{
  "$type": "site.standard.document",
  "description": "A gas turbine engine 200, 200', 200\" for mounting to an airframe of an aircraft comprises an engine core 210; a fan 214 located upstream of the engine core 210; a bifurcation 204 spanning a bypass duct 202 defined between the engine core 210 and a nacelle 221 surrounding the gas turbine engine 200…",
  "path": "/patents/1410642",
  "publishedAt": "2024-06-26T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "B64D13/02",
    "ROLLS ROYCE PLC [GB]"
  ],
  "textContent": "A gas turbine engine 200, 200', 200\" for mounting to an airframe of an aircraft comprises an engine core 210; a fan 214 located upstream of the engine core 210; a bifurcation 204 spanning a bypass duct 202 defined between the engine core 210 and a nacelle 221 surrounding the gas turbine engine 200, 200', 200\", the bifurcation 204 comprising aerodynamically shaped fairings 206 defining an interior space 208 therebetween; and a cabin blower system 100 arranged in the interior space 208 of the bifurcation 204.",
  "title": "GAS TURBINE ENGINE WITH CABIN BLOWER SYSTEM"
}