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Inlet Flow Angle Determination of Transonic Compressor Cascades PUBLIC ACCESS

[+] Author Affiliations
W. Steinert, R. Fuchs, H. Starken

Institut für Antriebstechnik, Linder Höhe, W. Germany

Paper No. 91-GT-274, pp. V001T01A086; 8 pages
doi:10.1115/91-GT-274
From:
  • ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Orlando, Florida, USA, June 3–6, 1991
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7898-9
  • Copyright © 1991 by ASME

abstract

Tests of transonic compressor cascades require special measuring techniques to determine the inlet flow angle around sonic inlet flow conditions. One of the main requirements for these methods is the ability to adjust the inlet flow angle during the test to a prescribed value. A method has been successfully applied which relies on theoretically determined suction surface velocities. The described method was applied in testing cascades at inlet Mach numbers between M1=0.75–1.18. The test results confirmed the practicability of this method.

Copyright © 1991 by ASME
This article is only available in the PDF format.

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