A fuel flow system for an aircraft has a fuel conduit 36 having a fuel inflow 31 and a fuel outflow 32 along which a fuel/water mix is configured to flow from the fuel inflow to the fuel outflow. The fuel conduit is fluidly communicable with a fuel tank 21. A peripheral conduit 38 surrounds at least part of the fuel conduit. A water-permeable filter member 42 allows the passage of water, but not fuel into the peripheral conduit 38. The system may apply a pressure differential over the water-permeable member 42, by means of a pump connected to the fuel conduit [25, fig 2] and a pump connected to the peripheral conduit [35, fig.2]. Preferably, the fuel flow system is a fuel recirculation system, which recirculates fuel to the fuel tank 21 of the aeroplane.


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    Titel :

    A fuel flow system


    Beteiligte:
    NEIL FROST (Autor:in)

    Erscheinungsdatum :

    2017-11-01


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02M Zuführen von Brennstoff-Luft-Gemischen oder deren Bestandteilen bei Brennkraftmaschinen allgemein , SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF



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