Fuel cell turboelectric fan for an aircraft

A propulsion system for an aircraft, the aircraft propulsion system comprising:

• a nacelle having a hollow ring-shaped interior surrounding a cylindrical passageway therethrough, the cylindrical passageway having a forward opening and a rearward opening;
• a shaft positioned centrally within the cylindrical passageway;
• a fan coupled to the shaft and positioned within the cylindrical passageway closer to the forward opening than to the rearward opening;
• a turbine coupled to the shaft and positioned within the cylindrical passageway closer to the rearward opening than to the forward opening, the turbine configured to provide primary torque to the shaft;
• an electric motor coupled to the shaft and positioned within the cylindrical passageway of the nacelle, the electric motor configured to provide additional torque to the shaft;
• a compressor coupled to the shaft and positioned within the cylindrical passageway;
• and
• a solid oxide fuel cell positioned within the hollow ring-shaped interior of the nacelle or radially around the gas turbine, the solid oxide fuel cell configured to receive compressed air from the compressor, provide power to at least the electric motor, and provide output gases to at least the turbine.