A fuel oxygen conversion unit for a vehicle or an engine of the vehicle includes a contactor; a mechanically-driven, first fuel gas separator defining a liquid fuel outlet and a stripping gas outlet, the fuel oxygen conversion unit defining a liquid fuel outlet path in fluid communication with the liquid fuel outlet of the first fuel gas separator; and a second fuel gas separator positioned in fluid communication with the liquid fuel outlet path at a location downstream of the first fuel gas separator.

A fuel oxygen conversion unit for a vehicle or an engine of the vehicle includes a contactor; a mechanically-driven, first fuel gas separator defining a liquid fuel outlet and a stripping gas outlet, the fuel oxygen conversion unit defining a liquid fuel outlet path in fluid communication with the liquid fuel outlet of the first fuel gas separator; and a second fuel gas separator positioned in fluid communication with the liquid fuel outlet path at a location downstream of the first fuel gas separator.

A heat exchanger including a sealed housing and a body positioned inside the housing, the body including a stack of least one first assembly of first and second plates pressed against each other, between which flows a first fluid, and at least one second assembly of third and fourth plates pressed against each other, between which flows a second fluid, the first and second assemblies being arranged so that they transfer heat between the first and second fluids. This configuration limits the risk of leaks and mixing of the two fluids.

An aircraft including a fuselage, a wing structure, at least one turbomachine running on hydrogen and generating thrust at a propulsion unit distant from the fuselage, at least one fuel tank positioned in the fuselage and configured to store hydrogen in the cryogenic state, at least one hydrogen supply device connecting the fuel tank and the turbomachine and including at least one pump positioned in the fuselage in the vicinity of the fuel tank, at least one hydrogen heating system positioned in the fuselage in the vicinity of the pump. This solution makes it possible to reduce a length of the complex double-walled pipes configured for carrying the hydrogen in the cryogenic state between the fuel tank and the hydrogen heating system.

An aircraft including at least one hydrogen engine, at least one hydrogen supply device including at least one hydrogen tank and at least one item of equipment through which the hydrogen flows and which is positioned between the hydrogen tank and the hydrogen engine. The aircraft includes at least one sealed container sealed from the outside air, in which sealed container the equipment of the hydrogen supply device is positioned. This solution allows a safe hydrogen installation to be obtained using existing equipment.

A thermal energy system for use with an aircraft includes a cooling loop and a cooler. The cooling loop includes a fluid conduit and a pump configured to move fluid through the fluid conduit to transfer heat from a heat source to the fluid in the fluid conduit to cool the heat source. The cooler includes an air-stream heat exchanger located in a duct and is in thermal communication with the fluid conduit to transfer heat between the fluid in the cooling loop and the air passing through the duct.

A thermal energy system for use with an aircraft includes a cooling loop and a cooler. The cooling loop includes a fluid conduit and a pump configured to move fluid through the fluid conduit to transfer heat from a heat source to the fluid in the fluid conduit to cool the heat source. The cooler includes an air-stream heat exchanger located in a duct and is in thermal communication with the fluid conduit to transfer heat between the fluid in the cooling loop and the air passing through the duct.

A gas turbine engine includes a primary gas path having, in fluid series communication: a primary air inlet, a compressor fluidly connected to the primary air inlet, a combustor fluidly connected to an outlet of the compressor, and a turbine fluidly connected to an outlet of the combustor. The turbine is operatively connected to the compressor to drive the compressor. A turbine cooling air conduit extends from an air inlet of the turbine cooling air conduit to an air outlet of the turbine cooling air conduit.

An access panel to be received in an access aperture in a lower skin of a wing on an aircraft incorporates a body surrounded by a sealing flange. The body is configured to be received in the access aperture and the sealing flange is configured to be received on a sealing land surrounding the access aperture. An integral heat exchanger extends from a top surface of the body into a fuel tank in the wing to conduct heat from the fuel to an external surface of the access panel.

An access panel to be received in an access aperture in a lower skin of a wing on an aircraft incorporates a body surrounded by a sealing flange. The body is configured to be received in the access aperture and the sealing flange is configured to be received on a sealing land surrounding the access aperture. An integral heat exchanger extends from a top surface of the body into a fuel tank in the wing to conduct heat from the fuel to an external surface of the access panel.