{
  "$type": "site.standard.document",
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  "description": "An assembly for an aircraft propulsion system (20) includes a compressor section (48), a combustor section (49), a turbine section (50) and a flowpath (110) extending sequentially through the compressor section (48), the combustor section (49) and the turbine section (50). The assembly also…",
  "path": "/patents/1393876",
  "publishedAt": "2025-10-08T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C3/107",
    "RTX CORP [US]"
  ],
  "textContent": "An assembly for an aircraft propulsion system (20) includes a compressor section (48), a combustor section (49), a turbine section (50) and a flowpath (110) extending sequentially through the compressor section (48), the combustor section (49) and the turbine section (50). The assembly also includes a rotating structure (78), a geartrain (82), a propulsor rotor (24) and a turbine (84). The rotating structure (78) includes a turbine rotor (69) within the turbine section (50). The geartrain (82) is coupled to the rotating structure (78). The propulsor rotor (24) is coupled to the geartrain (82). The rotating structure (78) is configured to drive rotation of the propulsor rotor (24) through the geartrain (82). The turbine (84) is coupled to the geartrain (82). The turbine (84) is configured to receive bleed gas from the flowpath (110).",
  "title": "SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM"
}