ZeroAvia, Inc.

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.

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.

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.

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 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.

The method allows to produce catalysts with nanoparticles of platinum and its alloys with metals of a given composition, with high values of catalytic activity in an oxygen electroreduction reaction, and with predetermined values of structural characteristics. The method comprises preparation of a solution of chloroplatinic acid or a mixture of chloroplatinic acid with metal salts, mixing thereof with dispersed carbon or non-carbon carriers, their mixtures and compositions with specific surface area of more than 60 m 2 /g, dispersion of the obtained mixture, chemical reduction of compounds of platinum and a metal salt with subsequent deposition of nanoparticles of metallic platinum or its alloys on a dispersed carrier being carried out by purging gases selected from: nitrogen oxides (N 2 O, NO, NO 2 ), carbon oxides (CO, CO 2 ), sulfur oxide (SO 2 ), ammonia (NH 3 ) or their mixtures through the solution at a temperature of the solution in the range from 5 to 98° C.

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.

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.