The patent relates to a transition of improved design for joining the merging surfaces of the airfoil and platform of an axial-flow compressor blade of the cantilevered type. The transition as viewed in profile is a line comprising an essentially straight major portion diverging outwardly from and faired into the airfoil and an outwardly concave minor portion extending along and faired into the platform.


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    Title :

    Blade Transition for Axial-Flow Compressors and the Like


    Contributors:

    Publication date :

    1972


    Size :

    7 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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