Abstract Some design and experimental data on three cascades with the same 12° bending angle for the primary nozzle block of a gas turbine are presented. As is seen from the investigation the most efficient at the transonic velocities of the outward flow are the blades, the back curvature of which in the bevel cut zone decreases to the trailing edge. Also presented is the fact that the blade with the increasing back curvature has noticeably larger losses.


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    Title :

    On choice of the blade back profile curvature in transonic turbine cascades


    Contributors:

    Published in:

    Publication date :

    2011-06-01


    Size :

    6 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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