A comparison of cylindrical and fan-shaped film-cooling holes on a vane endwall at low and high freestream turbulence levels

W. Colban, Karen Ann Thole, M. Haendler

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

    13 Scopus citations

    Abstract

    Fan-shaped film-cooling holes have been shown to provide superior cooling performance to cylindrical holes along flat-plates and turbine airfoils over a large range of different conditions. Benefits of fan-shaped holes include less required cooling air for the same performance, increased part lifetime, and fewer required holes. The major drawback however, is increased manufacturing cost and manufacturing difficulty, particularly for the vane platform region. To this point, there have only been extremely limited comparisons between cylindrical and shaped holes on a turbine endwall at either low or high freestream turbulence conditions. This study presents film-cooling effectiveness measurements on an endwall surface in a large-scale, low-speed, two-passage, linear vane cascade. Results showed that film-cooling effectiveness decreased with increasing blowing rate for the cylindrical holes, indicating jet lift-off. However, the fan-shaped passage showed increased film-cooling effectiveness with increasing blowing ratio. Overall, fan-shaped holes increased film-cooling effectiveness by an average of 75% over cylindrical holes for constant cooling flow.

    Original languageEnglish (US)
    Title of host publicationProceedings of the ASME Turbo Expo 2006 - Power for Land, Sea, and Air
    Pages25-35
    Number of pages11
    DOIs
    StatePublished - Nov 15 2006
    Event2006 ASME 51st Turbo Expo - Barcelona, Spain
    Duration: May 6 2006May 11 2006

    Publication series

    NameProceedings of the ASME Turbo Expo
    Volume3 PART A

    Other

    Other2006 ASME 51st Turbo Expo
    CountrySpain
    CityBarcelona
    Period5/6/065/11/06

    All Science Journal Classification (ASJC) codes

    • Engineering(all)

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