Geared turbofan with improved gear system maintainability

1. A gas turbine engine comprising:

a fan section including a hub supporting a plurality of fan blades rotatable about an axis;

a bearing assembly supporting rotation of the hub about the axis;

a gas generator including a fan drive turbine; and

a speed reduction device driven by the fan drive turbine for rotating the fan about the axis, wherein the speed reduction device is mounted radially inward and axially within an axial width of the plurality of fan blades supported by the hub forward of the bearing assembly supporting rotation of the hub.

2. The gas turbine engine as recited in claim 1 , wherein the bearing assembly includes an inner race supported by a static structure and an outer race supporting rotation of the hub.

3. The gas turbine engine as recited in claim 2 , wherein the outer race is disposed radially outward of the inner race and the hub is directly supported for rotation on the outer race.

4. The gas turbine engine as recited in claim 1 , including a rotating gutter disposed radially outside the speed reduction system for collecting lubricant and directing lubricant to a lubricant supply system.

5. The gas turbine engine as recited in claim 1 , wherein the speed reduction device is supported within the hub.

6. The gas turbine engine as recited in claim 1 , wherein the speed reduction system comprises a star gear system including a ring gear fixed for rotation with the hub.

7. The gas turbine engine as recited in claim 6 , wherein the star gear system includes a carrier supporting a plurality of intermediate gears fixed to a static engine structure.

8. The gas turbine engine as recited in claim 1 , wherein the speed reduction system comprises a planetary gear system including a carrier supporting a plurality of intermediate gears, wherein the carrier is fixed for rotation with the hub.

9. The gas turbine engine as recited in claim 8 , wherein the planetary gear system includes a ring gear circumscribing the intermediate gears, the ring gear fixed to a static engine structure.

10. The gas turbine engine as recited in claim 1 , wherein the speed reduction system is removable without removal of the fan section.

11. A method of removing a geared architecture from a gas turbine engine comprising:

accessing a geared architecture mounted radially inward and axially within an axial width of blades of the fan section supported by a hub and forward of a bearing assembly at least partially supporting the hub of the fan section;

decoupling a portion of the geared architecture from a fixed engine structure; and

removing the geared architecture in a direction forward of the fan section.

12. The method as recited in claim 11 , including decoupling a portion of the geared architecture from the fan section.

13. The method as recited in claim 12 , wherein the step of decoupling the geared architecture includes decoupling a plurality of intermediate gears from a ring gear fixed to the hub.

14. The method as recited in claim 13 , wherein decoupling the geared architecture includes decoupling a carrier supporting the plurality of intermediate gears from the fixed engine structure.

15. The method as recited in claim 12 , wherein decoupling the geared architecture includes decoupling the carrier supporting the plurality of intermediate gears from the hub.

16. The method as recited in claim 11 , including decoupling a sun gear of the geared architecture from a shaft.

17. The method as recited in claim 11 , including removing a nose cone attached to a hub of the fan section to provide access to the geared architecture.

18. The method as recited in claim 11 , wherein the fan section includes a hub that remains supported by the bearing assembly upon removal of the geared architecture.

19. The method as recited in claim 11 , wherein removing of the geared architecture includes moving the geared architecture along the axis forward of the fan section.