{
  "$type": "site.standard.document",
  "coverImage": {
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  "description": "A gas turbine engine (20) includes a fan section (22) including a fan (42) with fan blades (43). The fan section (22) drives air along a bypass flow path (B) in a bypass duct (13). A gear reduction (48) is in driving engagement with the fan (42). The gear reduction (48) is a planetary gear system…",
  "path": "/patents/1400480",
  "publishedAt": "2025-09-03T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C3/107",
    "RTX CORP [US]"
  ],
  "textContent": "A gas turbine engine (20) includes a fan section (22) including a fan (42) with fan blades (43). The fan section (22) drives air along a bypass flow path (B) in a bypass duct (13). A gear reduction (48) is in driving engagement with the fan (42). The gear reduction (48) is a planetary gear system (48). A low spool (30) includes a low pressure turbine (46) that drives a low pressure compressor (44) and drives the gear reduction (48) to drive the fan (42) at a speed slower than the low pressure turbine (46). A high spool (32) includes a high pressure turbine (54) that drives a high pressure compressor (52). A first low spool support bearing (38A) is located axially between the low pressure compressor (44) and the gear reduction (48). A second low spool support bearing (38B) is located axially between the low pressure compressor (44) and the high pressure compressor (52).",
  "title": "STRADDLE MOUNTED LOW PRESSURE COMPRESSOR"
}