An experimental investigation was made at the NASA Lewis Research Center to determine the reasons for the low aerodynamic performance of a 13.5-centimeter-tip-diameter aircraft engine starter turbine. The investigation consisted of an evaluation of both the stator and the stage. An approximate 10-percent improvement in turbine efficiency was obtained when the honeycomb shroud over the rotor blade tips was filled to obtain a solid shroud surface. (Author)


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    Title :

    Reasons for Low Aerodynamic Performance of 13.5-Centimeter-Tip-Diameter Aircraft Engine Starter Turbine


    Contributors:
    J. E. Haas (author) / R. J. Roelke (author) / P. Hermann (author)

    Publication date :

    1981


    Size :

    19 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English