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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    Titel :

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


    Beteiligte:
    J. E. Haas (Autor:in) / R. J. Roelke (Autor:in) / P. Hermann (Autor:in)

    Erscheinungsdatum :

    1981


    Format / Umfang :

    19 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch