{
  "$type": "site.standard.document",
  "description": "A gas turbine engine (10) for an aircraft includes at least a low pressure spool (26) with a low pressure turbine shaft (24) operatively connected to at least one turbine (20), the low pressure turbine shaft (24) rotatable about an engine axis, and a low pressure compressor (12) operatively…",
  "path": "/patents/1420731",
  "publishedAt": "2023-09-20T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "B64C29/0041",
    "PRATT & WHITNEY CANADA [CA]"
  ],
  "textContent": "A gas turbine engine (10) for an aircraft includes at least a low pressure spool (26) with a low pressure turbine shaft (24) operatively connected to at least one turbine (20), the low pressure turbine shaft (24) rotatable about an engine axis, and a low pressure compressor (12) operatively connected to a low pressure compressor shaft (32) that is independently rotatable relative to the low pressure turbine shaft (24). A differential gearbox (30; 130) has an input operatively connected to the low pressure turbine shaft (24), a first output and a second output, the first output of the differential gearbox operatively connected to the low pressure compressor shaft (32) and the second output of the differential gearbox (30; 130) operatively connected to an output shaft (26) of the gas turbine engine (10). The differential gearbox (30; 130) permits the output shaft (26), the low pressure compressor shaft (32) and the low pressure turbine shaft (24) to rotate at different speeds.",
  "title": "GAS TURBINE ENGINE WITH VARIABLE SPEED OUTPUT"
}