Annular Cascade Testing of Turbine Nozzles at High Exit Mach Numbers

[+] Author and Article Information
R. G. Williamson

Gas Dynamics Laboratory, National Research Council, Ottawa, Ontario, Canada K1A 0R6

S. H. Moustapha

Pratt and Whitney Canada Inc., Longueuil, Quebec, Canada

J. Fluids Eng 108(3), 313-320 (Sep 01, 1986) (8 pages) doi:10.1115/1.3242579 History: Received September 04, 1985; Online October 26, 2009


This paper presents detailed information on the three-dimensional flow field in a realistic low aspect ratio, high turning nozzle vane design which incorporates end-wall contouring and which has been tested over a range of exit Mach number from subsonic up to the design value at mean section of 1.15. The experimental results, in the form of nozzle surface pressure distributions as well as surveys of pressure losses and flow angles at exit, are compared with those calculated by a three-dimensional flow analysis. The effects of exit Mach number on the measured nozzle performance are also presented.

Copyright © 1986 by ASME
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