Stall of axial flow type compressor limits flexibility of operation of one- and two-spool turbojet engines; rotating stall at low values of equivalent rotative speed is serious source of blade vibrational failure; latter problem is also aggravated by inlet flow distortions.


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    Title :

    Compressor-stall problems in gas-turbine type aircraft engines


    Additional title:

    Soc Automotive Engrs -- Paper


    Contributors:
    Benser, W.A. (author) / Finger, H.B. (author)

    Conference:

    Society of Automotive Engineers -- Meeting ; 1956 Surges



    Publication date :

    1956


    Size :

    15 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English