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Heat Transfer Enhancement Within a Turbine Blade Cooling Passage Using Ribs and Combinations of Ribs With Film Cooling Holes FREE

[+] Author Affiliations
J. R. Shen

Chinese Academy of Sciences, Beijing, China

Z. Wang, P. T. Ireland, T. V. Jones

University of Oxford, Oxford, UK

A. R. Byerley

Mercer University, Macon, GA

Paper No. 94-GT-232, pp. V004T09A038; 8 pages
doi:10.1115/94-GT-232
From:
  • ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration
  • The Hague, Netherlands, June 13–16, 1994
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7886-6
  • Copyright © 1994 by ASME

abstract

A transient heat transfer method which uses liquid crystals has been applied to a scale model of a turbine rotor blade passage. Detailed contours of local heat transfer coefficient are presented for the passage in which the heat transfer to one wall was enhanced firstly by ribs and then with ribs combined with holes. The hole geometry and experimental dimensionless flow rates were representative of those occurring at the entrance to engine film cooling holes. The results for the ribbed passage are compared to established correlations for developed flow. Qualitative surface shear stress distributions were determined with liquid crystals. The complex distributions of heat transfer coefficient are discussed in the light of the interpreted flow field.

Copyright © 1994 by ASME
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