Effect of non-uniform inlet conditions on endwall secondary flows

K. S. Hermanson, Karen Ann Thole

    Research output: Contribution to conferencePaperpeer-review


    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)
    Number of pages10
    StatePublished - Dec 1 2002
    EventASME TURBO EXPO 2002:Heat Transfer, Manufacturing Materials and Metallurgy - Amsterdam, Netherlands
    Duration: Jun 3 2002Jun 6 2002


    OtherASME TURBO EXPO 2002:Heat Transfer, Manufacturing Materials and Metallurgy

    All Science Journal Classification (ASJC) codes

    • Engineering(all)


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