An incorporated air supplying apparatus for a fuel cell stack and a method for controlling an air flow using the same are described. The apparatus includes an air supply part supplying air to a plurality of fuel cell stacks, a plurality of pipes configured to transmit the air supplied from the air supply part to each of the fuel cell stacks, a flowmeter and a valve installed at each pipe, and a controller controlling an opening degree of each of the valves, based on information on the measured flow. The controller controls the opening degree of the valve installed at each pipe, thus enabling the air flow for each pipe to be controlled.

The invention relates to a method for fueling fuel cell systems (Sys A, Sys B) which are operated in an assembly (10) of a plurality of fuel cell systems (Sys A, Sys B), and to a fuel cell system assembly (10). According to the invention, a method is provided by means of which a load (100) operated by the assembly (10) can continue to be operated while a fueling process is carried out by a fueling device 20 assigned to the fuel cells (FC 1, FC 2) of the fuel cell system (Sys A, Sys B).

Described herein is a fuel cell and battery hybrid system (1) comprising one or more sets (2) of serially connected fuel cells (FC1-n). The one or more sets (2) of serially connected fuel cells (FC1-n) are further serially connected via a respective fuel cell series enhancer (3). The serially connected sets (2) are further connected in parallel with a battery (4) via a fuel cell power charge controller (5). Each respective set (2) of serially connected fuel cells (FC1-n) is further arranged be controlled by the fuel cell series enhancer (3) to operate electrically independent from other sets (2) of serially connected fuel cells (FC1-n) and at its own unique maximum power point or uniquely selected other operating point, regardless of the operating points of other sets (2) of serially connected fuel cells (FC1-n).

A method for distinguishing the cause of voltage losses in a fuel cell device includes: a) Detection of a quasi-stationary operation of the fuel cell device, b) Acquisition and storage of a measured current-voltage characteristic curve with the current values and the voltage values of a fuel cells stack of the fuel cell device, c) Use of a PtOx model to determine PtOx voltage losses and calculation of a corrected current-voltage characteristic curve for the PtOx-free and normally humidified fuel cell stack, and d) Comparison of the current-voltage characteristic curves determined in step b) and in step c) and detection of an at least partially dried-out fuel cell stack if the measured current-voltage characteristic curve runs below the corrected current-voltage characteristic curve. A fuel cell device and a motor vehicle comprising a fuel cell device are also provided.

a fuel cell system without a high pressure line of a hydrogen supplying system, including a gas charging line formed between a gas charging station and a high pressure vessel charged with gas by the gas charging station, and a gas supplying line formed between the high pressure vessel and a stack, includes: a regulator provided in the gas supplying line; a solenoid valve provided in the gas supplying line between the regulator and the high pressure vessel; and a check valve provided in a bypass line connecting one point of the gas supplying line between the regulator and the solenoid valve and one point of the gas charging line.

Systems and methods configured to receive a set of real-time flight conditions and a user-selected objective function. The user-selected objective function is one of a plurality of objective functions. The systems and methods determine, with an emissions tuning model, one of a plurality of sets of fuel cell operating conditions based on the set of real-time flight conditions and the user-selected objective function. The systems and methods are configured to control a fuel cell assembly operating parameter according to the determined one of the plurality of sets of fuel cell operating conditions.

A hydrogen supply control method of a fuel cell system is provided. The method includes measuring the pressure of a front line of a supply line having relatively low humidity and the pressure of a front end of an ejector, without a pressure sensor of an anode. The amount of supplied hydrogen is then adjusted using the measured pressure and the pressure of the anode is estimated more accurately.

A propulsion system including: a fuel cell assembly comprising a fuel cell, the fuel cell defining an outlet positioned to remove output products from the fuel cell and a fuel cell assembly operating condition; a combustion section that includes a combustor configured to receive a flow of aviation fuel from the aircraft fuel supply and further configured to receive the output products from the fuel cell; and a controller comprising memory and one or more processors, the memory storing instructions that when executed by the one or more processors cause the propulsion system to perform operations including: determining data indicative of at least one of an enthalpy or a composition of the output products from the fuel cell; and modifying the flow of aviation fuel from the aircraft fuel supply to the combustor based on the at least one of the enthalpy or the composition of the output products.

A gas turbine engine includes a fuel cell assembly including a fuel cell stack and defining a fuel cell assembly operating parameter, a fuel source, and a turbomachine. The turbomachine includes a compressor section, a combustor, and a turbine section arranged in serial flow order. The combustor is configured to receive a flow of fuel from the fuel source and further configured to receive output products from the fuel cell stack. A controller is configured to perform operations including receiving data indicative of system operation conditions, determining a set of fuel cell operating conditions to move the system emission output into or maintain the system emission output within an emissions range, and controlling the fuel cell assembly operating parameter according to the determined set of fuel cell operating conditions.

A safety management system for an aircraft, or a propulsion system thereof including a fuel cell assembly and a combustion engine, may include various sensors and controllers configured to execute a safety action. At least one sensor is configured to detect at least one operating parameter of the propulsion system, and a controller is configured to determine that the at least one operating parameter has achieved a safety threshold and to execute a safety action when the at least one operating parameter has achieved the safety threshold. The safety action is configured to control operation of the fuel cell assembly and to control operation of the combustion engine.