Combustor turbine interface studies - Part 1: Endwall effectiveness measurements

W. F. Colban, Karen Ann Thole, G. Zess

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

    16 Scopus citations

    Abstract

    Improved durability of gas turbine engines is an objective for both military and commercial aeroengines as well as for power generation engines. One region susceptible to degradation in an engine is the junction between the combustor and first vane given that the main gas path temperatures at this location are the highest. The platform at this junction is quite complex in that secondary flow effects, such as the leading edge vortex, are dominant. Past computational studies have shown that the total pressure profile exiting the combustor dictates the development of the secondary flows that are formed. This study examines the effect of varying the combustor liner film-cooling and junction slot flows on the adiabatic wall temperatures measured on the platform of the first vane. The experiments were performed using large-scale models of a combustor and nozzle guide vane in a wind tunnel facility. The results show that varying the coolant injection from the upstream combustor liner leads to differing total pressure profiles entering the turbine vane passage. Endwall adiabatic effectiveness measurements indicate that the coolant does not exit the upstream combustor slot uniformly but instead accumulates along the suction side of the vane and endwall. Increasing the liner cooling continued to reduce endwall temperatures, which was not found to be true with increasing the film-cooling from the liner.

    Original languageEnglish (US)
    Title of host publicationAmerican Society of Mechanical Engineers, International Gas Turbine Institute, Turbo Expo (Publication) IGTI
    Pages993-1001
    Number of pages9
    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

    All Science Journal Classification (ASJC) codes

    • Engineering(all)

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