{
  "$type": "site.standard.document",
  "description": "A gas turbine engine (10) comprising: a core nacelle defined about an engine centerline axis; a fan nacelle mounted at least partially around core nacelle to define a fan bypass airflow path for a fan bypass airflow; a gear train (22, 25) defined along an engine centerline axis, said gear train…",
  "path": "/patents/984694",
  "publishedAt": "2013-07-03T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C3/107",
    "UNITED TECHNOLOGIES CORP [US]"
  ],
  "textContent": "A gas turbine engine (10) comprising: a core nacelle defined about an engine centerline axis; a fan nacelle mounted at least partially around core nacelle to define a fan bypass airflow path for a fan bypass airflow; a gear train (22, 25) defined along an engine centerline axis, said gear train defines a gear reduction ratio of greater than or equal to about 2.3; a spool along said engine centerline axis which drives said gear train, said spool includes a three to six (3-6) stage low pressure turbine; and a fan variable area nozzle axially movable relative to said fan nacelle to vary a fan nozzle exit area (44) and adjust a pressure ratio of the fan bypass airflow during engine operation.",
  "title": "Gas turbine engine with low stage count low pressure turbine"
}