Effect of Dynamic Variations in Engine-inlet Pressure on the Compressor System of a Twin- Spool Turbofan Engine PDF Download
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Author: John E. McAulay
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
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Author: John E. McAulay
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 408
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 478
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Author: Oak Ridge National Laboratory
Publisher:
ISBN:
Category : Electric power distribution
Languages : en
Pages : 508
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 892
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Author: Oak Ridge National Laboratory
Publisher:
ISBN:
Category : Electric power distribution
Languages : en
Pages : 2864
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 228
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 580
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Book Description
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Author: Frank W. Burcham
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 108
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Flight tests were conducted with two F-111A airplanes to study the effects of steady-state and dynamic pressure phenomena on the propulsion system. Analysis of over 100 engine compressor stalls revealed that the stalls were caused by high levels of instantaneous distortion. In 73 percent of these stalls, the instantaneous circumferential distortion parameter, k sub theta, exhibited a peak just prior to stall higher than any previous peak. The K sub theta parameter was a better indicator of stall than the distortion factor, k sub d, and the maximum-minus-minimum distortion parameter, d, was poor indicator of stall. Inlet duct resonance occurred in both F-111A airplanes and is believed to have been caused by oscillations of the normal shock wave from an internal to an external position. The inlet performance of the two airplanes was similar in terms of pressure recovery, distortion, and turbulence, and there was good agreement between flight and wind-tunnel data up to a Mach number of approximately 1.8.
Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 320
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