303results about "Conditioning fuel arrangements" patented technology

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.

The invention belongs to the field of target drone fuel oil systems, and particularly relates to a self-adaptive supersonic speed target drone fuel oil system and a control method thereof. The system comprises a machine body oil tank, a first electromagnetic valve, an overflow valve, a pressurization oil tank, a fuel pump, an engine pump, a monitoring module and a control module. The body fuel tank comprises a main fuel tank and an auxiliary fuel tank which are arranged in a fuel tank in the middle of the target drone body and located in front of and behind the theoretical mass center of the target drone respectively. The pressurization oil tank is additionally arranged in the fuel oil cabin, fuel oil in the engine body oil tank enters the pressurization oil tank for pressure maintaining after being pressurized by the fuel oil pump, and then oil is supplied to the engine from the pressurization oil tank, so that stable oil supply to the engine is achieved by establishing a local pressure environment instead of a large pressure environment of the whole fuel oil cabin, and therefore when a fuel oil system works, the fuel oil can be stably supplied to the engine. The oil supply flow and pressure are controlled in a closed-loop mode in real time through the control system according to the engine state.

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 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.

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 turbine engine for an aircraft includes a fuel delivery assembly for a hydrocarbon fuel to flow therethrough, a combustor combusting the fuel to generate combustion gases, and a core air exhaust nozzle exhausting the combustion gases from the turbine engine. The turbine engine also includes a contrail mitigation system having a heater and a fuel precipitate separator. The heater is selectively operable to heat the hydrocarbon fuel and to generate fuel precipitates in the hydrocarbon fuel, and the fuel precipitate separator separates the fuel precipitates generated by the heater from the fuel. A controller is coupled to the heater to operate the heater to heat the hydrocarbon fuel and to generate fuel precipitates in the hydrocarbon fuel in response to a contrail mitigation input.

A fuel system for a gas turbine engine including a compressor section, a combustion section, and a turbine section includes a fuel tank for storing a fuel, a plurality of heat exchangers downstream of the fuel tank, and a valve downstream of the plurality of heat exchangers. The valve includes a fuel inlet in fluid communication with the plurality of heat exchangers, a first fuel outlet in fluid communication with a first fluid pathway, and a second fuel outlet in fluid communication with a second fluid pathway. The fuel system includes a fuel cell including an anode inlet and an anode outlet. The anode inlet is in fluid communication with the first fluid pathway. The fuel system also includes a combustion chamber of the combustion section in fluid communication with the second fluid pathway and the anode outlet of the fuel cell and a controller communicatively coupled to the valve.

A propulsion assembly comprising a propulsion system including at least one exhaust duct, from which an exhaust gas stream is discharged, and also a debris ejection zone, a supply device, configured to supply the propulsion system with gaseous fuel, including at least one conditioning system for the gaseous fuel, at least one enclosure in which the conditioning system is positioned, the enclosure being located in the propulsion assembly behind the debris ejection zone. Also an aircraft including at least one such propulsion 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).

The invention discloses an aircraft green inerting system with a water removal function. The aircraft green inerting system comprises an oil tank, a catalytic reactor, a water removal device and a control system. The system extracts oxygen and fuel oil steam in an oil tank through a first fan, the oxygen and the fuel oil steam are mixed with ram air, then the mixture is heated through an electric heater and burnt in a catalytic reactor to generate high-temperature inert gas, then the high-temperature inert gas is subjected to water removal through a first water separator, cooling through a heat exchanger, pressurization through a compressor and secondary water removal through a second water separator in sequence, and pressure reduction and temperature reduction are conducted through a cooling turbine; finally, low-temperature dry inert gas is formed and is reinjected into an oil tank through a fuel oil ejector, and the dual functions of inerting and water removal are achieved. The system monitors in real time through an oxygen concentration sensor, a temperature sensor and a flow sensor, dynamically adjusts the electric heating power and the rotating speed of a valve and a fan, and ensures safe and efficient operation. Catalytic combustion and high-pressure water removal technologies are combined, the oxygen concentration of the fuel tank and the water content of fuel are effectively reduced, and the device is energy-saving, environment-friendly, efficient in inerting and suitable for safety protection of various aircraft fuel systems.

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.

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.

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.

A hybrid drive having a load shaft, a motor / generator coupled to the load shaft, an internal combustion engine, an electromagnetic clutch disposed between the motor / generator and the internal combustion engine configured to releasably couple the internal combustion engine to the load shaft, and an electrical power supply coupled to the motor / generator and the electromagnetic clutch. In one embodiment, the hybrid drive is configured such that the internal combustion engine both drives the load shaft and causes the motor / generator to charge the electrical power supply.

An aircraft fuel system includes a first integrated boost stage having a boost pump configured to receive a fuel flow from a fuel tank via a boost supply line, at least one generator collocated with and operatively connected to the boost pump for driving the boost pump, and a tap fluidly connecting the boost pump and the at least one generator for selectively delivering an amount of the fuel flow to the at least one generator. The fuel system further includes a gearbox operatively connected to the at least one generator, and a main stage downstream of the boost stage and operatively connected to the gearbox. The main stage includes a main pump configured to receive the fuel flow from the boost pump along a main supply line, and a filter disposed along the main supply line upstream of the main pump for filtering the fuel flow.

A method (11000) of operating a gas turbine engine (10) is disclosed, the gas turbine engine (10) comprising an engine core (11) comprising a combustor (16) arranged to burn a fuel; a turbine (19), th

Systems and methods of operating a system are provided. For example, a system includes a fuel cooling loop including a cold fuel flow path having fuel flowing therethrough, a fuel cooler heat exchanger for cooling the fuel in fluid communication with the cold fuel flow path, and a cold fuel tank disposed along the cold fuel flow path for accumulating at least a portion of the cooled fuel. The system further includes a fuel heating loop including a hot fuel flow path for flow of the fuel, a fuel heater heat exchanger for heating the fuel in fluid communication with the hot fuel flow path, and a hot fuel tank disposed along the hot fuel flow path for accumulating at least a portion of the heated fuel. The fuel cooling loop is coupled to the fuel heating loop such that the fuel circulates through both the fuel cooling loop and the fuel heating loop.

Hydrogen supply device comprising at least two tanks configured to store hydrogen in liquid and supercritical states, respectively. The invention relates to a hydrogen supply device (18) comprising: at least one first tank (20) configured to store hydrogen in a liquid state at a pressure below 13 bar; at least one second tank (22) configured to store hydrogen in a supercritical state at a pressure greater than or equal to 13 bar; at least one upstream portion (26) comprising at least one first hydrogen flow control system (32, 32', 32'') configured to regulate the amount of hydrogen flowing from the first tank (20) to the second tank (22); at least one downstream portion (28) connecting the second tank (22) and a hydrogen-powered system (16). The invention also relates to an aircraft comprising at least one such supply device. Figure 2

A fuel conditioning system (SC) configured to supply an aircraft turbine engine with fuel (Q) from a cryogenic tank (RC), the conditioning system (SC) comprising at least one pumping turbine engine (1), a first heat exchanger (31), configured to heat the fuel (Q) in the fuel circuit (CQ) by circulating an air flow (A), and at least one heating turbine engine (2) configured to supply the first heat exchanger (31) with an air flow (A), the heating turbine engine (2) comprising an air intake compressor (21), a combustion chamber (24) and an air exhaust turbine (22) configured to drive the air intake compressor (21), the combustion chamber (24) being supplied with air taken from the air flow (A) and with fuel (Q) from the fuel circuit (CQ). Abstract Figure: Figure 4

The invention relates to an environmentally friendly aircraft. The aircraft stores cryogenic fuel in one or more suitably sized fuel tanks located within the fuselage of the aircraft or at other suitable locations on the aircraft, and stores non-cryogenic fuel in a plurality of standard jet fuel tanks (e.g., within the wings of the aircraft). The tank is resized using an automated aircraft resizing computing tool based on the defined mission range requirements, tank resizing logic, top aircraft requirements, and aircraft geometry and engine thrust levels to iteratively develop at least cryogenic fuel tank dimensions for a particular aircraft. A controller controls selective routing of non-cryogenic fuel or cryogenic (e.g., hydrogen) fuel to the dual fuel engine. In one mode of operation, dual fuel engines typically use cryogenic hydrogen fuel as the primary fuel and reserve non-cryogenic fuel for use only in exceptional cases for dual fuel engines to provide cleaner and more environmentally friendly operation.

An aircraft having at least one dihydrogen transport pipe, an embedding channel with a lower gutter, an aeration aperture with an air inlet collecting external air and at least one supply pipe opening at the air inlet, a control unit, and, for one or more lower gutters, a bypass box having, for each lower gutter, an inlet connected to the supply pipe and an outlet connected to the lower gutter, between each associated inlet and outlet, a door able to move alternately between an open position and a closed position, and, for each door, a maneuvering system controlled by the control unit and moving the door.

The invention relates to a fuel tank inerting system, a fuel tank inerting method and an aircraft. On one hand, the low-temperature rare gas generated by gasification of the liquid rare gas is directly used for replacing oxygen and fuel steam in the fuel tank and reducing the temperature in the fuel tank, and on the other hand, the low-temperature rare gas is used for cooling the fuel steam discharged out of the fuel tank; and then the cooled fuel steam or the fuel liquid drops formed by condensation are returned to the fuel tank to further reduce the temperature in the fuel tank and the concentration of the fuel steam, so that double inerting of the fuel tank is realized. The fuel tank inerting system and method according to the present disclosure may be applicable to various types of aircraft.

A system (22) is disclosed having an inerting device (44) that receives an intake air stream and separates it into nitrogen-enriched air (NEA) and oxygen-enriched air (OEA). The inerting system also has an oxygen concentration sensor (46) and a controller (48) connected to the oxygen concentration sensor (46). The controller (48) adjusts operation of the inerting system (22) during use based at least in part on feedback received from the oxygen concentration sensor (46).

An aviation vehicle includes: a vehicle body; a propulsion system operable with the vehicle body, the propulsion system including a gas turbine engine including a combustion section; a fuel delivery assembly including a gaseous fuel delivery section extending to the combustion section, the gaseous fuel delivery section defining a potential leakage location; and a fuel leak combustion assembly including a heat source positioned in communication with the potential leak location to ignite gaseous fuel leaking from the potential leak location of the gaseous fuel delivery section of the fuel delivery assembly.

An aeronautical vehicle comprising: a vehicle body; a propulsion system operable with the vehicle body, the propulsion system comprising a gas turbine engine, the gas turbine engine comprising a combustion section; a fuel delivery assembly comprising a gaseous fuel delivery section extending to the combustion section, the gaseous fuel delivery section defining a potential leak location; and a fuel leak combustion assembly comprising a heat source positioned in communication with potential leak location to ignite a gaseous fuel leaking from the potential leak location of the gaseous fuel delivery section of the fuel delivery assembly.

A system for supplying hydrogen to hydrogen consumer on an aircraft with a helium heat transfer circuit. The hydrogen consumer may be a combustion engine or a fuel cell. A supply pipe is fluidly connected between the tank and a hydrogen consumer. A first pump is arranged on the supply pipe and configured to circulate the liquid hydrogen from the tank to the hydrogen consumer.