A self-contained counter rotating turbo prop system (14) is driven by a gas turbine engine (10) through a reduction gearbox (12). A gear train housed separate from the reduction gearbox (12) provides the counter-rotation of a first and second pluralities of propeller blades (18,20). The entire counter-rotating propeller system (14) is disposed within cowlings (16A,16B) and is separate from the gas turbine engine (10) and reduction gearbox (12). The counter rotating propeller system (14) includes a collective blade angle actuation system (55) that provides for adjustment of blade angle of both the first and second plurality of propeller blades (18,20) with a single actuator.


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    Title :

    Modular counter rotating propeller system


    Additional title:

    Modulares gegenläufigen Propeller-System
    Système modulaire d'hélices contrarotatives


    Contributors:

    Publication date :

    2019-10-02


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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