{
  "$type": "site.standard.document",
  "description": "A gas turbine engine (1) has an annular bypass duct (4) defined between a fan nacelle (2) and a core fairing (3) through which fan air is discharged. One or more bifurcator members (5a-5i) are positioned inside the exit of the bypass duct (4) to bifurcate the air flow in the bypass duct around the…",
  "path": "/patents/1008074",
  "publishedAt": "2011-11-02T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "B64D33/06",
    "ROLLS ROYCE PLC [GB]"
  ],
  "textContent": "A gas turbine engine (1) has an annular bypass duct (4) defined between a fan nacelle (2) and a core fairing (3) through which fan air is discharged. One or more bifurcator members (5a-5i) are positioned inside the exit of the bypass duct (4) to bifurcate the air flow in the bypass duct around the bifurcator members (5a-5i) prior to exiting the bypass duct (4). The bifurcator members (5a-5i) modify the flow field of the air in the bypass duct radially and/or tangentially with respect to the axis of the annular bypass duct (4).",
  "title": "Gas turbine engine"
}