Abstract: A fuel cell system for an aircraft includes a hydrogen burner, an oxidizing agent, and a fuel cell. The hydrogen burner has a first inlet suitable for receiving a first oxidizing agent, a second inlet capable of receiving at least hydrogen, and an outlet suitable for delivering a second oxidizing agent and heat. The oxidizing agent conditioning system has an inlet and an outlet, said inlet being suitable for receiving the second oxidizing agent and heat, said outlet being capable of delivering the conditioned second oxidizing agent. The fuel cell has an anode and a cathode, the cathode has a cathode inlet connected to the outlet of the oxidizing agent conditioning system, the cathode inlet receiving the conditioned second oxidizing agent.

Abstract: A fuel cell system for an aircraft, includes a hydrogen burner, an oxidizing agent, and a fuel cell. The hydrogen burner has a first inlet suitable for receiving a first oxidizing agent, a second inlet capable of receiving at least hydrogen, and an outlet suitable for delivering a second oxidizing agent and heat, The oxidizing agent conditioning system has an inlet and an outlet, said inlet being suitable for receiving the second oxidizing agent and heat, said outlet being capable of delivering the conditioned second oxidizing agent, The fuel cell has an anode and a cathode, the cathode has a cathode inlet connected to the outlet of the oxidizing agent conditioning system, the cathode inlet receiving the conditioned second oxidizing agent.

Abstract: Embodiments of the present invention provide a single coolant loop (40) that can be used for cooling at least two systems (100, 26) that are generally operable at two different temperatures. Rather than providing two separate cooling loops that can provide the two different cooling temperatures, there is provided a single cooling loop (40) that can route, harness, and mix heated coolant so that the two system can be served by a single loop.

Abstract: Embodiments of the present disclosure relate generally to systems and methods for providing improved aircraft fuel cell systems. In one embodiment, the system provides separate zones, maintaining various equipment components in separate controlled hydrogen concentration zones. In one embodiment, the fuel cell system provided may be simpler such that it functions without a power converter and autonomous such that it functions without need for power from any aircraft supply.

Abstract: Embodiments of the present disclosure relate generally to systems and methods for providing improved aircraft fuel cell systems. In one embodiment, the system provides separate zones, maintaining various equipment components in separate controlled hydrogen concentration zones. In one embodiment, the fuel cell system provided may be simpler such that it functions without a power converter and autonomous such that it functions without need for power from any aircraft supply.

Abstract: Embodiments of the present disclosure relate generally to systems and methods for providing improved aircraft fuel cell systems. In one embodiment, the system provides separate zones, maintaining various equipment components in separate controlled hydrogen concentration zones. In one embodiment, the fuel cell system provided may be simpler such that it functions without a power converter and autonomous such that it functions without need for power from any aircraft supply.

Abstract: Embodiments of the present invention provide a single coolant loop (40) that can be used for cooling at least two systems (100, 26) that are generally operable at two different temperatures. Rather than providing two separate cooling loops that can provide the two different cooling temperatures, there is provided a single cooling loop (40) that can route, harness, and mix heated coolant so that the two system can be served by a single loop.

Abstract: Embodiments of the present disclosure relate generally to systems and methods for providing improved aircraft fuel cell systems. In one embodiment, the system provides separate zones, maintaining various equipment components in separate controlled hydrogen concentration zones. In one embodiment, the fuel cell system provided may be simpler such that it functions without a power converter and autonomous such that it functions without need for power from any aircraft supply.