Effects of combustor exit profiles on high pressure turbine vane aerodynamics and heat transfer

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

    12 Citations (Scopus)

    Abstract

    The goal of this work was to investigate the effects of different profiles representative of those exiting aero-engine combustors on high pressure turbine vane aerodynamics and heat transfer. The various profiles were produced using the non-reacting, inlet profile generator in the Turbine Research Facility (TRF) located at the Air Force Research Laboratory (AFRL). This paper reports how the pressure loading and heat transfer along the vane surface is affected by different turbine inlet pressure and temperature profiles at several different span locations. The results indicate that the different inlet total pressure profiles affected the aerodynamic loading by as much as 10%. The results also reveal that the combination of different total pressure and total temperature profiles significantly affected the vane heat transfer for a baseline test with relatively uniform inlet total pressure and total temperature profiles. Near the ID endwall, the baseline heat transfer was reduced 30 to 40% over the majority of the vane surface. Near the OD endwall, it was found that certain inlet profiles could increase the baseline heat transfer by 20 to 30%, while other profiles resulted in a decrease of the baseline heat transfer by 30 to 40%.

    Original languageEnglish (US)
    Title of host publicationProceedings of the ASME Turbo Expo 2006 - Power for Land, Sea, and Air
    Pages285-295
    Number of pages11
    Volume3 PART A
    DOIs
    StatePublished - Nov 15 2006
    Event2006 ASME 51st Turbo Expo - Barcelona, Spain
    Duration: May 6 2006May 11 2006

    Other

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

    Fingerprint

    Combustors
    Aerodynamics
    Turbines
    Heat transfer
    Research laboratories
    Temperature
    Engines
    Air

    All Science Journal Classification (ASJC) codes

    • Engineering(all)

    Cite this

    Barringer, M. D., Thole, K. A., & Polanka, M. D. (2006). Effects of combustor exit profiles on high pressure turbine vane aerodynamics and heat transfer. In Proceedings of the ASME Turbo Expo 2006 - Power for Land, Sea, and Air (Vol. 3 PART A, pp. 285-295) https://doi.org/10.1115/GT2006-90277
    Barringer, Michael David ; Thole, Karen Ann ; Polanka, M. D. / Effects of combustor exit profiles on high pressure turbine vane aerodynamics and heat transfer. Proceedings of the ASME Turbo Expo 2006 - Power for Land, Sea, and Air. Vol. 3 PART A 2006. pp. 285-295
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    Barringer, MD, Thole, KA & Polanka, MD 2006, Effects of combustor exit profiles on high pressure turbine vane aerodynamics and heat transfer. in Proceedings of the ASME Turbo Expo 2006 - Power for Land, Sea, and Air. vol. 3 PART A, pp. 285-295, 2006 ASME 51st Turbo Expo, Barcelona, Spain, 5/6/06. https://doi.org/10.1115/GT2006-90277

    Effects of combustor exit profiles on high pressure turbine vane aerodynamics and heat transfer. / Barringer, Michael David; Thole, Karen Ann; Polanka, M. D.

    Proceedings of the ASME Turbo Expo 2006 - Power for Land, Sea, and Air. Vol. 3 PART A 2006. p. 285-295.

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

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    Barringer MD, Thole KA, Polanka MD. Effects of combustor exit profiles on high pressure turbine vane aerodynamics and heat transfer. In Proceedings of the ASME Turbo Expo 2006 - Power for Land, Sea, and Air. Vol. 3 PART A. 2006. p. 285-295 https://doi.org/10.1115/GT2006-90277