A propulsion system for an aircraft includes a fan section having a fan; a turbomachine including a compressor section, a combustion section, and a turbine section arranged in serial flow order; at least one electric machine; a fuel cell assembly configured to supply power to the electric machine; and a controller including a memory and one or more processors. One or both of the turbomachine and the at least one electric machine are configured to drive rotation of the fan of the fan section. The fuel cell assembly includes at least one fuel cell, a first fluid inlet for receiving a flow of pressurized air, and a second fluid inlet for receiving a flow of fuel.
Pour en savoir plus : Fuel cell systems for aeronautical vehicles
