RING GEAR MOUNTING ARRANGEMENT WITH OIL SCAVENGE SCHEME

Abstract

An epicyclic gear train for a turbine engine includes a gutter with an annular channel. A rotating structure includes a ring gear that has an aperture that is axially aligned with the annular channel. Axially spaced apart walls extend radially outward relative to the rotating structure to define a passageway. The passageway is arranged radially between and axially aligned with the aperture and the annular channel. The walls are configured to inhibit an axial flow of an oil passing from the aperture toward the annular channel.

Claims

1. An epicyclic gear train for a turbine engine comprising: a gutter with an annular channel; a rotating structure includes a ring gear, the rotating structure has an aperture that is axially aligned with the annular channel; and axially spaced apart walls that extend radially outward relative to the rotating structure to define a passageway, the passageway is arranged radially between and axially aligned with the aperture and the annular channel, wherein the walls are configured to inhibit an axial flow of an oil passing from the aperture toward the annular channel.

2. The epicyclic gear train according to claim 1, comprising a fixed structure that supports the gutter.

3. The epicyclic gear train according to claim 1, comprising a seal arranged on each of axially opposing sides of the ring gear, the seals providing the walls.

4. The epicyclic gear train according to claim 3, wherein each seal includes a radially outwardly extending knife edge seal, the knife edge seals configured to further inhibit the axial flow of the oil passing from the aperture toward the annular channel.

5. The epicyclic gear train according to claim 1, wherein the walls are supported by the rotating structure.

6. The epicyclic gear train according to claim 1, wherein the gutter has a U-shaped cross-section.

7. The epicyclic gear train according to claim 1, wherein the walls each include a face that together define the passageway.

8. The epicyclic gear train according to claim 1, wherein the walls are arranged radially inward from the gutter.

9. A gas turbine engine comprising: a fan section; a turbine section; an epicyclic gear train interconnecting the fan section and the turbine section, the epicyclic gear train including: a gutter with an annular channel; a rotating structure includes a ring gear, the rotating structure has an aperture that is axially aligned with the annular channel; and axially spaced apart walls that extend radially outward relative to the rotating structure to define a passageway, the passageway is arranged radially between and axially aligned with the aperture and the annular channel, wherein the walls are configured to inhibit an axial flow of an oil passing from the aperture toward the annular channel.

10. The gas turbine engine according to claim 9, comprising a fixed structure that supports the gutter.

11. The gas turbine engine according to claim 9, comprising a seal arranged on each of axially opposing sides of the ring gear, the seals providing the walls.

12. The gas turbine engine according to claim 11, wherein each seal includes a radially outwardly extending knife edge seal, the knife edge seals configured to further inhibit the axial flow of the oil passing from the aperture toward the annular channel.

13. The gas turbine engine according to claim 9, wherein the walls are supported by the rotating structure.

14. The gas turbine engine according to claim 9, wherein the gutter has a U-shaped cross-section.

15. The gas turbine engine according to claim 9, wherein the walls each include a face that together define the passageway.

16. The gas turbine engine according to claim 9, wherein the walls are arranged radially inward from the gutter.

17. The gas turbine engine according to claim 9, wherein the rotating structure is configured to rotate about an axis extending in an axial direction, the axial flow configured to flow in the axial direction.

18. The gas turbine engine according to claim 17, wherein the rotating structure includes a sun gear coaxial with the axis, and multiple star gears arranged circumferentially about and meshing with the sun gear, and the ring gear is arranged about and intermeshes with the star gears.

19. The gas turbine engine according to claim 18, wherein the ring gear includes first and second portions operatively secured to one another by fastening elements.

20. The gas turbine engine according to claim 18, wherein the ring gear is operatively affixed to a shaft.

21. The gas turbine engine according to claim 20, wherein the fan section is operatively connected to the shaft.

22. The gas turbine engine according to claim 18, wherein the rotating structure has a carrier that is operatively connected to a fixed structure, the carrier rotationally supports the star gears.

23. The gas turbine engine according to claim 9, wherein the ring gear includes holes extending therethrough that provide the aperture.

24. The epicyclic gear train according to claim 1, wherein the rotating structure is configured to rotate about an axis extending in an axial direction, the axial flow configured to flow in the axial direction.

25. The epicyclic gear train according to claim 24, wherein the rotating structure includes a sun gear coaxial with the axis, and multiple star gears arranged circumferentially about and meshing with the sun gear, and the ring gear is arranged about and intermeshes with the star gears.

26. The epicyclic gear train according to claim 25, wherein the ring gear includes first and second portions operatively secured to one another by fastening elements.

27. The epicyclic gear train according to claim 25, wherein the ring gear is operatively affixed to a shaft.

28. The epicyclic gear train according to claim 27, wherein a fan section is operatively connected to the shaft.

29. The epicyclic gear train according to claim 25, wherein the rotating structure has a carrier that is operatively connected to a fixed structure, the carrier rotationally supports the star gears.

30. The epicyclic gear train according to claim 1, wherein the ring gear includes holes extending therethrough that provide the aperture.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0036] FIG. 1 is a partial cross-sectional view of a front portion of a gas turbine engine illustrating a turbo fan, epicyclic gear train and a compressor section.

[0037] FIG. 2 is an enlarged cross-sectional view of the epicyclic gear train shown in FIG. 1.

[0038] FIG. 3 is an enlarged cross-sectional view of an example ring gear similar to the arrangement shown in FIG. 2.

[0039] FIG. 4 is a view of the ring gear shown in FIG. 3 viewed in a direction that faces the teeth of the ring gear in FIG. 3.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT

[0040] A portion of a gas turbine engine 10 is shown schematically in FIG. 1. The turbine engine 10 includes a fixed housing 12 that is constructed from numerous pieces secured to one another. A compressor section 14 having compressor hubs 16 with blades are driven by a turbine shaft 25 about an axis A. A turbo fan 18 is supported on a turbo fan shaft 20 that is driven by a compressor shaft 24, which supports the compressor hubs 16, through an epicyclic gear train 22.

[0041] In the example arrangement shown, the epicyclic gear train 22 is a star gear train. Referring to FIG. 2, the epicyclic gear train 22 includes a sun gear 30 that is connected to the compressor shaft 24, which provides rotational input, by a splined connection. A carrier 26 is fixed to the housing 12 by a torque frame 28 using fingers (not shown) known in the art. The carrier 26 supports star gears 32 using journal bearings 34 that are coupled to the sun gear 30 by meshed interfaces between the teeth of sun and star gears 30, 32. Multiple star gears 32 are arranged circumferentially about the sun gear 30. Retainers 36 retain the journal bearings 34 to the carrier 26. A ring gear 38 surrounds the carrier 26 and is coupled to the star gears 32 by meshed interfaces. The ring gear 38, which provides rotational output, is secured to the turbo fan shaft 20 by circumferentially arranged fastening elements, which are described in more detail below.

[0042] Referring to FIGS. 3 and 4, the ring gear 38 is a two-piece construction having first and second portions 40, 42. The first and second portions 40, 42 abut one another at a radial interface 45. A trough 41 separates oppositely angled teeth 43 (best shown in FIG. 4) on each of the first and second portions 40, 42. The arrangement of teeth 43 forces the first and second portions 40, 42 toward one another at the radial interface 45. The back side of the first and second portions 40, 42 includes a generally S-shaped outer circumferential surface 47 that, coupled with a change in thickness, provides structural rigidity and resistance to overturning moments. The first and second portions 40, 42 have a first thickness T1 that is less than a second thickness T2 arranged axially inwardly from the first thickness T1. The first and second portions 40, 42 include facing recesses 44 that form an internal annular cavity 46.

[0043] The first and second portions 40, 42 include flanges 51 that extend radially outward away from the teeth 43. The turbo fan shaft 20 includes a radially outwardly extending flange 70 that is secured to the flanges 51 by circumferentially arranged bolts 52 and nuts 54, which axially constrain and affix the turbo fan shaft 20 and ring gear 38 relative to one another. Thus, the spline ring is eliminated, which also reduces heat generated from windage and churning that resulted from the sharp edges and surface area of the splines. The turbo fan shaft 20 and ring gear 38 can be rotationally balanced with one another since radial movement resulting from the use of splines is eliminated. An oil baffle 68 is also secured to the flanges 51, 70 and balanced with the assembly.

[0044] Seals 56 having knife edges 58 are secured to the flanges 51, 70. The first and second portions 40, 42 have grooves 48 at the radial interface 45 that form a hole 50, which expels oil through the ring gear 38 to a gutter 60 that is secured to the carrier 26 with fasteners 61 (FIG. 2). The direct radial flow path provided by the grooves 48 reduces windage and churning by avoiding the axial flow path change that existed with splines. That is, the oil had to flow radially and then axially to exit through the spline interface. The gutter 60 is constructed from a soft material such as aluminum so that the knife edges 58, which are constructed from steel, can cut into the aluminum if they interfere. Referring to FIG. 3, the seals 56 also include oil return passages 62 provided by first and second slots 64 in the seals 56, which permit oil on either side of the ring gear 38 to drain into the gutter 60. In the example shown in FIG. 2, the first and second slots 64, 66 are instead provided in the flange 70 and oil baffle 68, respectively.

[0045] Although a preferred embodiment of this invention has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this invention. For that reason, the following claims should be studied to determine the true scope and content of this invention.