{
  "$type": "site.standard.document",
  "description": "A method of operating an aircraft engine coupled to a wing of an aircraft including: setting a pitch of a plurality of rotor blades (128, 208) of a rotor assembly of the aircraft engine at non-uniform pitch angles along a circumferential direction of the aircraft engine such that the plurality of…",
  "path": "/patents/1412558",
  "publishedAt": "2025-10-22T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "B64C11/30",
    "GEN ELECTRIC [US]"
  ],
  "textContent": "A method of operating an aircraft engine coupled to a wing of an aircraft including: setting a pitch of a plurality of rotor blades (128, 208) of a rotor assembly of the aircraft engine at non-uniform pitch angles along a circumferential direction of the aircraft engine such that the plurality of rotor blades (128, 208) define a first pitch at a first position and a second pitch at a second position, wherein the second position is 180 degrees offset from the first position, and wherein the first pitch is different from the second pitch.",
  "title": "AIRCRAFT ENGINE"
}