US 11,939,926 B2
Selective power distribution for an aircraft propulsion system
Paul R. Hanrahan, Sedona, AZ (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Aug. 16, 2022, as Appl. No. 17/888,955.
Prior Publication US 2024/0060453 A1, Feb. 22, 2024
Int. Cl. F02C 7/36 (2006.01); F02C 3/107 (2006.01); F02C 6/08 (2006.01)
CPC F02C 7/36 (2013.01) [F02C 3/107 (2013.01); F02C 6/08 (2013.01)] 17 Claims
OG exemplary drawing
 
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.