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Preliminary Data on the Effects of Inlet Pressure Distortions on the J57-P-1 Turbojet EngineAn investigation to determine the steady-state and surge characteristics of the J57-P-1 two-spool turbojet engine with various inlet air-flow distortions was conducted in the altitude wind tunnel at the NACA Lewis laboratory. Along with a uniform inlet total-pressure distribution, one circumferential and three radial pressure distortions were investigated. Data were obtained over a complete range of compressor speeds both with and without intercompressor air bleed at a flight Mach number of 0.8 and at altitudes of 35,000 and 50,000 feet. Total-pressure distortions of the magnitudes investigated had very little effect on the steady-state operating line for either the outer or inner compressor. The small radial distortions investigated also had engine over that obtained with the uniform inlet pressure distribution. The circumferential distortion, however, raised the minimum speed at which the engine could operate without encountering surge when the intercompressor bleeds were closed. This increase in minimum speed resulted in a substantial reduction in the operable speed range accompanied by a reduction in the altitude operating limit.
Document ID
20090021949
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Wallner, Lewis E. (NASA Lewis Research Center Cleveland, OH, United States)
Lubick, Robert J. (NASA Lewis Research Center Cleveland, OH, United States)
Einstein, Thomas H. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 24, 2013
Publication Date
December 3, 1954
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
NACA-RM-SE54K19
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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