A fan assembly (16) for gas turbine engine (18) includes a plurality of fan blades (20) rotatable about a fan rotation axis (A), each of the plurality of fan blades movable about an axis (46) transverse to the fan rotation axis (A), a fan nacelle (26) partially surrounding the plurality of fan blades (20), and a pitch mechanism (40) coupled to the plurality of blades (20) that changes an angle of pitch for each of the plurality of blades corresponding to a circumferential position of the fan blade about the fan rotation axis (A).


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    Titel :

    BOUNDARY LAYER INGESTING FAN


    Weitere Titelangaben:

    GRENZSCHICHTFAN
    SOUFFLANTE D'INGESTION DE COUCHE LIMITE


    Beteiligte:

    Erscheinungsdatum :

    09.04.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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