{
  "$type": "site.standard.document",
  "description": "A reduction gear box (20) is part of a gas turbine engine (10) and includes a casing (32) and reduction epicyclic gear stages (22, 24) within the casing (32). The reduction gear stages (22, 24) comprise at least an epicyclic array of gears meshing together with at least one planetary gear (34)…",
  "path": "/patents/967648",
  "publishedAt": "2014-11-05T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D25/18",
    "PRATT & WHITNEY CANADA [CA]"
  ],
  "textContent": "A reduction gear box (20) is part of a gas turbine engine (10) and includes a casing (32) and reduction epicyclic gear stages (22, 24) within the casing (32). The reduction gear stages (22, 24) comprise at least an epicyclic array of gears meshing together with at least one planetary gear (34) mounted for rotation on a gear carrier (38) and a bearing (39) associated therewith. A lubricating oil delivery system is provided within the casing (32), surrounding a portion of the gear carrier (38). The oil delivery system includes a conduit (50); a closed oil reservoir (54); a first metered opening (58) communicating the conduit with the reservoir (54) and a plurality of metered outlet openings (60, 62, 64) communicating the reservoir (54) with the gear carrier (38) and the bearing (39) such that the reservoir (54) is filled with oil in normal flight operating conditions and the oil trapped in the reservoir (54) is released to the carrier (38) and bearing (39) when a temporary drop in the oil system pressure occurs.",
  "title": "Lubrication oil system for a reduction gearbox"
}