Bearing cavity and method of evacuating oil therefrom

1. A bearing chamber assembly for an aircraft engine, the bearing chamber assembly comprising a bearing chamber wall extending annularly and having a drain orifice at a bottom of the bearing chamber wall, the drain orifice connecting a scavenge line, and a baffle, the baffle having an apertured sheet and extending along a circumferential direction relative to an axis of the bearing chamber wall from a first circumferential edge to a second circumferential edge, the first circumferential edge connected downstream of the drain orifice to the bearing chamber wall, the baffle extending from the first circumferential edge in an upstream direction, over and past the drain orifice to the second circumferential edge being a free edge, the free edge spaced from the bearing chamber wall.

2. The bearing chamber assembly of claim 1 wherein apertures of the apertured sheet are arrayed along a surface of the apertured sheet.

3. The bearing chamber assembly of claim 2 wherein the apertures are configured in a staggered array of identical apertures along the surface of the apertured sheet.

4. The bearing chamber assembly of claim 3 wherein the bearing chamber wall defines the axis and an axial direction relative to the axis, and wherein an axial distance between apertures of a given row is of between 3/2 and 5/2 times a diameter of the apertures, and a circumferential distance between the apertures of successive rows is of between 5/4 and 2 times the diameter of the apertures.

5. The bearing chamber assembly of claim 3 wherein the bearing chamber wall has a radial direction and a circumferential direction relative to the axis, and wherein the apertures are rectangular, have an axially-oriented length of between 0.14 and 0.28 in, a circumferentially oriented width of between 5 and 10 in, an axial distance relative to the axis between apertures of a given row is of between 33 and 84 in, a circumferential distance between the apertures of successive rows is of between 14 and 38 in.

6. The bearing chamber assembly of claim 1 wherein the bearing chamber wall defines the axis and a radial direction relative to the axis, and wherein apertures of the apertured sheet slope radially outwardly towards the first circumferential edge.

7. The bearing chamber assembly of claim 6 wherein the apertures slope at an angle of between 30° and 50° relative to a surface of the apertured sheet.

8. The bearing chamber assembly of claim 1 wherein the apertured sheet is curved around an axis parallel to the axis of the bearing chamber wall, around a sheet radius of curvature between 1.2 and 1.5 times a bearing chamber wall radius of curvature.

9. The bearing chamber assembly of claim 1 wherein the first circumferential edge of the apertured sheet is welded to the bearing chamber wall.

10. The bearing chamber assembly of claim 1 wherein the apertured sheet has a thickness between 25×10 −3 in and 50×10 −3 in.

11. The bearing chamber assembly of claim 1 wherein apertures of the apertured sheet have a diameter between 3/32″ and 3/16″.

12. A method of operating a gas turbine engine, the method comprising rotating a rotor within a casing of the gas turbine engine via bearings, supplying the bearings with oil, capturing the oil exiting the bearings in a bearing cavity, the rotation of the rotor entraining a standing circumferential flow of air with oil droplets in the bearing cavity, collecting oil droplets carried by the air along a baffle generally extending along a circumferential direction relative to an axis of the bearing cavity from a first circumferential edge to a second circumferential edge, the first circumferential edge connected downstream of a scavenge port to a bearing chamber wall, the baffle extending from the first circumferential edge circumferentially and axially upstream, over and around the scavenge port to the second circumferential edge being spaced apart from the bearing chamber wall, collected oil droplets being pushed along a radially-inner surface of the baffle, reaching apertures in the baffle, moving across the apertures and into the scavenge port.

13. The method of claim 12 wherein the collected oil droplets move along a sloping internal face of the apertures, towards a downstream side of the bearing cavity, until they reach a sharp edge, and drop from the baffle towards the bearing chamber wall of the bearing cavity.

14. The method of claim 12 further comprising limiting a velocity of the air with oil droplets in a region between the baffle and the scavenge port.

15. The method of claim 12 wherein said rotating the rotor is performed at over 20 000 RPM.

16. The method of claim 15 wherein said rotating the rotor is performed at over 25 000 RPM.

17. A gas turbine engine comprising in serial flow configuration a compressor, a combustor, and a turbine, the compressor and turbine having rotating components mounted on at least one rotor, said rotor being rotatably held in the gas turbine engine via at least one bearing housed in a bearing chamber, an oil delivery system including an oil recirculation loop to send oil to the bearing, to be captured in the bearing chamber and guided into a scavenge line across a scavenge port, the scavenge port at a bottom of the bearing chamber; and a baffle, the baffle having an apertured sheet extending along a circumferential direction relative to an axis of a bearing chamber wall from a first circumferential edge to a second circumferential edge, the first circumferential edge connected to the bearing chamber downstream of the scavenge port, the apertured sheet extending from the first circumferential edge in an upstream direction, over and past the scavenge port to the second circumferential edge being a free edge, the free edge spaced from the bearing chamber wall.

18. The gas turbine engine of claim 17 wherein the apertures are configured in a staggered array of identical apertures along a surface of the apertured sheet.

19. The gas turbine engine of claim 17 wherein the apertures slope radially outwardly towards the first circumferential edge.

20. The gas turbine engine of claim 17 wherein the bearing chamber wall is generally annular, and wherein the apertured sheet is curved around an axis parallel to the axis of the bearing chamber wall, around a sheet radius of curvature between 1.2 and 1.5 times a bearing chamber wall radius of curvature.