A Method for Predicting Compressor Cascade Total Pressure Losses When the Inlet Relative Mach Number Is Greater Than Unity

[+] Author and Article Information
R. L. Balzer

The Boeing Company, Commercial Airplane Division, Seattle, Wash.

J. Eng. Power 93(1), 119-124 (Jan 01, 1971) (6 pages) doi:10.1115/1.3445377 History: Received January 13, 1970; Online July 14, 2010


During the last few years, considerable progress has been made in predicting the total pressure losses from viscous effects for axial-flow compressor cascades. With the advent of the transonic and the supersonic stage, another pressure loss generating mechanism was introduced—the shock wave. Various methods have been published over the past few years accounting for the pressure losses associated with the shock formation, but of those reviewed by this author, none of them has been consistently successful for predicting the losses at other than design conditions. This paper develops a method which has given consistent success at all flow conditions for compressors with subsonic axial and supersonic relative velocities.

Copyright © 1971 by ASME
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