A gas turbine engine has an upstream compressor having an upstream entrance area leading into a first vane upstream of the upstream compressor. A downstream compressor has an exit area at a leading edge of an exit vane for the downstream compressor. The entrance area divided by the exit area is greater than or equal to 13.8 and less than or equal to 15.3.


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    Title :

    COMPRESSOR AREA SPLITS FOR GEARED TURBOFAN


    Contributors:

    Publication date :

    2016-07-14


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



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