A pulse hydrogen supply system for a proton exchange membrane fuel cell is provided. The system comprises a fuel cell, a high-pressure hydrogen bottle, a first pressure relief valve, an ejector, a steam-water separator, a first pressure control valve, a first pressure sensor, a high-pressure vessel, a first electromagnetic valve, a low-pressure vessel, a diaphragm pump, and a second electromagnetic valve. The high-pressure hydrogen bottle, the first pressure relief valve, the first pressure control valve, the ejector and the first pressure sensor are sequentially arranged on a gas inlet pipeline; the high-pressure vessel and the first electromagnetic valve are sequentially arranged on a branch pipeline; the second electromagnetic valve, the low-pressure vessel and the diaphragm pump are sequentially arranged on a first output loop; and the first output pipeline and the gas inlet pipeline form a loop.

A fuel cell system includes a fuel cell, a cathode off-gas discharge channel, a gas-liquid separator, and a cover member. The gas-liquid separator includes a body, a first discharge channel including a first valve seat at an end, and a first valve device including a first valve element and a first driver. The cover member covers at least the first discharge channel and the first valve seat in the gas-liquid separator, and includes a gas channel defining portion that defines a gas channel communicating with the cathode off-gas discharge channel between the cover member and the gas-liquid separator. The gas channel is configured such that a cathode off-gas flowing into the cover member comes into contact with the first discharge channel and the first valve seat and does not come into contact with the first driver.

An aircraft propulsion system comprises a gas turbine engine arranged to provide propulsive thrust and a fuel cell system having an air input port, the aircraft propulsion system being configured such that air from a compressor of the gas turbine engine is provided to the air input port during operation of the aircraft propulsion system. The fuel cell system is able to provide appreciable electrical power at altitude without the need for a dedicated compressor.

In a fuel cell vehicle and a method of controlling the fuel cell vehicle, when a gas pressure in a high pressure tank becomes less than a first threshold pressure, the SOC of an energy storage device is increased to a margin SOC. When the gas pressure becomes a second threshold pressure which is lower than the first threshold pressure, the amount of fuel released from the high pressure tank is limited to prevent the occurrence of buckling, and limit the travel driving force by the motor to a required limit. At the time of limiting the travel driving force, electrical energy of the energy storage device is used to provide assistance in a manner that the travel driving force by the motor becomes the travel driving force of the required limit.

The present invention relates to a fuel cell system and a control method for the same, it may be configured to include a plurality of stacks connected in series with each other, and supply moisture from one or more stacks of the plurality of stacks to one or more other stacks according to an operation condition of each of the plurality of stacks, and it has an advantage of improving an operation performance by uniformly forming the humidity condition of each of the plurality of stacks.

The invention concerns a vehicle comprising an electricity production unit configured for generating an electrical current, a transformer unit and a fuel storage unit, the production unit comprising at least two fuel cell stacks and a single first electrical connection interface for transmitting the electrical current to the transformer unit. The production unit further comprises a single cooling circuit, an air supply circuit and a single gaseous hydrogen supply circuit for supplying gaseous hydrogen, from the fuel storage unit, to each fuel cell stack. The production unit is separate from the fuel storage unit and connected to the fuel storage unit by a single connection interface, the production unit being removable from the vehicle as an integrated unit independently from the fuel storage unit.

In order to provide a fuel cell device which can be produced simply and cost-effectively, it is proposed that the fuel cell device comprises the following: a plurality of fuel cell elements which are stacked one on top of another along a stacking direction and form a fuel cell stack; a clamping device for securing the fuel cell elements; a fluid guide unit for supplying fuel and/or oxidizer and/or coolant to the fuel cell elements and/or for removing fuel and/or oxidizer and/or exhaust gas and/or coolant from the fuel cell elements, wherein the clamping device comprises two or more crossmembers which extend at least approximately perpendicularly to the stacking direction, wherein in each case at least one crossmember is arranged at each end of the fuel cell stack, wherein the crossmembers can be drawn towards one another by means of clamping elements and the fuel cell stack can thereby be clamped between the crossmembers.

An aircraft includes a fuel cell-powered electric engine system configured to power the aircraft and produce water vapor exhaust, and an exhaust system configured to receive the water vapor exhaust, condense the water vapor into ice or water, and expel the ice or water from the aircraft such that water vapor cloud formation is inhibited. A method of powering an aircraft includes operating a fuel cell-powered electric engine system to power the aircraft, condensing water vapor exhaust of the fuel cell-powered electric engine system into ice or water, and expelling the ice or water from the aircraft such that water vapor cloud formation is inhibited.

A fuel cell system includes a fuel cell stack having a hydrogen hole in which hydrogen gas passes, a hydrogen-related auxiliary machine, and a hydrogen pipe that connects the hydrogen hole and the hydrogen-related auxiliary machine. The hydrogen pipe includes a liquid retention part that is located below the hydrogen hole, and a connecting point between the hydrogen pipe and the hydrogen-related auxiliary machine in a gravity direction.

A fuel cell system includes a fuel cell stack in fluid communication with a separator. The separator has a first portion and a second portion forming a chamber. The first portion has a continuous inner wall and an end wall, with an inlet conduit connected to the inner wall and a liquid drain connected to the end wall. The second portion has an end wall and an outlet conduit extending into the chamber to form a channel with the inner wall of the first portion. A fuel cell separator includes a first end and a second end connected by a side wall to define a separation chamber. An inlet conduit is tangentially connected to the wall. An outlet conduit is connected to the first end and extending into the chamber to form a channel with the wall. A liquid drain is connected to the second end.