Operation of the original engine configuration disclosed a severe compressor stall problem at high altitude, which was largely attributed to a radial flow distortion entering the high-pressure compressor. Engine modifications for eliminating or alleviating the stall problem were investigated. These included use of variable high-pressure compressor inlet guide vanes, increased turbine-stator areas, and minor alterations in both the low- and high-pressure compressor rotors.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Investigation of a Prototype Iroquois Turbojet Engine in an Altitude Test Chamber. COORD. NO. AF-P-6


    Contributors:

    Publication date :

    1958-06-13


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English