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

Claim 16:
17. An assembly for an aircraft propulsion system, comprising:
a propulsor rotor;
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 propulsor rotor;
an air turbine configured to receive bleed air from the compressor section, the air turbine configured to drive rotation of the propulsor rotor; and
an epicyclic geartrain comprising:
a sun gear coupled to the propulsor rotor;
a ring gear coupled to the air 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.