Recent trends in small advanced gas turbine engines call for higher turbine inlet temperatures. Advances in radial turbine technology have opened the way for a cooled metallic radial turbine capable of withstanding turbine inlet temperatures of 2500 F while meeting the challenge of high efficiency in this small flow size range. In response to this need, a small air-cooled radial turbine has been designed utilizing internal blade coolant passages. The coolant flow passage design is uniquely tailored to simultaneously meet rotor cooling needs and rotor fabrication constraints. The rotor flow-path design seeks to realize improved aerodynamic blade loading characteristics and high efficiency while satisfying rotor life requirements. An up-scaled version of the final engine rotor is currently under fabrication and, after instrumentation, will be tested in the warm turbine test facility at the NASA Lewis Research Center.


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    Title :

    The design of an air-cooled metallic high temperature radial turbine


    Additional title:

    Konstruktion einer luftgekuehlten Radialturbine aus Metall fuer hohe Gaseinlasstemperaturen


    Contributors:
    Snyder, P.H. (author) / Roelke, R.J. (author)

    Published in:

    AIAA-Papers ; Jul ; 1-8


    Publication date :

    1988


    Size :

    8 Seiten, 15 Bilder, 2 Tabellen, 20 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Design of an air-cooled metallic high-temperature radial turbine

    Snyder, Philip H. / Roelke, Richard J. | NTRS | 1990


    Design of an air-cooled metallic high-temperature radial turbine

    SNYDER, PHILIP H. / ROELKE, RICHARD J. | AIAA | 1990


    The design of an air-cooled metallic high temperature radial turbine

    SNYDER, PHILIP / ROELKE, RICHARD | AIAA | 1988



    Temperature Distribution Study in a Cooled Radial Inflow Turbine Rotor

    A. Hamed / E. Baskharone / W. Tabakoff | AIAA | 1977