{
  "$type": "site.standard.document",
  "description": "A method of operating a variable guide vane assembly (40) of an aircraft engine (10), the variable guide vane assembly (40) including guide vanes (42) rotatable about respective spanwise axes (S1) and circumferentially distributed about a central axis (11), the method comprising: obtaining a target…",
  "path": "/patents/1388329",
  "publishedAt": "2025-07-30T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D17/14",
    "PRATT & WHITNEY CANADA [CA]"
  ],
  "textContent": "A method of operating a variable guide vane assembly (40) of an aircraft engine (10), the variable guide vane assembly (40) including guide vanes (42) rotatable about respective spanwise axes (S1) and circumferentially distributed about a central axis (11), the method comprising: obtaining a target exit flow angle defined between a direction of a flow exiting the guide vanes (42) and the central axis (11); predicting an exit flow angle (T2; T2') as a function of at least a geometric angle (T1), the exit flow angle (T2; T2') defined between the direction of the flow (F1; F1') exiting the guide vanes (42) and the central axis (11), the geometric angle (T1) defined between the guide vanes (42) and the central axis (11); and when a difference between the exit flow angle (T2; T2') and the target exit flow angle is above a threshold, modulating the guide vanes (42) to modify the geometric angle (T1) until the difference between the exit flow angle (T2; T2') and the target exit flow angle is at or below the threshold.",
  "title": "VARIABLE GUIDE VANE ASSEMBLY AND CONTROL SYSTEM THEREOF"
}