The reasons for the low aerodynamic performance of a 13.5 cm tip diameter aircraft engine starter turbine were investigated. Both the stator and the stage were evaluated. Approximately 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. Efficiency improvements were obtained for three rotor configurations when the shroud was filled. It is suggested that the large loss associated with the open honeycomb shroud is due primarily to energy loss associated with gas transportation as a result of the blade to blade pressure differential at the tip section.


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    Title :

    Reasons for low aerodynamic performance of 13.5-centimeter-tip-diameter aircraft engine starter turbine


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

    Conference:

    SAE Aerospace Meeting ; 1980 ; Los Angeles, CA, United States


    Publication date :

    1981-03-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English