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RESEARCH PAPERS

Numerical Results for Axial Flow Compressor Instability

[+] Author and Article Information
F. E. McCaughan

Cornell University, Ithaca, NY 14853

J. Turbomach 111(4), 434-441 (Oct 01, 1989) (8 pages) doi:10.1115/1.3262291 History: Received July 08, 1987; Online November 09, 2009

Abstract

Using Cornell’s supercomputing facilities, we have carried out an extensive study of the Moore–Greitzer model, which gives accurate and reliable information about compressor instability. The bifurcation analysis in the companion paper shows the dependence of the mode of compressor response on the shape of the rotating stall characteristic. The numerical results verify and extend this with a more accurate representation of the characteristic. The effect of the parameters on the shape of the rotating stall characteristic is investigated, and it is found that the parameters with the strongest effects are the inlet length, and the shape of the compressor pressure rise versus mass flow diagram (i.e., tall diagrams versus shallow diagrams). We also discuss the effects of inlet guide vane loss on the characteristic. An evaluation is made of the h ′ = −g approximation, and a spectral analysis of the rotating stall cell given by the full model suggests why this breaks down.

Copyright © 1989 by ASME
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