143 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 invention relates to a low-temperature liquefied natural gas spray cooling performance test system and a test method, belongs to the technical field of low-temperature fuel spray cooling, and solves the problem that a test system and a test method for taking liquefied natural gas fuel as a spray cooling material are lacked in the prior art. And the performance of the liquefied natural gas fuel as the spray cooling material cannot be accurately analyzed. The test system comprises a double-layer structure spraying chamber, a nozzle, a heat source and a data acquisition system, lNG mist sprayed by the nozzle flows in the inner space of the double-layer structure mist spraying chamber; liquid nitrogen flows in the interlayer space of the double-layer structure spraying chamber and is used for low-temperature cooling of LNG spraying. According to the test system, a double-layer heat preservation structure is adopted, and the LNG partially gasified due to storage and transportation can be cooled by using low-temperature liquid nitrogen, so that the phase change heat absorption capacity of the LNG is exerted in spray cooling. And meanwhile, the influence of the external environment on the test result can be well isolated, and the external interference is reduced.

A turbine engine assembly includes a compressor section (26, 136) where an inlet airflow is compressed, a cryogenic fuel system (46) for generating flow of cryogenic fuel, an air separation system (66, 96) where an airflow is placed in thermal communication with a portion of the flow of cryogenic fuel for generating an enhanced oxygen flow (68). In a combustor section (28), the compressed inlet airflow and a portion of the enhanced oxygen flow (68) is mixed with fuel and ignited to generate an exhaust gas flow (44) that is communicated through a core flow path (C) to a turbine section (30, 140) where expansion of the exhaust gas flow (44) is utilized to generate a mechanical power output. Water is extracted from the exhaust gas flow (44) in condenser (58) transformed into a steam flow (56) for injection into the core flow path (C) in an evaporator system (54).

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 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.

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.

To provide an air-cooled fuel cell system excelling in drive performance of a fuel cell at low temperature while suppressing a case from increasing in size or becoming complicated.SOLUTION: A fuel cell system includes a fuel cell, a hydrogen system, a reactive air system, and a cooling air system. The fuel cell system has a case for housing the fuel cell. The case includes an upstream space and a downstream space in a flow direction of cooling air within the case, with the fuel cell as reference. The cooling air system has cooling-air blow means for generating a flow of the cooling air in the upstream space. The reactive air system includes a reactive air intake port and reactive air blow means in the upstream space. In a case where a predetermined switching condition arises, the fuel cell system stops driving the cooling air blow means and drives the reactive air blow means, thus reversing the flow of the cooling air within the case.SELECTED DRAWING: Figure 3

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.

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.

A pipe spacer for separating inner and outer pipes of a double-walled pipe assembly, comprises an annular body 60 for positioning between inner and outer pipes of the double-walled pipe assembly, the annular body being formed of a composite material. The spacer further comprises a plurality of outer and / or inner arms 70 extending radially outwardly / inwardly from the annular body for contacting the outer / inner pipe. Each of the arms are springs 71 that extend radially from the annular body and are configured to deform towards the annular body on contact with the respective outer or inner pipe. The arms are formed of a composite material. The arms can be attached to the annular body and can have a constant cross-section extending between opposing planar faces. The annular body can have a constant cross-section extending between opposing planar facer, and the opposing planar faces of the body and the arms are perpendicular to each other. The annular body can be plate like. A double walled pipe assembly comprises an inner and outer pipe and the pipe spacer. An aircraft assembly comprises a cryogenic fuel tank and the double walled pipe assembly.

An aircraft environmental control system includes a tank (144) holding cryogenic fuel, a heat exchanger (120), a first rotary machine (128), 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 (144) with an impeller (1341) 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.

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.

A pipe spacer for separating inner and outer pipes of a double-walled pipe assembly comprises an annular body 60 for positioning between inner and outer pipes of the double-walled pipe assembly. It further comprises springs 71 extending radially from the annular body, with each spring is configured to deform inwardly towards the annular body on contact with one of the inner and outer pipes, and a plurality of projecting stops 80, fig. 8) extending from the annular body which limit the inward deformation of the springs. The springs can be inner or outer springs extending radially inwardly or outwardly, respectively, from the annular body. The stops can contact the inner or outer pipe to limit the inward deformation of the spring. A double-walled pipe assembly comprises inner and outer pipes and the spacer. The space between the inner and outer pipes can be held at a vacuum pressure. An aircraft assembly comprises a cryogenic fuel tank and the double-walled pipe assembly.

A second layer of physical protection against failure for a fuel line of a vehicle for use with high pressure and cryogenic fuels increases safety. The primary fuel line can be assembled from one or more components. The secondary protection is a single outer sleeve that includes a selectively permeable or impermeable membrane and may be reinforced. The sleeve and enclosed volume can also be used to protect against oxygen liquification in cryogenic applications. A means to detect failure of the primary fuel line and optional means to vent leaking fuel depend on the application. Clamp designs may be used to mount and clamp such assemblies in a vehicle structure.

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.

The invention relates to an aircraft, in particular an airplane, comprising a wing structure, a fuselage with a longitudinal axis, a fuel system, and at least two engines associated with the fuselage, in particular arranged in the fuselage, wherein a first engine and a second engine have different maximum thrusts and at least one of the engines is configured for operation with different fuels, wherein the fuel system comprises a first fuel tank for supplying the engine with a liquid fossil fuel, wherein the fuel system comprises a second fuel tank for supplying the engine with a cryogenic fuel, wherein the second fuel tank is designed to be pressure-resistant for receiving the cryogenic fuel and is accommodated in the fuselage.

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 cryogenic fuel tank system includes a fuel tank configured to contain a cryogenic liquid such that a headspace above the cryogenic liquid contains cryogenic vapor. A fuel cell converts the cryogenic vapor from the headspace into electricity and water vapor. A vent valve directs excess cryogenic vapor from the headspace to the fuel cell when pressure in the fuel tank exceeds a predetermined pressure level.

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 a low-temperature fuel storage tank and a manufacturing method thereof. The storage box comprises an inner box, an outer box, a supporting structure, a penetrating pipe and a pipeline. The inner box body is composed of a lining and a composite material winding layer, a storage cavity and a center vacuum cavity are formed, and two flexible nesting pipes connected through a pull rod are symmetrically distributed in the center vacuum cavity. The outer box is composed of a shell and a pipeline distributor. The supporting structure is composed of a communicating base, a connecting ring and a supporting frame. The pipeline is composed of a liquid adding pipe, a liquid discharging pipe and an exhaust pipe. The two ends of the inner box are connected with the outer box through supporting structures based on flexible nested pipes, and an annular vacuum cavity is formed. The annular vacuum cavity is filled with the coating layer, and the storage cavity and the pipeline distributor are connected in a sealed mode through the pipeline. According to the low-temperature fuel storage tank, the problems that an existing low-temperature fuel storage tank is low in storage density, short in dormancy time, high in heat leakage and low in mechanical environment adaptability are solved on the premise that the weight is not 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.