Planetary gear system arrangement with auxiliary oil system

The gas turbine engine of claim 1, wherein said carrier and said sun gear rotate in the same direction.

The gas turbine engine of claim 2, wherein said carrier drives said fan, and said fan and said first compressor stage rotate in the same direction.

The gas turbine engine of claim 3, wherein said recess is radially outward of gear teeth on said ring gear.

The gas turbine engine of claim 4, wherein said ring gear comprises a first gear portion with a first set of teeth and a second gear portion with a second set of teeth, and wherein said recess comprises a first half-recess in the first gear portion and a second half-recess in said second gear portion.

The gas turbine engine of claim 5, wherein said force is caused by members of said planetary gear train shifting orientation relative to one another.

The gas turbine engine of claim 6, further comprising a lubricating system for said planetary gear train, the lubricating system including a lubricant input, there being a stationary first bearing receiving lubricant from said lubricant input, said first bearing having an inner first race in which lubricant flows, and a second bearing for rotation within said first bearing, said second bearing having a first opening in registration with said inner first race such that lubricant may flow from said inner first race through said first opening into a first conduit.

The gas turbine engine of claim 7, wherein said first conduit provides lubricant to said at least one planetary gear.

The gas turbine engine of claim 7, wherein said first bearing further comprises a stationary second race into which lubricant flows, and said second bearing having a second opening in registration with said second race such that lubricant flows from said second race through said second opening into a second conduit.

The gas turbine engine of claim 9, wherein said second conduit passes lubricant to a component of the gas turbine engine.

The gas turbine engine of claim 9, wherein said first conduit passes lubricant to a first part of the gas turbine engine and said second conduit passes lubricant to a second part of the gas turbine engine different from the first part of the gas turbine engine.

The gas turbine engine of claim 11, wherein said second conduit passes lubricant to a spray bar, wherein said spray bar is disposed on said carrier and provides lubricant to said at least one planetary gear and to said ring gear.

The gas turbine engine of claim 12, wherein said first bearing had a third inner race and said second bearing has a third opening in registration with said third inner race and a third conduit for passing lubricant through said first spray bar.

The gas turbine engine of claim 12, further comprising a second spray bar extending from the first spray bar.

The gas turbine engine of claim 14, wherein said second spray bar provides lubricant to said low spool.

The gas turbine engine of claim 11, wherein said ring gear comprises a first gear portion with a first set of teeth and a second gear portion with a second set of teeth, and wherein said recess comprises a first half-recess radially outward of gear teeth in the first gear portion and a second half-recess radially outward of gear teeth in said second gear portion.

The gas turbine engine of claim 16, wherein said force is caused by members of said planetary gear train shifting orientation relative to one another.

The gas turbine engine of claim 18, wherein the stationary oil transfer bearing is a first bearing and further comprising a second bearing projecting aft from the carrier about the low spool.

The gas turbine engine of claim 19, wherein said first bearing has an inner first race in which lubricant flows, and said second bearing is configured to rotation within said first bearing, said second bearing having a first opening in registration with said inner first race such that lubricant may flow from said inner first race through said first opening into a first conduit.

The gas turbine engine of claim 20, wherein said stationary oil transfer bearing is attached to said at least one gutter via a link, said link attached to an oil input coupling via a tab, the oil input coupling attached to the at least one gutter.

The gas turbine engine of claim 21, wherein said tab includes ears extending from said tab, and said link is attached to said ears via a pin.

The gas turbine engine of claim 21, wherein said stationary oil transfer bearing includes a boss, the boss including a pair of ears, and wherein said link is attached to said boss via a ball and a pin extending through said ball and said pair of ears.

The gas turbine engine of claim 23, wherein said ball allows said oil transfer bearing to flex or torque with the low spool.

The gas turbine engine of claim 20, wherein said first bearing also has a stationary second race into which lubricant flows, and said second bearing having a second opening in registration with said second race such that lubricant flows from said second race through said second opening into a second conduit.

The gas turbine engine of claim 25, wherein said first conduit passes lubricant to a first part of the gas turbine engine, and said second conduit passes lubricant to a second part of the gas turbine engine different from the first part of the gas turbine engine.

The gas turbine engine of claim 26, further comprising a spray bar disposed on said carrier receiving lubricant from said second conduit and providing lubricant to said at least one planetary gear and to said ring gear.

The gas turbine engine of claim 27, further comprising a second spray bar extending from the first spray bar.

The gas turbine engine of claim 28, wherein said second spray provides lubricant to said low spool.

The gas turbine engine of claim 29, wherein lubricant flows from said first spray bar to said second spray bar.