A gas turbine engine including a core engine and a variable pitch fan arranged in flow communication with the core engine is provided. The variable pitch fan includes a plurality of blades coupled to a disk (42), the blades and disk configured to rotate together about an axial direction of the engine. A rotatable front hub may be provided over a front end of the variable pitch fan, including the disk. The gas turbine engine additionally includes a plurality of trunnion mechanisms (92) coupling each of the plurality of fan blades to a respective disk segment (90) at the disk. Each trunnion mechanism (92) includes a bearing having one or more components formed of a nonferrous material, decreasing a weight of the respective trunnion mechanism and allowing for, e.g., a smaller front hub.


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    Title :

    FAN BEARINGS FOR A TURBINE ENGINE


    Additional title:

    LÜFTERLAGER FÜR EINEN TURBINENMOTOR
    PALIERS DE VENTILATEUR POUR MOTEUR À TURBINE



    Publication date :

    2016-10-12


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F02K JET-PROPULSION PLANTS , Strahltriebwerke / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS



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