Disclosed is a fuel cell having a Membrane Electrode Assembly (MEA) sandwiched between a pair of bipolar plates (BPPs). The BPPs are formed at least in part of a structural base layer and having one or more thermal performance layers (TPLs) in thermal contact with the structural base layer. The TPL is formed of a material having a thermal conductivity greater than that of the structural base layer.
H01M 8/026 - CollectorsSeparators, e.g. bipolar separatorsInterconnectors characterised by the configuration of channels, e.g. by the flow field of the reactant or coolant characterised by grooves, e.g. their pitch or depth
H01M 8/04 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
H01M 4/86 - Inert electrodes with catalytic activity, e.g. for fuel cells
Methods and systems for optimizing hydrogen fuel production facilities include processing user input data and sensor data from hardware sensors of a hydrogen fuel production facility with a computerized device to model at least one microgrid hydrogen-generating plant. A three-stage convex optimization model is operated on the computerized device to determine at least one implementation parameter of the microgrid hydrogen-generating plant. At least one hardware component of the microgrid hydrogen-generating plant is modeled. The hardware components include at least an electrolyzer. A model predictive control (MPC) controller is used to determine an optimal power flow schedule for a selected control scenario and schedule module, thereby optimizing the generated sensor data and the user input data over a time series window.
G05B 13/04 - Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric involving the use of models or simulators
3.
Air-cooled fuel cell stacks integrated into aircraft wings
A fuel-cell-powered aircraft system has integrated air-cooled fuel cell stacks positioned within an interior space of at least one wing of an aircraft. An airflow path is positioned in contact with at least a heat exchanger of the fuel cell stack. The induced flow of air through the airflow path cools the heat exchanger. The efficiently-induced flow of air for cooling the fuel cell stack has a zero or minimal drag penalty.
A system for monitoring a voltage condition of a fuel cell (FC) stack includes at least two FCs operating together in series. At least one light-emitting diode (LED) is in electrical communication with the at least two FCs. At least one sensor is in visual communication with the at least one LED to receive a visual emission from the at least one LED. At least one processor is in communication with the at least one sensor. The at least one processor has a computer-readable memory and a power supply. A brightness of the at least one LED is determined by a voltage condition of the at least two FCs.
Disclosed is an air-cooled fuel cell (FC) stack including a plurality of FCs arranged in a stack in a curved pattern. The plurality of FC stacks are arranged spaced from one another in a curved pattern, preferably a spiral pattern, more preferably an involute pattern. Also disclosed is an integrated FC electric engine for a vehicle such as an aircraft including a centrifugal compressor and a turbine rotatably mounted on a shaft, and one or more curved FC stacks arranged to an outside of the rotatably mounted centrifugal compressor and the rotatably mounted turbine.
A DC-DC converter-free hybrid fuel cell (PC)-energy storage (ES) system (FC-ES) is used for powering an electric device, wherein the PC and ES are electrically connected and configured so that the PC and ES intrinsically absorb and control system transients through state-of-charge cross-overs. The electric device preferably is a vehicle, and in particular a hydrogen fuel-cell-powered aircraft.
H01M 16/00 - Structural combinations of different types of electrochemical generators
B60L 1/00 - Supplying electric power to auxiliary equipment of electrically-propelled vehicles
B60L 50/70 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by fuel cells
H01M 10/0525 - Rocking-chair batteries, i.e. batteries with lithium insertion or intercalation in both electrodesLithium-ion batteries
A method and system of detecting mass air flow (MAF) sensor failure on an aircraft includes at least one signal from a non-MAF sensor received by a controller of a fuel cell system having at least one MAF sensor. The signal received by the controller is analyzed relative to a compressor map to estimate mass air flow. A MAF sensor failure is detected based on the estimated mass air flow. When a MAF sensor failure is detected, a safe operating mode of the fuel cell system may be activated to provide adequate power for operation of the aircraft to a safe landing while minimizing risk of damage to the fuel cell system.
Bipolar plates having two short sides, and two long sides for air-cooled fuel cells. The bipolar plate comprises an anode plate, a cathode plate, and an anode gas inlet an anode gas outlet. The anode plate and the cathode plate are connected to each other so that gaseous heat carrier distribution channels are formed therebetween such that, when a gaseous heat carrier is supplied, a time period through a hal of the bipolar plate near to the edge of the first long side is less than a time period through a half of the bipolar plate near to the edge of the second long side. The technical effect of the proposed invention is a reduced consumption of cooling air, reduced power consumption, dimensions and weight of a fuel cell cooling system, improved uniformity of bipolar plate cooling, which results in increased capacity and a longer service life of a fuel cell.
H01M 8/0258 - CollectorsSeparators, e.g. bipolar separatorsInterconnectors characterised by the configuration of channels, e.g. by the flow field of the reactant or coolant
H01M 8/04014 - Heat exchange using gaseous fluidsHeat exchange by combustion of reactants
An electrically-powered turbine assembly includes a fixed housing; an air compressor including a compressor stator fixed to the housing; a turbine including a turbine stator fixed to the housing; a central shaft supported by the compressor stator and affixed to the turbine stator; an electric motor including an electric motor stator fixed to the central shaft, said electric motor having a rotating shell; an air compressor rotor affixed to the rotating electric motor shell; and a turbine rotor affixed to the rotating electric motor shell. The electrically-powered turbine assembly preferably includes one or more fuel cells as an electric power source. The electrically-powered turbine assembly may be used to power an aircraft.
G01R 33/54 - Signal processing systems, e.g. using pulse sequences
A61B 5/00 - Measuring for diagnostic purposes Identification of persons
G01R 33/561 - Image enhancement or correction, e.g. subtraction or averaging techniques by reduction of the scanning time, i.e. fast acquiring systems, e.g. using echo-planar pulse sequences
10.
AERODYNAMIC HYDROGEN TANKS, AND CRYOGENIC INSULATED PIPES
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.
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 9/02 - Layered products essentially comprising a particular substance not covered by groups comprising animal or vegetable substances
B32B 29/00 - Layered products essentially comprising paper or cardboard
B32B 5/20 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by features of a layer containing foamed or specifically porous material foamed in situ
11.
AIR-COOLED FUEL CELL SYSTEM AND METHOD FOR OPERATING SAME
The invention relates to air-cooled fuel cell systems, in particular to mid-and high temperature fuel cells with operating temperatures ranging from 100 to 1.000° C. and to methods for operating an air-cooled fuel cell system. The air-cooled fuel cell system comprising at least one fuel cell stack (1) with a gaseous heat carrier distribution system (2), an anode gas distribution system (3) and a cathode gas distribution system (4); a burner (14); an expander (9; 24); a motor; a compressor (8; 23); a gaseous heat carrier recirculation system (5) connected to the gaseous heat carrier distribution system (2) and intended for mixing a gas stream delivered to the gaseous heat carrier distribution system and providing additional pressure thereto, and means for separating gas streams and controlling their flowrate. The technical effect improves reliability and operating efficiency of a fuel cell in any climatic conditions and in a broad range of aviation altitudes.
H01M 8/04014 - Heat exchange using gaseous fluidsHeat exchange by combustion of reactants
H01M 8/04007 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
H01M 8/04119 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyteHumidifying or dehumidifying
H01M 8/0612 - Combination of fuel cells with means for production of reactants or for treatment of residues with means for production of gaseous reactants from carbon-containing material
H01M 8/0662 - Treatment of gaseous reactants or gaseous residues, e.g. cleaning
Ram air cooling demands of a fuel-cell-powered aircraft are reduced by conducting exothermic heat generated by the fuel cells to a leading edge and/or trailing edge of the aircraft wings. The beat also may be used to deice the wings.
An electrically-powered turbine assembly includes a fixed housing; an air compressor including a compressor stator fixed to the housing; a turbine including a turbine stator fixed to the housing; a central shaft supported by the compressor stator and affixed to the turbine stator; an electric motor including an electric motor stator fixed to the central shaft, said electric motor having a rotating shell; an air compressor rotor affixed to the rotating electric motor shell; and a turbine rotor affixed to the rotating electric motor shell. The electrically-powered turbine assembly preferably includes one or more fuel cells as an electric power source. The electrically-powered turbine assembly may be used to power an aircraft.
B64D 27/355 - Arrangements for on-board electric energy production, distribution, recovery or storage using fuel cells
F04D 25/06 - Units comprising pumps and their driving means the pump being electrically driven
F04D 29/58 - CoolingHeatingDiminishing heat transfer
H01M 8/04014 - Heat exchange using gaseous fluidsHeat exchange by combustion of reactants
H01M 8/04082 - Arrangements for control of reactant parameters, e.g. pressure or concentration
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
H01M 8/2484 - Details of groupings of fuel cells characterised by external manifolds
H02K 1/20 - Stationary parts of the magnetic circuit with channels or ducts for flow of cooling medium
H02K 9/06 - Arrangements for cooling or ventilating by ambient air flowing through the machine having means for generating a flow of cooling medium with fans or impellers driven by the machine shaft
H02K 11/33 - Drive circuits, e.g. power electronics
A lighter-than-air craft includes an envelope defining an interior region. A lifting gas at least partially including hydrogen is located within the interior region. The lifting gas provides buoyancy for the lighter-than-air craft. A hydrogen fuel cell is fluidically coupled with the interior region. An inerting gas is located within the envelope, and the inerting gas at least partially includes exhaust from the hydrogen fuel cell. The inerting gas and the lifting gas have respective volumes such that a mixture thereof is nonflammable during operating conditions for the lighter-than-air craft. The hydrogen fuel cell is able to utilize the hydrogen of the lifting gas to generate electricity. A propulsion system is coupled to the envelope and is able to provide propulsion for the lighter-than-air craft.
B64D 37/32 - Safety measures not otherwise provided for, e.g. preventing explosive conditions
A62C 3/06 - Fire prevention, containment or extinguishing specially adapted for particular objects or places of highly inflammable material, e.g. light metals, petroleum products
A62C 3/08 - Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles in aircraft
2 from an external supply tank. The system includes a target patch or a cell of a temperature-dependent reflectivity material on an exterior of the vehicle fuel tank, and a sensor package including an electromagnetic (EM) radiation emitter and a radiation detection system positioned remote from the vehicle tank being filled. The sensor package is located on or adjacent an external refueling device with a line of sight to the target patch or cell.
F17C 5/06 - Methods or apparatus for filling pressure vessels with liquefied, solidified, or compressed gases for filling with compressed gases
F17C 5/00 - Methods or apparatus for filling pressure vessels with liquefied, solidified, or compressed gases
G01K 11/125 - Measuring temperature based on physical or chemical changes not covered by group , , , or using changes in colour, translucency or reflectance using changes in reflectance
16.
HYDROGEN TANK PRESSURE FLOW MONITORING, AND THERMAL PUMPING OF LIQUID HYDROGEN
B60L 58/30 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling fuel cells
A fuel cell system having at least one fuel cell with an external surface; and one or more of audio, image, or strain sensors external to the fuel cell surface, configured for detecting a change in the external surface of the fuel cell indicative of a fault condition. The at last one sensor may include a visual camera, an IR camera, an IR detector, or a UV-responsive camera, or an ultrasound transducer, a piezoelectric sensor and a vibration sensor, or a surface acoustic wave detector, or a mass spectrometer.
Disclosed is a cryogenic storage tank including an inner wall (50) and an outer wall (52) defining a space (56), wherein the space is filled at least in part with dried-in-place hollow glass microspheres which provides both insulating and structural properties to maintain the space, and methods for forming the cryogenic storage tank. Also disclosed is a cryogenic storage tank including an inner wall and an outer wall defining a space, wherein the inner wall and outer wall are spaced from one another by magnetic repulsion. In one embodiment the inner wall includes a high temperature superconducting material embedded in or on a surface of the inner wall, and the outer wall has a conventional magnet embedded in or on a surface of the outer wall.
A High Temperature Proton Exchange Membrane (HT-PEM) fuel cell includes a Proton Exchange Membrane (PEM); an anode catalyst layer on one surface of the PEM, and a cathode catalyst layer on the opposite surface of the PEM; Gas Diffusion Layers (GDLs) on outside surfaces of the anode and the cathode layers; and Bipolar Plates (BPPs) on outside surfaces of the GDLs. One or more contacting surfaces of the Membrane Exchange Assembly (MEA) subcomponents are coated, at least in part, with an electrically conductive polymer composite material that softens at or below the operating temperature of the HT-PEM. Also disclosed is a fuel cell bipolar plate (BPP) that includes a plurality of gaseous media coolant flow channels which have deflection barriers configured to cause the gaseous media coolant to divide and flow horizontally around a deflection barrier in a direction of an adjacent gaseous media coolant flow channel.
H01M 8/0228 - Composites in the form of layered or coated products
H01M 8/026 - CollectorsSeparators, e.g. bipolar separatorsInterconnectors characterised by the configuration of channels, e.g. by the flow field of the reactant or coolant characterised by grooves, e.g. their pitch or depth
H01M 8/0267 - CollectorsSeparators, e.g. bipolar separatorsInterconnectors having heating or cooling means, e.g. heaters or coolant flow channels
A fuel-cell-powered vehicle includes an electrically-powered turbine assembly having a housing, a rotating shaft, an air compressor comprising a compressor stator fixed to the housing and a compressor rotor fixed to the rotating shaft, an electric motor including an electric motor stator fixed to the compressor stator and an electric motor rotor fixed to the rotating shaft, a turbine including a turbine stator affixed to the housing, a turbine rotor fixed to the rotating shaft, and two or more fuel cells arranged around an outside of the electrically-powered turbine assembly.
F04D 25/06 - Units comprising pumps and their driving means the pump being electrically driven
F04D 29/58 - CoolingHeatingDiminishing heat transfer
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
21.
FUEL CELL WITH INTEGRATED BALANCE OF PLANT COMPONENTS
A fuel cell system includes a plurality of fuel cell stacks mechanically and electrically assembled to one another to provide a desired power and output voltage, and including a humidifier directly mated to inlet and outlet ports the individual fuel cell stacks.
H01M 8/04119 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyteHumidifying or dehumidifying
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
H01M 8/2483 - Details of groupings of fuel cells characterised by internal manifolds
H01M 8/249 - Grouping of fuel cells, e.g. stacking of fuel cells comprising two or more groupings of fuel cells, e.g. modular assemblies
22.
AIR-COOLED PROTON-EXCHANGE MEMBRANE FUEL CELL CAPABLE OF WORKING WITH COMPRESSED GASES, AND FUEL CELLS STACK
The present disclosure relates to fuel cells, in particular to high-temperature air-cooled fuel cells. A fuel cell 1 comprises a bipolar plate 2 and a membrane-electrode assembly 3. The bipolar plate 2 comprises an anode plate 5, a cathode plate 6 and a layer 7 of air cooling channels between the anode plate 5 and the cathode plate 6. Channels for an oxygen-containing gas are made in the cathode plate 6. Channels 10 for hydrogen are made in the anode plate 5, which are covered by the membrane-electrode assembly 3 contacting the anode plate 5. A fuel cell stack comprises at least two fuel cells, wherein the membrane-electrode assembly of one fuel cell contacts the anode plate of said one fuel cell, thus covering the channels for hydrogen, and contacts the cathode plate of said another fuel cell, which adjoins said one fuel cell, thus covering the channels for an oxygen-containing gas. The technical effect consists in reducing weight-dimension characteristics of the fuel cell and the fuel cell stack, while simultaneously reducing power consumption required for cooling, and increasing specific capacity per unit weight and power efficiency.
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 jettisoned from the aircraft.
Disclosed is a system for humidifying cabin and/or cockpit air of a fuel cell-powered aircraft system. The system includes a fuel cell stack configured for reacting hydrogen and oxygen to produce electrical energy and a cathode exhaust containing moist, warm air; a water separator configured to cool the moist, warm air and to condense and separate liquid water from the moist, warm air; and a humidifier configured to employ the separated liquid water to humidify pressurized cabin air.
H01M 8/04119 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyteHumidifying or dehumidifying
F04F 1/18 - Pumps using positively or negatively pressurised fluid medium acting directly on the liquid to be pumped the fluid medium being mixed with, or generated from, the liquid to be pumped
A fuel tank heat dissipation system for fuel cell (FC) cooling is disclosed. In one example, at least one FC is in thermal communication with an intermediary heat exchanger. A fuel tank is also in fluid communication with the intermediary heat exchanger. A fluid is used to receive heat from the intermediary heat exchanger and flow along a first fluid path to the fuel tank. A nozzle is used to spray the fluid about an interior surface of the fuel tank, where the spray of the fluid about the interior of the fuel tank allows the fluid to dissipate the heat. A second fluid path from the fuel tank to the intermediary heat exchanger, the second fluid path to return the fluid that has dissipated the heat to the intermediary heat exchanger.
A hydrogen boiloff capture system. The hydrogen boiloff capture system having a cryogenic tank for storing liquid hydrogen. The hydrogen boiloff capture system also includes an intermediate tank fluidically coupled with the cryogenic tank. The intermediate tank is configured to receive hydrogen gas boiloff from the cryogenic tank. The intermediate tank is further configured to provide the hydrogen gas boiloff to a lighter-than-air craft to regulate buoyancy of the lighter-than-air craft. The intermediate tank is also configured to provide the hydrogen gas boiloff to a hydrogen fuel cell coupled to the lighter-than-air craft.
An integrated hydrogen-electric includes a hydrogen fuel cell; a hydrogen fuel source; an electric motor assembly disposed in electrical communication with the fuel cell; n air compressor system configured to be driven by the motor assembly, and a cooling system having a heat exchanger radiator in a duct of the cooling system, and configured to direct an air stream including an air stream from the air compressor through the radiator, wherein an exhaust stream from a cathode side of the fuel cell is fed via an flow control nozzle into the air stream in the cooling duct downstream of the radiator.
B60L 58/33 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling fuel cells for controlling the temperature of fuel cells, e.g. by controlling the electric load by cooling
B60L 50/70 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by fuel cells
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
A fuel cell system having at least one fuel cell having an external surface; and one or more of audio, image, or strain sensors external to the fuel cell surface, configured for detecting a change in the external surface of the fuel cell indicative of a fault condition. The at last one sensor may include a visual camera, an IR camera, an IR detector, or a UV-responsive camera, or an ultrasound transducer, a piezoelectric sensor and a vibration sensor, or a surface acoustic wave detector, or a mass spectrometer.
An integrated fuel cell power delivery system includes a first power source configured to supply power to a propulsion inverter, a second power source configured to supply power to the propulsion inverter, a disconnect operably connected to the second power source, a bypass diode operably connected to the first power source and the second power source, a sensor that detects an output voltage of the integrated fuel cell power system, a processor, and a memory. The memory includes instructions stored thereon, which when executed by the processor, cause the integrated fuel cell power system to access a signal from the sensor, determine if the accessed first signal is greater than a first threshold voltage, and operably disconnect an output of the second power source to the integrated fuel cell power system by the disconnect based on the determination.
A propulsion system for a lighter-than-air craft including a motor outputting a driving force including one or more rotors. This propulsion system is a free-pivoting, swashplate-controlled system interconnecting the motor and the one or more rotors for lighter-than-air aircraft.
A lighter-than-air craft including an envelope. A mixture of helium and hydrogen disposed within the envelope. The mixture having a ratio of helium to hydrogen such that the mixture is nonflammable during operating conditions for the lighter-than-air craft. The mixture provides buoyancy for the lighter-than-air craft. A hydrogen fuel cell fluidically coupled with the mixture and configured to utilize the mixture to generate electricity. A propulsion system is coupled to the envelope, and the propulsion system is configured to provide propulsion for the lighter-than-air craft. The propulsion system is electrically coupled with the hydrogen fuel cell and receives electricity generated by the hydrogen fuel cell. The propulsion system is configured to utilize the electricity in providing the propulsion to the lighter-than-air craft.
A lighter-than-air craft including an envelope. A mixture of helium and hydrogen disposed within the envelope. The mixture having a ratio of helium to hydrogen such that the mixture is nonflammable during operating conditions for the lighter-than-air craft. The mixture provides buoyancy for the lighter-than-air craft. A hydrogen fuel cell fluidically coupled with the mixture and configured to utilize the mixture to generate electricity. A propulsion system is coupled to the envelope, and the propulsion system is configured to provide propulsion for the lighter-than-air craft. The propulsion system is electrically coupled with the hydrogen fuel cell and receives electricity generated by the hydrogen fuel cell. The propulsion system is configured to utilize the electricity in providing the propulsion to the lighter-than-air craft.
A hydrogen boiloff capture system. The hydrogen boiloff capture system having a cryogenic tank for storing liquid hydrogen. The hydrogen boiloff capture system also includes an intermediate tank fluidically coupled with the cryogenic tank. The intermediate tank is configured to receive hydrogen gas boiloff from the cryogenic tank. The intermediate tank is further configured to provide the hydrogen gas boiloff to a lighter-than-air craft to regulate buoyancy of the lighter-than-air craft. The intermediate tank is also configured to provide the hydrogen gas boiloff to a hydrogen fuel cell coupled to the lighter-than-air craft.
B64D 37/04 - Arrangement thereof in or on aircraft
B60L 58/30 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling fuel cells
In one or more embodiments of the novel aircraft fuel cell system without the use of a buffer battery, the fuel cell and compressor would be sized sufficiently larger for the intended application, allowing the compressor to change speeds much faster. This in turn would allow power outputs to change much quicker. If power outputs can change as quickly as the application dictates, then a buffer battery is not necessary. In one or more embodiments, because the system is mostly electronically controlled, software can be written to protect the fuel cell from instantaneous power spikes. If a large power output is suddenly requested of the fuel cell, the software can smooth out the demand curve to provide an easier load profile to follow.
B64D 41/00 - Power installations for auxiliary purposes
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
Electric power generation system based on pressurized fuel cell power system with air cooling and recirculation and method for electric power generation by the system
An air pressure in fuel cells of an electric power generation system comprising a fuel cell stack (PCS) is raised with a pressurized air cooling system with recirculation to values at least two times greater than typical values for an PCS with air cooling. The FCS is either placed in a high-pressure chamber to which air is injected, or air outgoing from the FCS is redirected via a duct back to the FCS inlet and a portion of pressurized fresh air is added thereto. The chamber or the duct is provided with a radiator by means of which circulating air heat is transferred into the external environment. Air recirculation in the chamber or the duct is effected by means of fans for cooling fuel cells. Useful capacity of electric power generation systems based on fuel cells is raised significantly, the necessity of using a humidifier is excluded, and the temperature range of fuel cell operation is expanded.
H01M 8/04014 - Heat exchange using gaseous fluidsHeat exchange by combustion of reactants
H01M 8/04007 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
An aircraft power plant for a fuel cell including a turbo assembly, a compressor assembly, a turbo assembly, a compressor assembly controller, a first stage turbo assembly and compressor assembly operation configured to generate a first stage compressed fluid generated from ambient air and excess oxygen exhausted from a fuel cell of an aircraft power plant. A second stage turbo assembly and compressor assembly operation configured to receive the first stage compressed fluid, and a controller bleed valve coupled with the first stage turbo assembly and compressor assembly and the second stage turbo assembly and compressor assembly. An oxygen supply system, the oxygen supply system fluidically coupled with the first stage turbo assembly and compressor assembly wherein a first compressed oxygen is generated by the first stage turbo assembly is combined with a second compressed oxygen generated by the second stage turbo assembly to generate a combined oxygen controlled by the controller bleed valve. A third stage turbo assembly and compressor assembly operation configured to receive the combined oxygen, and a hydrogen supply system configured to provide hydrogen fluidically coupled with the third stage turbo assembly and compressor assembly.
H01M 8/04 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
F02C 1/02 - Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being an unheated pressurised gas
H01M 8/04082 - Arrangements for control of reactant parameters, e.g. pressure or concentration
F02C 6/18 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
B64D 31/00 - Power plant control systemsArrangement of power plant control systems in aircraft
B64D 41/00 - Power installations for auxiliary purposes
A cooling system and cooling method for a fuel cell onboard a vehicle, wherein the fuel cell includes a gasifier configured to expand liquid hydrogen to gaseous hydrogen for feed to the fuel cell, the cooling system including a coolant system sized for less than peak power operation of the vehicle; and an auxiliary coolant system configured to provide supplemental cooling to the fuel cell, wherein the supplemental coolant system is configured to by-pass coolant to the gasifier and employ heat of gasification of the liquid hydrogen to provide supplemental cooling for the fuel cell during peak vehicle operation.
An air compression system for a fuel cell system, the air compression system has a main air compressor with a maximum air flow output approximately equal to a continuous mode air flow requirement of the fuel cell system. The main air compressor weighs less than an air compressor having a maximum air flow output approximately equal to a peak air flow requirement of the fuel cell system such that the weight of the air compression system is reduced compared to a conventional air compression system. The air compression system also includes a supplemental oxygen supply system which is fluidically coupled with the fuel cell system.
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
H01M 8/04082 - Arrangements for control of reactant parameters, e.g. pressure or concentration
40.
Fuel tank heat dissipation system for fuel cell cooling
A fuel tank heat dissipation system for fuel cell (FC) cooling is disclosed. In one example, at least one FC is in thermal communication with an intermediary heat exchanger. A fuel tank is also in fluid communication with the intermediary heat exchanger. A fluid is used to receive heat from the intermediary heat exchanger and flow along a first fluid path to the fuel tank. A nozzle is used to spray the fluid about an interior surface of the fuel tank, where the spray of the fluid about the interior of the fuel tank allows the fluid to dissipate the heat. A second fluid path from the fuel tank to the intermediary heat exchanger, the second fluid path to return the fluid that has dissipated the heat to the intermediary heat exchanger.
14 - Precious metals and their alloys; jewelry; time-keeping instruments
25 - Clothing; footwear; headgear
Goods & Services
Precious metals and their alloys and goods in precious
metals or coated therewith, including but not limited to
keychains and metal pins. Headgear and clothing.
09 - Scientific and electric apparatus and instruments
Goods & Services
hydrogen fuel cells for generating electricity, hydrogen fuel cells for generating electricity in a hydrogen fuel cell powered aircraft, hydrogen fuel cells for generating electricity for an electrical engine; hydrogen fuel cells for generating electricity in an electric vehicle
aircraft engine components for use in an aircraft, namely, a hydrogen-based powertrain comprising housing for inverters, gate board for inverters, EMI board for inverters, and manifold for inverters, a power distribution system being distributors for vehicles other than for land vehicles, a gearbox other than for land vehicles, heat exchangers being parts of engines not for land vehicles, propellers, and other components in an aircraft
04 - Industrial oils and greases; lubricants; fuels
Goods & Services
fuels, fuels used in a hydrogen fuel cell, fuels used in a hydrogen fuel cell powered aircraft, fuels to generate electrical energy in a hydrogen fuel cell, fuels to generate electrical energy in a hydrogen fuel cell powered aircraft
14 - Precious metals and their alloys; jewelry; time-keeping instruments
25 - Clothing; footwear; headgear
Goods & Services
Precious metals and their alloys and goods in precious
metals or coated therewith, including but not limited to
keychains and metal pins. Headgear and clothing.
46.
LEVERAGING A TURBOEXPANDER TO PROVIDE ADDITIONAL FUNCTIONALITY IN COMPRESSED GAS FUELED SYSTEMS
Leveraging a turboexpander to provide additional functionality in compressed gas fueled systems is disclosed. The system includes a compressed gas storage device storing a compressed gas at a first pressure. A turboexpander operably coupled with the compressed gas storage device, the turboexpander comprising a turbine coupled with a drive shaft, the turboexpander to maintain the compressed gas below a threshold temperature limit as it controllably expands the compressed gas from the first pressure to the second pressure via an amount of work obtained from a rotation of the turbine and the drive shaft. A compressed gas receiving device to receive the compressed gas at the second pressure from the turboexpander and generate an amount of electrical energy from the compressed gas.
F01K 25/10 - Plants or engines characterised by use of special working fluids, not otherwise provided forPlants operating in closed cycles and not otherwise provided for using special vapours the vapours being cold, e.g. ammonia, carbon dioxide, ether
F01D 15/02 - Adaptations for driving vehicles, e.g. locomotives
F01D 15/10 - Adaptations for driving, or combinations with, electric generators
F01K 7/16 - Steam engine plants characterised by the use of specific types of enginePlants or engines characterised by their use of special steam systems, cycles or processesControl means specially adapted for such systems, cycles or processesUse of withdrawn or exhaust steam for feed-water heating the engines being only of turbine type
47.
Cooling architecture for hydrogen fuel cell-powered aircraft
A cooling architecture for an integrated hydrogen-electric engine having a radiator and a hydrogen fuel cell includes a t and a manifold. The turbine is disposed in fluid communication with the hydrogen fuel cell. The turbine is configured to compress a predetermined amount of air and direct a first portion of the predetermined amount of the compressed air to the fuel cell for generating electricity that powers the integrated hydrogen-electric engine. The manifold is disposed in fluid communication with the turbine and positioned to direct a second portion of the predetermined amount of compressed air to the radiator for removing heat from the radiator.
B60L 58/33 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling fuel cells for controlling the temperature of fuel cells, e.g. by controlling the electric load by cooling
B64D 27/02 - Aircraft characterised by the type or position of power plants
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 41/00 - Power installations for auxiliary purposes
G01K 13/00 - Thermometers specially adapted for specific purposes
H01M 8/04007 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
H01M 8/04014 - Heat exchange using gaseous fluidsHeat exchange by combustion of reactants
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
12 - Land, air and water vehicles; parts of land vehicles
14 - Precious metals and their alloys; jewelry; time-keeping instruments
25 - Clothing; footwear; headgear
Goods & Services
Aircraft parts, namely, power plants which are comprised of
an aircraft engine, an aircraft propeller and components
thereof. Hydrogen fuel cell electric vehicles; aircraft; aircraft
powered with a hydrogen propulsion electrochemical reactor;
aircraft, namely, electrically powered aircraft; hydrogen
fuel cell powered aircraft; structural parts for hydrogen
fuel cell powered aircraft; aircraft structural parts,
namely, hydrogen fuel storage cells for aircraft; aircraft
structural parts, namely, a hydrogen propulsion
electrochemical reactor for aircraft. Precious metals and their alloys and goods in precious
metals or coated therewith, including but not limited to
keychains and metal pins. Headgear and clothing.
12 - Land, air and water vehicles; parts of land vehicles
14 - Precious metals and their alloys; jewelry; time-keeping instruments
25 - Clothing; footwear; headgear
Goods & Services
Aircraft parts, namely, power plants which are comprised of
an aircraft engine, an aircraft propeller and components
thereof. Hydrogen fuel cell electric vehicles; aircraft; aircraft
powered with a hydrogen propulsion electrochemical reactor;
aircraft, namely, electrically powered aircraft; hydrogen
fuel cell powered aircraft; structural parts for hydrogen
fuel cell powered aircraft; aircraft structural parts,
namely, hydrogen fuel storage cells for aircraft; aircraft
structural parts, namely, a hydrogen propulsion
electrochemical reactor for aircraft. Precious metals and their alloys and goods in precious
metals or coated therewith, including but not limited to
keychains and metal pins. Headgear and clothing.
50.
COOLING ARCHITECTURE FOR HYDROGEN FUEL CELL-POWERED AIRCRAFT
A cooling architecture for an integrated hydrogen-electric engine having a radiator and a hydrogen fuel cell includes a turbine and a manifold. The turbine is disposed in fluid communication with the hydrogen fuel cell. The turbine is configured to compress a predetermined amount of air and direct a first portion of the predetermined amount of the compressed air to the fuel cell for generating electricity that powers the integrated hydrogen-electric engine. The manifold is disposed in fluid communication with the turbine and positioned to direct a second portion of the predetermined amount of compressed air to the radiator for removing heat from the radiator.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
51.
SYSTEMS AND METHODS FOR REGULATING VOLTAGE FOR HYDROGEN-ELECTRIC ENGINES
A hydrogen-electric engine includes a fuel cell stack including a plurality of fuel cells. Each fuel cell of the plurality of fuel cells includes an anode and a cathode. The hydrogen-electric engine also includes an air compressor system configured to supply compressed air to the cathode, a hydrogen fuel source configured to supply hydrogen gas, an elongated shaft supporting the air compressor system and the fuel cell stack, and a motor assembly disposed in electrical communication with the fuel cell stack. Each fuel cell generates a voltage, as an open cell voltage, by forming water with the supplied compressed air and the supplied hydrogen gas and is electrically coupled with a clamp circuit.
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
H01M 8/04082 - Arrangements for control of reactant parameters, e.g. pressure or concentration
H01M 8/1007 - Fuel cells with solid electrolytes with both reactants being gaseous or vaporised
H01M 8/2457 - Grouping of fuel cells, e.g. stacking of fuel cells with both reactants being gaseous or vaporised
52.
COOLING ARCHITECTURE FOR HYDROGEN FUEL CELL-POWERED AIRCRAFT
A cooling architecture for an integrated hydrogen-electric engine having a radiator and a hydrogen fuel cell includes a turbine and a manifold. The turbine is disposed in fluid communication with the hydrogen fuel cell. The turbine is configured to compress a predetermined amount of air and direct a first portion of the predetermined amount of the compressed air to the fuel cell for generating electricity that powers the integrated hydrogen-electric engine. The manifold is disposed in fluid communication with the turbine and positioned to direct a second portion of the predetermined amount of compressed air to the radiator for removing heat from the radiator.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
53.
SYSTEMS AND METHODS FOR REGULATING VOLTAGE FOR HYDROGEN-ELECTRIC ENGINES
A hydrogen-electric engine includes a fuel cell stack including a plurality of fuel cells. Each fuel cell of the plurality of fuel cells includes an anode and a cathode. The hydrogen-electric engine also includes an air compressor system configured to supply compressed air to the cathode, a hydrogen fuel source configured to supply hydrogen gas, an elongated shaft supporting the air compressor system and the fuel cell stack, and a motor assembly disposed in electrical communication with the fuel cell stack. Each fuel cell generates a voltage, as an open cell voltage, by forming water with the supplied compressed air and the supplied hydrogen gas and is electrically coupled with a clamp circuit.
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
H01M 8/04082 - Arrangements for control of reactant parameters, e.g. pressure or concentration
B60L 58/30 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling fuel cells
B60L 58/33 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling fuel cells for controlling the temperature of fuel cells, e.g. by controlling the electric load by cooling
H01M 8/04007 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
14 - Precious metals and their alloys; jewelry; time-keeping instruments
25 - Clothing; footwear; headgear
Goods & Services
(1) Precious metals and their alloys, goods of precious metals or coated therewith, namely, watches, jewellery and jewellery articles, jewellery cases and boxes, imitation and costume jewellery, cufflinks, badges, insignias, trophies, medals, coins, sculptures, statues, statuettes, figures, figurines, tie clips, tie clasps and pins, lapel pins, metal lapel pins, ornamental pins, ornaments of precious metal in the nature of jewelry, model figures ornaments of precious metal, keychains, keyrings, key fobs and key pins, parts and fittings for the aforesaid goods of precious metals or coated therewith.
(2) Headgear, namely caps, hats, bandanas, and head scarves; clothing, namely, T-shirts, sweaters, shirts, blouses, blazers, cardigans, jeans, pants, dresses, skirts, shorts, tank tops, hoodies, sweat shirts, sweat pants, athletic clothing, vests, socks, underwear, pajamas, under clothes, hosiery, jackets, outerwear, coats, scarves, skirts, sleepwear, socks, suits, tank tops, tights, and track suits.
14 - Precious metals and their alloys; jewelry; time-keeping instruments
25 - Clothing; footwear; headgear
Goods & Services
(1) Precious metals and their alloys, goods of precious metals or coated therewith, namely, watches, jewellery and jewellery articles, jewellery cases and boxes, imitation and costume jewellery, cufflinks, badges, insignias, trophies, medals, coins, sculptures, statues, statuettes, figures, figurines, tie clips, tie clasps and pins, lapel pins, metal lapel pins, ornamental pins, ornaments of precious metal in the nature of jewelry, model figures ornaments of precious metal, keychains, keyrings, key fobs and key pins, parts and fittings for the aforesaid goods of precious metals or coated therewith.
(2) Headgear, namely caps, hats, bandanas, and head scarves; clothing, namely, T-shirts, sweaters, shirts, blouses, blazers, cardigans, jeans, pants, dresses, skirts, shorts, tank tops, hoodies, sweat shirts, sweat pants, athletic clothing, vests, socks, underwear, pajamas, under clothes, hosiery, jackets, outerwear, coats, scarves, skirts, sleepwear, socks, suits, tank tops, tights, and track suits.
12 - Land, air and water vehicles; parts of land vehicles
14 - Precious metals and their alloys; jewelry; time-keeping instruments
25 - Clothing; footwear; headgear
Goods & Services
(1) Aircraft parts, namely, power plants which are comprised of airplane engines, jet engines, and helicopter engines, and an aircraft propeller
(2) Aircraft; aircraft powered with a hydrogen propulsion electrochemical reactor; aircraft, namely, electrically powered aircraft; hydrogen fuel cell powered aircraft; structural parts for hydrogen fuel cell powered aircraft; aircraft structural parts, namely, hydrogen fuel storage cells for aircraft; aircraft structural parts, namely, a hydrogen propulsion electrochemical reactor for aircraft
(3) Precious metals and their alloys, goods of precious metals and coated therewith, namely, watches, jewellery, jewellery cases and boxes, imitation and costume jewellery, cufflinks, badges, insignias, trophies, medals, coins, sculptures, statues, statuettes, figures, figurines, tie clips, tie clasps and pins, lapel pins, metal pins, ornamental pins, ornamental button covers being jewellery, ornaments of precious metal in the nature of jewellery, keychains, keyrings, key fobs and key pins, parts and fittings for the aforesaid goods
(4) Clothing, namely, shirts, T-shirts, shorts, pants, jackets, sweaters, jeans, hats, and baseball caps
57.
JUMP-STARTING A HYDROGEN FUEL CELL-POWERED AIRCRAFT
A method for jump-starting a hydrogen fuel cell-powered aircraft is disclosed. The method accesses a fuel cell stack containing latent oxygen therein. Accesses a hydrogen fuel source and provides hydrogen from the hydrogen fuel source into the fuel cell stack causing the hydrogen to mix with the latent oxygen in the fuel cell stack and generate a voltage. The voltage is then provided to a component of the hydrogen fuel cell-powered aircraft such that additional oxygen is introduced to the fuel stack.
H01M 8/04089 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants
H01M 8/04225 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids during start-up or shut-downDepolarisation or activation, e.g. purgingMeans for short-circuiting defective fuel cells during start-up
H01M 8/04302 - Processes for controlling fuel cells or fuel cell systems applied during specific periods applied during start-up
A system and method for an aircraft evacuation system with hydrogen inflation is disclosed. The system includes an aircraft having an integrated hydrogen-electric engine. A fuel cell stack for powering an aircraft motor of the integrated hydrogen-electric engine. A hydrogen fuel source in fluid communication with the fuel cell stack, the hydrogen fuel source containing hydrogen. An inflatable slide and a pump operably coupled with the hydrogen fuel source and the inflatable slide to selectively pump the hydrogen to the inflatable slide for inflating the inflatable slide.
An integrated hydrogen-electric engine including an air compressor system, a hydrogen fuel source, a fuel cell stack, a heat exchanger, an elongated shaft, and a motor assembly. The heat exchanger is disposed in fluid communication with the hydrogen fuel source and the fuel cell stack. The elongated shaft supports the air compressor system, the fuel cell stack and the heat exchanger. The motor assembly is disposed in electrical communication with the fuel cell stack.
F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use
60.
MANAGING HYDROGEN FUEL IN HYDROGEN FUEL CELL-POWERED AIRCRAFT
Method and system for managing hydrogen fuel in hydrogen fuel cell-powered aircraft is disclosed. The method identifies unused hydrogen fuel in a fuel tank of the aircraft. Determines an amount of the unused hydrogen fuel in the fuel tank of the aircraft. Transfers the amount of the unused hydrogen fuel from the fuel tank of the aircraft into a hydrogen fuel cell of the aircraft and converts the amount of the unused hydrogen fuel into electricity via the hydrogen fuel cell of the aircraft.
A method for jump-starting a hydrogen fuel cell-powered aircraft is disclosed. The method accesses a fuel cell stack containing latent oxygen therein. Accesses a hydrogen fuel source and provides hydrogen from the hydrogen fuel source into the fuel cell stack causing the hydrogen to mix with the latent oxygen in the fuel cell stack and generate a voltage. The voltage is then provided to a component of the hydrogen fuel cell-powered aircraft such that additional oxygen is introduced to the fuel stack.
H01M 8/04302 - Processes for controlling fuel cells or fuel cell systems applied during specific periods applied during start-up
H01M 8/04225 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids during start-up or shut-downDepolarisation or activation, e.g. purgingMeans for short-circuiting defective fuel cells during start-up
H01M 8/04089 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants
Method and system for managing hydrogen fuel in hydrogen fuel cell-powered aircraft is disclosed. The method identifies unused hydrogen fuel in a fuel tank of the aircraft. Determines an amount of the unused hydrogen fuel in the fuel tank of the aircraft. Transfers the amount of the unused hydrogen fuel from the fuel tank of the aircraft into a hydrogen fuel cell of the aircraft and converts the amount of the unused hydrogen fuel into electricity via the hydrogen fuel cell of the aircraft.
B60L 53/20 - Methods of charging batteries, specially adapted for electric vehiclesCharging stations or on-board charging equipment thereforExchange of energy storage elements in electric vehicles characterised by converters located in the vehicle
B60L 58/30 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling fuel cells
B64D 7/04 - Arrangement of military equipment, e.g. armaments, armament accessories or military shielding, in aircraftAdaptations of armament mountings for aircraft the armaments being firearms fixedly mounted
H01M 8/04089 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants
H01M 8/04082 - Arrangements for control of reactant parameters, e.g. pressure or concentration
A system and method for an aircraft evacuation system with hydrogen inflation is disclosed. The system includes an aircraft having an integrated hydrogen-electric engine. A fuel cell stack for powering an aircraft motor of the integrated hydrogen-electric engine. A hydrogen fuel source in fluid communication with the fuel cell stack, the hydrogen fuel source containing hydrogen. An inflatable slide and a pump operably coupled with the hydrogen fuel source and the inflatable slide to selectively pump the hydrogen to the inflatable slide for inflating the inflatable slide.
Leveraging a turboexpander to provide additional functionality in compressed gas fueled systems is disclosed. The system includes a compressed gas storage device storing a compressed gas at a first pressure. A turboexpander operably coupled with the compressed gas storage device, the turboexpander comprising a turbine coupled with a drive shaft, the turboexpander to maintain the compressed gas below a threshold temperature limit as it controllably expands the compressed gas from the first pressure to the second pressure via an amount of work obtained from a rotation of the turbine and the drive shaft. A compressed gas receiving device to receive the compressed gas at the second pressure from the turboexpander and generate an amount of electrical energy from the compressed gas.
F02C 1/02 - Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being an unheated pressurised gas
B60L 58/33 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling fuel cells for controlling the temperature of fuel cells, e.g. by controlling the electric load by cooling
F02K 5/00 - Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
H01M 8/04007 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
12 - Land, air and water vehicles; parts of land vehicles
14 - Precious metals and their alloys; jewelry; time-keeping instruments
25 - Clothing; footwear; headgear
Goods & Services
(1) Aircraft parts, namely, power plants which are comprised of an aircraft engine, and an aircraft propeller
(2) Aircraft; aircraft powered with a hydrogen propulsion electrochemical reactor; aircraft, namely, electrically powered aircraft; hydrogen fuel cell powered aircraft; structural parts for hydrogen fuel cell powered aircraft; aircraft structural parts, namely, hydrogen fuel storage cells for aircraft; aircraft structural parts, namely, a hydrogen propulsion electrochemical reactor for aircraft
(3) Precious metals and their alloys, goods of precious metals and coated therewith, namely, watches, jewellery, jewellery cases and boxes, imitation and costume jewellery, cufflinks, badges, insignias, trophies, medals, coins, sculptures, statues, statuettes, figures, figurines, tie clips, tie clasps and pins, lapel pins, metal jewellery pins, ornamental pins, ornamental button covers being jewellery, ornaments of precious metal in the nature of jewellery, keychains, keyrings, key fobs and key pins, parts and fittings for the aforesaid goods
(4) Clothing, namely, shirts, T-shirts, shorts, pants, jackets, sweaters, jeans, hats, and baseball caps
Aircraft engine parts, namely, power units that are comprised of an aircraft engine, an aircraft propeller, and structural parts therefor Clothing, namely, shirts, T-shirts, shorts, pants, jackets, sweaters, jeans, hats, and baseball caps
70.
AIR-COOLED PROTON-EXCHANGE MEMBRANE FUEL CELL CAPABLE OF WORKING WITH COMPRESSED GASES, AND FUEL CELLS STACK
The present disclosure relates to fuel cells, in particular to high-temperature air-cooled fuel cells. A fuel cell (1) comprises a bipolar plate (2) and a membrane-electrode assembly (3). The bipolar plate (2) comprises an anode plate (5), a cathode plate (6) and a layer (7) of air cooling channels between the anode plate (5) and the cathode plate 6. Channels for an oxygen-containing gas are made in the cathode plate (6). Channels (10) for hydrogen are made in the anode plate (5), which are covered by the membrane-electrode assembly (3) contacting the anode plate (5). A fuel cell stack comprises at least two fuel cells, wherein the membrane-electrode assembly of one fuel cell contacts the anode plate of said one fuel cell, thus covering the channels for hydrogen, and contacts the cathode plate of said another fuel cell, which adjoins said one fuel cell, thus covering the channels for an oxygen- containing gas. The technical effect consists in reducing weight-dimension characteristics of the fuel cell and the fuel cell stack, while simultaneously reducing power consumption required for cooling, and increasing specific capacity per unit weight and power efficiency.
H01M 8/0258 - CollectorsSeparators, e.g. bipolar separatorsInterconnectors characterised by the configuration of channels, e.g. by the flow field of the reactant or coolant
H01M 8/0263 - CollectorsSeparators, e.g. bipolar separatorsInterconnectors characterised by the configuration of channels, e.g. by the flow field of the reactant or coolant having meandering or serpentine paths
H01M 8/0267 - CollectorsSeparators, e.g. bipolar separatorsInterconnectors having heating or cooling means, e.g. heaters or coolant flow channels
71.
FUEL CELL - BATTERY HYBRID SYSTEM FOR TRANSPORTATION USE
A power generating system includes a hydrogen fuel cell and rechargeable battery connected together in series to be used as a load following system without the use of a DC-DC converter. The hydrogen fuel cell's cathode air compressor is driven off of the output of this power generation system. The system is wired in series with the use of switches and bypass diodes and limits the system output voltage so that the maximum voltage of downstream components is not exceeded. The system further includes an isolated DC-DC converter to charge the rechargeable battery with the hydrogen fuel cell.
B60L 50/75 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using propulsion power supplied by both fuel cells and batteries
B60L 58/00 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles
H01M 12/08 - Hybrid cellsManufacture thereof composed of a half-cell of a fuel-cell type and a half-cell of the secondary-cell type
72.
FUEL CELL - BATTERY HYBRID SYSTEM FOR TRANSPORTATION USE
A power generating system includes a hydrogen fuel cell and rechargeable battery connected together in series to be used as a load following system without the use of a DC-DC converter. The hydrogen fuel cell's cathode air compressor is driven off of the output of this power generation system. The system is wired in series with the use of switches and bypass diodes and limits the system output voltage so that the maximum voltage of downstream components is not exceeded. The system further includes an isolated DC-DC converter to charge the rechargeable battery with the hydrogen fuel cell.
B60L 50/75 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using propulsion power supplied by both fuel cells and batteries
B60L 58/00 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles
H01M 12/08 - Hybrid cellsManufacture thereof composed of a half-cell of a fuel-cell type and a half-cell of the secondary-cell type
73.
MODULAR ELECTRIC POWERTRAIN CONVERSION FOR AIRCRAFT
An aircraft power plant includes a monolithic powertrain block with a composition of individual modules grouped by functionality. The aircraft power plant further includes electric motors, high power motor controllers, logical control electronics (a drivetrain computer), a cooling system, a hydraulics system, a low voltage power system, and ahigh voltage power source. The engine mounting frame of the aircraft is the main structure for mounting all individual modules.
An integrated fuel cell power delivery system includes a first power source configured to supply power to a propulsion inverter, a second power source configured to supply power to the propulsion inverter, a disconnect operably connected to the second power source, a bypass diode operably connected to the first power source and the second power source, a sensor that detects an output voltage of the integrated fuel cell power system, a processor, and a memory. The memory includes instructions stored thereon, which when executed by the processor, cause the integrated fuel cell power system to access a signal from the sensor, determine if the accessed first signal is greater than a first threshold voltage, and operably disconnect an output of the second power source to the integrated fuel cell power system by the disconnect based on the determination.
An integrated fuel cell power delivery system includes a first power source configured to supply power to a propulsion inverter, a second power source configured to supply power to the propulsion inverter, a disconnect operably connected to the second power source, a bypass diode operably connected to the first power source and the second power source, a sensor that detects an output voltage of the integrated fuel cell power system, a processor, and a memory. The memory includes instructions stored thereon, which when executed by the processor, cause the integrated fuel cell power system to access a signal from the sensor, determine if the accessed first signal is greater than a first threshold voltage, and operably disconnect an output of the second power source to the integrated fuel cell power system by the disconnect based on the determination.
12 - Land, air and water vehicles; parts of land vehicles
Goods & Services
Aircraft parts, namely, power plants which are comprised of
an aircraft engine, and components thereof. Hydrogen fuel cell electric vehicles; aircraft; aircraft
powered with a hydrogen propulsion electrochemical reactor;
aircraft, namely, electrically powered aircraft; hydrogen
fuel cell powered aircraft; structural parts for hydrogen
fuel cell powered aircraft; aircraft structural parts,
namely, hydrogen fuel storage cells for aircraft; aircraft
structural parts, namely, a hydrogen propulsion
electrochemical reactor for aircraft; aircraft propellers.
12 - Land, air and water vehicles; parts of land vehicles
Goods & Services
Aircraft parts, namely, power plants which are comprised of
an aircraft engine, an aircraft propeller and components
thereof. Aircraft, namely, electrically powered aircraft; hydrogen
fuel cell powered aircraft; structural parts for hydrogen
fuel cell powered aircraft; aircraft structural parts,
namely, hydrogen fuel storage cells for aircraft.
12 - Land, air and water vehicles; parts of land vehicles
Goods & Services
Aircraft parts, namely, power plants which are comprised of
an aircraft engine, an aircraft propeller and components
thereof (term considered too vague by the International
Bureau - Rule 13 (2) (b) of the Regulations). Aircraft, namely, electrically powered aircraft; hydrogen
fuel cell powered aircraft; structural parts for hydrogen
fuel cell powered aircraft; aircraft structural parts,
namely, hydrogen fuel storage cells for aircraft; aircraft
propeller.
12 - Land, air and water vehicles; parts of land vehicles
Goods & Services
(1) Aircraft parts, namely, power plants which are comprised of an aircraft engine, an aircraft propeller and components thereof.
(2) Aircraft, namely, electrically powered aircraft; hydrogen fuel cell powered aircraft; structural parts for hydrogen fuel cell powered aircraft; aircraft structural parts, namely, hydrogen fuel storage cells for aircraft.
12 - Land, air and water vehicles; parts of land vehicles
Goods & Services
(1) Aircraft parts, namely, power plants which are comprised of an aircraft engine, and an aircraft propeller.
(2) Aircraft, namely, electrically powered aircraft; hydrogen fuel cell powered aircraft; structural parts for hydrogen fuel cell powered aircraft; aircraft structural parts, namely, hydrogen fuel storage cells for aircraft; aircraft propeller.
84.
ELECTRIC ACCELERATION ASSIST FOR SHORT TAKEOFF AND LANDING CAPABILITIES IN FIXED-WING AIRCRAFT
A system for managing the ground roll of the landing gear of an aircraft includes an electrical motor, a battery, and an electronic motor controller. The electrical motor is operably associated with landing gear and configured to control the rotation associated therewith. The battery is operably coupled to the electrical motor and configured to supply power thereto. The electronic motor controller is configured to control the flow of electrical power between the battery and the electrical motor and the resultant torque associated with the electrical motor. The electronic motor controller is adapted to communicate with the throttle control of the aircraft. The electronic motor controller cooperates with one or more aircraft controls to provide power to the electrical motor as needed to control the rotation of the landing gear during aircraft takeoff or aircraft landing.
An aircraft power plant comprising a monolithic powertrain block with a composition of individual modules grouped by functionality, further comprising electric motors, high power motor controllers, logical control electronics (drivetrain computer), cooling system, hydraulics system, low voltage power system, and high voltage power source, wherein the engine mounting frame of the airplane is the main structure for mounting all individual modules.
In one or more embodiments, the ground roll assist system is based on the electric in-wheel motors integrated with the main landing gear of an aircraft and linked to the aircraft control system. It is well known that modern electric motors possess superior torque density characteristics, potentially exceeding best in class internal combustion engines by more than an order of magnitude. Furthermore, electric motors performance is generally thermally limited, which makes it possible to achieve even higher performance for a short period of time.
The disclosure relates to bipolar plates used in fuel cells and to methods for forming bipolar plates. A bipolar plate of a fuel cell with a composite corrosion-resistant, gastight, conductive coating comprises a core of a required shape, a first layer having high contact conductivity on the core, and a second layer having corrosion resistance, high gas-tightness, electric conductivity on the first layer and in pores of the first layer, the second layer covering at least the pores in the first layer. The first layer is preferably formed by a magnetron sputtering method, and the second layer is preferably formed by a method of thermolysis of a metalorganic compound. This ensures high gas-tightness and elasticity of a bipolar plate without compromising its corrosion resistance and contact conductivity.
C23C 14/35 - Sputtering by application of a magnetic field, e.g. magnetron sputtering
C23C 18/12 - Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coatingContact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material
C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material
An integrated hydrogen-electric engine including an air compressor system, a hydrogen fuel source, a fuel cell stack, a heat exchanger, an elongated shaft, and a motor assembly. The heat exchanger is disposed in fluid communication with the hydrogen fuel source and the fuel cell stack. The elongated shaft supports the air compressor system, the fuel cell stack and the heat exchanger. The motor assembly is disposed in electrical communication with the fuel cell stack.
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
Recognizing the fact of extremely low utilization of peak power (especially in the aviation use case), we propose a novel approach to significantly reduce the size and weight of the system by downsizing the main air compressor to match the air flow required to produce the desired continuous power (e.g., 55% of the peak power rating for the aviation applications, etc.), and provide the supplemental oxygen flow from an on-board high-pressure oxygen tank.
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
H01M 8/04082 - Arrangements for control of reactant parameters, e.g. pressure or concentration
91.
Multi-stage turbocharging compressor for fuel cell systems
An aircraft power plant comprising novel air management features for high-power fuel cell applications, the features combine supercharging and turbocharging elements with air and hydrogen gas pathways, utilize novel airflow concepts and provide for much stronger integration of various fuel cell drive components.
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
F02C 1/02 - Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being an unheated pressurised gas
H01M 8/04082 - Arrangements for control of reactant parameters, e.g. pressure or concentration
F02C 6/18 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
B64D 31/00 - Power plant control systemsArrangement of power plant control systems in aircraft
B64D 41/00 - Power installations for auxiliary purposes
92.
Aircraft fuel cell system without the use of a buffer battery
In one or more embodiments of the novel aircraft fuel cell system without the use of a buffer battery, the fuel cell and compressor would be sized sufficiently larger for the intended application, allowing the compressor to change speeds much faster. This in turn would allow power outputs to change much quicker. If power outputs can change as quickly as the application dictates, then a buffer battery is not necessary. In one or more embodiments, because the system is mostly electronically controlled, software can be written to protect the fuel cell from instantaneous power spikes. If a large power output is suddenly requested of the fuel cell, the software can smooth out the demand curve to provide an easier load profile to follow.
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
