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Film-Cooling Flowfields With Trenched Holes on an Endwall

[+] Author Affiliations
N. Sundaram, K. A. Thole

Pennsylvania State University, University Park, PA

Paper No. GT2008-50149, pp. 121-132; 12 pages
  • ASME Turbo Expo 2008: Power for Land, Sea, and Air
  • Volume 4: Heat Transfer, Parts A and B
  • Berlin, Germany, June 9–13, 2008
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4314-7 | eISBN: 0-7918-3824-2
  • Copyright © 2008 by ASME


The leading edge region along the endwall of a stator vane experiences high heat transfer rates resulting from the formation of horseshoe vortices. Typical gas turbine endwall designs include a leakage slot at the combustor-turbine interface as well as film-cooling holes. Past studies have documented the formation of a horseshoe vortex at the leading edge of a vane, but few studies have documented the flowfield in the presence of an interface slot and film-cooling jets. In this paper, a series of flowfield measurements are evaluated at the leading edge with configurations including: a baseline with neither film-cooling holes nor an upstream slot, a row of film-cooling holes and an interface slot, and a row of film-cooling holes in a trench and an interface slot. The results indicated the formation of a second vortex present for the case with film-cooling holes and a slot relative to the baseline study. In addition, turbulence intensity levels as high as 50% were measured at the leading edge with film-cooling holes and a slot compared to the 30% measured for the baseline study. A trench was shown to provide improved overall cooling relative to the no trench configuration as more of the coolant stayed attached to the endwall surface with the trench.

Copyright © 2008 by ASME
Topics: Cooling



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