{
  "$type": "site.standard.document",
  "description": "An aircraft gas turbine engine (10) has a row of FLADE fan blades (5) disposed radially outwardly of and drivingly connected to a fan (31) in the engine's fan section (14). The FLADE fan blades (5) extend across a FLADE duct (3) circumscribing the fan section (14). A two dimensional air discharge…",
  "path": "/patents/1000630",
  "publishedAt": "2012-07-04T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C9/20",
    "GEN ELECTRIC [US]"
  ],
  "textContent": "An aircraft gas turbine engine (10) has a row of FLADE fan blades (5) disposed radially outwardly of and drivingly connected to a fan (31) in the engine's fan section (14). The FLADE fan blades (5) extend across a FLADE duct (3) circumscribing the fan section (14). A two dimensional air discharge passage (81) is in fluid flow communication with the FLADE duct (3) and with FLADE air upstream and downstream discharge slots (400, 402) in a divergent flap (360) of a two dimensional exhaust nozzle (300). A valve fully closes the upstream slot (400) when the downstream slot (402) is fully opened and fully opens the upstream slot (400) when the downstream slot (402) is fully closed. The upstream and downstream slots (400, 402) may be located upstream and downstream respectfully of a nozzle discharge area (408) in the nozzle (300). A sliding deck (412) slides aft or down to open upstream slot (400) and close downstream slot (402) and slides forward or up to close upstream slot (400) and open downstream slot (402).",
  "title": "Flade discharge in 2-d exhaust nozzle"
}