Transonic high-pressure turbines are promising candidates for future aircraft engines. Recent studies in transonic turbine cascades showed that shock waves appeared over the uncooled flat tip, which affects its heat transfer. However, the effects of coolant injection on the thermal performance of transonic cooled tips are not clear. The current study aims to understand the thermal performance of a cooled flat tip and a cooled cavity tip in a transonic turbine cascade. The effects of tip film cooling are studied at five coolant pressure ratios (which are the stagnation pressure ratios of the coolant inlet and the cascade inlet) from 0.8 to 1.2. The flow physics over the tip, the heat transfer coefficient, the film-cooling effectiveness, and the heat flux of the tip are investigated. The effects of relative endwall motion are considered.


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    Titel :

    Thermal Performance of Transonic Cooled Tips in a Turbine Cascade


    Beteiligte:
    Zhou, Chao (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2015




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch



    Klassifikation :

    BKL:    55.50 Luftfahrzeugtechnik / 55.50
    Lokalklassifikation TIB:    770/7040