{
  "$type": "site.standard.document",
  "description": "Turbine engine systems include a core assembly having a compressor section, a burner section, and a turbine section arranged along a shaft, with a core flow path through the turbine engine such that exhaust from the burner section passes through the turbine section and exits through a nozzle. A…",
  "path": "/patents/1357655",
  "publishedAt": "2024-01-11T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C6/00",
    "RTX Corporation"
  ],
  "textContent": "Turbine engine systems include a core assembly having a compressor section, a burner section, and a turbine section arranged along a shaft, with a core flow path through the turbine engine such that exhaust from the burner section passes through the turbine section and exits through a nozzle. A core condenser is arranged downstream of the turbine section and upstream of the nozzle and configured to condense water from the core flow path. A fuel cell is operably connected to the core assembly. A fuel source is 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 is operably coupled to the core assembly and configured to impart power to a portion of the core assembly and the fuel cell is configured to supply electrical power to the at least one electric motor.",
  "title": "HYBRID ELECTRIC HYDROGEN ENGINE FOR AIRCRAFT"
}