Laminar and Transitional Boundary Layer Structures in Accelerating Flow With Heat Transfer

[+] Author and Article Information
K. Rued, S. Wittig

Lehrstuhl und Institut fuer Thermische Stroemungsmaschinen, Universitaet Karlsruhe, Karlsruhe, West Germany

J. Turbomach 108(1), 116-123 (Jul 01, 1986) (8 pages) doi:10.1115/1.3262010 History: Received January 20, 1986; Online November 09, 2009


The accurate prediction of heat transfer coefficients on cooled gas turbine blades requires consideration of various influence parameters. The present study continues previous work with special efforts to determine the separate effects of each of several parameters important in turbine flow. Heat transfer and boundary layer measurements were performed along a cooled flat plate with various freestream turbulence levels (Tu = 1.6−11 percent), pressure gradients (k = 0−6 × 10−6 ), and cooling intensities (T w /T ∞ = 1.0−0.53). Whereas the majority of previously available results were obtained from adiabatic or only slightly heated surfaces, the present study is directed mainly toward application on highly cooled surfaces as found in gas turbine engines.

Copyright © 1986 by ASME
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