{
  "$type": "site.standard.document",
  "description": "A method for in-flight monitoring of the health of an aero gas turbine engine (10) comprising in flow series a compressor system (23, 14), a core gas generator including a combustor (16), and a turbine (19), and further comprising a shaft system connecting the turbine to the compressor system and…",
  "path": "/patents/1417519",
  "publishedAt": "2024-07-17T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D21/003",
    "ROLLS ROYCE DEUTSCHLAND LTD & CO KG [DE]"
  ],
  "textContent": "A method for in-flight monitoring of the health of an aero gas turbine engine (10) comprising in flow series a compressor system (23, 14), a core gas generator including a combustor (16), and a turbine (19), and further comprising a shaft system connecting the turbine to the compressor system and forming a torque path there between. The method includes: measuring a first rotational speed of a forward portion of the shaft system; measuring a second rotational speed of a rear portion of the shaft system; measuring other operational parameters of the engine; calculating from the measured rotational speeds the power delivered by the torque path from the turbine (19) to the compressor system (23, 14); calculating from the other measured operational parameters the power delivered to the turbine (19) by the core gas generator; correlating the power delivered by the torque path at a given time with the power delivered to the turbine (19) at that time; and identifying a possible unhealthy condition of the torque path when the correlation departs from an expected correlation of the power delivered by the torque path with the power delivered to the turbine (19).",
  "title": "IN-FLIGHT MONITORING OF AERO ENGINE HEALTH"
}