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RESEARCH PAPERS

Unsteady Losses in Transonic Compressors

[+] Author and Article Information
W. F. Ng, A. H. Epstein

Massachusetts Institute of Technology, Cambridge, Mass. 02139

J. Eng. Gas Turbines Power 107(2), 345-353 (Apr 01, 1985) (9 pages) doi:10.1115/1.3239727 History: Received January 12, 1984; Online October 15, 2009

Abstract

A newly developed probe has been used to measure the time-resolved total temperature and pressure in a transonic compressor. The investigation revealed the presence of large fluctuations in the blade-to-blade core flow occurring at a frequency of three to four times blade passing. These variations are not steady in the rotor relative frame and are thought to be caused by unsteadiness in the rotor shock system, driven perhaps by a shed vortex in the blade wake. The loss associated with this unsteadiness is calculated and the implications for stage performance are discussed.

Copyright © 1985 by ASME
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