Experimental Cascade Analysis of a Transonic Compressor Rotor Blade Section

[+] Author and Article Information
H. A. Schreiber, H. Starken

Institut für Antriebstechnik, DFVLR, 5000 Cologne 90, West Germany

J. Eng. Gas Turbines Power 106(2), 288-294 (Apr 01, 1984) (7 pages) doi:10.1115/1.3239561 History: Received January 04, 1983; Online October 15, 2009


A transonic compressor rotor blade cascade was tested in order to elucidate the flow behavior in the transonic regime and to determine the performance characteristic in the whole operating range of a rotor blade section. The experiments have been conducted in a transonic cascade wind tunnel, which enables tests even at sonic inlet velocities. The influence of the upstream Mach number between 0.8 and 1.1 and the inlet flow angle between choking and stalling of the blade row was investigated. The effect of the axial velocity density ratio (AVDR) could be studied by applying an endwall suction device. Furthermore, the level of the shock losses was determined from a wake analysis. A final comparison of cascade losses and those of the corresponding rotor blade element shows good agreement which underlines the applicability of the cascade model in the design of axial flow turbomachines.

Copyright © 1984 by ASME
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