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Effect of screen-induced total-pressure distortion on axial-flow compressor stabilityAn experimental investigation was made to determine the effects of screen-induced total-pressure distortions on two J85-GE-13 turbojet engines. Results were compared to those from a previous program run with a third engine. All compressors were found to be sensitive to a critical angle of circumferential distortion equal to 60 deg., and they all adhered closely to the parallel compressor model. The sensitivity of compressor exit pressure to virtually any type of distortion pattern can be determined by defining stall lines for undistorted, hub radial distorted, and tip radial distorted inflows. The effect of multiple sectors of circumferential distortion is defined.
Document ID
19740014513
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Calogeras, J. E. (NASA Lewis Research Center Cleveland, OH, United States)
Johnsen, R. L. (NASA Lewis Research Center Cleveland, OH, United States)
Burstadt, P. L. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
May 1, 1974
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-3017
E-7792
Accession Number
74N22626
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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