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

[+] Author Affiliations
R. Kiock

Institute for Design Aerodynamics, DFVLR, Braunschweig, West-Germany

F. Lehthaus

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

N. C. Baines

Imperial College, London, UK

C. H. Sieverding

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

Paper No. 85-IGT-44, pp. V001T02A018; 10 pages
doi:10.1115/85-IGT-44
From:
  • ASME 1985 Beijing International Gas Turbine Symposium and Exposition
  • Volume 1: Aircraft Engine; Turbomachinery
  • Beijing, People’s Republic of China, September 1–7, 1985
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7942-9
  • Copyright © 1985 by ASME

abstract

Reliable cascade data are essential to the development of highspeed 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 © 1985 by ASME
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