{
  "$type": "site.standard.document",
  "description": "A gas turbine engine (10) includes a core section (12) having a low spool (58), intermediate spool (60) and a high spool (62) that rotate about a common axis (A). The intermediate spool (60) is supported at an aft position by an inter-shaft bearing arrangement (48) on the low spool (58). The low…",
  "path": "/patents/993329",
  "publishedAt": "2013-01-30T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D25/162",
    "UNITED TECHNOLOGIES CORP [US]"
  ],
  "textContent": "A gas turbine engine (10) includes a core section (12) having a low spool (58), intermediate spool (60) and a high spool (62) that rotate about a common axis (A). The intermediate spool (60) is supported at an aft position by an inter-shaft bearing arrangement (48) on the low spool (58). The low spool (58) is supported for rotation in an aft position by an aft roller bearing (46) supported on a turbine exhaust case (36) of the gas turbine engine (10). The high spool (62) is supported by a high spool aft roller bearing (64) disposed within a high spool bearing compartment (50). The high spool bearing compartment (50) is positioned within a radial space (66) between the combustor (26) and the axis (A).",
  "title": "Three spool engine bearing configuration"
}