{
  "$type": "site.standard.document",
  "description": "The gas turbine has a core engine (10) which surrounds a bypass duct (29). A supercharger (30) is provided in the inlet region of the core engine. A discharge channel is provided for supplying flow of air from the supercharger in the bypass duct. A fan (12) is located downstream to the bypass duct…",
  "path": "/patents/983263",
  "publishedAt": "2013-10-16T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D9/04",
    "ROLLS ROYCE DEUTSCHLAND [DE]"
  ],
  "textContent": "The gas turbine has a core engine (10) which surrounds a bypass duct (29). A supercharger (30) is provided in the inlet region of the core engine. A discharge channel is provided for supplying flow of air from the supercharger in the bypass duct. A fan (12) is located downstream to the bypass duct provided with the guide vanes (32). A blade root of the guide vane is formed as the core engine superimposing structural element downstream and the bypass duct is made to open in the drainage channel.",
  "title": "Aircraft gas turbine engine having a bleed channel in a guide vane root element of a bypass channel"
}