502results 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 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.

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 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.

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.

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.

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).

A waterborne vessel includes a fuselage, at least one forward wing coupled to the fuselage, at least one rearward wing coupled to the fuselage and aft of the at least one forward wing, a first pontoon positioned and coupled to a port side of the fuselage, a second pontoon positioned and coupled to a starboard side of the fuselage, and a tail assembly coupled to the fuselage and aft of the at least one rearward wing. The tail assembly includes at least one rudder. The vessel further includes at least one propulsive element coupled to the fuselage and configured to generate airflow toward the tail assembly.

Methods, apparatus, systems, and articles of manufacture are disclosed for a hydrogen fuel distribution system (100) with integrated thermal management. An example fuel distribution system (100) with integrated thermal management comprises a hydrogen fuel distributor (402) including a first tank (406) and a second tank (408). The hydrogen fuel distributor (402) circulates hydrogen fuel to a first fuel cell (606) and a second fuel cell (608). A coolant distributor (702) includes a heat exchanger (416). The coolant distributor (702) regulates a temperature of the fuel distribution system (100). A compressed air distributor (706) provides compressed air from a propulsor (730) to the first fuel cell (606) and the second fuel cell (608). An electrical distributor (602) transports electricity from the first fuel cell (606) and the second fuel cell (608) to an electric motor (726). The electric motor (726) drives the propulsor (730).

A fuselage of an aircraft includes a front portion and a rear portion, with at least one opening in the rear portion, with the opening being closeable by a structural panel fully removeable from the opening, wherein a locking structure for the structural panel is in the opening and configured to transfer loads between a primary structure of the fuselage and the structural panel. A method is disclosed for closing an opening of a fuselage, and an aircraft is disclosed having such a fuselage.

A cryogenic liquid storage system comprising an outer tank 22, and an inner tank 24 configured to hold cryogenic liquid, an isolation valve 40, and a collection chamber 26, outside the outer tank, and

A fuel system having a hydrogen fuel tank for fueling a fuel feed and propulsion system. The fuel system having a jet pump within the hydrogen fuel tank, at least one primary pump receiving fuel from the jet pump and pressurizing fuel to an outlet path and a first fuel recirculation path configured to selectively recirculate fuel to the hydrogen fuel tank. The first fuel recirculation path is fluidly connected to the outlet path. The first fuel recirculation path includes a heat exchanger positioned within the hydrogen fuel tank to cool fuel received from at least one of the fuel feed system or a tank pressurization system. The heat exchanger and a Joule-Thomson expansion at the jet pump minimizes recirculated fuel temperature, which in combination with a selective flow recirculation rate improve the life of the primary pump downstream.

A hydrogen fuelled aircraft comprising a fuselage and a wing, and at least one fuel tank. The hydrogen fuel tank is mounted to the wing, wherein the fuel tank is mounted above the wing and spaced from an upper surface of the wing by a tank mounting arrangement which does not interfere with the wing upper surface. [Use Figure 2]

A thermal management system (TMS) 100 for an aircraft comprising an air inlet 310 which receives ambient air from an external environment, an air outlet (120, figure 1) providing fluid communication b

A propulsion system for an aircraft includes a fan section having a fan; a turbomachine including a compressor section, a combustion section, and a turbine section arranged in serial flow order; at least one electric machine; a fuel cell assembly configured to supply power to the electric machine; and a controller including a memory and one or more processors. One or both of the turbomachine and the at least one electric machine are configured to drive rotation of the fan of the fan section. The fuel cell assembly includes at least one fuel cell, a first fluid inlet for receiving a flow of pressurized air, and a second fluid inlet for receiving a flow of fuel.

Hybrid propulsion systems that utilize liquid natural gas solid oxide fuel cells in a manner practical for use in aircraft that avoid the use of heavy batteries, provide transient response times suitable for use in aircraft, and / or simplify reactant pre-conditioning systems using a compressor and turbine pair operatively coupled to the solid oxide fuel cell. Such hybrid propulsion systems for an aircraft may include a liquid natural gas turboshaft engine, a turbo generator operatively coupled to the turboshaft engine, a liquid natural gas solid oxide fuel cell, and an electric fan. The electric fan may be configured to generate thrust for the aircraft and may be powered by the turbo generator and / or the solid oxide fuel cell. Fuel cell reactants may be pre-conditioned using turboshaft bleed air, and the liquid natural gas may be pre-heated by fuel exhaust from the solid oxide fuel cell.

An aircraft propulsion system includes aircraft systems having at least one hydrogen tank and an aircraft-systems heat exchanger and engine systems having at least a main engine core, a high pressure pump, a hydrogen-air heat exchanger, and a turbo expander (800). The main engine core includes a compressor section, a combustor section having a burner, and a turbine section. Hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the aircraft-systems heat exchanger, the high pressure pump, the hydrogen-air heat exchanger, and the turbo expander (800), prior to being injected into the burner for combustion. The turbo expander (800) includes a rotor (804) separated into a first expander portion (812) and a second expander portion (814) arranged about an output shaft (806) and the output shaft (806) is operably connected to a generator configured to generate electrical power.

The invention relates to a fuel system (1) for supplying an aircraft (2) with hydrogen (3). The fuel system (1) comprises a first inner tank (4) and a separate second inner tank (6), each for storing hydrogen (3), and an outer tank (5) which surrounds the inner tanks (4, 6). The first inner tank (4) and the second inner tank (6) are fluidically connected, separately from one another, to at least one first supply device (7) for supplying the aircraft (2) with hydrogen (3). The invention also relates to an aircraft (2) having a fuel system (1), and to a method.

A fuselage structure of an aircraft includes a first fuselage section and a second fuselage section connected to the first fuselage section, the second fuselage section including at least one first fuselage vessel extending the first fuselage section in a longitudinal direction, with the first fuselage section and the first fuselage vessels comprising circumferential flanges arranged at longitudinal ends of the first fuselage section and the first fuselage vessels extending radially in the first fuselage vessels and the first fuselage section wherein fasteners extend through abutting flanges of the first fuselage section and the fuselage vessel to establish a force-fit connection between the first fuselage section and the first fuselage vessels, when assembled, and wherein the first fuselage vessel provides a storage space for at least one tank structure. Also disclosed are a method for assembling the fuselage structure and an aircraft including the fuselage structure.

A heating device comprises a thermally-conductive outer tube, and a combustor arranged to combust air and gaseous hydrogen input to the device and introduce resulting combustion products into a first end of the outer tube. The device includes an igniter arranged to ignite the air and gaseous hydrogen. Combustion products produced by the combustor flow from the combustor to an output of the device along a flow path such that they are in contact with the internal surface of the outer tube over at least a portion of the flow path. Apparatus for heating a flow of hydrogen comprises a conduit for conducting the flow of hydrogen from a principal input port to a principal output port, the apparatus further comprising the heating device located at least partially within the conduit between the principal input port and the principal output port.