{
  "$type": "site.standard.document",
  "description": "A gas turbine engine (10) comprising an oil system (50) and a gearbox (33), the gearbox (33) is driven by at least one engine shaft (23, 24, 25), the oil system (50) comprises a pump (38) drivingly connected to the gearbox (33), an oil tank (42) connected to the pump (38) via a supply pipe (46) and…",
  "path": "/patents/1068195",
  "publishedAt": "2006-04-19T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D25/20",
    "ROLLS ROYCE PLC [GB]"
  ],
  "textContent": "A gas turbine engine (10) comprising an oil system (50) and a gearbox (33), the gearbox (33) is driven by at least one engine shaft (23, 24, 25), the oil system (50) comprises a pump (38) drivingly connected to the gearbox (33), an oil tank (42) connected to the pump (38) via a supply pipe (46) and a delivery pipe (47) connecting the pump to the engine (10) for delivery of oil thereto, an anti-siphon pipe (52) is connected between the tank (42) and the delivery pipe (47) to provide an excess oil flow to the engine (10) characterised in that the anti-siphon pipe (52) includes a variable flow valve (60) for regulating the flow of oil passing therethrough such that at low engine speeds an adequate supply of oil is provided to a sight glass (54) in the tank (42).",
  "title": "Adequate oil supply for an aeroengine oil tank system"
}