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  • Inorganic Chemistry  (3,763)
  • AIRCRAFT PROPULSION AND POWER  (1,211)
  • 1975-1979  (4,974)
Collection
Keywords
Publisher
Years
Year
  • 1
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    Investigation of air stream from combustor-liner air entry holes, 3 (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Jets flowing from air entry holes of the combustor liner of a gas turbine were investigated. Cold air was supplied through the air entry holes into the primary hot gas flows. The mass flow of the primary hot gas and issuing jets was measured, and the behavior of the air jets was studied by the measurement of the temperature distribution of the gas mixture. The air jets flowing from three circular air entry holes, single streamwise long holes, and two opposing circular holes, parallel to the primary flow were studied along with the effects of jet and gas stream velocities, and of gas temperature. The discharge coefficient, the maximum penetration of the jets, the jet flow path, the mixing of the jets, and temperature distribution across the jets were investigated. Empirical expressions which describe the characteristics of the jets under the conditions of the experiments were formulated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75430 , NAL-TR-369
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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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
  • 3
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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
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 4
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    Aircraft fuel conservation technology. Task force report, September 10, 1975 (1975)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An advanced technology program is described for reduced fuel consumption in air transport. Cost benefits and estimates are given for improved engine design and components, turboprop propulsion systems, active control systems, laminar flow control, and composite primary structures.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-74295
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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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
  • 6
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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
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 7
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    Summary of NASA aerodynamic and heat transfer studies in turbine vanes and blades (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: Aerodynamic effects of trailing edge geometry, hole size, angle, spacing, and shape have been studied in two- and three-dimensional cascades and in a warm turbine test series. Heat transfer studies have been carried out in various two- and three-dimensional test facilities in order to provide corresponding heat transfer data. Results are shown in terms of cooling effectiveness and aerodynamic efficiency for various coolant fractions, coolant-primary temperature ratios, and cooling configurations.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: SAE PAPER 760917
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Test engines promise less noise from small aircraft (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-NEWS-RELEASE-79-24 , P79-10025
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Experimental turbofan engine for small aircraft delivered (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-NEWS-RELEASE-79-137 , P79-10137
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    New materials for high temperature turbines; ONERA's DS composites confronted with blade problems (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: ONERA's refractory DS composites were cited as materials required for use in advanced aircraft turbines, operating at high temperatures. These materials were found to be reliable in the construction of turbine blades. Requirements for a blade material in aircraft turbines operating at higher temperatures were compared with the actual performance as found in COTAC DS composite testing. The structure and properties of the more fully developed 74 and 741 types were specified. High temperature structural stability, impact of thermal and mechanical fatigue, oxidation resistance and coating capability were thoroughly evaluated. The problem of cooling passages in DS eutectic blades is also outlined.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75216 , High Temp. Probl. in Gas Turbine Eng.; 19-23 Sept. 1977; Ankara
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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