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RESEARCH PAPERS

Improved Blade Profile Loss and Deviation Angle Models for Advanced Transonic Compressor Bladings: Part II—A Model for Supersonic Flow

[+] Author and Article Information
W. M. König, D. K. Hennecke

Department of Flight Propulsion, Technical University of Darmstadt, Darmstadt, Federal Republic of Germany

L. Fottner

Institute for Jet Propulsion, German Armed Forces University of Munich, Neubiberg, Federal Republic of Germany

J. Turbomach 118(1), 81-87 (Jan 01, 1996) (7 pages) doi:10.1115/1.2836610 History: Received March 02, 1994; Online January 29, 2008

Abstract

New blading concepts as used in modern transonic axial-flow compressors require improved loss and deviation angle correlations. The new model presented in this paper incorporates several elements and treats blade-row flows having subsonic and supersonic inlet conditions separately. The second part of the present report focuses on the extension of a well-known correlation for cascade losses at supersonic inlet flows. It was originally established for DCA bladings and is now modified to reflect the flow situation in blade rows having low-cambered, arbitrarily designed blades including precompression blades. Finally, the steady loss increase from subsonic to supersonic inlet-flow velocities demonstrates the matched performance of the different correlations of the new model.

Copyright © 1996 by The American Society of Mechanical Engineers
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