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  • Organic Chemistry  (694)
  • AIRCRAFT PROPULSION AND POWER
  • 1975-1979  (911)
  • 1978  (911)
  • 1
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    Propulsion-airframe interactions predictability (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An illustration of the possible magnitude of the transonic performance prediction problem is shown. These results derived from a careful and systematic set of tests run on a jet effects model, an aerodynamic and force model, and a pressure model, evaluated test techniques and wind tunnel effects. The results were then carefully compared with flight test data where significant discrepancies in zero-lift drag were observed. A vigorous review of the test techniques identified a number of potential error sources. Some of these were thought to be aircraft roughness and protuberances, tunnel anomalies, sting/model support corrections, and hot gas effects. In addition, there were questions on model metric splitline location and magnitude of corrections for scale and Reynolds number. Flight test inlet/engine characteristics were thought to differ, also, from those of the calibration settings in the ground facilities.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Performance Prediction Methods; 20 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Low cycle fatigue in turbines (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Behavior of certain components at low-cycle fatigue is a parameter related to the conditions of use of turbines, to the technology of engine production and to the precision of its regulation. The laboratory takes this into account using data from sophisticated tests and rigorous analyses. The production plan includes careful examination of possible causes of premature rupture. This parameter has motivated the metallurgy industry to develop new materials and new technology.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75264
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Fundamental Aspects of the Aerodynamics of Turbojet Engine Combustors (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Aerodynamic considerations in the design of high performance combustors for turbojet engines are discussed. Aerodynamic problems concerning the preparation of the fuel-air mixture, the recirculation zone where primary combustion occurs, the secondary combustion zone, and the dilution zone were examined. An aerodynamic analysis of the entire primary chamber ensemble was carried out to determine the pressure drop between entry and exit. The aerodynamics of afterburn chambers are discussed. A model which can be used to investigate the evolution of temperature, pressure, and rate and efficiency of combustion the length of the chamber was developed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75287 , ONERA-TP-1976
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Approximate dynamic model of a turbojet engine (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An approximate dynamic nonlinear model of a turbojet engine is elaborated on as a tool in studying the aircraft control loop, with the turbojet engine treated as an actuating component. Approximate relationships linking the basic engine parameters and shaft speed are derived to simplify the problem, and to aid in constructing an approximate nonlinear dynamic model of turbojet engine performance useful for predicting aircraft motion.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75263
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    NASA engine system technology programs - An overview (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: The various propulsion systems technology programs are examined. The Stratospheric Cruise Emission Reduction program has the objective to explore and demonstrate advanced technology fuel preparation and combustion systems which produce very low emission levels, particularly with respect to the oxides of nitrogen, during high altitude cruising flight. Other programs considered include the Quiet, Clean, General Aviation Turbofan program, the Variable Cycle Engine Technology program, the Helicopter Transmission Technology program, the Broad Specification Fuels Technology program, the Engine Component Improvement program, the Advanced Turboprop Technology program, the Supersonic Cruise Propulsion Technology program, the Materials for Advanced Turbine Engines program, and the Aeroelasticity of Turbine Engines program.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-928 , Joint Propulsion Conference; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Investigation of the jet-wake flow of a highly loaded centrifugal compressor impeller (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: Investigations, aimed at developing a better understanding of the complex flow field in high performance centrifugal compressors were performed. Newly developed measuring techniques for unsteady static and total pressures as well as flow directions, and a digital data analysis system for fluctuating signals were thoroughly tested. The loss-affected mixing process of the distorted impeller discharge flow was investigated in detail, in the absolute and relative system, at impeller tip speeds up to 380 m/s. A theoretical analysis proved good coincidence of the test results with the DEAN-SENOO theory, which was extended to compressible flows.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75232
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    A review of NASA's propulsion programs for civil aviation (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-08-27
    Description: Five NASA engine-oriented propulsion programs of major importance to civil aviation are presented and discussed. Included are programs directed at exploring propulsion-system concepts for (1) energy-conservative subsonic aircraft (improved current turbofans, advanced turbofans, and advanced turboprops), (2) supersonic cruise aircraft (variable-cycle engines), (3) general aviation aircraft (improved reciprocating engines and small gas turbines), (4) powered-lift aircraft (advanced turbofans), and (5) advanced rotorcraft. These programs reflect the opportunities still existing for significant improvements in civil aviation through the application of advanced propulsion concepts
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-43 , Aerospace Sciences Meeting; Jan 16, 1978 - Jan 18, 1978; Huntsville, AL
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Overview of NASA general aviation program (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-08-27
    Description: The NASA efforts devoted to new technology for general aviation are summarized. Areas covered include: (1) improved safety through improved crashworthy structural design, spin resistance, and improved operations around uncontrolled airports; (2) reduced environmental impact for both reciprocating and turbine engines; and (3) research for improvement in the performance of both aerodynamic and system components.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center The Rotary Combust. Engine; p 1-11
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Characterization of a swept-strut hydrogen fuel-injector for scramjet applications (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Results of an experimental investigation of a swept-strut hydrogen fuel-injector simulating the center strut of a three strut scramjet module at Mach 6 flight conditions are presented. Detailed wall pressure distributions from over 100 separate tests with overall fuel flow from 0.1 to 1.3 times stoichiometric and test gas stagnation temperature from 1100 to 2400 K were recorded. The distance for pressure rise from the point of injection was found to increase with increasing test stagnation temperature. This trend indicates that chemical kinetics in the immediate region of perpendicular injection are not likely to be the mechanism controlling the onset of pressure rise. A fluid dynamic mechanism is suggested involving separation of the boundary layer downstream of injection which is forced upstream from the trailing edge by pressure rise due to combustion occurring in the base region of the strut. The results obtained indicate that the swept-strut fuel-injector concept can be adapted to a wide range of flight conditions by varying the amount of perpendicular fuel injection.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Joint Army-Navy-NASA-Air Force, Interagency Propulsion Committee Combustion Meeting; Sept. 1978; Newport, RI
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Correlation of combustor acoustic power levels inferred from internal fluctuating pressure measurements (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Combustion chamber acoustic power levels inferred from internal fluctuating pressure measurements are correlated with operating conditions and chamber geometries over a wide range. The variables include considerations of chamber design (can, annular, and reverse-flow annular) and size, number of fuel nozzles, burner staging and fuel split, airflow and heat release rates, and chamber inlet pressure and temperature levels. The correlated data include those obtained with combustion component development rigs as well as engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Format: text
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    NASA TECHNICAL REPORTS
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