Effect of non-uniform inlet conditions on endwall secondary flows

K. S. Hermanson, Karen Ann Thole

    Research output: Contribution to conferencePaper

    Abstract

    Exit combustor flow and thermal fields entering downstream stator vane passages in a gas turbine engine are highly non-uniform. These flow and thermal fields can significantly affect the development of the secondary flows in the turbine passages contributing to high platform heat transfer and large aerodynamic losses. The flow and thermal fields combine to give non-uniform total pressure profiles entering the turbine passage which, along with the airfoil geometry, dictate the secondary flow field. This paper presents an analysis of the effects of varying total pressure profiles in both the radial and combined radial and circumferential directions on the secondary flow fields in a first stage stator vane. These inlet conditions used for the first vane simulations are based on the exit conditions predicted for a combustor. Prior to using the predictions, these CFD simulations were benchmarked against flow field data measured in a large-scale, linear, turbine vane cascade. Good agreement occurred between the computational predictions and experimentally measured secondary flows. Analyses of the results for several different cases indicate variations in the secondary flow pattern from pitch to pitch, which attributes to the rationale as to why some airfoils quickly degrade while others remain intact over time.

    Original languageEnglish (US)
    Pages245-254
    Number of pages10
    DOIs
    StatePublished - Dec 1 2002
    EventASME TURBO EXPO 2002:Heat Transfer, Manufacturing Materials and Metallurgy - Amsterdam, Netherlands
    Duration: Jun 3 2002Jun 6 2002

    Other

    OtherASME TURBO EXPO 2002:Heat Transfer, Manufacturing Materials and Metallurgy
    CountryNetherlands
    CityAmsterdam
    Period6/3/026/6/02

    Fingerprint

    Secondary flow
    Turbines
    Flow fields
    Combustors
    Airfoils
    Stators
    Cascades (fluid mechanics)
    Flow patterns
    Gas turbines
    Aerodynamics
    Computational fluid dynamics
    Heat transfer
    Geometry
    Hot Temperature

    All Science Journal Classification (ASJC) codes

    • Engineering(all)

    Cite this

    Hermanson, K. S., & Thole, K. A. (2002). Effect of non-uniform inlet conditions on endwall secondary flows. 245-254. Paper presented at ASME TURBO EXPO 2002:Heat Transfer, Manufacturing Materials and Metallurgy, Amsterdam, Netherlands. https://doi.org/10.1115/GT2002-30188
    Hermanson, K. S. ; Thole, Karen Ann. / Effect of non-uniform inlet conditions on endwall secondary flows. Paper presented at ASME TURBO EXPO 2002:Heat Transfer, Manufacturing Materials and Metallurgy, Amsterdam, Netherlands.10 p.
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    Hermanson, KS & Thole, KA 2002, 'Effect of non-uniform inlet conditions on endwall secondary flows' Paper presented at ASME TURBO EXPO 2002:Heat Transfer, Manufacturing Materials and Metallurgy, Amsterdam, Netherlands, 6/3/02 - 6/6/02, pp. 245-254. https://doi.org/10.1115/GT2002-30188

    Effect of non-uniform inlet conditions on endwall secondary flows. / Hermanson, K. S.; Thole, Karen Ann.

    2002. 245-254 Paper presented at ASME TURBO EXPO 2002:Heat Transfer, Manufacturing Materials and Metallurgy, Amsterdam, Netherlands.

    Research output: Contribution to conferencePaper

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    AU - Hermanson, K. S.

    AU - Thole, Karen Ann

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    N2 - Exit combustor flow and thermal fields entering downstream stator vane passages in a gas turbine engine are highly non-uniform. These flow and thermal fields can significantly affect the development of the secondary flows in the turbine passages contributing to high platform heat transfer and large aerodynamic losses. The flow and thermal fields combine to give non-uniform total pressure profiles entering the turbine passage which, along with the airfoil geometry, dictate the secondary flow field. This paper presents an analysis of the effects of varying total pressure profiles in both the radial and combined radial and circumferential directions on the secondary flow fields in a first stage stator vane. These inlet conditions used for the first vane simulations are based on the exit conditions predicted for a combustor. Prior to using the predictions, these CFD simulations were benchmarked against flow field data measured in a large-scale, linear, turbine vane cascade. Good agreement occurred between the computational predictions and experimentally measured secondary flows. Analyses of the results for several different cases indicate variations in the secondary flow pattern from pitch to pitch, which attributes to the rationale as to why some airfoils quickly degrade while others remain intact over time.

    AB - Exit combustor flow and thermal fields entering downstream stator vane passages in a gas turbine engine are highly non-uniform. These flow and thermal fields can significantly affect the development of the secondary flows in the turbine passages contributing to high platform heat transfer and large aerodynamic losses. The flow and thermal fields combine to give non-uniform total pressure profiles entering the turbine passage which, along with the airfoil geometry, dictate the secondary flow field. This paper presents an analysis of the effects of varying total pressure profiles in both the radial and combined radial and circumferential directions on the secondary flow fields in a first stage stator vane. These inlet conditions used for the first vane simulations are based on the exit conditions predicted for a combustor. Prior to using the predictions, these CFD simulations were benchmarked against flow field data measured in a large-scale, linear, turbine vane cascade. Good agreement occurred between the computational predictions and experimentally measured secondary flows. Analyses of the results for several different cases indicate variations in the secondary flow pattern from pitch to pitch, which attributes to the rationale as to why some airfoils quickly degrade while others remain intact over time.

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    Hermanson KS, Thole KA. Effect of non-uniform inlet conditions on endwall secondary flows. 2002. Paper presented at ASME TURBO EXPO 2002:Heat Transfer, Manufacturing Materials and Metallurgy, Amsterdam, Netherlands. https://doi.org/10.1115/GT2002-30188