{
  "$type": "site.standard.document",
  "coverImage": {
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  "description": "A gas turbine engine system comprises a nacelle (28), a gas turbine engine (10) within the nacelle (28), and a fan bypass passage (30) between the nacelle (28) and the gas turbine engine (10). A nozzle (40) having a cross-sectional area is associated with a bypass air flow through the fan bypass…",
  "path": "/patents/1007309",
  "publishedAt": "2011-12-14T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02K1/11",
    "UNITED TECHNOLOGIES CORP [US]"
  ],
  "textContent": "A gas turbine engine system comprises a nacelle (28), a gas turbine engine (10) within the nacelle (28), and a fan bypass passage (30) between the nacelle (28) and the gas turbine engine (10). A nozzle (40) having a cross-sectional area is associated with a bypass air flow through the fan bypass passage (30), the nozzle (40) having at least one section (40a) that is selectively moveable between a plurality of static positions for varying the cross-sectional and at least one thrust reverse position that is different from the plurality of static positions for reversing a direction of the bypass flow of the fan bypass passage (30). The system further comprises a controller (44) for selectively moving the at least one section (40a) responsive to one of a plurality of operational states of the gas turbine engine (10).",
  "title": "Gas turbine engine system and corresponding controlling method"
}