735results about "Fuel systems for specific fuels" patented technology

Heat exchangers for cryogenic fuel distribution systems and related methods are disclosed herein. An example aircraft disclosed herein includes a cryogenic fuel system including a cryogenic fuel, a hydraulic system including a hydraulic fluid, a gas turbine engine fluidly coupled to the cryogenic fuel system, and a heat exchanger fluidly coupled to the cryogenic fuel system, the heat exchanger is used to exchange heat between the cryogenic fuel and at least one of (1) hydraulic fluid or (2) working fluid thermally coupled to the hydraulic system.

The invention relates to the technical field of hydrogen energy aviation, and discloses a hydrogen energy aviation fuel storage-supply system and method based on solid hydrogen storage, and the hydrogen energy aviation fuel storage-supply system and method based on solid hydrogen storage are characterized in that the hydrogen release amount adjusting range of a hydrogen storage material is matched with the hydrogen fuel demand adjusting range of a power device by adjusting the hydrogen release catalytic reaction environment temperature of the solid hydrogen storage material; by adopting the pressure stabilizing device, the problem of flow and pressure fluctuation caused by hysteresis of hydrogen release adjustment is solved, and hydrogen release flow adjustment and engine throttling control can be carried out through the thrust rod.

A hydrogen aircraft includes: an airframe including a fuselage and a wing; at least one propulsion system fixed to the airframe; a pressurized chamber disposed inside the fuselage; a pressure bulkhead that is disposed at a rear part of the pressurized chamber and has strength to withstand pressurization of the pressurized chamber; a hydrogen tank that is disposed in an accommodation section and stores liquid hydrogen, the accommodation section being installed behind the pressure bulkhead, outside the pressurized chamber, and inside the fuselage; and a supply line that supplies the liquid hydrogen stored in the hydrogen tank to the propulsion system.

An aircraft pipework assembly is disclosed including an aircraft structure; pipework; a fixture arrangement between the pipework and the aircraft structure; a tie rod connecting the pipework to the aircraft structure; a first tie rod bearing which connects the tie rod to the pipework; and a second tie rod bearing which connects the tie rod to the aircraft structure. The fixture arrangement includes a spherical bearing, the spherical bearing comprising a ball mounted to the pipework, and a housing coupled to the aircraft structure. The ball includes a convex spherical bearing surface; and the housing comprises a concave spherical bearing surface which mates with the convex spherical bearing surface of the ball. The fixture arrangement is configured to enable the pipework to translate relative to the ball in an axial direction aligned with a longitudinal axis of the pipework.

An aircraft 10 comprising a first swept wing 14A and a second swept wing 14B, each swept wing having an inner wing section 26A, 26B comprising an integrated payload fuselage 20 and an outer wing secti

A fuel system for a hydrogen fueled aircraft propulsion system comprises first and second hydrogen fuel tanks configured to store liquid hydrogen, first fuel line and second fuel lines configured to supply hydrogen from the first hydrogen fuel tank to a combustor of a first gas turbine engine and from the second hydrogen fuel tank to a combustor of a second gas turbine engine respectively. First and second fuel pumps are provided, each being configured to pump fuel in a respective first and second fuel line. First and second fuel heaters are provided, each being configured to heat fuel in a respective first and second fuel line. A fuel cross-feed fuel line is provided, which is configured to transfer fuel between the first and second fuel lines. The fuel cross-feed line is provided downstream in fuel flow of the first and second fuel heaters.

An aircraft comprises a fuselage; wings; engines connected to the wings; a set of liquid hydrogen tanks; a vent located on the tail on the fuselage; a conduit system connecting the liquid hydrogen tanks to the vent; and a controller. The controller is configured to control the conduit system to remove gaseous hydrogen in the set of liquid hydrogen tanks to travel through the conduit system and exit at the vent in response to pressure in the set of liquid hydrogen tanks being greater than a specified tolerance.

A fuel system for a hydrogen fuelled aircraft propulsion system comprises a fuel tank configured to store hydrogen fuel, a main fuel conduit configured to provide fuel to a combustor of a gas turbine engine, a fuel heater comprising a catalytic combustor configured to catalytically combust a portion of the hydrogen fuel prior to delivery to the combustor and a heat exchanger configured to exchange heat between exhaust gases from the fuel heater and hydrogen fuel in the fuel conduit.

A pressure regulating device includes an on-board storage tank, a mixing chamber, first and second lines, a recirculation line, a pressure sensor and a controller. The storage tank stores and supplies cryogenic fuel to a combustion chamber and includes a booster pump. The first line supplies cryogenic fuel in the liquid state and includes a pressurizing pump and a first regulation valve. The second line supplies cryogenic fuel in the gaseous state and includes a compressor and a first control valve. The recirculation line includes a second regulation valve and with a first heat exchanger. The pressure sensor detects the pressure inside the storage tank. The controller receives the pressure and controls the first and second regulation valves, the first control valve, the pressurizing pump, the booster pump and the compressor, as a function of a value of a setpoint pressure inside the storage tank.

A system for a blended wing body aircraft with a combustion engine is illustrated. The aircraft comprises a blended wing body, at least a fuel store located within the blended wing body and configured to store a fuel, wherein the fuel includes liquid hydrogen, and at least a propulsor 5 configured to propel the blended wing body aircraft. The at least a propulsor comprises a combustion engine configured to burn the fuel from the fuel store and produce mechanical work to power the at least a propulsor.

A pipe support assembly (114), suitable for supporting pipework handling cryogenic fluids, where the pipework passes through a fuel tank support. The pipe support assembly includes first and second pipe supports (116) each having male (119) and female (152) portions that interlock with male (119) and female (152) portions of the other pipe support (116). The pipe supports (116) have an internal surface (121) that contacts a section of the pipe outer surface (112). Each pipe support (116) has a split (140) which allows for a change in dimension of the internal surface (121) of the pipe support (116) contacting the pipe (110). This allows the pipe support assembly (114) to provide a consistent clamping force to the pipe (110) during thermal contraction or expansion. Longitudinal movement of the pipe (110) is permitted if the pipe (110) overcomes the frictional force between itself and the pipe support assembly (114).

A fuel system for a hydrogen fuelled gas turbine engine comprises a tank configured to store hydrogen, a pump configured to provide pressurised hydrogen at an outlet thereof, and a pre-heater configured to heat at least a portion of pressurised hydrogen fuel downstream of the pump. A preheater return offtake is configured to return at least a portion of hydrogen fuel heated by the preheater to the tank.

An aircraft with a multi-walled fuel tank and method of manufacturing is presented. The aircraft includes a blended wing body and a fuel tank attached to the blended wing body configured to store liquified gas fuel. The fuel tank includes an inner wall, outer wall, and interstitial volume in between that is filled with insulation. The interstitial volume includes a reflective film layer and a structural insulation layer.

An aircraft power plant, has: an air mover for propelling an aircraft; an electric motor drivingly engaged with the air mover; a gas turbine engine having a compressor for pressurizing air, a combustor in which the pressurised air is mixed with fuel and ignited for generating combustion gases, and a turbine for extracting energy from the combustion gases; and a hydrogen fuel cell operatively connected to the electric motor for powering the electric motor with electricity generated by the hydrogen fuel cell, the hydrogen fuel cell operable to generate electricity using the air from the compressor and hydrogen from a source of hydrogen.

A fuel system (205) for an aircraft propulsion system (103) comprising a gas turbine engine. The fuel system includes a fuel tank (104) configured to store compressed gaseous hydrogen pressures greater than 100 Bar at a temperature below 200 Kelvin and a tank heating system (224, 232, 234, 242, 302, 406) configured to raise the temperature of hydrogen fuel within the hydrogen tank (104). The tank heating system includes a primary tank heater comprising an oil to fuel heat exchanger (242) and an auxiliary tank heater comprising one or more of a recuperator (224), an electric heater (232), a gas turbine engine core compressor bleed-air powered heater (302, 402), and an auxiliary combustor (306).

A sub-cooler for a sub-cooling cryogenic refueling system is disclosed herein. The sub-cooler includes a first valve to separate flowing cryogenic fuel into a primary flowline and an auxiliary flowline, a second valve to reduce the saturated pressure and temperature of the cryogenic fuel in the auxiliary flowline, a cryogenic heat exchanger to transfer heat from the primary flowline to the auxiliary flowline, a temperature sensor to measure the temperature of the sub-cooled cryogenic fuel in the primary flowline, and a sub-cooler controller to control the effective areas of the primary flowline inlet and the auxiliary flowline inlet at the first valve.

A hydrogen fuel system including a fuel delivery assembly, a purge gas source, and a vent. The fuel delivery assembly is configured to receive hydrogen fuel from a hydrogen fuel source and to provide the hydrogen fuel from the hydrogen fuel source to a power generator. The purge gas source is fluidly coupled to the fuel delivery assembly and configured to provide a purge gas to the fuel delivery assembly. The vent is fluidly coupled to the fuel delivery assembly and configured to vent hydrogen fuel from the fuel delivery assembly when the purge gas is provided to the fuel delivery assembly.

Multi-phase fluid fuel systems and related methods are disclosed. An example fuel system includes: a liquid hydrogen storage tank including a hydrogen fuel in a liquid phase; and at least one of a gaseous or liquid hydrogen storage tank, the at least one of the gaseous or liquid hydrogen storage tank comprising at least one of a gaseous or liquid hydrogen fuel, a first portion of the at least one of the gaseous or liquid hydrogen fuel exiting the at least one of the gaseous or liquid hydrogen storage tank and flowing to a combustor of the engine, a second portion of the at least one of the gas phase or liquid phase hydrogen fuel exits at least one of the gaseous or liquid hydrogen storage tanks and flows to the liquid hydrogen storage tank.

An aircraft fuselage for releasing a fuel tank from inside the aircraft fuselage in case of emergency includes an outer structure, a mounting device to releasably secure a sled device for carrying a fuel tank in an inside of the outer structure, and a first openable release door separating the inside from an outside of the outer structure, wherein the first release door is positioned in relation to the mounting device such that the fuel tank is released through the first release door when the mounting device releases the sled device. A method is disclosed for releasing a fuel tank from inside the aircraft fuselage in case of emergency as well as an aircraft including such an aircraft fuselage.

The invention relates to an injector arrangement (1) for an engine, in particular of an aircraft, for introducing a gaseous fuel and a liquid fuel as well as air into a combustion chamber (CC), comprising an injector shaft (2) and an injector main body (3) aligned along an injector longitudinal axis (L), wherein the injector main body (3) comprises: - a central air channel (14) arranged on the injector longitudinal axis (L) with an outlet opening (16) for directing a central airflow, - an outer air channel (36) arranged radially around the central air channel (14) with an outlet opening (40) for directing an outer airflow, - a liquid fuel supply (20) arranged radially between the central air channel (14) and the outer air channel (36) with at least one liquid fuel channel (22) and an outlet opening (24) for introducing the liquid fuel,and - a gas fuel supply (30) arranged radially between the liquid fuel supply (20) and the outer air duct (36), with at least one gas fuel channel (31) and an outlet opening (34) for introducing the gaseous fuel. An emission-optimized flow pattern is achieved by the outer air duct (36) having a radially outwardly oriented end section (37) at its downstream end for directing the external airflow entering the combustion chamber (CC) radially outwards.

The invention relates to the technical field of hydrogen-powered aircrafts, and particularly provides a hydrogen-powered aircraft and a composite solid hydrogen storage system, the hydrogen-powered aircraft comprises an aircraft body, a hydrolysis hydrogen production unit, a solid hydrogen storage and supply unit, a heat exchange system and a hydrogen engine; the hydrolysis hydrogen production unit and the solid hydrogen storage and supply unit are arranged in the machine body; the hydrolysis hydrogen production unit is used for reacting with water to generate hydrogen and storing the hydrogen into the solid hydrogen storage and supply unit; the solid hydrogen storage and supply unit is used for storing the hydrogen generated by the hydrolysis hydrogen production unit and outputting the hydrogen to a hydrogen engine in a controllable manner; the heat exchange system is arranged in the machine body, wraps the solid hydrogen storage and supply unit and is used for heating the solid hydrogen storage and supply unit after gas exhausted by the hydrogen engine is mixed with air so as to control the solid hydrogen storage and supply unit to release hydrogen; and the generated condensed water is supplied to the hydrolysis hydrogen production unit. According to the invention, reactants and energy can be provided for the hydrolysis hydrogen production unit and the solid hydrogen storage and supply unit, so that the hydrogen storage mass density is improved.

Example systems and methods for using multi-directional baffles in cryogenic fuel tanks are provided. An example cryogenic fuel tank comprises an inner surface defining an interior of the cryogenic fuel tank to hold a fuel and a plurality of baffles including a first baffle, the first baffle including a first member extending along a first plane and a second member extending along a second plane, the first plane different from the second plane, the second member connected to the first member, the plurality of baffles connected to the inner surface.

A propulsion system comprises a propulsive hydrogen-burning gas turbine engine, a first tank storing liquid hydrogen with an ullage and a first fuel line including a fuel pump and a vaporiser, the first fuel line providing gaseous hydrogen to the engine during operation of the system. A second tank storing gaseous hydrogen is coupled by a second fuel line to the first fuel line at a position thereon between the vaporiser and the engine, providing for engine start-up (when the vaporiser is inoperative) and power-boosting during operation of the system. A duct connects gaseous hydrogen within the second tank to the ullage in the first tank in order maintain pressure in the first tank as liquid hydrogen within it is depleted, preventing cavitation of liquid hydrogen within the fuel pump.

An aircraft assembly is disclosed including a wing structure, and a pipe assembly rotatably coupled to the wing structure by a fixture arrangement. The pipe assembly extends along a longitudinal direction, the fixture arrangement configured to restrict movement of at least a portion of the pipe assembly in the longitudinal direction relative to the wing structure and allow rotation of the pipe assembly relative to the wing structure.

Disclosed is an aircraft structure comprising at least one aircraft structural element defining a volume; a fuel-handling component arranged within the volume and configured to handle a fuel; a purging system comprising an inlet and an outlet, the purging system configured to provide a flow of purge gas from the inlet, through the volume, to the outlet, to thereby purge leaked fuel from the volume; and a flow guide member formed of a reticulated foam, arranged within the volume and externally to the fuel-handling component, and configured to guide the flow of purge gas within the volume. An aircraft comprising the aircraft structure is also disclosed.

A fuel system for a hydrogen-fueled gas turbine engine includes a main fuel conduit configured to conduct hydrogen fuel from a hydrogen storage unit to a core combustor of the gas turbine engine, a pre-heater including an auxiliary combustor configured to combust hydrogen fuel diverted from the main fuel conduit to heat hydrogen fuel in the main fuel conduit. A first exhaust passage is configured to conduct combustion products from the auxiliary combustor to the core combustor of the gas turbine engine.

A hydrogen distribution system for supplying hydrogen to a hydrogen consumer comprising: a tank storing a liquid hydrogen fuel; a conditioning system configured to provide a gaseous hydrogen stream downstream from the tank towards the hydrogen consumer; a compressor downstream of the conditioning system and configured to receive the gaseous hydrogen stream and provide a high-pressure gaseous hydrogen stream; a heater downstream of the compressor and configured to receive the high-pressure gaseous hydrogen stream and provide a high-temperature, high-pressure gaseous hydrogen stream; and, a valve downstream of the heater and configured to adjust a flow of the high-temperature, high-pressure gaseous hydrogen stream; wherein the hydrogen consumer is downstream of the valve and configured to receive the high-temperature, high-pressure gaseous hydrogen stream and provide energy by consuming hydrogen from the high-temperature, high-pressure gaseous hydrogen stream. Also, an aircraft with such a system.

The invention relates to a method for installing a tank in a nacelle for a hydrogen-powered aircraft and an intermediate structure for the installation method. The invention relates to a method for mounting a compartment (2) containing at least a part of the equipment required to deliver dihydros to the engine of an aircraft, referred to as a hydrogen compartment, comprising the step of positioning the hydrogen compartment (2) in the cabin by means of a chassis (4) fixed to the cabin (1) and / or at least one track of the hydrogen compartment (2).