A gas turbine engine (20,100,109) comprises a nacelle (94,110) that encloses a fan rotor (103) carrying a plurality of fan blades (98). The nacelle (94,110) is formed such that one portion (96) extends axially further from the fan blades (98) than does another portion (97). The nacelle (94,110) is rotatable such that a circumferential location of the one portion (96) and the other portion (97) may be varied dependent on flight conditions.


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    Title :

    GAS TURBINE ENGINE WITH ROTATING INLET


    Additional title:

    GASTURBINENMOTOR MIT ROTIERENDEM EINLASS
    TURBINE À GAZ AYANT UNE ADMISSION ROTATIVE


    Contributors:

    Publication date :

    2020-04-22


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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