A fuel cell system (200), wherein the fuel cell system (200) has: a) a fuel cell stack (10), b) an anode gas path (20) which fluidically communicates with the fuel cell stack (10) and which serves for supplying anode gas from an anode gas store (22) to the fuel cell stack (10), c) a cathode gas path (30) which fluidically communicates with the fuel cell stack (10) and which serves for supplying cathode gas from a cathode gas store (32) to the fuel cell stack (10), d) a cooling fluid path (40) which fluidically communicates with the fuel cell stack (10) and which serves for supplying cooling fluid from a cooling fluid store (42) to the fuel cell stack (10), e) a vibration generator (60) which is in data-transmitting communication with a control unit (50) and which serves for setting the fuel cell stack (10) into a vibrating state, and f) the control unit (50) for actuating the vibration generator (60) in order to set the fuel cell stack (10) into the vibrating state by means of the vibration generator (60).

The present disclosure generally relates to systems and methods for using an energy storage device to assist a venturi or an ejector in a fuel cell or fuel stack system.

The present disclosure generally relates to systems and methods for using an energy storage device to assist a venturi or an ejector in a fuel cell or fuel stack system.

The invention provides an SOFC cooling system. For the feature that not all components work in the full operation process of an SOFC, a DC step-down transformer DCDC, a fan and a condenser are connected in parallel, and a solenoid valve is installed in each parallel pipeline for controlling on/off of each pipeline according to a corresponding signal. Compared with the traditional SOFC cooling system, the constant-flow serial cooling system will reduce pressure losses and the power of a water pump; a solenoid valve is installed in each parallel pipeline for controlling on/off of each branch according to a corresponding signal; considering the cooling requirements of SOFC during start-up, power generation and shutdown, all components are cooled in parallel through reasonable design of each parallel pipeline, consequently to improve the cooling effect and reduce the energy consumption; the invention also discloses a fuel cell and hybrid vehicle.

A fuel cell module is configured or operated, or both, such that after a shut down procedure a fuel cell stack is discharged and has its cathode electrodes at least partially blanketed with nitrogen during at least some periods of time. If the fuel cell module is restarted in this condition, electrochemical reactions are limited and do not quickly re-charge the fuel cell stack. To decrease start up time, air is moved into the cathode electrodes before the stack is re-charged. The air may be provided by a pump, fan or blower driven by a battery or by the flow or pressure of stored hydrogen. For example, an additional fan or an operating blower may be driven by a battery until the fuel cell stack is able to supply sufficient current to drive the operating blower for normal operation.

A fuel cell module is configured or operated, or both, such that after a shut down procedure a fuel cell stack is discharged and has its cathode electrodes at least partially blanketed with nitrogen during at least some periods of time. If the fuel cell module is restarted in this condition, electrochemical reactions are limited and do not quickly re-charge the fuel cell stack. To decrease start up time, air is moved into the cathode electrodes before the stack is re-charged. The air may be provided by a pump, fan or blower driven by a battery or by the flow or pressure of stored hydrogen. For example, an additional fan or an operating blower may be driven by a battery until the fuel cell stack is able to supply sufficient current to drive the operating blower for normal operation.

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.

A system for operating a fuel cell includes a controller configured to derive an output limit value of the fuel cell through an interval average value corresponding to an average of output values of the fuel cell for a designated time and a cumulative average value corresponding to an average of the output values of the fuel cell until the current point in time after starting to operate the fuel cell, and to control operation of the fuel cell based on the derived output limit value.

A fuel cell cooling system and a control method are provided. The fuel cell cooling system includes a fuel cell module having a fuel cell stack and a first cooling water line through which primary cooling water undergoing heat exchange with the fuel cell stack to adjust a temperature of the fuel cell stack circulates. A cooling module includes a second cooling water line through which secondary cooling water circulates and a cooling tower is configured to adjust a temperature of the secondary cooling water. A heat exchanger is connected between the first cooling water line of the fuel cell module and the second cooling water line of the cooling module for heat exchange. A controller configured to operate the fuel cell module and the cooling module.

Provided is a flight vehicle that makes it possible to prevent electricity generation by a fuel cell from being stopped in flight even when a mistaken operation is conducted. The flight vehicle including a fuel cell and a propeller, the propeller to be driven by electric power generated by the fuel cell, the flight vehicle including: a stop device giving an instruction to stop the generation of electricity by the fuel cell; a control unit processing stopping of the generation of electricity by the fuel cell; a leg part grounding when the flight vehicle lands, to support a load of the flight vehicle; and a sensor detecting the load applied to the leg part, wherein the control unit permits the stopping of the generation of electricity based on signals from the stop device and the sensor only if a predetermined amount of the load is applied to the leg part.