{
  "$type": "site.standard.document",
  "description": "A propulsion system for an aircraft includes a core engine (20) generating an exhaust gas flow (55) that is expanded through a turbine section (32), a hydrogen fuel system (52) suppling hydrogen fuel to the combustor (30) through a fuel flow path (45), a condenser (80) extracting water from the…",
  "path": "/patents/1395565",
  "publishedAt": "2025-08-20T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C3/22",
    "RTX CORP [US]"
  ],
  "textContent": "A propulsion system for an aircraft includes a core engine (20) generating an exhaust gas flow (55) that is expanded through a turbine section (32), a hydrogen fuel system (52) suppling hydrogen fuel to the combustor (30) through a fuel flow path (45), a condenser (80) extracting water from the exhaust gas flow (55), an evaporator (112) receiving a portion of the water extracted by the condenser (80) and generating a steam flow (114). The steam flow (114) is injected into a core flow path (25) upstream of the turbine section (32) and a cooled cooling air system (100) uses water extracted from the exhaust gas flow (55) for cooling a cooling airflow (90, 120) communicated to the turbine section (32).",
  "title": "HYDROGEN STEAM INJECTED TURBINE ENGINE WITH COOLED COOLING AIR"
}