{
  "$type": "site.standard.document",
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  "description": "An aircraft engine (10), has: an inlet (12) leading to a compressor section (13), the inlet (12) extending circumferentially around a central axis (A); an annular inlet duct (22) extending circumferentially around the central axis (A), the annular inlet duct (22) having a duct inlet (22A) fluidly…",
  "path": "/patents/1394142",
  "publishedAt": "2025-09-24T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "B64D33/02",
    "PRATT & WHITNEY CANADA [CA]"
  ],
  "textContent": "An aircraft engine (10), has: an inlet (12) leading to a compressor section (13), the inlet (12) extending circumferentially around a central axis (A); an annular inlet duct (22) extending circumferentially around the central axis (A), the annular inlet duct (22) having a duct inlet (22A) fluidly connected to an environment outside of the aircraft engine (10) and a duct outlet (22D) fluidly connected to the inlet (22A), the duct outlet (22D) extending circumferentially around the central axis (A); and a flow restrictor (26) located within the annular inlet duct (22), the flow restrictor (26) extending across the annular inlet duct (22), being movable within the annular inlet duct (22) along a circumferential direction (D1) relative to the central axis (A) in response to a fluid pressure differential on opposed sides of the flow restrictor (26).",
  "title": "AIRCRAFT ENGINE INTAKE DUCT WITH PASSIVELY MOVABLE FLOW RESTRICTOR"
}