A gas turbine engine comprises a nacelle that encloses a fan rotor carrying a plurality of fan blades. The nacelle is formed with droop such that one portion extends axially further from the fan blades than does another portion. The nacelle is rotatable such that a circumferential location of the one portion and the other portion may be varied dependent on flight conditions. A method of operating a gas turbine engine is also disclosed.


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    Title :

    GAS TURBINE ENGINE WITH ROTATING INLET


    Contributors:

    Publication date :

    2017-06-22


    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 / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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