{
  "$type": "site.standard.document",
  "description": "A vane assembly (20) for a gas turbine engine having an outer casing surrounding rotating blades of a rotor, the assembly comprising:a tubular wall portion (68) of the outer casing located downstream of the blades, the wall portion having a series of circumferentially and regularly spaced apart…",
  "path": "/patents/995080",
  "publishedAt": "2012-12-19T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D9/042",
    "PRATT & WHITNEY CANADA [CA]"
  ],
  "textContent": "A vane assembly (20) for a gas turbine engine having an outer casing surrounding rotating blades of a rotor, the assembly comprising:a tubular wall portion (68) of the outer casing located downstream of the blades, the wall portion having a series of circumferentially and regularly spaced apart openings (74) defined therethrough; an inner shroud located inwardly of and concentric with the wall portion, the inner shroud and wall portion defining a flow path therebetween; a grommet (66) sealingly engaged in each one of the openings, the grommet having a slot defined therethrough; and a vane (30) for each grommet (66) and extending radially between the wall portion and the inner shroud, each said vane (30) having an airfoil portion (36) extending between a tip (34) and a vane root (32), the tip (34) being engaged to the inner shroud, the vane root (32) including an outer platform (46) and an inner button portion (58) interconnecting the platform (46) and the airfoil portion (36), the platform (46) being located outside of the outer casing and having a configuration preventing the platform from passing through the corresponding opening (74), the airfoil portion (36) having a configuration allowing the airfoil to pass through the slot of the grommet (66), and the button portion (58) being sealingly received in the slot of the grommet (66).",
  "title": "Vane assembly with improved vane roots"
}