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  • PROPULSION SYSTEMS  (9)
  • 1
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    Turbine aerodynamic considerations for advanced turbines (1971)
    In:  CASI
    Details
    Publication Date: 2006-04-20
    Description: Aerodynamic characteristics of advanced turbine engines
    Keywords: PROPULSION SYSTEMS
    Type: AIRCRAFT PROPULSION 1971; P 37-55
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Cold-flow performance of several variations of a ram-air-cooled plug nozzle for supersonic-cruise aircraft (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental data were obtained with a 21.59 cm (8.5 in.) diameter cold-flow model in a static altitude facility to determine the thrust and pumping characteristics of several variations of a ram-air-cooled plug nozzle. Tests were conducted over a range of nozzle pressure ratios simulating supersonic cruise and takeoff conditions. Primary throat area was also varied to simulate afterburner on and off. Effect of plug size, outer shroud length, primary nozzle geometry, and varying amounts of secondary flow were investigated. At a supersonic cruise pressure ratio of 27, nozzle efficiencies were 99.7 percent for the best configurations.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-3110 , E-7975
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Summary of tests on two highly loaded turbine blade concepts in three-dimensional cascade sector (1969)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Tangential jet, tandem, jet flap and vortex generator blade concepts investigated for turbine blade loading efficiency
    Keywords: PROPULSION SYSTEMS
    Type: ASME PAPER 69-WA/GT-5 , AMERICAN SOCIETY OF MECHANICAL ENGINEERS, WINTER ANNUAL MEETING; Nov 16, 1969 - Nov 20, 1969; LOS ANGELES, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Airbreathing engines for space shuttle (1972)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The requirements imposed on the airbreathing engines by the shuttle mission and some results from engine design studies are discussed. In particular, some of the engine system weight study results are presented, potential problem areas and required engine modifications are identified, and testing requirements for a development and qualification program are discussed. The engines of interest for the shuttle are engines that are currently being developed for other applicatons. The potential problems, engine modifications, and testing requirements result primarily from the new environments associated with launch, space residence, and reentry.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-68098 , E-7018 , Natl. Aerospace Eng. and Manuf. Meeting; Oct 02, 1972 - Oct 05, 1972; San Diego, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Shuttle airbreathing propulsion (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Requirements analysis of airbreathing gas turbine engines for shuttle vehicles
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-67806
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Shuttle airbreathing propulsion (1971)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Space shuttle airbreathing propulsion systems requirements and design studies, considering cruise, landing, go-around and ferry capabilities
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 71-662 , PROPULSION JOINT SPECIALIST CONFERENCE; Jun 14, 1971 - Jun 18, 1971; SALT LAKE CITY, UT; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Airbreathing engines for Space Shuttle. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The requirements imposed on the airbreathing engines by the shuttle mission and some results from engine design studies are discussed. In particular some of the engine system weight study results are presented, potential problem areas and required engine modifications are identified, and testing requirements for a development and qualification program are discussed. The engines of interest for the shuttle are engines that are currently being developed for other applications. The potential problems, engine modifications, and testing requirements result primarily from the new environments associated with launch, space residence, and reentry.
    Keywords: PROPULSION SYSTEMS
    Type: SAE PAPER 720805 , National Aerospace Engineering and Manufacturing Meeting; Oct 02, 1972 - Oct 05, 1972; San Diego, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    A turbojet simulator for Mach numbers up to 2.0. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A turbojet simulator has been designed and fabricated for use in wind tunnel models. The simulator contains a six-stage, axial-flow compressor powered by a three-stage, axial-flow turbine. High pressure heated air was used to drive the turbine. At design conditions, compressor axial flow, turbine exit flow, and a third supplementary flow all entered the exhaust nozzle at equal values of pressure and temperature. Overall aerodynamic design, instrumentation, and calibration procedure is presented. Performance of the device when used to simulate a J-85 turbojet engine at transonic speeds is reported. The installed nozzle performance obtained with the simulator is also discussed and compared with flight data.
    Keywords: PROPULSION SYSTEMS
    Type: ASME PAPER 72-GT-89 , American Society of Mechanical Engineers, Gas Turbine and Fluids Engineering Conference and Products Show; Mar 26, 1972 - Mar 30, 1972; San Francisco, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    A turbojet simulator for Mach numbers up to 2.0 (1972)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A turbojet simulator was designed and fabricated for use in wind tunnel models. The simulator contains a six-stage, axial-flow compressor powered by a three-stage, axial-flow turbine. High pressure heated air was used to drive the turbine. At design conditions, compressor axial flow, turbine exit flow, and a third supplementary flow all entered the exhaust nozzle at equal values of pressure and termperature. Overall aerodynamic design, compressor operating conditions, automatic controls, turbine aerodynamic design, instrumentation, and calibration procedure is presented. Performance of the device when used to simulate a J-85 turbojet engine at transonic speeds is reported. The installed nozzle performance obtained with the simulator is also discussed and compared with flight data.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-67973 , E-6690 , Ann. Intern. Gas Turbine Conf. and Products Show; Mar 23, 1972 - Mar 30, 1972; San Francisco, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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