An aircraft having an engine, a dihydrogen tank, devices to be heated, a first air intake for taking in air at a low pressure or at an intermediate pressure, a second air intake for taking in air at a high pressure, a first heat exchanger, a first pipe which passes through the first heat exchanger and feeds the devices to be heated. Upstream of the first heat exchanger, the first pipe is divided into two sub-pipes connected respectively to the first air intake and the second air intake, and a fuel pipe that is connected between the tank and the combustion chamber and passes through the first heat exchanger. The use of heat exchangers on the dihydrogen pipe allows a regulation of the temperature of the devices to be heated and of the engine and to increase the temperature of the dihydrogen before its combustion.

An embodiment of a gear pump arrangement includes a first gear defining a first set of teeth; and a second gear defining a second set of teeth, the first set of teeth and the second set of teeth being in meshed communication such that fluid is pumped in response to rotation of the first gear and the second gear, at least one of the first set of teeth and the second set of teeth having at least one gear tooth passageway through each tooth thereby fluidically connecting opposing faces of the tooth.

An embodiment of a gear pump arrangement includes a first gear defining a first set of teeth; and a second gear defining a second set of teeth, the first set of teeth and the second set of teeth being in meshed communication such that fluid is pumped in response to rotation of the first gear and the second gear, at least one of the first set of teeth and the second set of teeth having at least one gear tooth passageway through each tooth thereby fluidically connecting opposing faces of the tooth.

Commercial aircraft fuel tanks, such as the center wing tank or body tanks, can be subject to explosion hazard due to heat balance around the tanks. Various embodiments of the present disclosure reduce the flammability exposure of the fuel tank by drawing cold air from a cold air unit of the aircraft and passing the air to a space proximate the fuel tank, without disrupting the cold air system in flight performance.

Commercial aircraft fuel tanks, such as the center wing tank or body tanks, can be subject to explosion hazard due to heat balance around the tanks. Various embodiments of the present disclosure reduce the flammability exposure of the fuel tank by drawing cold air from a cold air unit of the aircraft and passing the air to a space proximate the fuel tank, without disrupting the cold air system in flight performance.

Aircraft fuel ice capturing filter device housings, aircraft fuel ice capturing filter devices, and methods of use are provided.

Aircraft fuel ice capturing filter device housings, aircraft fuel ice capturing filter devices, and methods of use are provided.

Aircraft fuel ice capturing filter device housings, aircraft fuel ice capturing filter devices, and methods of use are provided.

Aircraft fuel ice capturing filter device housings, aircraft fuel ice capturing filter devices, and methods of use are provided.

A method of fuel desulfurization comprises receiving fuel from a source of fuel in a gaseous phase and condensing the fuel in the gaseous phase in a fuel condenser to convert at least a portion of the fuel into a liquid phase. The method further comprises delivering the fuel in the liquid phase directly to a reformer and returning the uncondensed portion of the fuel in the gaseous phase to the source of fuel to inert the source of fuel.