An aircraft fuel system has a bottom wall, and a rib with a bottom edge joined to the bottom wall. The rib provides a boundary between first and second compartments, and at least the first compartment is arranged to carry fuel when the system is in use. An open recess is located in the bottom edge of the rib, and a rib sealing arrangement between the bottom edge of the rib and the bottom wall prevents fuel from flowing across the bottom edge of the rib except at the open recess. The system has a pump and a conduit coupled at one end to the open recess and at another end to the pump, the open recess and the conduit together providing a flow path for fuel to flow across the bottom edge of the rib from the first compartment into the pump. The flow path is sealed so that the fuel flowing along the flow path is prevented from flowing out of the flow path into the second compartment.


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    Titel :

    AIRCRAFT FUEL SYSTEM


    Weitere Titelangaben:

    FLUGZEUGKRAFTSTOFFSYSTEM
    SYSTÈME DE CARBURANT D'AÉRONEFS


    Beteiligte:
    MORGAN ANGUS (Autor:in)

    Erscheinungsdatum :

    2017-08-02


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64C AEROPLANES , Flugzeuge



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