{
  "$type": "site.standard.document",
  "description": "The engine has core engine unit (1) comprising high pressure turbine (6) and downstream low pressure turbine (7). The core engine unit is surrounded by a bypass duct (18) and mixer (19) is arranged in an inlet portion of low pressure turbine. The bypass flow path extended from bypass duct and core…",
  "path": "/patents/1008518",
  "publishedAt": "2011-10-19T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D25/08",
    "ROLLS ROYCE DEUTSCHLAND [DE]"
  ],
  "textContent": "The engine has core engine unit (1) comprising high pressure turbine (6) and downstream low pressure turbine (7). The core engine unit is surrounded by a bypass duct (18) and mixer (19) is arranged in an inlet portion of low pressure turbine. The bypass flow path extended from bypass duct and core flow path extended from core flow path are connected to the mixer. An independent claim is included for method of using aircraft gas turbine engine.",
  "title": "Aircraft gas turbine drive"
}