Geared architecture gas turbine engine with planetary gear oil scavenge
A fan drive gear system for a turbofan engine according to an exemplary embodiment of this disclosure, among other possible things includes a sun gear that is rotatable about an axis, a plurality of intermediate gears driven by the sun gear, and a baffle that is disposed between at least two of the plurality of intermediate gears for defining a lubricant flow path from an interface between the sun gear and at least one of the plurality of intermediate gears. The baffle includes a channel with at least one ramp portion directing lubricant.
1. A fan drive gear system for a gas turbine engine comprising:
a sun gear rotatable about an axis;
a plurality of intermediate gears driven by the sun gear;
a carrier supporting the intermediate gears;
a ring gear circumscribing the intermediate gears, wherein the ring gear is fixed and the carrier rotates about the axis;
a forward gutter forward of the carrier;
an aft gutter aft of the carrier; and
a baffle attached to the carrier and disposed between at least two of the plurality of intermediate gears for defining a lubricant flow path from an interface between the sun gear and at least one of the plurality of intermediate gears, the baffle including a channel with at least one flow splitter directing flow forward and aft of the baffle, an inlet opening into the channel, a first ramp portion directing lubricant forward toward the forward gutter, a second ramp portion directing lubricant aft toward the aft gutter, wherein the flow splitter includes a splitter portion and a support portion extending radially within the channel from the splitter portion toward the first ramp portion and the second ramp portion and the inlet is disposed radially inward of the first ramp portion and the second ramp portion.
2. The fan drive gear system as recited in claim 1 , wherein the baffle includes an apex between the first ramp portion and the second ramp portion, the apex is disposed at a midpoint of an axial width of the channel to direct equal amounts of lubricant forward and aft.
3. The fan drive gear system as recited in claim 1 , wherein the baffle includes an apex between the first ramp portion and the second ramp portion, the apex spaced apart from a midpoint of an axial width of the channel to direct unequal amounts of lubricant forward and aft.
4. The fan drive gear system as recited in claim 3 , wherein the apex is disposed at the inlet opening to the channel.
5. The fan drive gear system as recited in claim 3 , wherein the apex is spaced aft of the midpoint of the axial width to direct more lubricant along the first ramp portion forward of the carrier than is directed along the second ramp portion aft of the carrier.
6. The fan drive gear system as recited in claim 1 , wherein the flow splitter is spaced apart from a midway point of an axial width of the channel such that incoming lubricant flow is unequally distributed forward and aft of the baffle.
7. The fan drive gear system as recited in claim 1 , wherein the baffle includes a wedge extending into a circumferential cavity between oppositely facing helical gear regions of the sun gear.
8. A gas turbine engine comprising:
a fan section rotatable about an axis;
a core engine section disposed about the axis;
a primary lubrication system including a sump for gathering lubricant;
an auxiliary lubrication system configured to supply a lubricant flow in an absence of lubricant flow from the primary lubrication system;
a fan drive gear system driven by the core engine section for rotating the fan section about the axis, the fan drive gear system including:
a sun gear rotatable about the axis, the sun gear including a circumferential cavity disposed between a first gear region and a second gear region;
a plurality of intermediate gears driven by the sun gear;
a carrier supporting the plurality of intermediate gears;
a ring gear circumscribing the intermediate gears, wherein the ring gear is fixed and the carrier rotates about the axis; and
a baffle attached to the carrier and disposed between at least two of the plurality of intermediate gears for defining a lubricant flow path from an interface between the sun gear and at least one of the plurality of intermediate gears, the baffle including a channel with a flow splitter proportionally directing lubricant to the auxiliary lubrication system and toward the sump, a wedge extending into the circumferential cavity between oppositely facing helical gear regions of the sun gear, a first ramp portion directing lubricant toward one of the auxiliary lubrication system and the sump, a second ramp portion directing lubricant toward the other of the auxiliary lubrication system and the sump, wherein the flow splitter includes a splitter portion and a support portion extending radially within the channel from the splitter portion toward the first ramp portion and the second ramp portion.
9. The gas turbine engine as recited in claim 8 , including a forward gutter forward of the carrier and an aft gutter aft of the carrier, wherein the first ramp portion directs lubricant toward the forward gutter and the second ramp portion directs lubricant toward the aft gutter and the forward gutter directs lubricant flow to the auxiliary lubrication system and the aft gutter directs lubricant flow to the sump.
10. The gas turbine engine as recited in claim 9 , wherein the baffle directs more lubricant flow to the forward gutter and the auxiliary lubrication system than lubricant flow directed to the aft gutter and the sump.
11. The gas turbine engine as recited in claim 10 , wherein an apex between the first ramp portion and the second ramp portion is spaced aft of a midpoint of an axial width to direct more lubricant along the first ramp portion forward of the carrier than is directed along the second ramp portion aft of the carrier.
12. The gas turbine engine as recited in claim 9 , wherein an apex between the first ramp portion and the second ramp portion is disposed at a midpoint of an axial width to direct equal amounts of lubricant along the first ramp portion forward of the carrier and along the second ramp portion aft of the carrier.
13. The gas turbine engine as recited in claim 8 , wherein the core engine includes a low pressure turbine including a number of rotors and a ratio between a number of fan blades in the fan section and the number of rotors in the low pressure turbine is between 3.3 and 8.6.
14. The gas turbine engine as recited in claim 8 , wherein the core engine includes a turbine section with a mid-turbine frame disposed between a high pressure turbine and a low pressure turbine, the mid-turbine frame supporting a bearing system disposed between the high pressure turbine and the low pressure turbine.
15. A fan drive gear system for a gas turbine engine comprising:
a sun gear rotatable about an axis;
a plurality of intermediate gears driven by the sun gear;
a carrier supporting the intermediate gears;
a ring gear circumscribing the intermediate gears, wherein the ring gear is fixed and the carrier rotates about the axis; and
a baffle attached to the carrier and disposed between at least two of the plurality of intermediate gears for defining a lubricant flow path from an interface between the sun gear and at least one of the plurality of intermediate gears, the baffle including a channel with at least one flow splitter at an inlet for splitting lubricant between a first ramp portion and a second ramp portion, wherein the flow splitter includes a splitter portion and a support portion extending radially within the channel from the splitter portion toward the first ramp portion and the second ramp portion.
16. The fan drive gear system as recited in claim 15 , wherein the flow splitter includes an apex between the first ramp portion and the second ramp portion, the apex is disposed at a midpoint of an axial width of the channel to direct equal amounts of lubricant forward and aft.
17. The fan drive gear system as recited in claim 16 , wherein the flow splitter includes an apex between the first ramp portion and the second ramp portion, the apex spaced apart from a midpoint of an axial width of the channel to direct unequal amounts of lubricant forward and aft.
18. The fan drive gear system as recited in claim 15 , wherein the flow splitter includes an apex between the first ramp portion and the second ramp portion, the apex is spaced aft of the midpoint of the axial width to direct more lubricant along the first ramp portion forward of the carrier than is directed along the second ramp portion aft of the carrier.
19. The fan drive gear system as recited in claim 15 , including a forward gutter forward of the carrier and an aft gutter aft of the carrier, wherein the first ramp portion directs lubricant toward the forward gutter and the second ramp portion directs lubricant toward the aft gutter and the forward gutter directs lubricant flow to an auxiliary lubrication system and the aft gutter directs lubricant flow to a sump.