An integrated propulsion system comprising at least two gas turbine engines, at least one fan, and a transmission assembly coupling the at least two gas turbine engines to the at least one fan wherein the at least two gas turbine engines are disposed within a main body of an airframe comprising the main body and a pair of wings, and wherein the number of gas turbine engines is greater than the number of fans.


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    Title :

    INTEGRATED AIRCRAFT PROPULSION SYSTEM


    Contributors:

    Publication date :

    2017-03-02


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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