Circumferential plenum for oil damper
A bearing assembly is provided. The bearing assembly includes an inner race configured to couple to a shaft, an outer race disposed around the inner race, and a housing disposed around the outer race. The housing and the outer race define an annulus and a buffer region, and the buffer region defines an axial boundary of the annulus.
1. A bearing assembly for a shaft configured to rotate about an axis, comprising:
an inner race configured to couple to the shaft;
an outer race disposed around the inner race;
a housing disposed around the outer race, wherein the housing and the outer race define an annulus and a buffer region, wherein the buffer region defines an axial boundary of the annulus; and
an inlet and an outlet defined in the housing, the outlet connected to a channel defined in the housing, the channel being positioned radially outward of the buffer region and also connected to the buffer region, and the inlet connected to the annulus.
2. The bearing assembly of claim 1 , further comprising a first seal disposed between the outer race and the housing, wherein the first seal defines a boundary between the annulus and the buffer region.
3. The bearing assembly of claim 2 , further comprising a second seal disposed between the outer race and the housing, wherein the second seal defines a boundary between the buffer region and an atmosphere.
4. The bearing assembly of claim 3 , wherein the first seal comprises at least one of a piston seal or an O-ring seal.
5. The bearing assembly of claim 3 , wherein a radial thickness of the buffer region is greater than a radial thickness of the annulus.
6. The bearing assembly of claim 3 , wherein the channel is configured to increase a cross-sectional area of the buffer region.
7. A squeeze-film damper comprising:
an outer race having an annular geometry;
a housing disposed about the outer race;
a first seal and a second seal between the outer race and the housing, wherein the housing, the outer race, the first seal and the second seal define a thin-film region;
a third seal proximate the second seal and defining a buffer region between the second seal and the third seal; and
an inlet and an outlet defined in the housing, the outlet connected to a channel defined in the housing, the channel being positioned radially outward of the buffer region and also connected to the buffer region, and the inlet connected to the thin-film region.
8. The squeeze-film damper of claim 7 , wherein the third seal comprises at least one of an O-ring seal, a face seal, or a piston seal.
9. The squeeze-film damper of claim 7 , wherein the second seal comprises at least one of a piston seal or an O-ring seal.
10. The squeeze-film damper of claim 7 , wherein a radial thickness of the buffer region is at least twice a radial thickness of the thin-film region.
11. The squeeze-film damper of claim 7 , wherein a radial thickness of the buffer region is greater than a radial thickness of the thin-film region.
12. The squeeze-film damper of claim 7 , wherein the channel is configured to increase a cross-sectional area of the buffer region.
13. A gas turbine engine comprising:
a shaft;
an inner bearing race coupled to the shaft;
an outer bearing race surrounding the inner bearing race, wherein the shaft and the inner bearing race are configured to rotate within the outer bearing race;
a housing surrounding the outer bearing race, wherein the outer bearing race is configured to whirl within the housing, wherein a thin-film region and a buffer region are defined between the outer bearing race and the housing; and
an inlet and an outlet defined in the housing, the outlet connected to a channel defined in the housing, the channel being positioned radially outward of the buffer region and also connected to the buffer region, and the inlet connected to the thin-film region.
14. The gas turbine engine of claim 13 , further comprising a first seal disposed between the outer bearing race and the housing, wherein the first seal defines a boundary between the thin-film region and the buffer region.
15. The gas turbine engine of claim 14 , wherein the first seal comprises at least one of an O-ring seal or a piston seal.
16. The gas turbine engine of claim 14 , further comprising a second seal disposed between the outer bearing race and the housing, wherein the second seal defines a boundary between the buffer region and an atmosphere.
17. The gas turbine engine of claim 14 , wherein a radial thickness of the buffer region is greater than a radial thickness of the thin-film region.
18. The gas turbine engine of claim 14 , wherein the channel is configured to increase a cross-sectional area of the buffer region.