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

Claim 15:
16. An assembly for an aircraft propulsion system, comprising:
a first propulsor rotor;
a second propulsor rotor;
a geartrain;
an engine core including a compressor section, a combustor section, a turbine section, a flowpath and a rotating structure, the flowpath extending through the compressor section, the combustor section and the turbine section, the rotating structure comprising a turbine rotor within the turbine section, and the rotating structure configured to drive rotation of the first propulsor rotor and the second propulsor rotor through the geartrain;
a turbine configured to drive rotation of the second propulsor rotor through the geartrain, the turbine configured to receive bleed gas from the flowpath; and
the geartrain comprising:
a sun gear coupled to the second 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 and the first propulsor rotor,

each of the plurality of intermediate gears rotatably mounted to the carrier.