US 12,129,802 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 Sep. 6, 2022, as Appl. No. 17/903,681.
Prior Publication US 2024/0077033 A1, Mar. 7, 2024
Int. Cl. F02C 7/36 (2006.01)
CPC F02C 7/36 (2013.01) [F05D 2220/323 (2013.01); F05D 2260/40311 (2013.01); F05D 2260/902 (2013.01)] 20 Claims
OG exemplary drawing
 
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, the turbine rotor within the turbine section;
a propulsor rotor, the turbine rotor configured to rotatably drive the propulsor rotor;
a geartrain, the rotating structure coupled to the propulsor rotor through the geartrain; and
an auxiliary turbine comprising an auxiliary turbine rotor, the auxiliary turbine rotor configured to rotatably drive the propulsor rotor with the turbine rotor, the auxiliary turbine configured to receive bleed gas from the flowpath, and the auxiliary turbine rotor operatively coupled to the propulsor rotor independent of the geartrain.