113 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 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 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 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.

Disclosed in the present invention are a cryogenic fuel engine cold-start system, a control method, an apparatus, a device, a medium, and a vehicle. The cryogenic fuel engine cold-start system comprises: a cryogenic fuel engine, a cryogenic fuel tank, a master controller, a battery, and a cryogenic fuel injector. The cryogenic fuel tank is connected to a feed port of the cryogenic fuel injector; a nozzle of the cryogenic fuel injector is connected to the cryogenic fuel engine, and is used for injecting a cryogenic fuel to the cryogenic fuel engine; the cryogenic fuel engine is provided with an electric heating apparatus communicationally connected to the master controller; the battery is electrically connected to the electric heating apparatus; and the electric heating apparatus at least comprises an air channel heating apparatus. In the present invention, by means of the air channel heating apparatus arranged in an air inlet channel, a cryogenic fuel jet is boiled, thereby solving the cold-start problem of a cryogenic fuel, i.e., solving the cold-start problem of methanol, and matching an extended-range technology route. In addition, compared with the prior art that gasoline is used for heating, the present invention uses the electric heating apparatus, thereby avoiding the problems in the prior art of emission exceedance and emission aftertreatment that need to be considered when gasoline is used for heating.

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.

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 carbon capture system for an LNG fueled power plant (1) and method for LNG combustion and carbon capture, wherein the method comprises - gasifying the LNG stream by heating to obtain a gasified NG stream - combusting the gasified NG stream to obtain exhaust gas stream- separating water from the cooled exhaust gas stream to obtain a dry exhaust gas stream - adsorbing CO2 from the dry exhaust gas stream to obtain a CO2 depleted exhaust gas stream - desorbing CO2, pressurizing it and cooling it with the cold from the gasification of the LNG - separating CO2 from the desorbing stream.

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.

The present invention relates to a fuel management system 100 for an electrically powered aircraft. The system comprises a cryogenic fuel source 100; a refuel arrangement 120 and a conduit 111, 112, 1

There is described a method of and system of recovering fuel and a ventable stream from a purging stream purging an engine of a seagoing vessel, the vessel having fuel in a low-temperature fuel tank configured to supply the engine, comprising at least the steps of: • (a) purging the engine with a purging gas (120) to produce a fuel-containing purge gas stream (122); • (b) passing the fuel-containing purge gas stream to one or more holding tanks (142) on the vessel to create a holding gas (140); • (c) passing the holding gas into a low-temperature recovery heat exchanger (174); • (d) passing a cooling stream of fuel (160) provided from the fuel tank (116) into the low-temperature recovery heat exchanger to cool the holding gas and to provide a warmer cooling stream (171), and a cooler holding gas stream (177); • (e) passing the cooler holding gas stream into a separator (175) to provide a gaseous reduced-fuel stream (176) and a liquid fuel stream (173); and • (f) treating the gaseous reduced-fuel stream to further reduce the fuel percentage in the gaseous reduced-fuel stream, and to provide a ventable stream (265). There is also described a vessel, such as a liquefied cargo carrier, using said method and system.

A cryogenic insulated pipe having a conformally-bonded aerogel paper layer on an outer surface of the pipe. The conformally-bonded aerogel paper layer is conformally-bonded to the pipe outer surface in a pre-applied resin layer. An insulative blanket is applied over the aerogel paper, and a breathable protective layer is applied over the insulative blanket. Also disclosed is a cryogenic fuel tank for retrofitting a conventional fossil fuel-powered aircraft, or for a purposely built aircraft to run on hydrogen has an aerodynamically shaped outer surface including an ogive shaped nose cone, and a tapered tail cone, wherein the tapered tail cone includes actively adjustable elements for adjusting aerodynamic characteristics of the cryogenic fuel tank. The cryogenic fuel tank is configured to be attached below wings of the aircraft, through support pylons, which include sensors configured to measure forces applied by the cryogenic fuel tank to the airframe. The cryogenic fuel tank includes a nozzle and valve configured to vent gas from the cryogenic fuel tank by expansion through the nozzle in the event that the cryogenic fuel tank is j ettisoned from the aircraft.

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 apparatus for supplying gas from an aircraft (100, figure 1) to ground equipment (110) comprising a gas supply 318 housed within an aircraft, and at least one gas line 322 in communication between the aircraft gas supply and the ground equipment. The gas used may in this instance comprise liquid hydrogen. A supply of nitrogen 318 housed on an aircraft, for example a Nitrogen Generating System, is used in conjunction with a gas line 322 to supply nitrogen into the fuel line 316, to flush out potentially combustible materials before liquid hydrogen is supplied through the fuel line 316. The aircraft supply of nitrogen 318 is also used to supply inert gas, via a gas line 334, to the Ground Support Equipment (110, figure 1) refuelling or defueling the aircraft 100. This can provide redundancy for the Ground Support Equipment’s systems, and may allow the aircraft (100) to operate at less well-equipped airports. The application comprises a plurality of apparatus and methods relatable to hydrogen / cryogenic refuelling.

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.

A fuel delivery system for an aircraft turbine engine assembly includes a storage tank that is configured for storage of a cryogenic fuel in a liquid phase, at least one thermal compression tank where liquid fuel from the fuel storage tank is pressurized by exposure to thermal energy to elevate a pressure of the liquid fuel, a heat communication device that is in thermal communication with the thermal compression tank for communicating thermal energy to the liquid fuel within the thermal compression tank, a valve system for controlling the flow of pressurized liquid fuel into and out of the thermal compression tank, and a controller that is programmed to operate the valve system to release pressurized liquid fuel from the thermal compression tank into a conduit for communication to a combustor.

The invention relates to a volumetric booster for gaseous and / or cryogenic fuel with a four and a half stroke cycle. 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 restore them during the suction and / or compression phases, in which an internal or external heating system makes it possible to increase the pressure and temperature of the outgoing fuel flow. The invention is located on the fuel supply circuit of a receiver, with the aim of providing it with fuel or a fuel-rich flow under satisfactory pressure and temperature conditions for its proper operation. Figure for the abstract: [Fig 1]

The invention provides an aero-engine closed circulation system based on low-temperature fuel cold energy utilization, and belongs to the technical field of low-temperature fuel aero-engines. The low-temperature fuel storage tank conveys low-temperature fuel to a combustion chamber of the aero-engine through the first channel. The compression and expansion circulation assembly comprises a compressor, a first turbine, a first power generator and a wake flow heat exchanger; the compressor pressurizes a cycle working medium, the pressurized cycle working medium absorbs waste heat of high-temperature fuel gas through the wake flow heat exchanger and then enters the first turbine to expand and do work to drive the first turbine to rotate, the first turbine drives the compressor and the first power generator to operate, and the cycle working medium obtained after expansion and do work enters the second channel to exchange heat with low-temperature fuel. And the circulating working medium passing through the fuel preheating heat exchanger returns to the compressor. The cold energy utilization rate of low-temperature fuel of the aero-engine is increased, and the output work of the engine is increased.

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.

Systems, apparatus, articles of manufacture, and methods are disclosed including a fuel distribution system for an engine, the fuel distribution system including: a first pump downstream of a fuel tank; a first motor coupled to the first pump; a second pump downstream of the first pump; a second motor coupled to the second pump; a third pump downstream of the second pump, the third pump having an inlet and an outlet; a bypass path from an outlet of the third pump to an inlet of the third pump; and a recirculation valve aligned with the bypass path.

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].

An aircraft propulsion system includes a core engine that includes a combustor where a cryogenic fuel is mixed with compressed air and ignited to generate an exhaust gas flow, a propulsive fan driven by shaft power that is generated by the core engine, a cryogenic fuel system that includes a cryogenic fuel storage tank, a fuel flow path where a fuel flow is circulated from upstream in a direction downstream toward the combustor of the core engine, a bottoming compressor where a gaseous fuel flow is compressed, a first heat exchanger where the gaseous fuel flow exhausted from the bottoming compressor is heated, a turboexpander where the gaseous fuel flow from the first heat exchanger is expanded to generate shaft power, and a mixer where the gaseous fuel flow mixes with and heats a liquid fuel flow to generate a gaseous fuel flow for communication to the bottoming compressor.

A method of health monitoring aircraft fuel system structures can include monitoring guided waves emitted by at least one guided wave emitter mounted to an inner hydrogen tank using at least one guided wave detector mounted to the inner hydrogen tank to monitor for a change versus a first baseline. The method can include monitoring guided waves emitted by at least one guided wave emitter mounted to an outer hydrogen tank surrounding the inner hydrogen tank using at least one guided wave detector mounted to the outer tank to monitor for a change versus a second baseline. The method includes outputting an alert to at least one of aircraft avionics and / or an onboard integrated Vehicle Health Management system (IVHM) if a change versus either or both of the first or second baselines is detected.

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.

The invention discloses a side storage tank connecting space of a ship fuel tank and a connecting method, and belongs to the field of ships. The technical scheme comprises a ship body; the fuel storage tank is used for storing low-temperature fuel; the connecting space is fixedly connected to the outer side face of the fuel storage tank to form a closed containing space for containing a fuel pipeline; and the flexible supporting device is flexibly connected with the connecting space and the ship body and comprises a spring supporting device or a rubber supporting device. The supporting device is applied to side face installation of the connecting space of the ship clean fuel storage tank, solves the technical problem that the connecting space of the fuel storage tank is arranged on the side face of the storage tank, so that the storage tank rotates due to unbalanced stress, and a pipeline is damaged, and has the characteristics of preventing the storage tank from rotating and preventing the supporting device from deforming due to temperature stress.

Use of cryogenic fuel tanks for the cooling of power electronics circuits to improve cooling capabilities for power electronics in vehicles or an aircraft. The power electronics circuit can be cooled via a cryogenic cooling loop by the fuel directly, or the fuel is used to cool a separated coolant tank. A control valve controls the coolant flow within the cryogenic cooling loop based on an electrical property of the power switching element of the power electronics circuit and or based on the way the power switching elements are electrically connected together. The control valve can control the coolant flow such that a junction temperature is achieved which minimizes the drain-source resistance.

This invention discloses a variable environment fuel atomization quality testing system and method. The system includes a high-pressure common rail injection system, a cryogenic refrigeration system, an electronic control system, an image data acquisition system, and an environmental test chamber. The cryogenic refrigeration system reduces the temperature of the fuel inside the injector through convective heat transfer. The environmental test chamber simulates the ambient air pressure, temperature, and humidity based on actual in-cylinder environmental parameters during engine operation. The image data acquisition system acquires and processes images of the cryogenic fuel spray in the variable environment. By measuring the cyclic injection volume during fuel injection, the Sauter mean diameter is calculated using different empirical formulas, and the fuel atomization characteristics are comprehensively analyzed. This invention provides a reliable experimental means for studying fuel atomization in low-temperature environments during engine cold starts, deeply analyzing the impact of complex environments on engine cold starts, and thus seeking to improve engine cold start performance.

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 invention discloses a full-flow afterburning circulation thrust chamber and a cooling method thereof. The problem that in the prior art, the working efficiency of an engine is reduced is solved. A path of high-temperature fuel-rich or oxygen-rich fuel gas is led out from the exhaust end of the gas turbine and is input into the thrust chamber body through the fuel gas branch pipe and the fuel gas cooling collector to serve as a membrane coolant of the thrust chamber body, and an engine does not need to independently lead a path of high-pressure low-temperature fuel behind a fuel pump to serve as the membrane coolant of the thrust chamber body; the specific impulse performance of the engine can be improved by nearly 1%, and the pressure loss can be reduced by more than one time.