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Instantaneous distortion in a Mach 2.5, 40-percent-internal-contraction inlet and its effect on turbojet stall marginAn experimental wind tunnel investigation was conducted to determine the effects of time-variant distortions produced in a supersonic inlet on a J85-GE-13 turbojet engine. Results are presented principally in terms of instantaneous distortion amplitudes and total-pressure contours measured through compressor stall. They indicate that, although a time-averaged distortion may be far from a stall-inducing value, corresponding instantaneous distortion amplitudes can approach or exceed this value. Seven engine stall events were studied. In six of these events instantaneous distortion peaks of sufficient magnitude to cause stall were observed in the time period shortly before stall was detected.
Document ID
19740022130
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Burstadt, P. L. (NASA Lewis Research Center Cleveland, OH, United States)
Calogeras, J. E. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
July 1, 1974
Subject Category
Propulsion Systems
Report/Patent Number
NASA-TM-X-3002
E-6294
Accession Number
74N30243
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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