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RESEARCH PAPERS

Effect of Velocity and Temperature Distribution at the Hole Exit on Film Cooling of Turbine Blades

[+] Author and Article Information
V. K. Garg

AYT Corporation, NASA Lewis Research Center, Mail Stop 5-11, Cleveland, OH 44135

R. E. Gaugler

Turbine Branch, Turbomachinery & Propulsion Systems Division. NASA Lewis Research Center, Mail Stop 5-11, Cleveland, OH 44135

J. Turbomach 119(2), 343-351 (Apr 01, 1997) (9 pages) doi:10.1115/1.2841117 History: Received February 04, 1995; Online January 29, 2008

Abstract

An existing three-dimensional Navier–Stokes code (Arnone et al., 1991), modified to include film cooling considerations (Garg and Gaugler, 1994), has been used to study the effect of coolant velocity and temperature distribution at the hole exit on the heat transfer coefficient on three film-cooled turbine blades, namely, the C3X vane, the VKI rotor, and the ACE rotor. Results are also compared with the experimental data for all the blades. Moreover, Mayle’s transition criterion (1991), Forest’s model for augmentation of leading edge heat transfer due to free-stream turbulence (1977), and Crawford’s model for augmentation of eddy viscosity due to film cooling (Crawford et al., 1980) are used. Use of Mayle’s and Forest’s models is relevant only for the ACE rotor due to the absence of showerhead cooling on this rotor. It is found that, in some cases, the effect of distribution of coolant velocity and temperature at the hole exit can be as much as 60 percent on the heat transfer coefficient at the blade suction surface, and 50 percent at the pressure surface. Also, different effects are observed on the pressure and suction surface depending upon the blade as well as upon the hole shape, conical or cylindrical.

Copyright © 1997 by The American Society of Mechanical Engineers
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