A fan assembly for a gas turbine engine includes a fan disk, a trunnion, a fan blade, and a counterweight assembly. The fan disk is configured to rotate about an axial centerline of the gas turbine engine when installed in the gas turbine engine. The trunnion is mounted to the fan disk and defines a slot extending through a portion of the trunnion. The fan blade defines a pitch axis and is rotatably attached to the fan disk about its pitch axis through the trunnion. The counterweight assembly includes a link arm extending to the trunnion and an engagement device mounted to the link arm that is disposed to move through the slot of the trunnion.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Levered counterweight feathering system



    Erscheinungsdatum :

    24.10.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS



    Levered suspension

    Bound, R.H. | Engineering Index Backfile | 1944


    Blade feathering and feathering hinges

    Baumgartl, P. | Engineering Index Backfile | 1952


    Levered connector extractor

    Takahashi, Ted H. | NTRS | 1989


    SEMI-LEVERED SHRINK LANDING GEAR

    DAHL BRUCE A / SAKURAI SEIYA | Europäisches Patentamt | 2023

    Freier Zugriff

    FEATHERING HORIZONTAL FINS

    AKHAPKIN SERGEJ SERGEEVICH | Europäisches Patentamt | 2018

    Freier Zugriff