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  • 1
    facet.materialart.
    Unknown
    Gas turbine engine with convertible accessories (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Drive means for connecting a gas turbine engine to its accessories are so constructed as to allow the accessories to be selectively positioned to any one of several predetermined circumferential positions about the perimeter of the engine. This feature permits convenient mounting of the same engine upon vehicles demanding radically different engine mounting arrangements.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    Variable thrust nozzle for quiet turbofan engine and method of operating same (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An improved method of operating a gas turbine engine is presented wherein engine-generated noise is maintained at a reduced level during reduced thrust operation. Fan speed was maintained at a constant level while fan nozzle area was increased. This maintained high inlet Mach numbers for reduced forward noise propagation and also permited reduced nozzle exhaust velocity for reduced shear noise. In another embodiment, airflow was increased by means of a fan blade pitch change or speed increase while the fan nozzle area was increased, yielding both a net reduction in engine thrust and noise.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    Integrated gas turbine engine-nacelle (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A nacelle for use with a gas turbine engine is presented. An integral webbed structure resembling a spoked wheel for rigidly interconnecting the nacelle and engine, provides lightweight support. The inner surface of the nacelle defines the outer limits of the engine motive fluid flow annulus while the outer surface of the nacelle defines a streamlined envelope for the engine.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 4
    facet.materialart.
    Unknown
    Gas turbine engine with recirculating bleed (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Carbon monoxide and unburned hydrocarbon emissions in a gas turbine engine are reduced by bleeding hot air from the engine cycle and introducing it back into the engine upstream of the bleed location and upstream of the combustor inlet. As this hot inlet air is recycled, the combustor inlet temperature rises rapidly at a constant engine thrust level. In most combustors, this will reduce carbon monoxide and unburned hydrocarbon emissions significantly. The preferred locations for hot air extraction are at the compressor discharge or from within the turbine, whereas the preferred reentry location is at the compressor inlet.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Unknown
    Impact absorbing blade mounts for variable pitch blades (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A variable pitch blade and blade mount are reported that are suitable for propellers, fans and the like and which have improved impact resistance. Composite fan blades and blade mounting arrangements permit the blades to pivot relative to a turbine hub about an axis generally parallel to the centerline of the engine upon impact of a large foreign object, such as a bird. Centrifugal force recovery becomes the principal energy absorbing mechanism and a blade having improved impact strength is obtained.
    Keywords: MECHANICAL ENGINEERING
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Unknown
    Integrated gas turbine engine-nacelle (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A nacelle for use with a gas turbine engine is provided with an integral webbed structure resembling a spoked wheel for rigidly interconnecting the nacelle and engine. The nacelle is entirely supported in its spacial relationship with the engine by means of the webbed structure. The inner surface of the nacelle defines the outer limits of the engine motive fluid flow annulus, while the outer surface of the nacelle defines a streamlined envelope for the engine.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Unknown
    Quiet clean short-haul experimental engine /QCSEE/ design rationale (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The principal design features of the NASA QCSEE Under-The-Wing and Over-The-Wing powered lift propulsion systems are given. In the UTW engine, these include noise reduction features, a variable pitch low pressure ratio fan, a fan drive reduction gear, an advanced core and low pressure turbine with a low pollution combustor, a digital control, and advanced composite construction for the inlet, fan frame, fan exhaust duct, and variable area fan exhaust nozzle. The OTW engine is similar but has higher fan pressure and a fixed pitch fan. Both engines are scheduled to be fabricated and tested starting in 1976.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: SAE PAPER 750605 , Society of Automotive Engineers, Air Transportation Meeting; May 06, 1975 - May 08, 1975; Hartford, CT
    Format: text
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    NASA TECHNICAL REPORTS
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