Unducted fan for an aircraft turbine engine, comprising at least one propeller comprising a hub and an annular array of blades extending substantially radially outwards from said hub, the hub comprising an annular array of cowls which are mounted between the radially inner ends of the blades and suitable for being fixed to an upstream collar and to a downstream collar of the hub, wherein at least one cowl comprises, at a circumferential end, at least one joint edge which is contiguous with a complementary joint edge of an adjacent cowl, and wherein said at least one cowl and at least one of said upstream and downstream collars are configured so that the cowl can be mounted and dismounted by a movement including, at least at the start thereof, a pivoting about an initial pivot axis which is circumferentially separated from said at least one joint edge in the direction of a centre of the cowl, and so that, during said pivoting, said at least one joint edge moves radially away from said complementary joint edge by moving towards the inside of said hub.


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    Titel :

    UNDUCTED FAN FOR AN AIRCRAFT TURBINE ENGINE



    Erscheinungsdatum :

    2016-08-25


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen



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