{
  "$type": "site.standard.document",
  "description": "A nacelle assembly for a high-bypass gas turbine engine (10) includes a fan nacelle (34) that includes a first fan nacelle section (34A) and a second fan nacelle section (34B), the second fan nacelle section (34B) movable relative to the first fan nacelle section (34A). A cascade array (56) is…",
  "path": "/patents/1010350",
  "publishedAt": "2011-08-10T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02K1/68",
    "UNITED TECHNOLOGIES CORP [US]"
  ],
  "textContent": "A nacelle assembly for a high-bypass gas turbine engine (10) includes a fan nacelle (34) that includes a first fan nacelle section (34A) and a second fan nacelle section (34B), the second fan nacelle section (34B) movable relative to the first fan nacelle section (34A). A cascade array (56) is mounted to the first fan nacelle section (34A) for movement relative thereto between a stored position and a deployed position, the stored position locates the cascade array (56) at least partially within the first fan nacelle section (34A).",
  "title": "Translatable cascade thrust reverser"
}