Inlet Flow Distortion in Turbomachinery

[+] Author and Article Information
B. S. Seidel, M. D. Matwey

University of Delaware

J. J. Adamczyk

NASA Lewis Research Center

J. Eng. Power 102(4), 924-929 (Oct 01, 1980) (6 pages) doi:10.1115/1.3230362 History: Received December 07, 1979; Online September 28, 2009


A single stage axial compressor with distorted inflow is studied. The inflow distortion occurs far upstream and may be a distortion in stagnation temperature, stagnation pressure or both. The blade rows are modelled as semi-actuator disks. Losses, quasi-steady deviation angles, and reference incidence correlations are included in the analysis. Both subsonic and transonic relative Mach Numbers are considered. A parameter study is made to determine the influence of such variables as Mach Number and swirl angle on the attenuation of the distortion.

Copyright © 1980 by ASME
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