Film-cooling flowfields with trenched holes on an endwall

N. Sundaram, K. A. Thole

Research output: Chapter in Book/Report/Conference proceedingConference contribution

7 Scopus citations


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.

Original languageEnglish (US)
Title of host publication2008 Proceedings of the ASME Turbo Expo
Subtitle of host publicationPower for Land, Sea, and Air
Number of pages12
EditionPART A
StatePublished - 2008
Event2008 ASME Turbo Expo - 2008 ASME Turbo Expo, Germany
Duration: Jun 9 2008Jun 13 2008

Publication series

NameProceedings of the ASME Turbo Expo
NumberPART A


Other2008 ASME Turbo Expo
City2008 ASME Turbo Expo

All Science Journal Classification (ASJC) codes

  • General Engineering


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