Compound star gear system with rolling element bearings
A compound star gear system includes a sun gear rotatable about a first axis that drives a first plurality of star gears rotatable about a plurality of fixed axes. The first plurality of star gears drives a second plurality of star gears spaced axially apart from the first plurality of star gears. The second plurality of star gears drive the ring gear that in turn drives a fan drive shaft.
1. A fan drive gear assembly comprising:
a sun gear rotatable about a first axis, wherein the sun gear is fixed to a shaft driven by a turbine section of the gas turbine engine;
a first plurality of star gears directly engaged to the sun gear and rotatable about a plurality of fixed axes;
a second plurality of star gears rotatable with the first plurality of star gears about the plurality of fixed axes;
a ring gear directly engaged to the second plurality of star gears; and
a fan drive shaft driven by the ring gear, wherein sun gear and the first plurality of star gears are engaged within a first plane and the second plurality of star gears and the ring ear are engaged within a second plane spaced axially apart from the first plane, wherein each of the first plane and the second plane are disposed perpendicular to both the first axis and the plurality of fixed axes.
2. The fan drive gear assembly as recited in claim 1 , wherein each of the first plurality of star gears comprises a first diameter and each of the second plurality of star gears comprises a second diameter greater than the first diameter.
3. The fan drive gear assembly as recited in claim 1 , wherein the first plurality of star gears and the second plurality of star gears are supported for rotation by corresponding pluralities of rolling elements.
4. The fan drive gear assembly as recited in claim 3 , wherein the rolling elements comprise cylindrical roller bearings.
5. The fan drive gear assembly as recited in claim 3 , wherein the rolling elements comprise spherical roller bearings.
6. The fan drive gear assembly as recited in claim 3 , wherein the rolling elements comprise tapered roller bearings.
7. The fan drive gear assembly as recited in claim 3 , including a plurality of shafts supporting rotation of the first and second plurality of star gears.
8. The fan drive gear assembly as recited in claim 1 , wherein the first plurality of star gears comprise helical gears including a first helix angle and the second plurality of star gears comprise helical gears including a second helix angle opposite the first helix angle.
9. The fan drive gear assembly as recited in claim 8 , wherein the sun gear comprises a helical gear including a primary helix angle disposed opposite the first helix angle of the first plurality of star gears.
10. The fan drive gear assembly as recited in claim 1 , including a carrier supporting the plurality of first star gears and second star gears.
11. The fan drive gear assembly as recited in claim 1 , wherein the gear assembly comprises a gear reduction ratio up to 5.0.
12. A gas turbine engine comprising:
a fan rotatable about an engine axis;
a core engine section including a turbine section rotating at a first speed; and
a fan drive gear system driven by the turbine section for driving the fan, the fan drive gear system including a sun gear fixed to a shaft driven by the turbine section at the first speed, the sun gear rotatable about the engine axis, a first plurality of star gears directly engaged with the sun gear and rotatable about a plurality of fixed axes, a second plurality of star gears rotatable with the first plurality of star gears about the plurality of fixed axes, a ring gear directly engaged with the second plurality of star gears, and a fan drive shaft driven by the ring gear, wherein the first plurality of star gears and the sun gear are disposed within a first plane perpendicular to the engine axis and the second plurality of star gears are disposed within a second plane perpendicular to the engine axis and spaced axially apart from the first plane.
13. The gas turbine engine as recited in claim 12 , wherein the core engine section includes a compressor section having a low pressure compressor and a high pressure compressor and the low pressure compressor is driven at a speed common with the fan drive shaft.
14. The gas turbine engine as recited in claim 12 , wherein the core engine section includes a compressor section having a low pressure compressor and a high pressure and the turbine section includes a low pressure turbine and a high pressure turbine and the low pressure compressor is rotated at a speed common with the low pressure turbine.
15. The gas turbine engine as recited in claim 12 , wherein the fan drive gear system includes a gear reduction ratio of up to 5.0.
16. The gas turbine engine as recited in claim 12 , wherein the first and second plurality of star gears are supported by rolling element bearings.
17. The gas turbine engine as recited in claim 16 , wherein the rolling element bearings comprise cylindrical roller bearings.
18. The gas turbine engine as recited in claim 16 , wherein the rolling element bearings comprise spherical roller bearings.
19. The gas turbine engine as recited in claim 16 , wherein the rolling element bearings comprise tapered roller bearings.