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.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    COMPRESSOR STALL PROBLEMS IN GAS-TURBINE-TYPE AIRCRAFT ENGINES


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    Pre-1964 SAE Technical Papers ; 1906



    Publication date :

    1957-01-01




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Compressor-stall problems in gas-turbine type aircraft engines

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




    Supersonic STOVL aircraft with turbine bypass/turbo-compressor engines

    Franciscus, L. C. / Luidens, R. W. | NTRS | 1984