An Experimental Study of Heat Transfer and Film Cooling on Large-Scale Turbine Endwalls

[+] Author and Article Information
M. F. Blair

United Aircraft Research Laboratories, East Hartford, Conn.

J. Heat Transfer 96(4), 524-529 (Nov 01, 1974) (6 pages) doi:10.1115/1.3450239 History: Received June 11, 1974; Online August 11, 2010


Experiments were conducted to determine the film cooling effectiveness and convective heat transfer coefficient distributions on the endwall of a large-scale turbine vane passage. The vane test models employed simulated the passage geometry and upstream cooling slot geometry of a typical first stage turbine. The test models were constructed of low thermal conductivity foam and foil heaters. The tests were conducted at a typical engine Reynolds number but at lower than typical Mach numbers. The film cooling effectiveness distribution for the entire endwall and the heat transfer distribution for the downstream one-half of the endwall were characterized by large gapwise variations which were attributed to a secondary flow vortex.

Copyright © 1974 by ASME
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