Study of leakage flows for a first vane in a gas turbine

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

    Abstract

    Turbine inlet temperatures are continuing to increase as driven by the need to improve the engine's performance. Moreover, thermal pattern factors exiting the combustor are being driven towards a flatter profile to reduce NOx combustion, which in turn gives high temperature gradients near the vane endwalls. For these reasons, the endwall of the first vane is subjected to severe heat transfer conditions. To combat these high heat transfer levels, film cooling is generally used and is proven to be one of the most effective cooling methods for the endwall. This paper presents a computational study of a film-cooled endwall that also includes a realistic upstream slot, representing the combustor-turbine junction, and a midpassage gap, representing the mating between adjacent vanes. The focus of the results is on comparing adiabatic film-cooling effectiveness levels on the endwall with varying upstream slot widths and varying geometries of the mid-passage gap. Changes in the upstream slot widths occur because of thermal expansions and contractions during engine operation. Varying the inclination angle of the midpassage gap produced varying results along the endwall. The predictions indicated more effective cooling on the endwall as the gap flow was injected towards the suction side of the vane relative to the gap flow being injected towards the pressure side of the vane. The area showing the most improvement in cooling for injection towards the suction side was the trailing edge region along the suction side of the airfoil.

    Original languageEnglish (US)
    Title of host publicationProceedings of the 11th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC-11
    Pages330-343
    Number of pages14
    StatePublished - Dec 1 2006
    Event11th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC-11 - Honolulu, HI, United States
    Duration: Feb 26 2006Mar 2 2006

    Publication series

    NameProceedings of the 11th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC-11
    Volume1

    Other

    Other11th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC-11
    CountryUnited States
    CityHonolulu, HI
    Period2/26/063/2/06

    Fingerprint

    Gas turbines
    Cooling
    Combustors
    Turbines
    Heat transfer
    Engines
    Airfoils
    Thermal gradients
    Thermal expansion
    Geometry
    Temperature

    All Science Journal Classification (ASJC) codes

    • Mechanical Engineering

    Cite this

    Hada, S., & Thole, K. A. (2006). Study of leakage flows for a first vane in a gas turbine. In Proceedings of the 11th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC-11 (pp. 330-343). (Proceedings of the 11th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC-11; Vol. 1).
    Hada, S. ; Thole, Karen Ann. / Study of leakage flows for a first vane in a gas turbine. Proceedings of the 11th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC-11. 2006. pp. 330-343 (Proceedings of the 11th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC-11).
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    title = "Study of leakage flows for a first vane in a gas turbine",
    abstract = "Turbine inlet temperatures are continuing to increase as driven by the need to improve the engine's performance. Moreover, thermal pattern factors exiting the combustor are being driven towards a flatter profile to reduce NOx combustion, which in turn gives high temperature gradients near the vane endwalls. For these reasons, the endwall of the first vane is subjected to severe heat transfer conditions. To combat these high heat transfer levels, film cooling is generally used and is proven to be one of the most effective cooling methods for the endwall. This paper presents a computational study of a film-cooled endwall that also includes a realistic upstream slot, representing the combustor-turbine junction, and a midpassage gap, representing the mating between adjacent vanes. The focus of the results is on comparing adiabatic film-cooling effectiveness levels on the endwall with varying upstream slot widths and varying geometries of the mid-passage gap. Changes in the upstream slot widths occur because of thermal expansions and contractions during engine operation. Varying the inclination angle of the midpassage gap produced varying results along the endwall. The predictions indicated more effective cooling on the endwall as the gap flow was injected towards the suction side of the vane relative to the gap flow being injected towards the pressure side of the vane. The area showing the most improvement in cooling for injection towards the suction side was the trailing edge region along the suction side of the airfoil.",
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    Hada, S & Thole, KA 2006, Study of leakage flows for a first vane in a gas turbine. in Proceedings of the 11th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC-11. Proceedings of the 11th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC-11, vol. 1, pp. 330-343, 11th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC-11, Honolulu, HI, United States, 2/26/06.

    Study of leakage flows for a first vane in a gas turbine. / Hada, S.; Thole, Karen Ann.

    Proceedings of the 11th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC-11. 2006. p. 330-343 (Proceedings of the 11th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC-11; Vol. 1).

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

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    Hada S, Thole KA. Study of leakage flows for a first vane in a gas turbine. In Proceedings of the 11th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC-11. 2006. p. 330-343. (Proceedings of the 11th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC-11).