{
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  "description": "A propulsion system for an aircraft includes a core engine that includes a core flow path (C) where a core flow (50) is compressed in a compressor section (24), communicated to a combustor section (30), mixed with a hydrogen-based fuel and ignited to generate a gas flow that is expanded through a…",
  "path": "/patents/1394008",
  "publishedAt": "2026-03-25T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C3/06",
    "RTX CORP [US]"
  ],
  "textContent": "A propulsion system for an aircraft includes a core engine that includes a core flow path (C) where a core flow (50) is compressed in a compressor section (24), communicated to a combustor section (30), mixed with a hydrogen-based fuel and ignited to generate a gas flow that is expanded through a turbine section (32). A fuel system (56) is configured to supply a hydrogen based fuel to the combustor (30) through a fuel flow path (62). A condenser (72) is arranged along the core flow path (C) and configured to extract water from the gas flow. An intercooling system (90) receives a portion of water from the condenser (72) for cooling a portion of the core flow (50) at a first location within the compressor section (24). Heated water from the intercooling system (90) is exhausted to a second location within the core flow path (C) downstream of the first location.",
  "title": "INTER-COOLED PREHEAT OF STEAM INJECTED TURBINE ENGINE"
}