{
  "$type": "site.standard.document",
  "description": "The aircraft gas turbine engine has an engine core (10) that is surrounded by a secondary flow channel (29). A side wall (30) is arranged radially outside the secondary flow channel. The radial inner wall (31) of the secondary flow channel is extended similar to that of the side wall. A secondary…",
  "path": "/patents/994035",
  "publishedAt": "2013-01-09T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02K1/08",
    "ROLLS ROYCE DEUTSCHLAND [DE]"
  ],
  "textContent": "The aircraft gas turbine engine has an engine core (10) that is surrounded by a secondary flow channel (29). A side wall (30) is arranged radially outside the secondary flow channel. The radial inner wall (31) of the secondary flow channel is extended similar to that of the side wall. A secondary flow nozzle (32) is arranged between the radial inner wall and the side wall. An adjusting element extended around the peripheral surface of the inner wall, is radially deformed to the outer side. The adjusting element is made of elastic material.",
  "title": "Gas turbine engine with variable bypass nozzle"
}