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RESEARCH PAPERS

Stalling Pressure Rise Capability of Axial Flow Compressor Stages

[+] Author and Article Information
C. C. Koch

Aircraft Engine Group, General Electric Co., Evendale, Ohio 45215

J. Eng. Power 103(4), 645-656 (Oct 01, 1981) (12 pages) doi:10.1115/1.3230787 History: Received December 04, 1980; Online September 28, 2009

Abstract

A procedure for estimating the maximum pressure rise potential of axial flow compressor stages is presented. A simplified stage average pitchline approach is employed so that the procedure can be used during a preliminary design effort before detailed radial distributions of blading geometry and fluid parameters are established. Semi-empirical correlations of low speed experimental data are presented that relate the stalling static-pressure-rise coefficient of a compressor stage to cascade passage geometry, tip clearance, bladerow axial spacing and Reynolds number. Blading aspect ratio is accounted for through its effect on normalized clearances, Reynolds number and wall boundary layer blockage. An unexpectedly strong effect of airfoil stagger and of the resulting flow coefficient of the stage’s vector triangle is observed in the experimental data. This is shown to be caused by the differing ability of different types of stage vector triangles to re-energize incoming low-momentum fluid. Use of a suitable “effective” dynamic head in the pressure rise coefficient gives a good correlation of this effect. Stalling pressure rise data from a wide range of both low speed and high speed compressor stages are shown to be in good agreement with these correlations.

Copyright © 1981 by ASME
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