{
  "$type": "site.standard.document",
  "description": "The aircraft gas turbine engine has an engine core (10) that is surrounded by a secondary flow channel. An annular cooling element (30) is arranged in the region of a radial inner wall (21) of the secondary flow channel, corresponding to the downstream direction of guide vanes (31). The annular…",
  "path": "/patents/994053",
  "publishedAt": "2013-01-09T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02K3/06",
    "ROLLS ROYCE DEUTSCHLAND & CO KG [DE]"
  ],
  "textContent": "The aircraft gas turbine engine has an engine core (10) that is surrounded by a secondary flow channel. An annular cooling element (30) is arranged in the region of a radial inner wall (21) of the secondary flow channel, corresponding to the downstream direction of guide vanes (31). The annular cooling element is provided as a surface cooling element. The guide vanes are connected with the annular cooling element, for transferring heat with the annular cooling element. Cooling passages are formed in circumferential direction of annular cooling element.",
  "title": "Turbofan engine with heat exchanger on the core engine housing"
}