This paper describes recently completed and current advanced liner research applicable to advanced small gas turbine engines. Research relating to the evolution of fuel efficient small gas turbine engines capable of meeting future commercial and military aviation needs is currently underway at NASA Lewis Research Center. As part of this research, a reverse-flow combustor geometry was maintained while different advanced liner wall cooling techniques were investigated and compared to a baseline combustor. The performance of the combustosr featuring counter-flow film-cooled liner (CFFC) panels, transpiration cooled liner walls (TRANS), and compliant metal/ceramic (CMC) walls was obtained over a range of simulated flight conditions of a 16:1 pressure ratio gas turbine engine and fuel air ratios up to 0.034. All the combustors featured an identical fuel injection system, identical geometric configuration outline, and similar designed internal aerothermodynamics.


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    Title :

    Liner cooling research at NASA Lewis Research Center


    Additional title:

    Erforschung der Auskleidungskuehlung im NASA Lewis Research Center


    Contributors:

    Published in:

    AIAA-Papers ; Jul ; 1-16


    Publication date :

    1987


    Size :

    16 Seiten, 10 Bilder, 1 Tabelle, 9 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English