This paper was presented at the SAE National Aeronautic Meeting, New York, April 12, 1956.STALL of axial-flow-type compressors limits the flexibility of operation of 1- and 2-spool aircraft turbojet engines. Complete compressor stall or surge is a problem with regard to engine acceleration as well as low-and high-Mach-number flight at high altitudes.Deterioration of compressor performance due to low Reynolds numbers at extreme altitudes aggravates the stall problem. Inlet-flow distortions increase the severity of this problem, particularly for supersonic flight.Rotating stall at low values of equivalent rotative speed is a serious source of blade vibrational failure. This latter problem is also aggravated by inlet-flow distortions.This paper was presented at the SAE National Aeronautic Meeting, New York, April 12, 1956.STALL of axial-flow-type compressors limits the flexibility of operation of 1- and 2-spool aircraft turbojet engines. Complete compressor stall or surge is a problem with regard to engine acceleration as well as low-and high-Mach-number flight at high altitudes.Deterioration of compressor performance due to low Reynolds numbers at extreme altitudes aggravates the stall problem. Inlet-flow distortions increase the severity of this problem, particularly for supersonic flight.Rotating stall at low values of equivalent rotative speed is a serious source of blade vibrational failure. This latter problem is also aggravated by inlet-flow distortions.This paper was presented at the SAE National Aeronautic Meeting, New York, April 12, 1956.STALL of axial-flow-type compressors limits the flexibility of operation of 1- and 2-spool aircraft turbojet engines. Complete compressor stall or surge is a problem with regard to engine acceleration as well as low-and high-Mach-number flight at high altitudes.Deterioration of compressor performance due to low Reynolds numbers at extreme altitudes aggravates the stall problem. Inlet-flow distortions increase the severity of this problem, particularly for supersonic flight.Rotating stall at low values of equivalent rotative speed is a serious source of blade vibrational failure. This latter problem is also aggravated by inlet-flow distortions.


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    Titel :

    COMPRESSOR STALL PROBLEMS IN GAS-TURBINE-TYPE AIRCRAFT ENGINES


    Weitere Titelangaben:

    Sae Technical Papers


    Beteiligte:

    Kongress:

    Pre-1964 SAE Technical Papers ; 1906



    Erscheinungsdatum :

    1957-01-01




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




    Compressor-stall problems in gas-turbine type aircraft engines

    Benser, W.A. / Finger, H.B. | Engineering Index Backfile | 1956



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