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.
A fuel flow system
2017-11-01
Patent
Electronic Resource
English
Automotive engineering | 1979
|Tema Archive | 1979
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