{
  "$type": "site.standard.document",
  "description": "A gas turbine engine for an aircraft that comprises a shaft fixed to a compressor of the gas turbine engine; at least one of a turboprop and a turbofan; a power gearbox having a power output shaft fixed to the at least one of the turboprop and the turbofan, wherein the power gearbox receives an…",
  "path": "/patents/1421476",
  "publishedAt": "2025-08-06T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D25/20",
    "ROLLS ROYCE CORP [US]"
  ],
  "textContent": "A gas turbine engine for an aircraft that comprises a shaft fixed to a compressor of the gas turbine engine; at least one of a turboprop and a turbofan; a power gearbox having a power output shaft fixed to the at least one of the turboprop and the turbofan, wherein the power gearbox receives an input rotation from the shaft; an auxiliary gearbox having an auxiliary output shaft powering at least one auxiliary component of the gas turbine engine; a first lubrication system; and a second lubrication system that is separated from the first lubrication system. The first lubrication system circulates a first lubricant through the power gearbox and the second lubrication system circulates a second lubricant through the auxiliary gearbox. A method is also disclosed.",
  "title": "GAS TURBINE ENGINE HAVING FIRST AND SECOND LUBRICATION SYSTEMS AND ASSOCIATED METHOD"
}