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Theoretical and Experimental Analysis of a Compressor Cascade at Supercritical Flow Conditions FREE

[+] Author Affiliations
A. Weber, M. Faden, H. Starken, V. Jawtusch

Institut für Antriebstechnik, Köln, W. Germany

Paper No. 87-GT-256, pp. V001T01A099; 11 pages
doi:10.1115/87-GT-256
From:
  • ASME 1987 International Gas Turbine Conference and Exhibition
  • Volume 1: Turbomachinery
  • Anaheim, California, USA, May 31–June 4, 1987
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7923-8
  • Copyright © 1987 by ASME

abstract

A comparison theory - experiment in terms of profile Mach number distribution, loss behavior and exit flow angle has been made for a compressor rotor cascade at M1 = 0.85. Measurements in the cascade wind tunnel and calculations were performed over the whole incidence range.

(A) A 2-D finite element method applied to the full potential equation is used as analysis code.

(B) Viscous effects are considered by using McNally’s integral boundary layer method with additional procedures for laminar and turbulent separation and shock boundary layer interaction.

(A) and (B) are coupled iteratively by adding the displacement thickness to the metal blade contour.

(C) The averaged exit flow properties and the total pressure loss coefficient are evaluated by application of the conservation laws.

Copyright © 1987 by ASME
This article is only available in the PDF format.

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