Patent ID: 11885267
Assignee: GE AVIO S.R.L.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 1:
2. A gas turbine engine comprising:
a fan assembly comprising a plurality of fan blades; and
a turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order, the turbomachine comprising
a first input power source;
a second input power source configured to counter-rotate relative to the first input power source;
a power output component operably connected to the fan assembly; and
a gear assembly located forward of the combustion section of the turbomachine, the gear assembly configured to receive power from the first input power source and the second input power source and provide power to the power output component, the gear assembly comprising a helical gear, wherein the gear assembly comprises:
a first planet gear configured to operably connect the first input power source to the power output component; and
a second planet gear, wherein the second planet gear is configured to operably connect the second input power source to the power output component,
wherein the second planet gear comprises a forward gear and an aft gear, wherein the second input power source comprises a second sun gear, wherein the power output component comprises a ring gear, wherein the forward gear of the second planet gear is configured to mesh with the ring gear, and wherein the aft gear of the second planet gear is configured to mesh with the second sun gear.