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  • AIRCRAFT PROPULSION AND POWER  (58)
  • 2015-2019
  • 1975-1979  (58)
  • 1935-1939
  • 1810-1819
  • 1978  (58)
  • 1
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    F100(3) parallel compressor computer code and user's manual (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Pratt & Whitney Aircraft multiple segment parallel compressor model has been modified to include the influence of variable compressor vane geometry on the sensitivity to circumferential flow distortion. Further, performance characteristics of the F100 (3) compression system have been incorporated into the model on a blade row basis. In this modified form, the distortion's circumferential location is referenced relative to the variable vane controlling sensors of the F100 (3) engine so that the proper solution can be obtained regardless of distortion orientation. This feature is particularly important for the analysis of inlet temperature distortion. Compatibility with fixed geometry compressor applications has been maintained in the model.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135388 , PWA-5549-8
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Variable mixer propulsion cycle (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A design technique, method and apparatus are delineated for controlling the bypass gas stream pressure and varying the bypass ratio of a mixed flow gas turbine engine in order to achieve improved performance. The disclosed embodiments each include a mixing device for combining the core and bypass gas streams. The variable area mixing device permits the static pressures of the core and bypass streams to be balanced prior to mixing at widely varying bypass stream pressure levels. The mixed flow gas turbine engine therefore operates efficiently over a wide range of bypass ratios and the dynamic pressure of the bypass stream is maintained at a level which will keep the engine inlet airflow matched to an optimum design level throughout a wide range of engine thrust settings.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Multitube turbojet noise-suppression studies using cross-correlation techniques (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The noise-generating region of a suppressed turbojet exhaust is studied by cross-correlating static pressure fluctuations within the exhaust with far-field sound for Mach numbers up to 0.99, using a 31-tube nozzle having an area ratio of 3.1. Measurements made with an unsuppressed turbojet exhaust having an equivalent area ratio and operating under effectively equal thrust loads serve as the experimental control. Static pressure-level measurements, made with a calibrated high-temperature acoustically damped probe tube, show that noise suppression by multitube nozzles results from reduced turbulence levels. The maximum fluctuating static-pressure level in the unsuppressed turbojet exhaust is typically 5-6 dB higher than static-pressure levels in the suppressed exhaust under conditions of effectively equal static thrust. This suggests that the turbulence intensity in the multitube suppressor flow is reduced in excess of 20% compared with the unsuppressed jet exhaust.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Acoustical Society of America; vol. 63
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Propulsion (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: NASA aims at developing propulsion technology to reduce the fuel consumption of present engines by 5%, that of new engines of the late 1980s by at least 12%, and that of an advanced early 1990s turboprop by an additional 15%. This paper reviews three separate NASA programs which take up these aims. They are, respectively, Engine Component Improvement, Energy Efficient Engine, and Advanced Turboprops.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Astronautics and Aeronautics; 16; July-Aug
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Gas turbine engine emission reduction technology program (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Progress in the development of combustor technology to meet the standards for the allowable pollutant emission levels of aircraft gas turbine engines is reported. The high-bypass-ratio turbofan engines which power the large commercial aircraft were emphasized along with efforts to reduce emission for near term applications. Recommendations for continuing research to reduce emissions to meet far term needs are given.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center CTOL Transport Technol., 1978; p 205-216
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Status of advanced turboprop technology (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Research is reviewed in the following areas: turboprop powered transport aircraft; wind tunnel aerodynamic and acoustics tests of model propellers; turboprop maintenance; and wind tunnel tests on airframe-turboprop interactions. Continued development of the technology for advanced turboprop transport was emphasized.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center CTOL Transport Technol., 1978; p 139-166
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Energy efficient engine: Preliminary design and integration studies (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A mixed exhaust, direct drive fan turbofan configuration was selected from four candidates. This choice was based on its ability to exceed study goals of 12% lower thrust specific fuel consumption and 5% lower direct operating cost by the 1990's with commercially acceptable technical risk and relative mechanical simplicity. The evaluation leading to configuration selection is discussed. Necessary technology advancements are identified and related to the goals.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center CTOL Transport Technol., 1978; p 89-110
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    CF6 performance improvement (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Potential CF6 engine performance improvements directed at reduced fuel consumption were identified and screened relative to airline acceptability and are reviewed. The screening process developed to provide evaluations of fuel savings and economic factors including return on investment and direct operating cost is described. In addition, assessments of development risk and production potential are made. Several promising concepts selected for full-scale development based on a ranking involving these factors are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center CTOL Transport Technol., 1978; p 59-78
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    ACEE Propulsion Overview (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Technology for fuel-efficient subsonic CTOL transport aircraft is discussed. The engine component improvement project, the energy efficient engine project, and the advanced turboprop project are included. The overall goals and objectives of each project are reviewed and the approach and schedule for accomplishing these project goals and objectives are given.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center CTOL Transport Technol., 1978; p 9-23
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Quiet, Clean, Short-Haul Experimental Engine (QCSEE) Over-The-Wing (OTW) engine acoustic design (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The acoustic considerations involved in the low source noise basic engine design and the design procedures followed in the development of the over-the-wing (OTW) nacelle acoustic treatment design are presented. Laboratory experiments, component tests, and scale model and engine tests supporting the OTW engine acoustic design are referenced. Acoustic design features include a near-sonic inlet, low fan and core pressure ratios, low fan tip speed, high and low frequency stacked core treatment, multiple thickness treatment, and fan frame and stator vane treatment.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135268 , R76AEG228
    Format: application/pdf
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