RING GEAR MOUNTING ARRANGEMENT WITH OIL SCAVENGE SCHEME

Abstract

A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor supported on a propulsor shaft, a turbine section including a turbine shaft, and an epicyclic gear train interconnecting the propulsor shaft and the turbine shaft. The epicyclic gear train includes a sun gear coupled to the turbine shaft, intermediary gears arranged circumferentially about and meshing with the sun gear, a carrier supporting the intermediary gears, and a ring gear including first and second portions each having an inner periphery with teeth intermeshing with the intermediate gears. The first and second portions have axially opposed faces abutting one another at a radial interface and respective flanges extending along the radial interface radially outward from the teeth. The first and second portions define a trough axially between and separating the teeth of the first portion from the teeth of the second portion. The first and second portions include facing recesses that form an internal annular cavity along the radial interface.

Claims

1. A gas turbine engine comprising: a propulsor section including a propulsor supported on a propulsor shaft; a turbine section including a turbine shaft; a compressor section having compressor hubs with blades driven by the turbine shaft about an axis; and an epicyclic gear train interconnecting the propulsor shaft and the turbine shaft, the epicyclic gear train comprising: a sun gear coupled to the turbine shaft such that the sun gear is rotatable about the axis; intermediary gears arranged circumferentially about and meshing with the sun gear; a carrier supporting the intermediary gears; and a ring gear including first and second portions, the first and second portions each having an inner periphery with teeth intermeshing with the intermediate gears, the first and second portions having axially opposed faces abutting one another at a radial interface, the first and second portions including respective flanges extending along the radial interface radially outward from the teeth, the first and second portions defining a trough axially between and separating the teeth of the first portion from the teeth of the second portion, the radial interface extending radially outward from the trough relative to the axis, and the first and second portions including facing recesses that form an internal annular cavity along the radial interface.

2. The gas turbine engine as recited in claim 1, wherein the ring gear is a two-piece construction comprising the first and second portions.

3. The gas turbine engine as recited in claim 2, wherein the teeth of the first and second portions are oppositely angled teeth that force the axially opposed faces of the first and second portions toward one another at the radial interface in operation.

4. The gas turbine engine as recited in claim 3, further comprising oil return passages that each drain oil on a respective side of the ring gear into a gutter, and the gutter aligned with the radial interface relative to the axis.

5. The gas turbine engine as recited in claim 4, wherein the epicyclic gear train is a star gear train, and the propulsor shaft is secured to the flanges of the first and second portions of the ring gear such that the ring gear provides a rotational output of the gear train.

6. The gas turbine engine as recited in claim 5, wherein the first and second portions have grooves at the radial interface defining a passageway that expels oil in operation to the gutter.

7. The gas turbine engine as recited in claim 6, wherein each of the intermediate gears is supported on a respective journal bearing.

8. The gas turbine engine as recited in claim 1, wherein the internal annular cavity is radially between the trough and the flanges relative to the axis.

9. The gas turbine engine as recited in claim 8, wherein the ring gear includes at least one passageway that expels oil in operation through an aperture, and the first and second portions have grooves at the radial interface to define the at least one passageway.

10. The gas turbine engine as recited in claim 9, wherein the at least one passageway includes a plurality of passageways circumferentially distributed along the radial interface.

11. The gas turbine engine as recited in claim 9, wherein the epicyclic gear train includes a gutter having an annular channel, and the aperture expels oil to the annular channel in operation.

12. The gas turbine engine as recited in claim 11, wherein the aperture is axially aligned with the annular channel with respect to the axis.

13. The gas turbine engine as recited in claim 12, wherein the at least one passageway includes a first segment and a second segment established by the grooves, the first segment interconnects the trough and the annular cavity, and the second segment interconnects the annular cavity and the aperture.

14. The gas turbine engine as recited in claim 13, wherein opposed sidewalls of the facing recesses establish a first width of the annular cavity relative to the axis, a second width is established across the trough between the teeth of the first and second portions relative to the axis, and the first width is greater than the second width.

15. The gas turbine engine as recited in claim 13, wherein the ring gear is a two-piece construction comprising the first and second portions.

16. The gas turbine engine as recited in claim 15, wherein the teeth of the first and second portions are oppositely angled teeth that force the axially opposed faces of the first and second portions toward one another at the radial interface in operation.

17. The gas turbine engine as recited in claim 16, wherein the trough extends radially outward of the teeth relative to the axis.

18. The gas turbine engine as recited in claim 16, further comprising oil return passages that each drain oil on a respective side of the ring gear into the gutter.

19. The gas turbine engine as recited in claim 18, wherein the oil return passages extend along the respective flanges of the first and second portions.

20. The gas turbine engine as recited in claim 19, wherein the at least one passageway includes a plurality of passageways circumferentially distributed along the radial interface.

21. The gas turbine engine as recited in claim 20, wherein walls of the ring gear inhibit axial flow of oil passing from the aperture towards the annular channel in operation.

22. The gas turbine engine as recited in claim 20, wherein the annular cavity includes a pair of radially outwardly facing walls provided by respective ones of the facing recesses, and the pair of radially outwardly facing walls slope radially inwards from the opposed sidewalls of the annular cavity to an apex along the radial interface with respect to the axis to establish a V-shaped geometry.

23. The gas turbine engine as recited in claim 15, wherein: the epicyclic gear train is a star gear train, the propulsor shaft includes a radially outward extending flange secured to the flanges of the first and second portions of the ring gear; and the carrier is fixed to a housing by a torque frame.

24. The gas turbine engine as recited in claim 23, further comprising oil return passages that each drain oil on a respective side of the ring gear into the gutter.

25. The gas turbine engine as recited in claim 24, wherein the oil return passages extend along the respective flanges of the first and second portions, and the at least one passageway is axially spaced apart from the oil return passages relative to the axis.

26. The gas turbine engine as recited in claim 25, wherein back sides of the first and second portions each have a generally S-shaped outer circumferential surface that provide a first thickness and a second thickness, the flanges of the first and second portions extend radially outwardly from the respective outer circumferential surface relative to the axis, the first thickness is established by a respective sidewall of the ring gear, and the second thickness is established adjacent to a base of the respective flange such that the second thickness is greater than the first thickness.

27. The gas turbine engine as recited in claim 26, wherein the teeth of the first and second portions are oppositely angled teeth that force the axially opposed faces of the first and second portions toward one another at the radial interface in operation.

28. The gas turbine engine as recited in claim 27, further comprising an oil baffle secured to the flanges of the ring gear and the propulsor shaft, wherein one of the oil return passages is established between the flange of the second portion and the oil baffle.

29. The gas turbine engine as recited in claim 28, wherein the propulsor shaft and the ring gear are rotationally balanced with one another.

30. The gas turbine engine as recited in claim 28, further comprising seals arranged on axially opposing sides of the ring gear, and wherein the seals inhibit axial flow of oil passing from the aperture towards the annular channel in operation.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0035] 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.

[0036] FIG. 2 is an enlarged cross-sectional view of the epicyclic gear train shown in FIG. 1.

[0037] FIG. 3 is an enlarged cross-sectional view of an example ring gear similar to the arrangement shown in FIG. 2.

[0038] 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

[0039] 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.

[0040] 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.

[0041] 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.

[0042] 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.

[0043] 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.

[0044] 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.