Thrust bearing for turbo compressor
Disclosed herein is a thrust bearing for a turbo compressor, the thrust bearing has a structure that is modified in response to a portion where a deformation amount of a thrust runner is relatively large on the basis of magnitude of a force applied at the time of rotation of a shaft of a turbo compressor, to maintain a thickness of an oil film constantly and to increase a load supporting force of the thrust bearing, thereby ensuring improved durability of the thrust bearing.
1. A thrust bearing comprising:
a thrust runner having a circular plate shape, the thrust runner being configured to be coupled to a shaft of a turbo compressor and rotatably support an impeller;
a bearing plate disposed at a surface of the thrust runner; and
a bump foil assembly disposed on the bearing plate and including (i) a plurality of bump foils mounted to the bearing plate and (ii) a top foil placed between the plurality of bump foils and the thrust runner and configured to cover the plurality of bump foils,
wherein the thrust runner is configured to at least partially deform as the shaft rotates, and
wherein at least one of the bearing plate, one or more of the plurality of bump foils, or the top foil is configured to at least partially deform based on the thrust runner deforming,
wherein the top foil has a thickness that increases in a radial direction from a first portion of the thrust runner towards a second portion of the thrust runner such that a distance between the top foil and the thrust runner is configured to, based on the thrust runner being deformed as the shaft rotates, be constant in the radial direction between the first portion and the second portion, the first portion being configured to deform less than the second portion as the shaft rotates.
2. The thrust bearing of claim 1 , wherein the thrust runner is configured to, based on the shaft rotating, deform to be spaced apart from the bump foil assembly with increasing distances in a direction away from the shaft.
3. The thrust bearing of claim 1 , wherein the bump foil assembly includes a first rigidity foil and a second rigidity foil having rigidity higher than the first rigidity foil,
wherein the thrust runner includes a first runner portion and a second runner portion configured to deform more than the first runner portion as the shaft rotates,
wherein the first rigidity foil is placed closer to the first runner portion than the second runner portion, and
wherein the second rigidity foil is placed closer to the second runner portion than the first runner portion.
4. The thrust bearing of claim 3 , wherein the bump foil assembly includes a leading edge and a trailing edge,
wherein the trailing edge is located at one end of each of the plurality of bump foils and coupled to the bearing plate,
wherein the leading edge is located at the other end of each of the plurality of bump foils and is a free end, and
wherein a direction from the trailing edge toward the leading edge corresponds to a direction of rotation of the thrust bearing.
5. The thrust bearing of claim 3 , wherein a first bump length of the first rigidity foil is longer than a second bump length of the second rigidity foil, the first bump length being a distance between starting and ending portions of a bump crest of the first rigidity foil, and the second bump length being a distance between starting and ending portions of a bump crest of the second rigidity foil.
6. The thrust bearing of claim 5 , wherein each of one or more of the plurality of bump foils includes the first rigidity foil and the second rigidity foil.
7. The thrust bearing of claim 3 , wherein one end of the top foil is coupled to the bearing plate, and the other end of the top foil is a free end.
8. The thrust bearing of claim 1 , wherein the bump foil assembly includes a plurality of first rigidity foils and a plurality of second rigidity foils, each second rigidity foil having rigidity higher than each first rigidity foil,
wherein the thrust runner includes a first runner portion and a second runner portion configured to deform more than the first runner portion as the shaft rotates,
wherein the plurality of first rigidity foils is placed closer to the first runner portion than the second runner portion,
wherein the plurality of second rigidity foils is placed closer to the second runner portion than the first runner portion,
wherein the plurality of first rigidity foils are continuously placed,
wherein the plurality of second rigidity foils are continuously placed, and
wherein the plurality of first rigidity foils and the plurality of second rigidity foils are separate on the bearing plate.
9. A turbo compressor comprising
a shaft;
an impeller; and
a thrust bearing of claim 1 .
10. The turbo compressor of claim 9 , wherein the thrust runner is configured to, based on the shaft rotating, deform to be spaced apart from the bump foil assembly with increasing distances in a direction away from the shaft.
11. The turbo compressor of claim 9 , wherein the bump foil assembly includes a first rigidity foil and a second rigidity foil having rigidity higher than the first rigidity foil,
wherein the thrust runner includes a first runner portion and a second runner portion configured to deform more than the first runner portion as the shaft rotates,
wherein the first rigidity foil is placed closer to the first runner portion than the second runner portion, and
wherein the second rigidity foil is placed closer to the second runner portion than the first runner portion.
12. The turbo compressor of claim 11 , wherein the bump foil assembly includes a leading edge and a trailing edge,
wherein the trailing edge is located at one end of each of the plurality of bump foils and coupled to the bearing plate,
wherein the leading edge is located at the other end of each of the plurality of bump foils and is a free end, and
wherein a direction from the trailing edge toward the leading edge corresponds to a direction of rotation of the thrust bearing.
13. The turbo compressor of claim 11 , wherein a first bump length of the first rigidity foil is longer than a second bump length of the second rigidity foil, the first bump length being a distance between starting and ending portions of a bump crest of the first rigidity foil, and the second bump length being a distance between starting and ending portions of a bump crest of the second rigidity foil.
14. The turbo compressor of claim 13 , wherein each of one or more of the plurality of bump foils includes the first rigidity foil and the second rigidity foil.
15. The turbo compressor of claim 11 , wherein one end of the top foil is coupled to the bearing plate, and the other end of the top foil is a free end.
16. The turbo compressor of claim 9 , wherein the bump foil assembly includes a plurality of first rigidity foils and a plurality of second rigidity foils, each second rigidity foil having rigidity higher than each first rigidity foil,
wherein the thrust runner includes a first runner portion and a second runner portion configured to deform more than the first runner portion as the shaft rotates,
wherein the plurality of first rigidity foils is placed closer to the first runner portion than the second runner portion,
wherein the plurality of second rigidity foils is placed closer to the second runner portion than the first runner portion,
wherein the plurality of first rigidity foils are continuously placed,
wherein the plurality of second rigidity foils are continuously placed, and
wherein the plurality of first rigidity foils and the plurality of second rigidity foils are separate on the bearing plate.
17. A thrust bearing comprising:
a thrust runner having a circular plate shape, the thrust runner being configured to be coupled to a shaft of a turbo compressor and rotatably support an impeller;
a bearing plate disposed at a surface of the thrust runner; and
a bump foil assembly disposed on the bearing plate and including (i) a plurality of bump foils mounted to the bearing plate and (ii) a top foil placed between the plurality of bump foils and the thrust runner and configured to cover the plurality of bump foils,
wherein the thrust runner is configured to at least partially deform as the shaft rotates, and
wherein at least one of the bearing plate, one or more of the plurality of bump foils, or the top foil is configured to at least partially deform based on the thrust runner deforming,
wherein the thrust runner has a thickness that increases in a direction from an outer circumference of the thrust runner towards the shaft.
18. The thrust bearing of claim 17 , wherein each of the bearing plate and the top foil has a shape corresponding to a shape of the bearing housing, and wherein a bearing plate is spaced apart from the top foil at a constant distance in a radial direction of the thrust runner.
19. A thrust bearing comprising:
a thrust runner having a circular plate shape, the thrust runner being configured to be coupled to a shaft of a turbo compressor and rotatably support an impeller;
a bearing plate disposed at a surface of the thrust runner; and
a bump foil assembly disposed on the bearing plate and including (i) a plurality of bump foils mounted to the bearing plate and (ii) a top foil placed between the plurality of bump foils and the thrust runner and configured to cover the plurality of bump foils,
wherein the thrust runner is configured to at least partially deform as the shaft rotates, and
wherein at least one of the bearing plate, one or more of the plurality of bump foils, or the top foil is configured to at least partially deform based on the thrust runner deforming,
wherein a bearing housing has a thickness that increases in a direction from a first portion of the thrust runner towards a second portion of the thrust runner, the first portion configured to deform less than the second portion as the shaft rotates.