Propagation of Inlet Flow Distortions through an Axial Compressor Stage

[+] Author and Article Information
J. Colpin

Von Karman Institute for Fluid Dynamics, Rhode-St-Genese, Belgium

J. Eng. Power 101(1), 116-124 (Jan 01, 1979) (9 pages) doi:10.1115/1.3446432 History: Received December 14, 1977; Online July 14, 2010


This contribution will present an original calculation method predicting the development of an inlet flow distortion through a compressor stage. A finite difference technique is used to treat the flow equations outside the blade rows. That flow is two-dimensional, compressible and nonviscous. The blade rows are modelized using a quasi actuator disk approach, but include the unsteady transfer terms due to the rotor relative motion in a non uniform inlet flow. A set of experimental data, measured on a one stage axial compressor, submitted to a rectangular inlet total pressure distortion will be discussed and will serve as basis for a comparison between theory and experiments.

Copyright © 1979 by ASME
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