Patent ID: 11873767
Assignee: GE AVIO S.R.L.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. A turbomachine engine comprising:
a fan assembly comprising a plurality of fan blades;
a core engine comprising a turbine and a core engine output shaft rotatable with the turbine and configured to rotate in a first rotational direction;
a secondary gear assembly that receives and is driven by the core engine output shaft and drives a secondary gear output shaft in a second rotational direction that is opposite of the first rotational direction; and
a primary gear assembly that receives and is driven by the secondary gear output shaft at a first speed and drives a fan shaft coupled to the fan assembly at a second speed, the second speed being slower than the first speed, the primary gear assembly comprising a sun gear, a plurality of planet gear layshafts that each support a first stage planet gear and a second stage planet gear, and a ring gear, the sun gear disposed about a longitudinal centerline of the primary gear assembly;
wherein the first stage planet gear comprises a first gear set and a second gear set supported at the planet gear layshaft, and the second stage planet gear comprises a third gear set supported at a first outer portion of the planet gear layshaft and a fourth gear set supported at a second outer portion of the planet gear layshaft,
wherein the primary gear assembly is an epicyclic gear assembly,
wherein the secondary gear assembly is positioned between the turbine and the primary gear assembly, and
wherein a gear ratio of the primary gear assembly ranges from 6:1 to 14:1.