Short-length annular combustor for turbojet engines eliminates change of exit temperature profile. Individual scoops of full annular height control air distribution so that shifts in the radial velocity profile of air entering the combustor will not affect combustion process or alter exit temperature profile.


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    Title :

    Gas turbine combustor insensitive to compressor outlet distortion


    Contributors:

    Publication date :

    1970-06-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :




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