Patent ID: 11920491
Assignee: GE AVIO S.R.L.
Field: Mechanical elements (Mechanical engineering)
Classification: CPC F | 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 an input shaft rotatable with the turbine;
a gear assembly that receives the input shaft at a first speed and drives an output shaft coupled to the fan assembly at a second speed, the second speed being slower than the first speed, the 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 rotating about a longitudinal centerline of the gear assembly, and the gear assembly having an aft side and a fore side; and
a lubrication system comprising a plurality of lubrication fluid supply lines, including at least a first lubrication supply line,
wherein the plurality of planet gear layshafts each comprise an interior passageway that extends between an aft side of the planet gear layshaft and a fore side of the layshaft,
the first lubrication supply line extends along the aft side of the gear assembly, through the interior passageway of a respective one of the plurality of planet gear layshafts, and extends along the fore side of the gear assembly to a main lubrication fluid manifold,
the main lubrication fluid manifold being in fluid communication with a first lubrication distribution system at a sun gear-mesh region, and
the first lubrication supply line has one or more openings along a portion that extends through the interior passageway of the respective one of the plurality of planet gear layshafts to direct fluid from within the first lubrication supply line to the interior passageway of the planet gear layshaft.