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RESEARCH PAPERS

Multiple Segment Parallel Compressor Model for Circumferential Flow Distortion

[+] Author and Article Information
R. S. Mazzawy

Compressor Group, Pratt and Whitney Aircraft, East Hartford, Conn.

J. Eng. Power 99(2), 288-296 (Apr 01, 1977) (9 pages) doi:10.1115/1.3446288 History: Received July 08, 1976; Online July 14, 2010

Abstract

A nonlinear compressible flow model has been developed for the prediction of compressor performance and stability with a circumferential flow distortion. This model uses multiple parallel compressor segments and accounts for deviations from undistorted compressor performance. It is applicable to large-amplitude inlet distortions of total pressure and/or temperature, as well as circumferential variations in exit static pressure. The basic model requires the undistorted performance characteristics for each blade row; however, a modified version based upon the overall compressor performance gives an accurate approximation when detailed blade row characteristics are not available.

Copyright © 1977 by ASME
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