{
  "$type": "site.standard.document",
  "description": "A gas turbine engine (10) comprises an engine core having high and low pressure compressors (15, 14) and high and low pressure turbines (17, 19). The engine further comprises a fan (23) coupled to a low pressure shaft (26) and the low pressure turbine (19) by a reduction gearbox (30). The low…",
  "path": "/patents/1417733",
  "publishedAt": "2025-06-04T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C3/06",
    "ROLLS ROYCE PLC [GB]"
  ],
  "textContent": "A gas turbine engine (10) comprises an engine core having high and low pressure compressors (15, 14) and high and low pressure turbines (17, 19). The engine further comprises a fan (23) coupled to a low pressure shaft (26) and the low pressure turbine (19) by a reduction gearbox (30). The low pressure compressor (14) comprises no more than two compressor stages (41, 42), and the low and high pressure compressor (14, 15) together define a cruise overall core pressure ratio of between 30 and 50.",
  "title": "GAS TURBINE ENGINE"
}