{
  "$type": "site.standard.document",
  "description": "A gas turbine engine (20) includes a turbine section (28) that includes a fan drive turbine (46). A geared architecture (48) includes a sun gear (70) in driving engagement with the fan drive turbine (46). A plurality of planet gears (74) surrounds the sun gear (70). A ring gear (78) surrounds the…",
  "path": "/patents/1412947",
  "publishedAt": "2024-09-25T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D25/34",
    "RTX CORP [US]"
  ],
  "textContent": "A gas turbine engine (20) includes a turbine section (28) that includes a fan drive turbine (46). A geared architecture (48) includes a sun gear (70) in driving engagement with the fan drive turbine (46). A plurality of planet gears (74) surrounds the sun gear (70). A ring gear (78) surrounds the plurality of planet gears (74). A deflection limiter (84A-D) mechanically attaches the ring gear (78) to an engine static structure (36). The deflection limiter (84A-D) includes a first support (86A-D) fixed to the ring gear (78) that has a first interlocking feature and a second support (88A-D) fixed to the engine static structure (36) that has a second interlocking feature. The first and second interlocking features define at least one of a radial clearance (94A-D) of between 0.005 inches (0.127 mm) and 0.080 inches (2.032 mm) or a circumferential clearance (96A-D)of between 0.005 inches (0.127 mm) and 0.250 inches (6.350 mm). A fan section (22) includes a plurality of fan blades (42) in driving engagement with the geared architecture (48) through a fan drive shaft (82).",
  "title": "DEFLECTION LIMITER FOR A GAS TURBINE ENGINE"
}