{
  "$type": "site.standard.document",
  "description": "An aircraft propulsion system (12) includes a fan section (14) that includes a fan shaft (16) that is rotatable about a fan axis (26) and that includes a fan gear (24). The aircraft propulsion system (12) also includes a boost turbine engine (28) that includes a first output shaft (32) that…",
  "path": "/patents/1420259",
  "publishedAt": "2025-11-12T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C3/107",
    "RTX CORP [US]"
  ],
  "textContent": "An aircraft propulsion system (12) includes a fan section (14) that includes a fan shaft (16) that is rotatable about a fan axis (26) and that includes a fan gear (24). The aircraft propulsion system (12) also includes a boost turbine engine (28) that includes a first output shaft (32) that includes a first gear (34) that is coupled to the fan gear (24) and has a first maximum power capacity. The aircraft propulsion system (12) further includes a cruise gas turbine engine (30) that includes a second output shaft (58) that includes a second gear (60) that is coupled to the fan gear (34) and has a second maximum power capacity that is less than the first maximum power. The fan section (14) produces a thrust that corresponds to power input through the fan gear (34) from the boost turbine engine (28) and the cruise turbine engine (30).",
  "title": "MULTI CORE GEARED GAS TURBINE ENGINE"
}