{
  "$type": "site.standard.document",
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  "description": "A geared turbofan engine (10) includes a first rotor (20), a fan (28), a second rotor, a gear train (26), a fan casing, a nacelle (12) and a plurality of discrete acoustic liner segments (38a, 38b, 38c, 38d, 38e, 38f). The fan (28) is connected to the first rotor (20) and is capable of rotation at…",
  "path": "/patents/1409201",
  "publishedAt": "2026-03-11T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D25/24",
    "RTX CORP [US]"
  ],
  "textContent": "A geared turbofan engine (10) includes a first rotor (20), a fan (28), a second rotor, a gear train (26), a fan casing, a nacelle (12) and a plurality of discrete acoustic liner segments (38a, 38b, 38c, 38d, 38e, 38f). The fan (28) is connected to the first rotor (20) and is capable of rotation at frequencies between 200 and 6000 Hz and has a fan pressure ratio of between 1.25 and 1.60. The gear train (26) connects the first rotor (20) to the second rotor. The fan casing and nacelle (12) are arranged circumferentially about a centerline (CL) and define a bypass flow duct (30) in which the fan (28) is disposed. The plurality of discrete acoustic liner segments (38a, 38b, 38c, 38d, 38e, 38f) with varied geometric properties are disposed along the bypass flow duct (30).",
  "title": "ACOUSTIC LINER WITH VARIED PROPERTIES"
}