{
  "$type": "site.standard.document",
  "description": "A gas turbine engine (10) includes a turbine (12) and a compressor (14) in rotational communication with the turbine via a shaft (16). The shaft is rotatable about a longitudinal centerline (18) and includes a first axial end (20, 22) and a second axial end (20, 22) opposite the first axial end…",
  "path": "/patents/1418162",
  "publishedAt": "2025-10-29T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D25/16",
    "RTX CORP [US]"
  ],
  "textContent": "A gas turbine engine (10) includes a turbine (12) and a compressor (14) in rotational communication with the turbine via a shaft (16). The shaft is rotatable about a longitudinal centerline (18) and includes a first axial end (20, 22) and a second axial end (20, 22) opposite the first axial end. The gas turbine engine further includes a first bearing compartment (26, 28) including a first compartment casing (32) detachably mounted axially outside the compressor and the turbine. The first bearing compartment is in contact with the first axial end of the shaft and includes a first bearing (30) which rotatably supports the shaft. The first bearing compartment is self-contained such that an internal lubrication system (44) of the first bearing compartment is fluidally isolated from a remainder of the gas turbine engine outside the first bearing compartment.",
  "title": "MODULAR BEARING COMPONENT"
}