52 results about "Cryogenic fuel" 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 to exchange heat between the cryogenic fuel and at least one of (1) the hydraulic fluid or (2) a working fluid thermally coupled to the hydraulic system.

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.

An aircraft propulsion system includes a cryogenic fuel system and a fuel flow path where a fuel flow is circulated from upstream in a direction downstream to a combustor of the core engine. A first heat exchanger inputs heat into the fuel flow downstream of the first heat exchanger is used to heat the fuel flow from the fuel storage tank and a second heat exchanger inputs thermal energy from a heat source into the fuel flow from the core engine downstream of the first heat exchanger. A turboexpander is configured to generate shaft power from expansion of the fuel flow exhausted downstream from at least one of the first heat exchanger and the second heat exchanger.

The invention provides an intelligent power supply system for solid-liquid fuel composite hydrogen production and high and low temperature fuel cell coupling. Comprising an aluminum hydride fuel tank, a methanol steam reforming hydrogen production reactor, a high-temperature proton exchange membrane fuel cell stack and a low-temperature proton exchange membrane fuel cell stack, an outlet of the aluminum hydride fuel tank is connected with an inlet of the high-pressure hydrogen storage bottle through a pipeline; an outlet of the high-pressure hydrogen storage bottle is connected with an anode inlet of the low-temperature proton exchange membrane fuel cell stack through a pressure reducing valve; according to the double-hydrogen-source cooperative coupling mechanism, through reaction characteristic complementation and energy gradient utilization, the inherent limitation of a single hydrogen source in fuel cell application is effectively solved, the traditional system architecture of a single hydrogen source and a single type of fuel cell is broken through, two hydrogen production modes and two electric pile technologies are creatively and deeply fused, and the energy utilization rate of the fuel cell is improved. The comprehensive breakthrough of the system in efficiency, dynamic response, fuel adaptability and reliability is realized.

A fuel system (300) supplies the combustion chamber of an aircraft turbomachine. It comprises a liquid cryogenic fuel storage tank (110) connected by a pipeline (120) to the combustion chamber, a heating element (112) to bring the cryogenic fuel to a temperature that allows its evaporation, a fuel accumulator (310) in the gaseous state, and an injection system (114) controlling the injection of the gaseous fuel into the combustion chamber. Since the thermal inertia of the heating element may not be sufficient to maintain the fuel within an acceptable temperature range, the fuel accumulator (310) includes an internal heating element (311) for the gaseous fuel. This additional element provides supplementary thermal energy to the gaseous fuel in the event of a flow transient.It also allows for more precise control of the temperature of the gaseous fuel actually injected into the combustion chamber. Figure for the abbreviation: [Fig 3].

The embodiment of the present application provides a combustion chamber semi-regenerative cooling structure, a gas generator, an engine and a liquid rocket, the combustion chamber semi-regenerative cooling structure comprises a throttle hole and a cooling channel arranged on the front section of the combustion chamber; the throttle hole is arranged on the outer wall of the front section of the combustion chamber, and the cooling channel is arranged between the inner wall and the outer wall of the front section of the combustion chamber; the throttle hole is in communication with the cooling channel and is used for guiding a small part of low-temperature fuel in a liquid collecting ring into the cooling channel; the cooling channel extends from one end of the front section of the combustion chamber provided with an injector to the other end, is used for guiding the low-temperature fuel out of the front section of the combustion chamber, and is used for spraying the low-temperature fuel on the inner wall of the rear section of the combustion chamber connected with the front section of the combustion chamber, so that the inner wall of the front section of the combustion chamber and the inner wall of the rear section of the combustion chamber connected with the front section of the combustion chamber are cooled. The combustion chamber semi-regenerative cooling structure, the gas generator, the rocket engine and the liquid rocket provided by the present application can effectively improve the manufacturing process and the problem of complex structure.

An apparatus includes a cryo-fuel tank, at least two heat exchangers, at least one valve, and a condenser. The cryo-fuel tank is configured to store cryo-fuel. The at least two heat exchangers are configured to reduce heat of a core flow through an engine, where the at least two heat exchangers have different heat transfer efficiencies. The at least one valve is configured to control the core flow between each of the at least two heat exchangers. The condenser is configured to exchange heat between the cryo-fuel and the core flow processed through the at least two heat exchangers.

The present invention relates to a cryogenic fuel supply assembly (5) for an aircraft engine (1), comprising: - a cryogenic pipeline (7), in which the cryogenic fuel is liquid in a first operating mode and is vaporized in a second operating mode, - at least one heating installation (9) comprising an arm (25), from which extends a forearm (27) movable between a first position and a second position, the arm (25) being subjected to a heat input, in the first position, the forearm (27) being distant from the cryogenic pipeline (7), in the second position, the forearm (27) being in thermal conduction with the cryogenic pipeline (7) to create a thermal bridge between the cryogenic pipeline (7) and the arm (25).The invention also relates to an aircraft engine (1) equipped with such an assembly (5), an aircraft equipped with such an aircraft engine (1), and a method for maintaining such an assembly (5). Figure for the abstract: Fig. 2.

An aircraft propulsion system includes a core engine that includes a core flow path through a main compressor where an inlet airflow is compressed and communicated to a combustor to generate an exhaust gas flow that is expanded through a main turbine section to generate mechanical power to drive the main compressor and a propulsive fan, a cryogenic fuel system that includes a cryogenic fuel storage tank, a fuel flow path for routing a cryogenic fuel flow to the combustor of the core engine, and a thermoelectric generator that is in thermal communication with the cryogenic fuel flow and a heat source to generate a temperature differential across the thermoelectric generator utilized to generate electric power.

An aircraft environmental control system includes a tank holding cryogenic fuel, a heat exchanger, a first rotary machine, a first outlet duct, and a second outlet duct. The heat exchanger includes a cold side flow path downstream from the tank to evaporate the fuel, a first hot side flow path, and a second hot side flow path. The first rotary machine includes a first compressor section with an impeller upstream from the second hot side flow path. The first rotary machine includes a first shaft tied to the impeller and a first motor to rotate the impeller. The first duct and the second duct are downstream from the heat exchanger. The first duct provides a first portion of vaporized fuel to a power generator. The second duct provides a second portion of vaporized fuel to a burner that creates hot air to move through the first hot side flow path.

The present application belongs to hydrogen energy technical field, and particularly relates to a high-efficiency flexible medium-low temperature fuel cell waste heat refrigeration system.The technical scheme is as follows: a high-efficiency flexible medium-low temperature fuel cell waste heat refrigeration system, comprising a CO2 transcritical heat pump system, a lithium bromide absorption refrigeration system and a fuel cell power generation system, hot water generated by the CO2 transcritical heat pump system and hot water generated by the fuel cell power generation system are mixed and supplied to the lithium bromide absorption refrigeration system, and hot water generated by the lithium bromide absorption refrigeration system is sent back to the fuel cell power generation system.The present application provides a high-efficiency flexible medium-low temperature fuel cell waste heat refrigeration system, which fully utilizes fuel cell power and utilizes low-grade heat, can greatly improve the temperature range of the fuel cell, and improves the overall energy utilization efficiency.

The invention relates to a four-and-a-half-stroke volumetric booster for gaseous and / or cryogenic fuel. The device comprises a volumetric machine associated with a closed and independent transfer chamber (10), intended to receive the residual gases after expansion and to deliver them during the suction and / or compression phases. An internal or external heating system in this chamber increases the pressure and temperature of the outgoing fuel stream. The invention is situated within the fuel supply circuit of a receiver, with the aim of providing it with fuel or a fuel-rich stream under satisfactory pressure and temperature conditions for its proper operation. Figure for the abstract: [Fig 1]

The invention relates to a turbine engine (M) of an aircraft (A), which turbine engine includes a fuel circuit (CC) comprising: a tank (10) of cryogenic fuel in the liquid state; a primary distribution circuit (1) in fluid communication with the tank; a secondary distribution circuit (2) intended to be in fluid communication with a combustion chamber (C) of the turbine engine (M); a fluid-heating device (3) comprising a fluid inlet (31) and a fluid outlet (32) in fluid communication with the primary distribution circuit (1) and the secondary distribution circuit (2), respectively, the heating device (3) being configured such that the cryogenic fuel changes from the liquid state to the gaseous state when it passes through the heating device (3), the cryogenic fuel being in the gaseous state at the fluid outlet in communication with the secondary distribution circuit (2).

The invention provides a turbine low-temperature fuel cell vertical take-off and landing type dual-mode combined engine, and belongs to the technical field of aero-engines. According to the turbine low-temperature fuel cell vertical take-off and landing type dual-mode combined engine, a connecting part is arranged at the front end of a shell, a first fan is connected with the connecting part, a first telescopic structure is located on the shell, the first telescopic structure is connected with the connecting part, and the first telescopic structure has a contraction state and an extension state; the first telescopic structure drives the first fan to rotate to a vertical state through the connecting part; when the first telescopic structure is in the stretching state, the first telescopic structure drives the first fan to rotate to the horizontal state through the connecting part. The turbine low-temperature fuel cell vertical take-off and landing type dual-mode combined engine is suitable for horizontal flight and vertical take-off and landing dual-mode aircrafts, the oil consumption rate is low, and the endurance time is long.

An aircraft propulsion system includes a core engine that includes a main compressor where an inlet airflow is compressed and communicated to a combustor to generate an exhaust gas flow that is expanded through a main turbine section to generate power that is used to drive the main compressor and a propulsive fan, a bottoming cycle where a working fluid is heated and expanded through a bottom turbine to generate shaft power, the bottoming cycle includes a primary compressor loop that includes a first bottoming compressor and a secondary compressor loop that includes a second bottoming compressor and the flow of working fluid flow is adjusted to flow through at least one of the primary compressor loop and the secondary compressor loop, an exhaust gas heat exchanger where heat from the exhaust gas flow heats the working fluid of the bottoming cycle, a cryogenic fuel system that includes a cryogenic fuel storage tank, a fuel flow path for routing the cryogenic fuel to the combustor of the core engine, and a fuel / working fluid heat exchanger for cooling the working fluid within the primary compressor loop. The secondary compressor loop bypasses the fuel / working fluid heat exchanger.

The invention discloses a power device of a low-temperature fuel direct injection gas compressor, a control method and an aero-engine, and belongs to the technical field of aero-engines. The power device comprises an engine body and a low-temperature fuel storage and transportation system; the low-temperature fuel storage and transportation system comprises a hydrogen storage tank and a flow distributor, the hydrogen storage tank is connected with a first channel and a second channel, and the flow distributor is used for controlling the flow of fuel entering the first channel and the second channel from the hydrogen storage tank. The first channel penetrates through the exhaust nozzle heat exchanger to exchange heat with high-temperature fuel gas in the exhaust nozzle, the tail end of the first channel is connected with a combustion nozzle, and the combustion nozzle is used for spraying fuel subjected to heat exchange to the combustion chamber; the tail end of the second channel is connected with a fuel atomization nozzle, and the fuel atomization nozzle is used for spraying low-temperature fuel to at least one of the interstage or the front end of the compressor unit. The technical problems that an indirect cooling heat exchanger arranged in the air compressor is complex in structure, space is limited, and pneumatic loss is large are solved.

The invention relates to an aircraft turbomachine (M) (A) comprising a fuel circuit (CC) including: - a liquid cryogenic fuel tank (10); - a primary distribution circuit (1) in fluidic communication with the tank; - a secondary distribution circuit (2) intended to be in fluidic communication with a combustion chamber (C) of the turbomachine (M); - a fluid heating device (3) comprising a fluid inlet (31) and a fluid outlet (32) in fluidic communication with the primary (1) and secondary (2) distribution circuits respectively, the heating device (3) being configured such that the cryogenic fuel changes from a liquid to a gaseous state when passing through the heating device (3), the cryogenic fuel being in a gaseous state at the fluid outlet in communication with the secondary distribution circuit (2). Figure 1

An aircraft propulsion system includes a core engine that includes a main compressor where an inlet airflow is compressed and communicated to a combustor to generate an exhaust gas flow that is expanded through a main turbine section to generate power that is used to drive the main compressor and a propulsive fan, a bottoming cycle where a working fluid is heated and expanded through a bottom turbine to generate shaft power, the bottoming cycle includes a primary compressor loop that includes a first bottoming compressor and a secondary compressor loop that includes a second bottoming compressor and the flow of working fluid flow is adjusted to flow through at least one of the primary compressor loop and the secondary compressor loop, an exhaust gas heat exchanger where heat from the exhaust gas flow heats the working fluid of the bottoming cycle, a cryogenic fuel system that includes a cryogenic fuel storage tank, a fuel flow path for routing the cryogenic fuel to the combustor of the core engine, and a fuel / working fluid heat exchanger for cooling the working fluid within the primary compressor loop. The secondary compressor loop bypasses the fuel / working fluid heat exchanger.

A fuel delivery system for a combustor of a gas turbine engine. The fuel delivery system having a primary fuel tank configured to store liquid hydrogen and a secondary fuel tank configured to store fuel, such as Jet A or SAF. The fuel being provided and mixed in the jet engine to alleviate the production of contrails. In addition, the primary fuel tank may be a cryogenic tank to enable the storage of liquid hydrogen, or liquid natural gas. As a result, the primary fuel may be utilized to cool the secondary fuel and / or the gas turbine engine.

A turbine engine assembly includes a compressor section where an inlet airflow is compressed, a cryogenic fuel system for generating flow of cryogenic fuel, an air separation system where an airflow is placed in thermal communication with a portion of the flow of cryogenic fuel for generating an enhanced oxygen flow. In a combustor section, the compressed inlet airflow and a portion of the enhanced oxygen flow is mixed with fuel and ignited to generate an exhaust gas flow that is communicated through a core flow path to a turbine section where expansion of the exhaust gas flow is utilized to generate a mechanical power output. Water is extracted from the exhaust gas flow in condenser transformed into a steam flow for injection into the core flow path in an evaporator system.

The invention relates to a cryogenic liquid storage system, an aircraft comprising a cryogenic liquid storage system, a method of accessing a measurement probe of a cryogenic liquid storage system, and an aircraft comprising a cryogenic fuel storage system. The cryogenic liquid storage system includes: an outer tank; an inner tank inside the outer tank and configured to store a cryogenic liquid; an isolation valve; a collection chamber external to the outer tank and fluidly connected to the inner tank such that fluid can flow from the inner tank to the collection chamber via an isolation valve, where the isolation valve can be actuated to isolate the collection chamber from the inner tank; and a measurement probe movable between the inner tank and the collection chamber.

The invention relates to an aircraft having a refuelling connection which is fluidically connected to a tank arranged in the aircraft, wherein the refuelling connection and the tank are designed to receive a cryogenic fuel, wherein the refuelling connection has a pipe section (7) specially designed for conducting a cryogenic fuel and / or a coupling (25) which is fixed to an aircraft-fixed structure, wherein, in order to fix the pipe section (7) and / or the coupling (25), a first half-shell (17) and a second half-shell (18) are provided, wherein the first half-shell (17) is fixed to the aircraft-fixed structure, and wherein the second half-shell (18) is connected to the first half-shell (17) by an elastic clamping connection so as to exert a clamping force on the pipe section (7) and / or the coupling (25), and is guided so as to be displaceable relative to the aircraft-fixed structure in a linear guide (26).

A structure for refuelling an aircraft with cryogenic fuel includes a walkway to allow personnel to access the aircraft and a pipework arrangement attached to the walkway. The pipework arrangement includes a feed line, a return line and a bypass valve between the feed line and the return line and fluidically connecting the inlet line to the return line. A first end of the feed line is configured to connect to a source of cryogenic fuel, and a second, opposite end of the feed line is configured to connect to the aircraft. The bypass valve is switchable between a refuelling configuration in which the bypass valve prevents fluid flow between the feed line and return line through the bypass valve, and a chill down configuration in which the bypass valve allows fluid flow between the feed line and the return line through the bypass valve.

An aircraft propulsion system includes a core engine and a bottoming cycle where a working fluid is circulated within a closed circuit. A first heat exchanger is used to transfer heat from a portion of thermal energy from the exhaust gas flow to working fluid of the bottoming cycle. A fuel / working fluid heat exchanger provides the cryogenic fuel to cool the working fluid exhausted from a bottoming turbine and before a bottoming compressor.

The utility model discloses a liquid nitrogen wash low-temperature fuel discharge liquid water bath reheating recovery device which comprises a liquid nitrogen wash cold box, a water bath heating assembly, a hot circulating water assembly, a cold circulating water assembly and a fuel gas outlet assembly. The hot circulating water assembly is communicated with a second liquid inlet of the water bath heating assembly, the cold circulating water assembly is communicated with a liquid outlet of the water bath heating assembly, and the fuel gas outlet assembly is communicated with a gas outlet of the water bath heating assembly. The water bath heating assembly is filled with hot circulating water through the hot circulating water assembly, low-temperature discharge liquid is reheated in the water bath heating assembly, reheated fuel gas is recycled through the fuel gas outlet assembly, heat-exchanged hot circulating water is recycled through the cold circulating water assembly, cold energy recycling is achieved, meanwhile, reheated steam consumption is reduced, and energy conservation and emission reduction are achieved. The effective heat value of the low-temperature discharge liquid is fully utilized, resources are fully utilized, and the purposes of energy conservation and up-to-standard discharge are achieved.

The invention relates to an aircraft having a refuelling connection which is fluidically connected to a tank arranged in the aircraft, wherein the refuelling connection and the tank are designed to receive a cryogenic fuel, wherein the refuelling connection comprises a pipe section (7) specially designed for conducting a cryogenic fuel and a coupling (23) which is fixed to an aircraft-fixed structure, wherein the pipe section (7) and / or the coupling (23) has at least two diametrically arranged radially outwardly projecting lug flanges (17, 20), and at least two projecting mounting flanges (18, 21) are provided on the aircraft-fixed structure, on which mounting flanges the pipe section (7) and / or the coupling (23) is fixed to the aircraft by means of the lug flanges (17, 20).

An aircraft propulsion system includes a primary energy conversion device that uses a cryogenic fuel and air to generate power and thermal energy, a pylon that is configured to support the primary energy conversion device, the pylon includes an interior space, a bottoming cycle that is supported within the interior space of the pylon, the bottoming cycle includes a working fluid that is circulated within a closed circuit that includes a bottoming compressor section and a bottoming turbine section, the working fluid is compressed in the bottoming compressor section and expanded through the bottoming turbine section to generate shaft power, a primary heat exchanger that is configured to communicate thermal energy that is generated by the primary energy conversion device into the working fluid, and a fuel / working fluid heat exchanger that is configured to transfer thermal energy from the working fluid into the cryogenic fuel.

Disclosed is a structure for refuelling aircraft with cryogenic fuel the structure comprising a walkway 12 for personnel and a pipe work arrangement 14 attached to the walkway. The pipe work arrangeme

The invention relates to the technical field of aircraft propulsion, in particular to a turbine low-temperature fuel cell jet-propelled bimodal combined engine which comprises a fuel cell, an aircraft propulsion system and an energy management system. The aircraft propulsion system comprises a ducted fan, a medium-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a medium-pressure turbine, a low-pressure turbine, a fuel cell, a hydrogen fuel storage tank, a low-pressure shaft, a medium-pressure shaft, a high-pressure shaft, a low-pressure shaft motor, a medium-pressure shaft motor and a high-pressure shaft motor. The ducted fan is connected with the low-pressure turbine through a low-pressure shaft, a low-pressure shaft motor is arranged on the low-pressure shaft, the medium-pressure compressor is connected with the medium-pressure turbine through a medium-pressure shaft, a medium-pressure shaft motor is arranged on the medium-pressure shaft, and the high-pressure compressor is connected with the high-pressure turbine through a high-pressure shaft. Organic combination of the fuel cell and the gas turbine engine is achieved through the dual-mode combined engine. The fuel cell works in the cruising stage, and due to the fact that the working time of the cruising stage is longest, the efficiency of the fuel cell is high, and emission can be greatly reduced.