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Experimental and Computational Comparisons of Fan-Shaped Film-Cooling on a Turbine Vane Surface

[+] Author Affiliations
W. Colban, K. A. Thole

Virginia Polytechnic Institute and State University

M. Haendler

Siemens Power Generation

Paper No. IMECE2005-79596, pp. 455-465; 11 pages
  • ASME 2005 International Mechanical Engineering Congress and Exposition
  • Heat Transfer, Part A
  • Orlando, Florida, USA, November 5 – 11, 2005
  • Conference Sponsors: Heat Transfer Division
  • ISBN: 0-7918-4221-5 | eISBN: 0-7918-3769-6
  • Copyright © 2005 by ASME


The flow exiting the combustor in a gas turbine engine is considerably hotter than the melting temperature of the turbine section components, of which the turbine nozzle guide vanes see the hottest gas temperatures. One method used to cool the vanes is to use rows of film-cooling holes to inject bleed air that is lower in temperature through an array of discrete holes onto the vane surface. The purpose of this study was to evaluate the row-by-row interaction of fan-shaped holes as compared to the performance of a single row of fan-shaped holes in the same locations. This study presents adiabatic film-cooling effectiveness measurements from a scaled-up, two-passage vane cascade. High resolution film-cooling measurements were made with an infrared (IR) camera at a number of engine representative flow conditions. Computational fluid dynamics (CFD) predictions were also made to evaluate the performance of some of the current turbulence models in predicting a complex flow such as turbine film-cooling. The RNG k-ε turbulence model gave a closer prediction of the overall level of film-effectiveness, while the v2 -f turbulence model gave a more accurate representation of the flow physics seen in the experiments.

Copyright © 2005 by ASME
Topics: Cooling , Turbines



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