A bypass gas turbine engine (10) includes a variable area fan nozzle (42) with a second fan nacelle section (54) axially movable relative to a first fan nacelle (52) section to define an auxiliary port to vary a fan nozzle exit area (44) and adjust fan bypass airflow. The second fan nacelle section (54) includes a leading edge region (54L) that defines a concave external contour and the first fan nacelle section (52) includes a trailing edge (52T) region that defines a convex internal contour.


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    Title :

    Gas turbine engine with variable area fan nozzle


    Additional title:

    Gasturbinenmotor mit verstellbarer Fandüse
    Moteur à turbine à gaz doté d'une section de soufflante variable


    Contributors:

    Publication date :

    2019-07-10


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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