{
  "$type": "site.standard.document",
  "description": "A compressor for a gas turbine engine with variable inlet guide vanes (42) each defining an airfoil portion (48) twisted such that at each location of the airfoil portion (48) along the pivot axis (P), an angle (±) is defined between a respective chord extending between the leading and trailing…",
  "path": "/patents/982477",
  "publishedAt": "2013-10-30T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D17/165",
    "PRATT & WHITNEY CANADA [CA]"
  ],
  "textContent": "A compressor for a gas turbine engine with variable inlet guide vanes (42) each defining an airfoil portion (48) twisted such that at each location of the airfoil portion (48) along the pivot axis (P), an angle (±) is defined between a respective chord extending between the leading and trailing edges (50, 52) and a same reference plane (54) containing the pivot axis (P) and extending radially with respect to the compressor. The angle, which is measured along a direction of rotation of the rotor, varies from a minimum value near the hub side wall (34) to a maximum value near the shroud side wall (36).",
  "title": "Twisted variable inlet guide vane"
}