995results about "Fuel systems for specific fuels" patented technology

Systems, apparatus, articles of manufacture, and methods for leak detection and mitigation for hydrogen fueled aircraft are disclosed. An example apparatus disclosed herein includes machine readable instructions, and programmable circuitry to at least one of instantiate or execute the machine readable instructions to determine a hydrogen concentration threshold for a location within an undercowl of an engine of an aircraft, based on an engine condition of the aircraft, determine, based on an output of a hydrogen concentration sensor within the undercowl, a hydrogen concentration at the location, compare the hydrogen concentration to the hydrogen concentration threshold, and conduct a mitigation action in the hydrogen fuel distribution system based on the comparison of the hydrogen concentration and the hydrogen concentration threshold.

The present disclosure relates to hydrogen pumping systems for pumping hydrogen from a fuel tank (where the hydrogen is stored as liquid hydrogen LH2) to a power generation device at which the hydrogen is used as fuel. The pumping systems include features providing system redundancy, effective heat exchange for warming the hydrogen, gas turbine air bleed cooling, component cooling and removal of hydrogen gas.

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.

A hydrogen supply assembly for an aircraft propulsion system includes a storage housing, a hydrogen supply component, and a leak detection system. The storage housing surrounds and forms a storage plenum. The hydrogen supply component is disposed within the storage housing coincident with the storage plenum. The leak detection system includes an interior pressure sensor, an exterior pressure sensor, and a controller. The interior pressure sensor is connected in fluid communication with the storage plenum. The exterior pressure sensor is connected in fluid communication with an ambient atmosphere outside the storage housing. The controller is configured to determine a differential pressure between the storage plenum and the ambient atmosphere with the interior pressure sensor and the exterior pressure sensor and identify a presence or an absence of hydrogen leakage from the hydrogen supply component to the storage plenum by comparing the determined differential pressure to a first differential pressure threshold.

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.

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.

System and associated methods relate to detecting and responding to hydrogen leakage in an aircraft. The system includes a hydrogen tank and a fuel pipeline surrounded by an enclosed chamber. The system further includes one or more vacuum pumps fluidly coupled to the enclosed chamber to create the control volume vacuum. The system further includes vacuum sensors mounted within the control volume vacuum, configured to sense a vacuum pressure value. The system further includes hydrogen detectors fluidly connected downstream of the one or more vacuum pumps, configured to sense the hydrogen concentration of the exhaust from the one or more vacuum pumps. The system further includes a controller and an emergency vacuum. The controller is configured to evaluate whether an emergency hydrogen leak condition exists based upon the vacuum pressure value and the hydrogen concentration. The controller can then open a valve to operate emergency vacuum if necessary.

Disclosed is an aircraft 1 which comprises a fuselage 20 and, installed therein, at least one fuel tank 10. The fuel tank 10 has a tank wall comprising a spherical zone or a cylindrical portion 10c, and a first cap portion 10t and a second cap portion 10g enclosing the spherical zone or the cylindrical portion 10c, respectively. The first cap portion 10t of the at least one fuel tank 10 installed in the fuselage 20 faces a roof portion 20r of the fuselage, and its second cap portion 10g faces a bottom portion 20b of the fuselage. In particular, the aircraft 1 thus comprises an upright arrangement of the at least one fuel tank 10. Support elements 41, 42 may serve to support the at least one fuel tank 10 against a shell 22 and / or against at least one frame component 21, 21' of the fuselage 20.

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 and an outer wing section (30A, 30B) for extending the wingspan, in which each outer wing section has a thickness less than a thickness of the corresponding inner wing section, a central region (12) where the first swept wing meets the second swept wing, a first transition region (23A) where the first inner wing meets the first outer wing section, a second transition region (23B) where the second inner wing meets the second outer wing section, in which at least one extension (44) having an internal volume is provided behind the trailing edge of the wings, the at least one extension being disposed in the central region.

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

The present disclosure provides systems and methods for storing, transporting, and using hydrogen. In some embodiments, the method may comprise (a) storing hydrogen fuel in one or more fuel storage modules; (b) transporting the one or more fuel storage modules to a vehicle fueling site, wherein one or more hydrogen fuel compatible vehicles are located at or near the vehicle fueling site; (c) loading the one or more fuel storage modules into the one or more hydrogen fuel compatible vehicles, wherein the one or more fuel storage modules are configured to be releasably coupled to the one or more hydrogen fuel compatible vehicles; and (d) decoupling the one or more fuel storage modules from the one or more hydrogen fuel compatible vehicles after the one or more fuel storage modules are depleted or partially depleted.

An aircraft propulsion module comprises a hydrogen storage system, an electrochemical converter (7) connected to the hydrogen storage system, wherein the at least one electrochemical converter is adapted to convert hydrogen supplied from the hydrogen storage system (12) into electric energy, and an electric motor (5) electrically connected to the electrochemical converter, wherein the electric motor is adapted to generate thrust; wherein the propulsion module comprises at least one separation means (9) adapted to separate at least one component of the propulsion module from the propulsion module. An aircraft comprises at least one such aircraft propulsion module. A method for operating a propulsion module comprises that: during operation of the propulsion module, at least one separation means is actuated, by which actuation at least one component of the propulsion module is separated from the remaining propulsion module and then falls from the remaining propulsion module.

A system is provided for an aircraft. This aircraft system includes an engine, a fuel system and an air system. The fuel system includes a fuel circuit, a fuel source, a heat exchanger and a turboexpander. The fuel circuit is configured to direct fuel from the fuel source, through the heat exchanger and the turboexpander, to the engine for combustion. The heat exchanger is configured to transfer heat energy from combustion products generated by the combustion of the fuel in the engine into the fuel in the fuel circuit. The air system is discrete from the engine. The air system includes an air compressor and the turboexpander. The air system is configured to expand the fuel directed across the turboexpander by the fuel circuit to power operation of the air compressor.

The present invention relates to a propulsion system for an aircraft, the system comprising: a first cryogenic fuel propulsion system; and, a second cryogenic fuel propulsion system; the first cryogenic fuel propulsion system comprising: a first cryogenic fuel source; a first propulsion source arranged to generate propulsion from a cryogenic fuel; a first flow path for transporting cryogen from the first cryogenic fuel source to the first propulsion source; the second cryogenic fuel propulsion system comprising: a second cryogenic fuel source; a second propulsion source arranged to generate propulsion from a cryogenic fuel; a second flow path for transporting cryogen from the second cryogenic fuel source to the second propulsion source; the system further comprising: a first conduit, arranged to transport fluid cryogen from the first cryogenic fuel propulsion system to the second cryogenic fuel propulsion system, a second conduit, arranged to transport fluid cryogen from the second cryogenic fuel propulsion system to the first cryogenic fuel propulsion system.

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.

The invention discloses a low-temperature-resistant hydrogen energy unmanned aerial vehicle system capable of adapting to high-altitude flight. The low-temperature-resistant hydrogen energy unmanned aerial vehicle system comprises an unmanned aerial vehicle body, a hydrogen energy fuel cell module, a driving module and a control module, the hydrogen energy fuel cell module generates electric energy through hydrogen and oxygen and provides the electric energy to the driving module, and the driving module drives the unmanned aerial vehicle body to fly; and the control module controls the hydrogen energy fuel cell module according to the flight height and the flight environment temperature of the unmanned aerial vehicle body and the residual hydrogen content in the hydrogen storage bottle, so that the hydrogen energy fuel cell module works in one of the following modes: an intelligent high-altitude oxygen supply mode, a weight-reduction endurance mode and a low-temperature-resistant mode. According to the invention, the problems of low temperature and low oxygen in high-altitude flight can be well solved, and the application prospect is wide; the control module can autonomously select an intelligent high-altitude oxygen supply mode, a weight-reduction endurance mode or a low-temperature-resistant mode to work according to the flight environment and the state of the unmanned aerial vehicle.

A dual fuel propulsion system is disclosed. The aircraft is capable of performing a flight mission during which the first or the second selectively useable. The aircraft comprises: at least one internal combustion engine capable of generating propulsive thrust using selectively a first kerosene based jet fuel and a second liquid hydrogen fuel, and two independent sets of fuel systems, including a first fuel system feeding the first fuel from a first set of fuel storage tanks to the internal combustion engine and a second fuel system feeding the second fuel from a second set of fuel storage tanks to the internal combustion engine. Both sets of fuel storage tanks host the required fuel for the flight mission plus reserve fuel.

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.

The present invention discloses a large-load, long-endurance hydrogen fuel cell drone; the present invention relates to the field of hydrogen energy technology; a large-load, long-endurance hydrogen fuel cell drone, mainly composed of a drone body UAV1, a cargo hold 2, a hydrogen fuel cell group 3, an unlocking component 4, and a traction air supply pipe 8. The drone body UAV1 is designed with a special installation space to accommodate the hydrogen fuel cell group 3, which converts hydrogen into electrical energy through an electrochemical reaction to provide power for the drone. One end of the traction air supply pipe 8 is connected to a ground pump station, and the other end is connected to the hydrogen fuel cell group 3 through a special interface; by introducing a self-locking air supply pump and a flexible unlocking component, the technology of the present invention enables the drone to quickly and safely disconnect from the traction air supply pipe when needed, thereby getting rid of the limitations of the ground air supply system. It enables the drone to fly for a longer time and a longer distance, greatly expanding its scope of application.

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 fuel conditioning system for an aerobic hydrogen engine, including: at least one hydrogen pump configured to increase the pressure of the liquid hydrogen delivered at the outlet of a tank, one or several heat exchangers configured to increase the temperature of the pressurized hydrogen, an air supply circuit, at least one combustion device configured to ensure a partial combustion of the hydrogen with air coming from the air supply circuit in order to produce a fuel including a gas mixture including gaseous hydrogen and devoid of oxygen.

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).

An aircraft comprising a structure, a tank housed in the fuselage, and fastening means which comprise a front fastening system, a rear fastening system and a lateral fastening system. The front system comprises a front plate, two lateral connecting rods and a central connecting rod that are fastened between the front plate and the tank. The rear system comprises a rear plate and a rear connecting rod fastened between the rear plate and the tank. The lateral system comprises a lateral connecting rod fastened between the structure and the tank, wherein one of the connection points is behind the other connection point.

The present invention relates to a crash-load absorbing attachment fitting (1; 101; 201; 301; 401), comprising a first and second part (3, 6; 103, 106; 203, 206; 303, 306; 403, 406) that are joined to each other at a joint (10; 110; 210; 310; 410), the first and second parts being load-bearing parts. The joint is configured such that the joint is capable of transferring, during normal use of the crash-load absorbing attachment fitting, a load (F) which is below a pre-determined load-absorption activation threshold value between the first and second parts, and such that the joint breaks when the load reaches or exceeds the pre-determined load-absorption activation threshold value. The crash-load absorbing attachment fitting further comprises a destroyer device (15; 115; 215; 315; 415), wherein the destroyer device is rigidly connected to and / or rigidly supported by one of the first and second parts and wherein the destroyer device is arranged so as to be capable of destructively acting on the other one of the first and second parts after breaking of the joint. Moreover, the invention proposes an aircraft or spacecraft (91) comprising a tank for storing hydrogen, in particular liquefied hydrogen, and at least one such crash-load absorbing attachment fitting (1; 101; 201; 301; 401), the tank being attached to a structural member (78) of the aircraft or spacecraft using the crash-load absorbing attachment fitting.

System and associated methods relate to detecting and responding to hydrogen leakage in an aircraft. The system includes a hydrogen tank and a fuel pipeline surrounded by an enclosed chamber. The system further includes one or more vacuum pumps fluidly coupled to the enclosed chamber to create the control volume vacuum. The system further includes vacuum sensors mounted within the control volume vacuum, configured to sense a vacuum pressure value. The system further includes hydrogen detectors fluidly connected downstream of the one or more vacuum pumps, configured to sense the hydrogen concentration of the exhaust from the one or more vacuum pumps. The system further includes a controller and an emergency vacuum. The controller is configured to evaluate whether an emergency hydrogen leak condition exists based upon the vacuum pressure value and the hydrogen concentration. The controller can then open a valve to operate emergency vacuum if necessary.