Jet engine combustor liners were tested in the structural component response facility at NASA Lewis. In this facility combustor liners were thermally cycled to simulate a flight envelope of takeoff, cruise, and return to idle. Temperatures were measured with both thermocouples and an infrared thermal imaging system. A conventional stacked-ring louvered combustor liner developed a crack at 1603 cycles. This test was discontinued after 1728 cycles because of distortion of the liner. A segmented or float wall combustor liner tested at the same heat flux showed no significant change after 1600 cycles. Changes are being made in the facility to allow higher temperatures.


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    Titel :

    High-Temperature Combustor Liner Tests in Structural Component Response Test Facility


    Beteiligte:
    P. E. Moorhead (Autor:in)

    Erscheinungsdatum :

    1988


    Format / Umfang :

    9 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





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