{
  "$type": "site.standard.document",
  "description": "A gas turbine engine (10) for an aircraft comprises an engine core (11); a fan (23) located upstream of the engine core (11) and having a fan diameter (112); a nacelle (21) surrounding the engine core (11) and defining a bypass duct (22) between the engine core (11) and the nacelle (21); a first…",
  "path": "/patents/1437274",
  "publishedAt": "2022-06-08T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D25/162",
    "ROLLS ROYCE PLC [GB]"
  ],
  "textContent": "A gas turbine engine (10) for an aircraft comprises an engine core (11); a fan (23) located upstream of the engine core (11) and having a fan diameter (112); a nacelle (21) surrounding the engine core (11) and defining a bypass duct (22) between the engine core (11) and the nacelle (21); a first (14) and a second compressor (15); an outer core casing (76) comprising a flange connection (60) and a fan outlet guide vane (OGV) (58) extending radially across the bypass duct (22), the fan OGV (58) having a radially inner edge (58a) and a radially outer edge (58b), wherein an axial midpoint of the radially inner edge (58a) is defined as the fan OGV root centrepoint (58a). A fan OGV root position ratio of: axial distance (108) between flange connection and fan OGV root centrepoint vs. flange radius (104) is equal to or less than 2.6.",
  "title": "GAS TURBINE ENGINE WITH FAN OUTLET GUIDE VANES"
}