An Experimental and Computational Study of Transonic Three-Dimensional Flow in a Turbine Cascade

[+] Author and Article Information
J.-J. Camus, J. D. Denton, J. V. Soulis

Whittle Laboratory, Engineering Department, Cambridge University, Cambridge, England

C. T. J. Scrivener

Rolls Royce Limited, Derby, England

J. Eng. Gas Turbines Power 106(2), 414-420 (Apr 01, 1984) (7 pages) doi:10.1115/1.3239581 History: Received November 30, 1982; Online October 15, 2009


Detailed experimental measurements of the flow in a cascade of turbine rotor blades with a nonplanar end wall are reported. The cascade geometry was chosen to model as closely as possible that of a H.P. gas turbine rotor blade. The blade section is designed for supersonic flow with an exit Mach number of 1.15 and the experiments covered a range of exit Mach numbers from 0.7–1.2. Significant three-dimensional effects were observed and the origin of these is discussed. The measurements are compared with data for the same blade section in a two-dimensional cascade and also with the predictions of two different fully three-dimensional inviscid flow calculation methods. It is found that both these calculations predict the major three-dimensional effects on the flow correctly.

Copyright © 1984 by ASME
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