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

[+] Author and Article Information
J. R. Shen

Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing, China

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

Dept. of Engineering Science, University of Oxford, Oxford, United Kingdom

A. R. Byerley

Department of Mechanical Engineering, Mercer University, Macon, GA 31207

J. Turbomach 118(3), 428-434 (Jul 01, 1996) (7 pages) doi:10.1115/1.2836683 History: Received February 15, 1994; Online January 29, 2008


A transient heat transfer method using 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 first 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 light of the interpreted flow field.

Copyright © 1996 by The American Society of Mechanical Engineers
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