{
  "$type": "site.standard.document",
  "description": "A gas turbine engine (10) for an aircraft comprises: an engine core (11) comprising: a compressor system comprising a lower pressure compressor (14) and a higher pressure compressor (15); and an outer core casing (70) surrounding the compressor system. The gas turbine engine further comprises a fan…",
  "path": "/patents/1437207",
  "publishedAt": "2022-06-08T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D25/243",
    "ROLLS ROYCE PLC [GB]"
  ],
  "textContent": "A gas turbine engine (10) for an aircraft comprises: an engine core (11) comprising: a compressor system comprising a lower pressure compressor (14) and a higher pressure compressor (15); and an outer core casing (70) surrounding the compressor system. The gas turbine engine further comprises a fan (23) located upstream of the engine core (11), the fan comprising a plurality of fan blades (23a) and having a fan diameter (112). The outer core casing comprises a first flange connection (60) having a first flange radius (104). A fan diameter ratio of:",
  "title": "GAS TURBINE ENGINE WITH IMPROVED BENDING RESISTANCE"
}