A gas turbine engine (24) comprises a housing having an inlet leading to a fan rotor (42). A bypass door (28) is mounted upstream of the inlet to the fan rotor (42), and is moveable away from a non-bypass position to a bypass position to selectively bypass boundary layer air vertically beneath (38) the engine (24). An aircraft (20) is also disclosed.


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    Title :

    VARIABLE-GEOMETRY BOUNDARY LAYER DIVERTER


    Additional title:

    GRENZSCHICHTUMLENKER MIT VARIABLER GEOMETRIE
    DÉVIATEUR DE COUCHE LIMITE À GÉOMÉTRIE VARIABLE


    Contributors:

    Publication date :

    2022-08-24


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64C AEROPLANES , Flugzeuge



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