number of technical options were examined in relation to the total estimated program cost to facilitate selection of the most cost effective option. It is concluded that a flight test program meeting the overall objective of determining the levels of aerodynamic and inertia load levels to which the engine is exposed during the initial flight acceptance test and normal flight maneuvers is feasible and desirable. A specific recommended flight test program, based on the evaluation of cost effectiveness, is defined.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159717 , PWA-5512-46
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 96
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    Evaluation of approximate methods for the prediction of noise shielding by airframe components (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An evaluation of some approximate methods for the prediction of shielding of monochromatic sound and broadband noise by aircraft components is reported. Anechoic-chamber measurements of the shielding of a point source by various simple geometric shapes were made and the measured values compared with those calculated by the superposition of asymptotic closed-form solutions for the shielding by a semi-infinite plane barrier. The shields used in the measurements consisted of rectangular plates, a circular cylinder, and a rectangular plate attached to the cylinder to simulate a wing-body combination. The normalized frequency, defined as a product of the acoustic wave number and either the plate width or cylinder diameter, ranged from 4.6 to 114. Microphone traverses in front of the rectangular plates and cylinders generally showed a series of diffraction bands that matched those predicted by the approximate methods, except for differences in the magnitudes of the attenuation minima which can be attributed to experimental inaccuracies. The shielding of wing-body combinations was predicted by modifications of the approximations used for rectangular and cylindrical shielding. Although the approximations failed to predict diffraction patterns in certain regions, they did predict the average level of wing-body shielding with an average deviation of less than 3 dB.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1004 , A-6961
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 97
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    A review of propeller discrete frequency noise prediction technology with emphasis on two current methods for time domain calculations (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A review of propeller noise prediction technology is presented which highlights the developments in the field from the successful attempt of Gutin to the current sophisticated techniques. Two methods for the predictions of the discrete frequency noise from conventional and advanced propellers in forward flight are described. These methods developed at MIT and NASA Langley Research Center are based on different time domain formulations. Brief description of the computer algorithms based on these formulations are given. The output of these two programs, which is the acoustic pressure signature, is Fourier analyzed to get the acoustic pressure spectrum. The main difference between the programs as they are coded now is that the Langley program can handle propellers with supersonic tip speed while the MIT program is for subsonic tip speed propellers. Comparisons of the calculated and measured acoustic data for a conventional and an advanced propeller show good agreement in general.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Journal of Sound and Vibration; 71; Aug. 8
    Format: text
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    NASA TECHNICAL REPORTS
  • 98
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    Performance, emissions, and physical characteristics of a rotating combustion aircraft engine, supplement A (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Testing was conducted using the basic RC2-75 engine, to which several modifications were incorporated which were designed to reduce the hydrocarbon emissions and reduce the specific fuel consumption. The modifications included close-in surface gap spark plugs, increased compression ratio rotors, and provisions for utilizing either side or peripheral intake ports, or a combination of the two if required. The proposed EPA emissions requirements were met using the normal peripheral porting. The specific fuel economy demonstrated for the modified RC2-75 was 283 g/kW-hr at 75% power and 101 brake mean effective pressure (BMEP) and 272.5 g/kW-hr at 75% power and 111 BMEP. The latter would result from rating the engine for takeoff at 285 hp and 5500 rpm, instead of 6000 rpm.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135119 , CW-WR-76-028.3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 99
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    Static calibration of a two-dimensional wedge nozzle with thrust vectoring and spanwise blowing (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a static calibration of the two dimensional wedge nozzles on a STOL configuration of a large-scale fighter model are reported. These nozzles internally turn the efflux produced by two turbojets down 25 degrees and exhaust it over the deflected trailing edge of the wing. This arrangement provides direct thrust lift, enhances wing lift by producting supercirculation, and provides thrust vectoring by varying the deflection of the wing's trailing edge. The thrust is vectored from 10 deg to 38 deg. This system was calibrated with spanwise blowing for augmentation of the leading-edge vortex. When 16% of the turbojet efflux is blown spanwise, the thrust recovered is 92% of the thrust produced when the total efflux is exhausted longitudinally.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-81161 , A-8043
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 100
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    CF6 jet engine performance improvement: New fan (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: 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.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159699 , R79AEG413
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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