Patent ID: 11939926
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. An assembly for an aircraft propulsion system, comprising:
a compressor section, a combustor section, a turbine section and a flowpath extending sequentially through the compressor section, the combustor section and the turbine section;
a rotating structure comprising a turbine rotor within the turbine section;
a geartrain coupled to the rotating structure;
a propulsor rotor coupled to the geartrain, the rotating structure configured to drive rotation of the propulsor rotor through the geartrain;
a turbine coupled to the geartrain, the turbine configured to receive bleed gas from the flowpath; and
the geartrain comprising:
a sun gear coupled to the propulsor rotor;
a ring gear coupled to the turbine;
a plurality of intermediate gears, each of the plurality of intermediate gears between and meshed with the sun gear and the ring gear; and
a carrier coupled to the rotating structure, each of the plurality of intermediate gears rotatably mounted to the carrier.