Combustor turbine interface studies - Part 2

Flow and thermal field measurements

W. F. Colban, A. T. Lethander, Karen Ann Thole, G. Zess

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

    11 Citations (Scopus)

    Abstract

    Most turbine inlet flows resulting from the combustor exit are non-uniform in the near-platform region as a result of cooling methods used for the combustor liner. These cooling methods include injection through film-cooling holes and injection through a slot that connects the combustor and turbine. This paper presents thermal and flow field measurements in the turbine vane passage for a combustor exit flow representative of what occurs in a gas turbine engine. The experiments were performed in a large-scale wind tunnel facility that incorporates combustor and turbine vane models. The measured results for the thermal and flow fields indicate a secondary flow pattern in the vane passage that can be explained by the total pressure profile exiting the combustor. This secondary flow field is quite different than that presented for past studies with an approaching flat plate turbulent boundary layer along the upstream platform. A counter-rotating vortex that is positioned above the passage vortex was identified from the measurements. Highly turbulent and highly unsteady flow velocities occur at flow impingment locations along the stagnation line.

    Original languageEnglish (US)
    Title of host publicationAmerican Society of Mechanical Engineers, International Gas Turbine Institute, Turbo Expo (Publication) IGTI
    Pages1003-1009
    Number of pages7
    Volume3 B
    DOIs
    StatePublished - 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

    Combustors
    Turbines
    Flow fields
    Secondary flow
    Cooling
    Vortex flow
    Inlet flow
    Unsteady flow
    Flow velocity
    Flow patterns
    Wind tunnels
    Gas turbines
    Hot Temperature
    Boundary layers
    Experiments

    All Science Journal Classification (ASJC) codes

    • Engineering(all)

    Cite this

    Colban, W. F., Lethander, A. T., Thole, K. A., & Zess, G. (2002). Combustor turbine interface studies - Part 2: Flow and thermal field measurements. In American Society of Mechanical Engineers, International Gas Turbine Institute, Turbo Expo (Publication) IGTI (Vol. 3 B, pp. 1003-1009) https://doi.org/10.1115/GT2002-30527
    Colban, W. F. ; Lethander, A. T. ; Thole, Karen Ann ; Zess, G. / Combustor turbine interface studies - Part 2 : Flow and thermal field measurements. American Society of Mechanical Engineers, International Gas Turbine Institute, Turbo Expo (Publication) IGTI. Vol. 3 B 2002. pp. 1003-1009
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    abstract = "Most turbine inlet flows resulting from the combustor exit are non-uniform in the near-platform region as a result of cooling methods used for the combustor liner. These cooling methods include injection through film-cooling holes and injection through a slot that connects the combustor and turbine. This paper presents thermal and flow field measurements in the turbine vane passage for a combustor exit flow representative of what occurs in a gas turbine engine. The experiments were performed in a large-scale wind tunnel facility that incorporates combustor and turbine vane models. The measured results for the thermal and flow fields indicate a secondary flow pattern in the vane passage that can be explained by the total pressure profile exiting the combustor. This secondary flow field is quite different than that presented for past studies with an approaching flat plate turbulent boundary layer along the upstream platform. A counter-rotating vortex that is positioned above the passage vortex was identified from the measurements. Highly turbulent and highly unsteady flow velocities occur at flow impingment locations along the stagnation line.",
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    Colban, WF, Lethander, AT, Thole, KA & Zess, G 2002, Combustor turbine interface studies - Part 2: Flow and thermal field measurements. in American Society of Mechanical Engineers, International Gas Turbine Institute, Turbo Expo (Publication) IGTI. vol. 3 B, pp. 1003-1009, ASME TURBO EXPO 2002: Heat Transfer, Manufacturing Materials and Metallurgy, Amsterdam, Netherlands, 6/3/02. https://doi.org/10.1115/GT2002-30527

    Combustor turbine interface studies - Part 2 : Flow and thermal field measurements. / Colban, W. F.; Lethander, A. T.; Thole, Karen Ann; Zess, G.

    American Society of Mechanical Engineers, International Gas Turbine Institute, Turbo Expo (Publication) IGTI. Vol. 3 B 2002. p. 1003-1009.

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

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    T2 - Flow and thermal field measurements

    AU - Colban, W. F.

    AU - Lethander, A. T.

    AU - Thole, Karen Ann

    AU - Zess, G.

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    N2 - Most turbine inlet flows resulting from the combustor exit are non-uniform in the near-platform region as a result of cooling methods used for the combustor liner. These cooling methods include injection through film-cooling holes and injection through a slot that connects the combustor and turbine. This paper presents thermal and flow field measurements in the turbine vane passage for a combustor exit flow representative of what occurs in a gas turbine engine. The experiments were performed in a large-scale wind tunnel facility that incorporates combustor and turbine vane models. The measured results for the thermal and flow fields indicate a secondary flow pattern in the vane passage that can be explained by the total pressure profile exiting the combustor. This secondary flow field is quite different than that presented for past studies with an approaching flat plate turbulent boundary layer along the upstream platform. A counter-rotating vortex that is positioned above the passage vortex was identified from the measurements. Highly turbulent and highly unsteady flow velocities occur at flow impingment locations along the stagnation line.

    AB - Most turbine inlet flows resulting from the combustor exit are non-uniform in the near-platform region as a result of cooling methods used for the combustor liner. These cooling methods include injection through film-cooling holes and injection through a slot that connects the combustor and turbine. This paper presents thermal and flow field measurements in the turbine vane passage for a combustor exit flow representative of what occurs in a gas turbine engine. The experiments were performed in a large-scale wind tunnel facility that incorporates combustor and turbine vane models. The measured results for the thermal and flow fields indicate a secondary flow pattern in the vane passage that can be explained by the total pressure profile exiting the combustor. This secondary flow field is quite different than that presented for past studies with an approaching flat plate turbulent boundary layer along the upstream platform. A counter-rotating vortex that is positioned above the passage vortex was identified from the measurements. Highly turbulent and highly unsteady flow velocities occur at flow impingment locations along the stagnation line.

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    Colban WF, Lethander AT, Thole KA, Zess G. Combustor turbine interface studies - Part 2: Flow and thermal field measurements. In American Society of Mechanical Engineers, International Gas Turbine Institute, Turbo Expo (Publication) IGTI. Vol. 3 B. 2002. p. 1003-1009 https://doi.org/10.1115/GT2002-30527