The Transonic Flow Through a Plane Turbine Cascade as Measured in Four European Wind Tunnels

[+] Author and Article Information
R. Kiock

Institute for Design Aerodynamics, DFVLR, Flughafen, D-3300 Braunschweig, West Germany

F. Lehthaus

Institute for Experimental Fluid Mechanics, DFVLR, D-3400 Göttingen, West Germany

N. C. Baines

Imperial College, Department of Mechanical Engineering, London SW7 2BX, United Kingdom

C. H. Sieverding

Von Karman Institute for Fluid Dynamics, B-1640 Rhode-St.-Genèse, Belgium

J. Eng. Gas Turbines Power 108(2), 277-284 (Apr 01, 1986) (8 pages) doi:10.1115/1.3239900 History: Received May 13, 1985; Online October 15, 2009


Reliable cascade data are esssential to the development of high-speed turbomachinery, but it has long been suspected that the tunnel environment influences the test results. This has now been investigated by testing one plane gas turbine rotor blade section in four European wind tunnels of different test sections and instrumentation. The Reynolds number of the transonic flow tests was Re2 = 8 × 105 based on exit flow conditions. The turbulence was not increased artificially. A comparison of results from blade pressure distributions and wake traverse measurements reveals the order of magnitude of tunnel effects.

Copyright © 1986 by ASME
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