HYBRID ELECTRIC HYDROGEN ENGINE FOR AIRCRAFT

A turbine engine system includes a core assembly having a compressor section (404), a burner section (406), and a turbine section (408) arranged along a shaft, with a core flow path (416) through the turbine engine (400) such that exhaust from the burner section (406) passes through the turbine section (408) and exits through a nozzle. A core condenser (420) is arranged downstream of the turbine section (408) and upstream of the nozzle and configured to condense water from the core flow path (416). A fuel cell (430) is operably connected to the core assembly. A fuel source (410) is configured to supply a fuel to each of the burner section (406) for combustion and the fuel cell (430) for reaction to generate electricity. At least one electric motor (432, 434) is operably coupled to the core assembly and configured to impart power to a portion of the core assembly and the fuel cell (430) is configured to supply electrical power to the at least one electric motor (432, 434).