{
  "$type": "site.standard.document",
  "description": "A gas turbine engine (100) includes a fan shaft (110) rotatable about an axis (A), a fan (112) connected to the fan shaft (110), and an outer housing (114) surrounding the fan (112) to define a bypass passage (B). A compressor section (24) has both a low pressure compressor (106) that is fixed to…",
  "path": "/patents/1392213",
  "publishedAt": "2026-02-25T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C3/107",
    "RTX CORP [US]"
  ],
  "textContent": "A gas turbine engine (100) includes a fan shaft (110) rotatable about an axis (A), a fan (112) connected to the fan shaft (110), and an outer housing (114) surrounding the fan (112) to define a bypass passage (B). A compressor section (24) has both a low pressure compressor (106) that is fixed to rotate with the fan shaft (116) and a high pressure compressor (124). A turbine section (28) has a low pressure turbine (104) driving a low speed spool (116) and a high pressure turbine (122) driving the high pressure compressor (124). The low pressure turbine (104) includes rotating blades and a static structure (130) aft of the rotating blades. A fan drivetrain (120) includes a geared architecture (102) connecting the low speed spool (116) to the fan shaft (110) such that the fan (112) and low pressure compressor (106) rotate at a lower speed than the low pressure turbine (104). A thrust bearing (132) is axially aft of the geared architecture (102) and axially forward of the high pressure compressor (122). A tower shaft (140) is rotatably driven by the low speed spool (116).",
  "title": "GEARED TURBOFAN WITH OVER-SPEED PROTECTION"
}