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Turbine Blade Film Cooling Study: The Effects of Film Hole Location on the Pressure Side

[+] Author Affiliations
Luzeng Zhang, Hee-Koo Moon

Solar Turbines, Inc., San Diego, CA

Paper No. GT2007-27546, pp. 497-506; 10 pages
  • ASME Turbo Expo 2007: Power for Land, Sea, and Air
  • Volume 4: Turbo Expo 2007, Parts A and B
  • Montreal, Canada, May 14–17, 2007
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4793-4 | eISBN: 0-7918-3796-3
  • Copyright © 2007 by ASME


In efforts to optimize turbine blade film cooling, film effectiveness on the pressure side was investigated for shaped hole injections at three streamwise locations in a warm cascade that simulated realistic engine operation conditions. Local film effectiveness distribution was obtained for individual row of injections as well as the combination of two and three rows using the pressure sensitive paint (PSP) technique. Nitrogen gas was used to simulate cooling flow as well as a tracer gas to indicate oxygen concentration such that film effectiveness by the mass transfer analogy could be obtained. Three different cooling mass flows were injected to each of the film cooling rows and also the combination of them. For comparison among the locations, the same mass flow ratios (MFR) were kept for each of the rows. The corresponding blowing ratios were also provided for comparison. Local film effectiveness distributions were measured, and spanwise averaged for comparison. The curvature and Mach number associated with the film hole exit location had a significant effect to the value of the film cooling effectiveness. Comparing three single row injection locations, the film effectiveness for the downstream location was found to be higher than that for the upstream location. For the combined injections, the film effectiveness downstream from the second row was not only much higher than that for single row injection, but it was also higher than that predicted by a superposition model using individual row injection results. This suggests that for blade pressure surface film cooling, upstream injection could improve the downstream injection significantly, resulting in much improved film effectiveness overall.

Copyright © 2007 by ASME



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