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

Claim 0:
1. 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 includes a first planet gear configured to operably connect the first input power source to the power output component, wherein the first planet gear comprises the helical gear, wherein the power output component comprises an output sun gear, and wherein the helical gear is configured to mesh with the output sun gear.