Hybrid electric hydrogen engine for aircraft

A turbine engine system, comprising:

• a core assembly comprising a compressor section, a burner section, and a turbine section arranged along a shaft, with a core flow path through the core assembly such that exhaust from the burner section passes through the turbine section and exits through a nozzle;
• a core condenser arranged downstream of the turbine section of the core assembly along the core flow path and upstream of the nozzle, the core condenser configured to condense water from the core flow path;
• a fuel cell operably connected to the core assembly;
• a fuel source configured to supply a fuel to each of the burner section for combustion and the fuel cell for reaction to generate electricity;
• at least one electric motor operably coupled to the core assembly and configured to impart power to a portion of the core assembly, wherein the fuel cell is configured to supply electrical power to the at least one electric motor;
• and
• a controller configured to operate the fuel cell when the core assembly is at a low power setting and to disengage the fuel cell when the core assembly is at a high power setting,
• wherein a portion of the water condensed from the core condenser is directed through a cooling element of the fuel cell to provide cooling thereto based on operation thereof.