{
  "$type": "site.standard.document",
  "description": "A gas turbine engine (20) includes a fan section (22). A turbine section (28) is coupled to the fan section (22) via a geared architecture (48). The geared architecture (48) includes a torque frame (68) and a flex support (72) spaced apart from one another at a location. A gear train is supported…",
  "path": "/patents/1425870",
  "publishedAt": "2023-03-08T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D15/12",
    "RAYTHEON TECH CORP [US]"
  ],
  "textContent": "A gas turbine engine (20) includes a fan section (22). A turbine section (28) is coupled to the fan section (22) via a geared architecture (48). The geared architecture (48) includes a torque frame (68) and a flex support (72) spaced apart from one another at a location. A gear train is supported by the torque frame (68). A damper (78) is provided between the torque frame (68) and the flex support (72) at the location.",
  "title": "GAS TURBINE ENGINE FAN DRIVE GEAR SYSTEM DAMPER"
}