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Experimental Cascade Analysis of a Transonic Compressor Rotor Blade Section FREE

[+] Author Affiliations
H. A. Schreiber, H. Starken

DFVLR, Institut für Antriebstechnik, Cologne, West Germany

Paper No. 83-GT-209, pp. V001T01A056; 8 pages
doi:10.1115/83-GT-209
From:
  • ASME 1983 International Gas Turbine Conference and Exhibit
  • Volume 1: Turbomachinery
  • Phoenix, Arizona, USA, March 27–31, 1983
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7951-1
  • Copyright © 1983 by ASME

abstract

A transonic compressor rotor blade cascade was tested in order to elucidate the flow behaviour 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 © 1983 by ASME
This article is only available in the PDF format.

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