{
  "$type": "site.standard.document",
  "description": "A turbofan engine includes a fan section. A turbine section is in driving engagement with the fan section through a geared architecture (48A). A flexible support (96A) supports the geared architecture (48A) relative to an engine static structure (36). A deflection limiter (150A) includes at least…",
  "path": "/patents/1421700",
  "publishedAt": "2023-09-27T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C7/06",
    "RAYTHEON TECH CORP [US]"
  ],
  "textContent": "A turbofan engine includes a fan section. A turbine section is in driving engagement with the fan section through a geared architecture (48A). A flexible support (96A) supports the geared architecture (48A) relative to an engine static structure (36). A deflection limiter (150A) includes at least one of an axially extending branch or a radially extending branch. A flexible output shaft (120) is in driving engagement with the fan section and driven by the geared architecture (48A). A speed change mechanism for a gas turbine engine is also disclosed.",
  "title": "GEARED ARCHITECTURE FOR GAS TURBINE ENGINE"
}