Abstract: A system for an aircraft includes an engine bleed source of a gas turbine engine. The system also includes a means for chilling an engine bleed air flow from the engine bleed source to produce a chilled working fluid. The system further includes a means for providing the chilled working fluid for an aircraft use.

Abstract: A compressed gas storage system that includes a pressure vessel. The pressure vessel includes a first vessel portion and a second vessel portion in fluid communication with the first vessel portion. The pressure vessel includes a third vessel portion in fluid communication with the second vessel portion. The compressed gas storage system includes a first valve positioned between the first vessel portion and the second vessel portion and a second valve positioned between the second vessel portion and the third vessel portion. The first valve allows and impedes fluid flow between the first and the second vessel portions. The second valve allows and impedes fluid flow between the second and the third vessel portions.

Abstract: For improving storage of hydrogen in a vehicle, a hydrogen tank assembly is provided for a vehicle. The hydrogen tank assembly includes an inner tank wall defining a hydrogen tank volume configured for storing liquid hydrogen; and an outer hydrogen collector defining, together with the inner tank wall, at least one cavity outside of the hydrogen tank volume and including at least one hydrogen outlet for leading gaseous hydrogen which leaks from the hydrogen tank through the inner tank wall into the at least one cavity to a hydrogen storage or a hydrogen consumer.

Abstract: A liquid petroleum gas (LPG) fuel supply system for a vehicle having an internal combustion engine includes an LPG tank, a fuel pump housing, a fuel pump inside the fuel pump housing, a fuel supply line connected between the LPG tank and the fuel pump housing, and a vapor release port located on the fuel pump housing. The vapor release port is connected to the LPG tank by a vapor return line. The fuel pump housing fills with LPG from the LPG tank under the action of gravity. Vapor forms in the fuel pump housing, separates from the liquid, gathers toward the top of the fuel pump housing, and under the action of gravity, displaces through the vapor port, rises through the vapor return conduit, and is released into the LPG tank 19, balancing pressure and preventing vapor lock.

Abstract: A heat exchange system for a surgical instrument includes a valve, a load, and a load conduit extending between the valve and the load. The load conduit delivers fluid from the valve to the load. The heat exchange system also includes an exhaust conduit that directs the fluid away from the valve. A portion of the load conduit is positioned so as to thermally transfer heat to a portion of the exhaust conduit.

Abstract: A ship comprises: a liquefied gas storage tank; a multi-stage compressor for compressing a boil-off gas discharged from a storage tank and comprising a plurality of compression cylinders; a second heat exchanger for heat exchanging a fluid, which has been compressed by the multi-stage compressor, and thus cooling same; a first decompressing device for expanding a flow (“flow a1”) partially branched from the flow (“flow a”) that has been cooled by the second heat exchanger; a third heat exchanger for heat exchanging, by “flow a1” which has been expanded by the first decompressing device as a refrigerant, the remaining flow (“flow a2”) of “flow a” after excluding “flow a1” that has been branched and thus cooling same; and a second decompressing device for expanding “flow a2” which has been cooled by the third heat exchanger.

Abstract: A system and method for controlling the temperature and pressure within a propellant tank containing cryogenic liquid and gaseous phase propellants, the latter also referred to as ullage, by adding an atomized fluid or mixture of fluids having one or more constituent parts to the ullage, where the atomized fluid(s) has a temperature less than the temperature of the ullage. The motive fluid may include a condensable constituent which aids in reducing pressure in the tank or a incondensable constituent which aides in maintaining pressure in the tank.

Abstract: A lightweight, high power density, fault-tolerant fuel cell system, method, and apparatus for full-scale clean fuel electric-powered aircraft having a fuel cell module including a plurality of fuel cells working together to process gaseous oxygen from air compressed by turbochargers, superchargers, blowers or local oxygen supply and gaseous hydrogen from liquid hydrogen transformed by heat exchangers, with an electrical circuit configured to collect electrons from the plurality of hydrogen fuel cells to supply voltage and current to motor controllers commanded by autopilot control units configured to select and control an amount and distribution of electrical voltage and torque or current for each of the plurality of motor and propeller assemblies, wherein electrons returning from the electrical circuit combine with oxygen in the compressed air to form oxygen ions, then the protons combine with oxygen ions to form H2O molecules and heat.

Abstract: A fuel storage system is disclosed having a fuel tank configured to store a liquid fuel; a controllable pressure source for altering the pressure in an ullage space of the fuel tank; and a controller. The controller is configured to determine a target pressure for the ullage space at a given time based on information relating to a temperature of fuel inside the fuel tank at the given time; and to control the pressure source such as to cause the pressure in the ullage space to be substantially equal to the target pressure.

Abstract: A cryogenic energy system for cooling and powering an indoor environment includes a cryogenic open loop comprising a cryogen source to supply a cryogen and at least one transfer-expansion stage in fluid connection with the cryogen source, each transfer-expansion stage comprising at least one heat exchanger for heat transfer therein from a hot fluid to the cryogen and a power unit for expansion therein of the cryogen that has been heated in the at least one heat exchanger to generate electricity, the at least one heat exchanger including an evaporator; and a heat supply open loop configured to provide the hot fluid for heat exchange with the cryogen in the at least one heat exchanger; the cryogenic energy system configured to perform heat removal from a first heat transfer loop of a conventional cooling system, the first heat transfer loop transferring heat obtained from air in the indoor environment.

Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a thermal enhancement feature can enhance a heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.

Abstract: An integrated multimode thermal energy transfer system, method and apparatus for full-scale clean fuel electric-powered multirotor aircraft with automatic on-board-capability to provide sensor-based temperature awareness and adjustment to critical components and zones of the aircraft. Automatic computer monitoring, including by a programmed triple-redundant digital autopilot computer, controls each motor-controller and motor to produce pitch, bank, yaw and elevation, while simultaneously measuring, calculating, and adjusting temperature and heat transfer of aircraft components and zones, to protect critical components from exceeding operating parameters and to provide a safe, comfortable environment for occupants during flight.

Abstract: A fuel injector includes an injector housing having a fuel connector, and an outer housing surface extending around a longitudinal axis of the injector housing. The outer housing surface includes a cylindrical upper section, a cylindrical lower section, and a middle section. The fuel connector defines a connector axis oriented normal to a longitudinal axis of the injector housing and extending between a first connector end attached to the middle section, and a terminal connector end radially outward of the outer housing surface and having therein a fuel inlet. The fuel connector includes an outer connector surface having an unthreaded base section, and an externally threaded end section adjacent to the terminal connector end.

Abstract: Provided are a novel heat utilization system and heat generating device that utilize an inexpensive, clean, and safe heat energy source. A heat utilization system 10 includes a heat-generating element 14 configured to generate heat by occluding and discharging hydrogen, a sealed container 15 having a first chamber 21 and a second chamber 22 partitioned by the heat-generating element 14, and a temperature adjustment unit 16 configured to adjust a temperature of the heat-generating element 14. The first chamber 21 and the second chamber 22 have different hydrogen pressures. The heat-generating element 14 includes a support element 61 made of at least one of a porous body, a hydrogen permeable film, and a proton conductor, and a multilayer film 62 supported by the support element 61.

Abstract: A liquefied natural gas (LNG) bunkering equipment test and evaluation system is provided. The system includes a storage tank module configured to store a liquefied natural gas, a supply module for connecting the storage tank module and the bunkering module, a bunkering module configured to perform bunkering by being supplied with the liquefied natural gas, a simulation module provided at a part under the bunkering module and the supply module and the simulation module is configured to simulate a maritime situation by giving a fluidity to the bunkering module and the supply module, and a controller configured to control a driving of the simulation module, thereby simulating various situations of sea areas by giving fluidity to the storage tank module and the bunkering module.

Abstract: A thermal management system is described. The thermal management system includes an open circuit refrigeration circuit that has a refrigerant fluid flow path, with the refrigerant fluid flow path including a receiver configured to store a refrigerant fluid, an ejector having a primary flow inlet configured to receive refrigerant, a liquid separator, an evaporator configured to extract heat from a heat load that contacts the evaporator, with the evaporator coupled to the ejector and the liquid separator, and an exhaust line coupled to a vapor side outlet of the liquid separator. In operation, the evaporator in the open circuit refrigeration circuit would be coupled to a heat load.

Abstract: An inlet duct for a vehicle battery system includes an inlet part having an inlet hole open toward a vehicle interior, outlet parts divided from the inlet part and having outlet holes so as to supply air introduced to the inlet hole to the battery system via two separated paths, and a grill provided in the inlet part by having multiple ribs forming a grid to cover the inlet hole.

Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a dual-modal cooling structure can enhance heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.

Abstract: A method for large-scale offshore LNG production from natural gas gathered from an onshore gas pipe network is described. The natural gas is pre-treated on an onshore facility for removal of mercury, acid gas, water and C5+ hydrocarbons, and then compressed and piped to an offshore platform for further compression and cooling before being transferred to a floating liquefaction, storage and offloading vessel for liquefaction of the natural gas.

Abstract: A vehicle thermal management system includes a cooling apparatus including a radiator, a first water pump, and a valve connected through a coolant line, a battery cooling apparatus including a second water pump and a battery module connected by a battery coolant line; a chiller connected to the battery coolant line and connected to an air conditioner through a refrigerant connection line connected to the battery coolant line and connected to a refrigerant line of the air conditioner through a refrigerant connection line, to adjust a temperature of the coolant by performing heat exchange between a coolant supplied to the battery coolant line and a refrigerant selectively supplied from the air conditioner; and a heating circuit for warming an interior of the vehicle by use of the coolant having a temperature increased while the coolant passes through at least one electrical component.

Abstract: An electronics cooling system for an aircraft includes a heat exchanger comprising a coolant circuit, an air circuit, and a fuel circuit such that each of the circuits is in thermal communication with at least one of the other circuits. The coolant circuit is in thermal communication with one or more aircraft electronics. The air circuit is in fluid communication with at least one air source. The fuel circuit is in fluid communication with a fuel tank between the fuel tank and an engine of the aircraft.

Abstract: The invention relates to a novel solid heat exchanger module containing a plurality of heat exchanger tubes having a particular shape and being arranged in a special manner.

Abstract: A fuel system for an internal combustion engine includes a liquefied gas tank that stores liquefied gas and a pressurized gas production unit connected to the liquefied gas tank to produce pressurized gas from the liquefied gas. A fuel rail is connected to the pressurized gas production unit. The fuel rail receives the pressurized gas and delivers the pressurized gas to a fuel injector that injects the pressurized gas into a cylinder of the engine. The pressurized gas production unit receives the liquefied gas via a mixing unit that is provided between the liquefied gas tank and the pressurized gas production unit. The mixing unit receives excess gas in the form of vaporized gas from the liquefied gas tank and/or pressurized gas from the fuel rail and mixes the excess gas with the liquefied gas received from the liquefied gas tank.

Abstract: Devices for cooling beverages in cooperation with a compressed gas cartridge. The devices include a housing, a head, a working fluid, and a release mechanism. The housing defines a chamber complementarily configured with the compressed gas cartridge to receive the compressed gas cartridge. The head couples to the housing and defines an interior void in fluid communication with the chamber. The working fluid is contained with the interior void of the head. The release mechanism is operably connected to the housing and configured to selectively release compressed gas from the compressed gas cartridge into the interior void of the head. The compressed gas cools the working fluid when the compressed gas is selectively released from the compressed gas cartridge and contacts the working fluid in the interior void. The head is configured to be placed in a beverage to cool the beverage.

Abstract: Disclosed are a fuel supply system and method for a ship engine. The fuel supply system for a ship engine of the present invention comprises: a submersible pump which is provided to an LNG storage tank of a ship for supplying LNG to the engine of the ship; a high-pressure pump which has the LNG supplied thereto from the submersible pump and pressurizes the same under high pressure; and a return flow channel which, at the upstream of the high-pressure pump, returns the LNG to the LNG storage tank, wherein the flow of the LNG returning through the return flow channel is controlled, and the temperature of the LNG is controlled at the front end of the high-pressure pump.

Abstract: An apparatus, system and method for capture, utilization and sendout of latent heat in boil off gas (“BOG”) onboard a cryogenic storage vessel is described. A liquefied gas vessel comprises a cryogenic cargo tank onboard a liquefied gas vessel, the cargo tank comprising a liquefied gas and a BOG, a latent heat exchanger fluidly coupled to a stream of the liquefied gas and a stream of the BOG, wherein the latent heat exchanger transfers a heat between the BOG stream and the liquefied gas stream to produce a condensed BOG, means for combining the condensed BOG and the liquefied gas stream to obtain a combined stream, the means for combining the condensed BOG and the liquefied gas stream fluidly coupled to the latent heat exchanger, and a liquefied gas regasifier onboard the vessel and fluidly coupled to the combined stream, wherein the liquefied gas regasifier regasifies the combined stream.

Abstract: A heating/cooling system for furnishing employs an electrochemical heat transfer device. An electrochemical heat transfer device may be an electrochemical hydrogen compressor that pumps hydrogen into and out of a tank having a metal hydride forming alloy therein. The absorption of hydrogen by the metal hydride forming alloy is exothermic, produces heat, and the desorption of the hydrogen from the metal hydride forming, alloy is endothermic and draws heat in. An electrochemical hydrogen compressor may be configured between the tanks and pump hydrogen back and forth to form a heat transfer device. A heat exchange device may be coupled with the tank or may comprise the outer surface of the tank to transfer heat to an object or to the surroundings. A closed loop may be configured having two tanks and one or two electrochemical hydrogen compressors to pump the hydrogen in a loop around the system.

Abstract: A method for performing communication in a multi-stage beam forming system includes determining statistical channel information which indicates a priority of analog beams transmitted by a base station, configuring an adaptive code book for digital beam forming, based on the statistical channel information and analog beams which the base station uses in actual communication among the analog beams, and performing communication with the base station through the digital beam forming based on the adaptive code book. A terminal includes a channel estimator configured to perform channel estimation for analog beams transmitted from a base station, a controller configure to determine statistical channel information indicating a priority of the analog beams, and configure an adaptive code book for digital beam forming based on the statistical channel information and analog beams that the base station uses in actual communication among the analog beams, and a communication unit.

Abstract: A fuel feeding system for storing liquefied gas and feeding gaseous fuel to be used in a piston engine, which fuel feeding system includes at least two cryogenic fuel tank arrangements having a first tank arrangement and a second tank arrangement in connection with each other. The fuel feeding system includes a gaseous fuel feed line connected at its first end to at least one piston engine, in which system the first tank arrangement is provided with a pressure build-up system having a first heat exchanger unit. The inlet of the heat exchanger unit is connected to a bottom section of the first tank arrangement the outlet of which is connectable to the top section of the first tank arrangement. The first tank arrangement and the second tank arrangement are both pressure vessels, and the first tank arrangement is selectively connectable to the fuel feed line by a gas line extending from an outlet in the top section of the first tank arrangement.

Abstract: A command device (13) includes a sensor (15,16) for the measurement of a measured value VM of a characteristic C of a fluid FR,A and a comparison (14) of the measured value VM of the characteristic C of the fluid FR,A with at least two step-values VSmin, VSmax of the characteristic C. The command device (13) includes an upstream temperature sensor (20) to be positioned upstream the evaporator (12) according to the air flow direction (6) to measure an upstream temperature T2 of the air flow (3) and give an information (18) which is taken into account by the command device (13) in order to determine the step-values VSmin, VSmax of the characteristic C.

Abstract: A liquid container of the present invention is designed to include an autonomous selective cooling device. The cooling device includes a heat exchanger (15) comprising a first body (20) with a cavity (21), a second body (22) inside the cavity (21), a fluid passage (25) formed between an outer surface of the second body (22) and the surface of the cavity (21), and some means for causing a cooling fluid to flow while expanding along fluid passage (25) up to an exhaust duct (19) of the second\0.8body (22).

Abstract: Disclosed is a method for controlling the flammability of fuel vapors in an aircraft main fuel tank that is located in whole or in part in the fuselage contour. The method comprises a fuel system architecture and fuel consumption sequencing maintaining liquid fuel in said main tanks during all normal operations. Ceasing the withdrawal of fuel from the main tank when the fuel reaches a predetermined level thereby limiting the volume and flammability exposure time of the fuel vapor ullage. Once the predetermined level is met the fuel is supplied from wing tanks throughout the remainder of the mission. The predetermined main tank fuel level at which wing tank fuel begins to be consumed is determined by the aircraft flight reserves fuel volume stored in the main tank as well as the amount necessary to continuously submerge the main tank fuel pumps during the entire mission.

Abstract: In one embodiment of the disclosure, an apparatus is provided for fueling a device using a cryogenic fluid. The apparatus may comprise: a cryogenic fluid supply container; a vessel connected to the supply container with an entrance valve to regulate flow of cryogenic fluid from the supply container; a heat transfer system capable of transferring heat from a device to the vessel to heat gas in the vessel; and an accumulator connected to the vessel with an exit valve to regulate flow of gas from the vessel to the accumulator. The accumulator may be capable of being connected to a device. In other embodiments, methods are provided of controllably mixing at least one fluid within a fluid mixing device.

Abstract: A heat exchanger includes a housing disposed in a first atmosphere and having an upstream end, a downstream end and a chamber within the housing; a metallic block disposed in the chamber and having a passageway therethrough and through which a cryogen can flow; and a heat pipe assembly in contact with the metallic block and extending to a second atmosphere which is separate from the first atmosphere for providing heat transfer at the second atmosphere.

Abstract: In one embodiment of the disclosure, an apparatus is provided for fueling a device using a cryogenic fluid. The apparatus may comprise: a cryogenic fluid supply container; a vessel connected to the supply container with an entrance valve to regulate flow of cryogenic fluid from the supply container; a heat transfer system capable of transferring heat from a device to the vessel to heat gas in the vessel; and an accumulator connected to the vessel with an exit valve to regulate flow of gas from the vessel to the accumulator. The accumulator may be capable of being connected to a device. In other embodiments, methods are provided of controllably mixing at least one fluid within a fluid mixing device.

Abstract: Provided is a nonflammable mixed refrigerant for use in a reliquefaction apparatus of a fuel supply system that compresses BOG generated in an LNG storage tank to a medium pressure, reliquefies the compressed BOG, compresses the reliquefied BOG to a high pressure, gasifies the compressed requefied BOG, and supplies the gasified BOG to a high-pressure natural gas injection engine. A nonflammable mixed refrigerant for use in a fuel supply system for a high-pressure natural gas injection engine is provided. The nonflammable mixed refrigerant cools the BOG by heat exchange with the BOG in the reliquefaction apparatus. The nonflammable mixed refrigerant comprises a mixture of nonflammable refrigerants with different boiling points, and the boiling point of each of the nonflammable refrigerant ranges between a room temperature and a liquefaction temperature of natural gas.

Abstract: An aircraft adaptive power thermal management system for cooling one or more aircraft components includes an air cycle system, a vapor cycle system, and a fuel recirculation loop operably disposed therebetween. An air cycle system heat exchanger is between the air cycle system and the fuel recirculation loop, a vapor cycle system heat exchanger is between the vapor cycle system and the fuel recirculation loop, and one or more aircraft fuel tanks are in the fuel recirculation loop. An intercooler including a duct heat exchanger in an aircraft gas turbine engine FLADE duct may be in the air cycle system. The system is operable for providing on-demand cooling for one or more of the aircraft components by increasing heat sink capacity of the fuel tanks.

Abstract: A reversible aerospace plane includes an air intake at a first end of the aerospace plane, at least one heat exchanger disposed in the aerospace plane, and an engine at a second end of the aerospace plane, wherein the aerospace plane is configured to accelerate in a first direction and configured to glide and land in a second direction, wherein the second direction is substantially in a reverse direction from the first direction.

Abstract: The present invention relates to a refrigeration vehicle comprising at least one refrigeration space, which can be cooled via at least one supplemental heat exchanger. The supplemental heat exchanger in the refrigeration space is connected to other components, preferably via couplings and flexible lines, establishing a heat exchange loop being able to exchange heat with an evaporator for low-temperature liquefied combustible gas. Moreover the Refrigeration vehicle comprises at least one first vehicle part and one second vehicle part being dividable and wherein the first vehicle part comprises an internal combustion engine and the evaporator for the low-temperature liquefied combustible gas.

Abstract: A controller, for use in a power plant having a liquid cooling system and an air cooling system, comprising one or more inputs, configured to receive a signal from at least one deposit sensor, wherein the signal from the deposit sensor is indicative of deposits in the liquid cooling system; and one or more processors, configured to process the signal received from the deposit sensor to control the air cooling system.

Abstract: An avionics cooling system including an avionics cooling circuit operating with a liquid coolant; a fuel circuit; and a vapor cooling cycle operating with a refrigerant. The avionics cooling circuit transfers heat withdrawn from avionics to the fuel circuit, whereby the heat is dumped into fuel, and the vapor cooling cycle transfers heat that cannot be dumped into the fuel from the fuel circuit to ram air.

Abstract: An aircraft cooling system includes a refrigerant cycle including a first heat exchanger, a second heat exchanger, and a compressor. A component of the aircraft is in thermal communication with the first heat exchanger. A heat sink fluid passes through the second heat exchanger to absorb heat from the refrigerant cycle. A hydraulic motor is mechanically connected with the compressor and powered by the heat sink fluid, which is circulated by a pump.

Abstract: The disclosure provides for a chemical reaction-based thermal management system and method. The system comprises a heat source for heating a first flow element, a heat exchanger for transferring heat from the first flow element to a reaction mixture flow, and a heat sink comprising one or more endothermic chemical reactions to absorb heat from the heat exchanger. The system further comprises a reactor element for approaching chemical equilibrium of the reaction mixture flow, a product removal element for removing one or more products from the one or more endothermic chemical reactions, and a plurality of driver elements for moving the first flow element and for moving the reaction mixture flow.

Abstract: Embodiments of the disclosed technology comprise a combination refrigeration and combustion system including a tank that holds liquefied gas, an expansion valve in fluid connection with the tank, and a sealable chamber housing an evaporator, with the evaporator in fluid connection with the expansion valve. The system is configured for expulsion of the liquefied gas from the tank into the expansion valve. The expulsion takes place in at least one pulse over part of a defined time interval. After an expulsion of gas, the liquefied gas expands into gaseous form in the evaporator, allowing for continuous combustion of the gas in gaseous form.

Abstract: A fuel tank safety system includes an ullage cooling assembly and a system controller. The ullage cooling assembly includes a compressor configured to extract a quantity of ullage gas from the fuel tank, a heat exchanger coupled in flow communication downstream of the compressor, wherein the heat exchanger is configured to receive the quantity of ullage gas from the compressor and reduce a temperature of the ullage gas. The ullage cooling assembly includes a turbine coupled in flow communication downstream of the heat exchanger, wherein the turbine is configured to further reduce the temperature of the ullage gas and facilitate channeling the ullage gas to the fuel tank. The system controller is operatively coupled to the ullage cooling assembly and is configured to transmit to the ullage cooling assembly one of a start signal to activate the ullage cooling assembly or a stop signal to deactivate the ullage cooling assembly.

Abstract: A fuel gas supply system of a vessel, such as an LNG carrier, is provided for supplying fuel gas to a high-pressure gas injection engine of an LNG carrier, wherein LNG is extracted from an LNG storage tank of the LNG carrier, compressed at a high pressure, gasified, and then supplied to the high-pressure gas injection engine. In one embodiment, the system includes a boil-off gas reliquefaction apparatus for reliquefying boil-off gas generated in the LNG tank.

Abstract: A fuel gas supply system of a vessel, such as an LNG carrier, is provided for supplying fuel gas to a high-pressure gas injection engine of an LNG carrier, wherein LNG is extracted from an LNG storage tank of the LNG carrier, compressed at a high pressure, gasified, and then supplied to the high-pressure gas injection engine. In one embodiment, the system is operated to supply fuel to an MEGI engine.

Abstract: A system for producing, dispensing, using and monitoring a hydrogen enriched fuel includes a producing system configured to produce the hydrogen enriched fuel, a vehicle having an engine configured to use the hydrogen enriched fuel, and a dispensing system configured to store and dispense the hydrogen enriched fuel into the vehicle. The system also includes a fuel delivery system on the vehicle configured to deliver the hydrogen enriched fuel to the engine, and a control system configured to control the producing system and to monitor the use of the hydrogen enriched fuel by the vehicle. A method includes the steps of producing hydrogen gas and a hydrocarbon fuel, blending the hydrogen gas and the hydrocarbon fuel into the hydrogen enriched fuel, using the hydrogen enriched fuel in the engine, and tracking emissions during the producing step and during the using step.

Abstract: A fuel gas supply system of a ship is provided for supplying fuel gas to a high-pressure gas injection engine of the ship, wherein the ship has an LNG fuel tank for storing LNG as fuel and LNG is extracted from an LNG fuel tank of the ship, compressed at a high pressure, gasified, and then supplied to the high-pressure gas injection engine.

Abstract: In one embodiment, a combined cooling and heating system comprises a hydrogen reservoir. The combined cooling and heating system may be used in an aircraft. During a charging of the hydrogen reservoir, with hydrogen, a kitchen appliance is heated, and during the discharging process, the hydrogen reservoir cools the fuel cell system.