Patent ID: 11971085
Assignee: GE AVIATION CZECH S.R.O.
Field: Mechanical elements (Mechanical engineering)
Classification: CPC F | IPC F

Claim 18:
19. A turbine engine comprising:
a core turbine engine coupled to an input shaft;
a fan coupled to an output shaft; and
a gearbox assembly, wherein a torque is transferrable from the input shaft to the output shaft through the gearbox assembly, the gearbox assembly comprising:
a plurality of planet gears, at least one planet gear of the plurality of planet gears including a layshaft that supports a first stage planet gear and a second stage planet gear, the at least one planet gear being characterized by a Radial Stage Distance greater than or equal to 30 millimeters and less than or equal to 100 millimeters, the Radial Stage Distance being Rrm1−Rrt2, wherein Rrm1 is a first stage rim inner radius of the first stage planet gear and Rrt2 is a second stage root radius of the second stage planet gear.