{
  "$type": "site.standard.document",
  "coverImage": {
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  "description": "An aircraft engine (10), has: an inlet (12) extending circumferentially around a central axis (A); an annular inlet duct (22) having a duct inlet (22A) fluidly connected to an environment outside of the aircraft engine (10) and a duct outlet (220) fluidly connected to the inlet (22A); a flow…",
  "path": "/patents/1394156",
  "publishedAt": "2025-10-01T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D17/08",
    "PRATT & WHITNEY CANADA [CA]"
  ],
  "textContent": "An aircraft engine (10), has: an inlet (12) extending circumferentially around a central axis (A); an annular inlet duct (22) having a duct inlet (22A) fluidly connected to an environment outside of the aircraft engine (10) and a duct outlet (220) fluidly connected to the inlet (22A); a flow restrictor (26) extending across the annular inlet duct (22) and being movable within the annular inlet duct (22); an actuator (31) engaged to the flow restrictor (26) and operable to move the flow restrictor (26); and a controller (34) operatively connected to at least one sensor (32A, 328, 33A, 33B) and the actuator (31), the controller (34) having a processing unit (702) and a computer-readable medium (704) operatively connected to the processing unit (702) and containing instructions (706) for: receiving a signal indicative of a pressure difference between opposite sides of the flow restrictor (26); and powering the actuator (31) to move the flow restrictor (26) with the actuator (31) from a first position to a second position offset form the first position as a function of the pressure difference.",
  "title": "AIRCRAFT INTAKE DUCT WITH ACTIVELY MOVABLE FLOW RESTRICTOR"
}