{
  "$type": "site.standard.document",
  "description": "A gas turbine engine 101 for an aircraft comprises a high-pressure (HP) spool comprising an HP compressor 105 and a first electric machine 117 driven by an HP turbine 107; a low-pressure (LP) spool comprising an LP compressor 104 and a second electric machine 119 driven by an LP turbine 108; a…",
  "path": "/patents/1434415",
  "publishedAt": "2022-08-31T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "B64D15/00",
    "ROLLS ROYCE PLC [GB]"
  ],
  "textContent": "A gas turbine engine 101 for an aircraft comprises a high-pressure (HP) spool comprising an HP compressor 105 and a first electric machine 117 driven by an HP turbine 107; a low-pressure (LP) spool comprising an LP compressor 104 and a second electric machine 119 driven by an LP turbine 108; a combustion system 106 comprising a fuel metering unit; and an engine controller 123 configured to, in response to a change of a power lever angle setting indicative of a deceleration event, reduce fuel flow to the combustion system 106 by the fuel metering unit, and to operate the first electric machine 117 in a generator mode to reduce the HP spool rotational speed and engine core mass flow.",
  "title": "IMPROVING DECELERATION OF A GAS TURBINE"
}