A fuel system for an aircraft is provided including a fuel tank configured to receive fuel and a fuel pump. The fuel pump includes a motor disposed proximate the fuel tank. The fuel pump further includes a power supply in electrical communication with the motor and disposed outside the fuel tank. The fuel pump further includes an impeller disposed within the fuel tank and rotatably coupled to the motor. The impeller includes a shaft having a first end and a second end spaced from the first end with the motor coupled to the first end. The shaft has a resistivity greater than the resistivity of the fuel tank between the first end and the second end to minimize electrical transfer between the motor and the fuel.

A fuel system for an aircraft is provided including a fuel tank configured to receive fuel and a fuel pump. The fuel pump includes a motor disposed proximate the fuel tank. The fuel pump further includes a power supply in electrical communication with the motor and disposed outside the fuel tank. The fuel system further includes an isolator component disposed between the power supply and the fuel tank. The isolator component has a resistivity greater than the resistivity of the fuel tank to minimize electrical transfer between the power supply and the fuel.

A hydrogen supply unit for an aircraft comprises a tank for storing liquid hydrogen, an extraction chamber provided in the tank with one or more openings for extracting the liquid hydrogen from the tank through the extraction chamber, at least one line connected to the extraction chamber and configured for supplying the liquid hydrogen to a consumer of the aircraft, and at least one pump connected to the line. Two or more such extraction chambers may be provided, wherein each extraction chamber is connected to an assigned valve which is connected to a control unit configured for opening and closing the valves depending on attitudes and accelerations of the aircraft.

A hydrogen supply unit for an aircraft comprises a tank for storing liquid hydrogen, an extraction chamber provided in the tank with one or more openings for extracting the liquid hydrogen from the tank through the extraction chamber, at least one line connected to the extraction chamber and configured for supplying the liquid hydrogen to a consumer of the aircraft, and at least one pump connected to the line. Two or more such extraction chambers may be provided, wherein each extraction chamber is connected to an assigned valve which is connected to a control unit configured for opening and closing the valves depending on attitudes and accelerations of the aircraft.

An aircraft including a fuselage, a power generator configured to provide power to the aircraft, and at least one fuel tank for holding fuel for the power generator, and a fuel delivery assembly. The fuel tank is positioned in the fuselage and is configured to hold hydrogen fuel in a liquid phase. The fuel tank has a chamber for holding the hydrogen fuel and a fuel extraction line fluidly coupled to the chamber. The fuel extraction line extends from the fuel tank in a forward direction of the fuselage and at a downward angle relative to a centerline of the fuselage. The fuel delivery assembly is fluidly coupled to the fuel extraction line and fluidly connects the fuel tank to the power generator. The fuel delivery assembly is configured to provide the hydrogen fuel from the fuel tank to the power generator.

An aircraft including a fuselage, a power generator configured to provide power to the aircraft, and at least one fuel tank for holding fuel for the power generator, and a fuel delivery assembly. The fuel tank is positioned in the fuselage and is configured to hold hydrogen fuel in a liquid phase. The fuel tank has a chamber for holding the hydrogen fuel and a fuel extraction line fluidly coupled to the chamber. The fuel extraction line extends from the fuel tank in a forward direction of the fuselage and at a downward angle relative to a centerline of the fuselage. The fuel delivery assembly is fluidly coupled to the fuel extraction line and fluidly connects the fuel tank to the power generator. The fuel delivery assembly is configured to provide the hydrogen fuel from the fuel tank to the power generator.

There is disclosed a fuel tank valve assembly 24 for a fuel tank 4. The fuel tank valve assembly comprises a discharge valve 30 which in normal operation is closed, and which can be opened to discharge fluid from the fuel tank; and a water passageway 56 across which extends a membrane 60 which is permeable to water but impermeable to fuel. There is also disclosed a fuel tank 4 comprising a fuel tank valve assembly 24.

There is disclosed a fuel tank valve assembly 24 for a fuel tank 4. The fuel tank valve assembly comprises a discharge valve 30 which in normal operation is closed, and which can be opened to discharge fluid from the fuel tank; and a water passageway 56 across which extends a membrane 60 which is permeable to water but impermeable to fuel. There is also disclosed a fuel tank 4 comprising a fuel tank valve assembly 24.

An aircraft comprising a dihydrogen transport pipe, a pipe shroud around the transport pipe, a dihydrogen tank, a chamber delimiting a fluidtight volume containing a system fluidically connected to the transport pipe which joins the pipe shroud through a chimney, an extraction chamber into which the chimney and the pipe shroud open, and a device for extracting to the outside the gases present in the extraction chamber.

An aircraft comprising a dihydrogen transport pipe, a pipe shroud around the transport pipe, a dihydrogen tank, a chamber delimiting a fluidtight volume containing a system fluidically connected to the transport pipe which joins the pipe shroud through a chimney, an extraction chamber into which the chimney and the pipe shroud open, and a device for extracting to the outside the gases present in the extraction chamber.