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An Experimental and Numerical Investigation of the Effect of Cooling Channel Crossflow on Film Cooling Performance

[+] Author Affiliations
Harald Peter Kissel, Bernhard Weigand, Jens von Wolfersdorf, Sven Olaf Neumann

University of Stuttgart, Stuttgart, Germany

Antje Ungewickell

Rolls-Royce Deutschland Ltd. & Co. KG, Blankenfelde-Mahlow, Germany

Paper No. GT2007-27102, pp. 147-158; 12 pages
  • ASME Turbo Expo 2007: Power for Land, Sea, and Air
  • Volume 4: Turbo Expo 2007, Parts A and B
  • Montreal, Canada, May 14–17, 2007
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4793-4 | eISBN: 0-7918-3796-3
  • Copyright © 2007 by ASME


This paper presents an experimental and numerical investigation into film cooling performance over a flat plate. As previous studies have shown, the flow situation at the entry-side of the cooling hole shows a notable effect on film cooling performance. The present investigation takes this into account feeding the cooling holes from an internal cooling channel and not from a stagnant plenum. High resolution heat transfer coefficient and adiabatic film cooling effectiveness distributions received from transient liquid crystal experiments are presented. The Reynolds numbers of the hot gas channel and the coolant crossflow feeding the holes are varied. Furthermore, the effects of 45° angled ribs, introduced into the cooling channel, are investigated. The experiments are performed at constant blowing, momentum and pressure ratios. Numerical calculations of the adiabatic film cooling effectiveness for selected configurations using FLUENT are presented. Comparison reveals the influence of coolant channel Reynolds number and the introduced ribs on the cooling hole flow pattern leading to a changed film cooling performance.

Copyright © 2007 by ASME



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