A torque generating system is described, and includes a fuel cell power device, a high-voltage battery, an electric drive unit, and a controller. The fuel cell power device has a non-linear power-temperature relationship that has a local temperature maxima at a first electric power level and a local temperature minima at a second electric power level. A first operating point of the fuel cell power device is less than the first electric power level, and a second operating point of the fuel cell power device is set at a third electric power level that is greater than the first electric power level, wherein the third electric power level generates a fuel cell temperature that is less than the local temperature maxima. The fuel cell power device is controlled to one of the first operating point or the second operating point to transfer electric power to the electric drive unit.

A torque generating system is described, and includes a fuel cell power device, a high-voltage battery, an electric drive unit, and a controller. The fuel cell power device has a non-linear power-temperature relationship that has a local temperature maxima at a first electric power level and a local temperature minima at a second electric power level. A first operating point of the fuel cell power device is less than the first electric power level, and a second operating point of the fuel cell power device is set at a third electric power level that is greater than the first electric power level, wherein the third electric power level generates a fuel cell temperature that is less than the local temperature maxima. The fuel cell power device is controlled to one of the first operating point or the second operating point to transfer electric power to the electric drive unit.

A lightweight, high power density, fault-tolerant fuel cell system, method, and apparatus for full-scale clean fuel electric-powered aircraft having a fuel cell module including a plurality of fuel cells working together to process gaseous oxygen from air compressed by turbochargers, superchargers, blowers or local oxygen supply and gaseous hydrogen from liquid hydrogen transformed by heat exchangers, with an electrical circuit configured to collect electrons from the plurality of hydrogen fuel cells to supply voltage and current to motor controllers commanded by autopilot control units configured to select and control an amount and distribution of electrical voltage and torque or current for each of the plurality of motor and propeller assemblies, wherein electrons returning from the electrical circuit combine with oxygen in the compressed air to form oxygen ions, then the protons combine with oxygen ions to form H.sub.2O molecules and heat.

A lightweight, high power density, fault-tolerant fuel cell system, method, and apparatus for full-scale clean fuel electric-powered aircraft having a fuel cell module including a plurality of fuel cells working together to process gaseous oxygen from air compressed by turbochargers, superchargers, blowers or local oxygen supply and gaseous hydrogen from liquid hydrogen transformed by heat exchangers, with an electrical circuit configured to collect electrons from the plurality of hydrogen fuel cells to supply voltage and current to motor controllers commanded by autopilot control units configured to select and control an amount and distribution of electrical voltage and torque or current for each of the plurality of motor and propeller assemblies, wherein electrons returning from the electrical circuit combine with oxygen in the compressed air to form oxygen ions, then the protons combine with oxygen ions to form H.sub.2O molecules and heat.

A fuel cell system installed in a vehicle, the system comprising: a fuel cell, a secondary cell, a temperature acquirer for acquiring a temperature of the fuel cell, a state-of-charge value acquirer for acquiring a state-of-charge-value of the secondary cell, an outside temperature acquirer for acquiring an outside temperature, an outside pressure acquirer for acquiring an outside pressure, and a controller for controlling power of the secondary cell, wherein, when the temperature of the fuel cell exceeds a predetermined temperature, when the state-of-charge value of the secondary cell is a predetermined threshold value or more, when the outside temperature is a predetermined temperature or more, and when the outside pressure is a predetermined pressure or less, the controller increases the power of the secondary cell larger than power required of the secondary cell for normal running of the vehicle.

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 propulsion system for an aircraft includes a fuel cell assembly, the fuel cell assembly including a fuel cell, and a turbomachine, the turbomachine including a compressor section, a combustor, and a turbine section arranged in serial flow order. The combustor is configured to receive a flow of fuel and further configured to receive output products from the fuel cell. A controller is configured to receive data indicative of an engine constraint of the turbomachine, determine that the engine constraint has achieved a fuel cell trim threshold; and perform a fuel cell corrective action with the fuel cell assembly in response to determining that the engine constraint has achieved the fuel cell trim threshold.

A propulsion system for an aircraft includes a fuel cell assembly, the fuel cell assembly including a fuel cell, and a turbomachine, the turbomachine including a compressor section, a combustor, and a turbine section arranged in serial flow order. The combustor is configured to receive a flow of fuel and further configured to receive output products from the fuel cell. A controller is configured to receive data indicative of an engine constraint of the turbomachine, determine that the engine constraint has achieved a fuel cell trim threshold; and perform a fuel cell corrective action with the fuel cell assembly in response to determining that the engine constraint has achieved the fuel cell trim threshold.

A vehicle includes a fuel cell having an air inlet port and an air outlet port and an air supply system having a compressor connected in fluid communication with the inlet port and a throttle valve connected in fluid communication with the outlet port. A controller is programmed to change a position of the throttle valve based on a target mass air flow, a measured mass air flow, a measured pressure, and the position of the throttle valve.

A fuel cell vehicle is mounted with a fuel cell system including a fuel cell stack and a battery. The fuel cell vehicle controls operation of the fuel cell system with an ECU, to perform standby power generation from activation to when travel is allowed and to perform power generation during operation of the fuel cell vehicle after travel has been allowed. In an activation method, the power generation current is increased in accordance with a low-temperature efficiency rate during the power generation during operation, the battery is charged and the power generation current is increased in accordance with a standby current increase rate that is lower than the low-temperature efficiency rate during the standby power generation.