The report describes experimental research conducted with a linear, stationary, supersonic compressor cascade with blades of constant spanwise geometry and contoured sidewalls. The cascade incorporated splitter vanes midway between blades in the latter half of each blade passage. A prior investigation with this cascade was conducted without splitter vanes and was reported previously. The principal objective of that program was to obtain cascade-type data for a selected blade element from a compressor configuration resulting from the Aerospace Research Laboratories in-house program of research on supersonic axial compressors. Splitter vanes, designed in a manner similar to those used in the rotor, were incorporated in the supersonic compressor cascade. Additional work was conducted and the primary objective was to obtain cascade-type data for the particular compressor blade-splitter vane combination. (Modified author abstract)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Test of a Supersonic Compressor Cascade with Splitter Vanes


    Contributors:

    Publication date :

    1973


    Size :

    471 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English