Hydraulic pitch actuation mechanism includes vaned rotor within timing chamber surrounded by annular timing chamber wall within fan hub and variable area and volume retarding and advancing chambers within timing chamber. Timing pocket walls extend inwardly from timing chamber wall and interdigitated with timing vanes extending outwardly from vane shaft of vaned rotor. Hydraulic retarding and advancing fluid passages extend through fan drive shaft and through the fan hub to the retarding and advancing chambers respectively. Fluid passages include annular axially spaced apart retarding and advancing passage discharge sections, annular and axially spaced apart retarding and advancing passage entry sections spaced apart from and aft of retarding and advancing passage discharge sections respectively. Retarding and advancing connecting passage sections extend through fan drive shaft and fluidly connect retarding and advancing passage entry sections to retarding and advancing passage discharge sections. Hub passages through fan hub connect passage discharge sections to chambers.


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    Titel :

    Aircraft gas turbine engine blade pitch change mechanism


    Beteiligte:

    Erscheinungsdatum :

    2021-09-14


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64C AEROPLANES , Flugzeuge / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS



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