CN115654021A - Gas dynamic pressure thrust bearing - Google Patents
Gas dynamic pressure thrust bearing Download PDFInfo
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- CN115654021A CN115654021A CN202211089544.0A CN202211089544A CN115654021A CN 115654021 A CN115654021 A CN 115654021A CN 202211089544 A CN202211089544 A CN 202211089544A CN 115654021 A CN115654021 A CN 115654021A
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Abstract
The application discloses a gas dynamic pressure thrust bearing, which comprises a bearing bottom plate, a wave foil and a flat foil which are arranged in a stacking mode; the bearing bottom plate is in an annular plate shape, the wave foils and the foil sheets are distributed in an annular array mode around the central hole of the bearing bottom plate, the outer ring boundary of the flat foil sheet outwards exceeds the outer ring boundary of the wave foil sheet, and the inner ring boundary of the flat foil sheet inwards exceeds the inner ring boundary of the wave foil sheet. The wave foil directly supports the flat foil, and the edges of the inner side and the outer side of the ring of the flat foil outwards exceed the edges of the inner side and the outer side of the ring of the wave foil, so that the edges of the inner side and the outer side of the ring of the flat foil are suspended relative to the wave foil to form a cantilever structure, the deformation characteristic of the edges of the inner side and the outer side of the ring of the flat foil is improved, and the edges of the inner side and the outer side of the ring of the flat foil generate enough deformation under a specific working condition, so that the abrasion degree of the edges of the inner side and the outer side of the ring of the flat foil is reduced, and the air inflow between the flat foil and the wave foil is improved to improve the convection heat dissipation capability of the dynamic pressure gas thrust bearing.
Description
Technical Field
The application relates to the technical field of bearings, in particular to a gas dynamic pressure thrust bearing.
Background
Compared with the traditional rolling bearing and sliding bearing, the gas dynamic pressure bearing can use the environmental gas as a lubricating medium, and generate a high-pressure gas film on the surface of the bearing through the dynamic pressure effect to realize the complete suspension of the rotating shaft, so the gas dynamic pressure bearing has a series of advantages of high rotating speed, good precision, high reliability, oil-free lubrication, small friction loss, capability of working in a high-temperature environment and the like.
Aerodynamic thrust bearings are a common form of aerodynamic bearing.
At present, the widely applied gas dynamic pressure thrust bearing is a wave foil type thrust bearing. The wave foil type thrust bearing is disc-shaped, and the rotating shaft is arranged in a disc central hole of the wave foil type thrust bearing. The deformation degree of the inner edge and the outer edge of the disc of the wave foil type thrust bearing is limited, so that the inner edge and the outer edge of the disc of the wave foil type thrust bearing are easy to collide and rub with adjacent parts, and external air does not flow into the disc of the wave foil type thrust bearing from the inner edge and the outer edge of the disc of the wave foil type thrust bearing, so that the local temperature rise of the wave foil type thrust bearing is serious, and the foil outlet coating is likely to fail and the shaft seizing phenomenon is likely to occur.
Disclosure of Invention
The utility model aims at providing a gaseous dynamic pressure thrust bearing can reduce the frictional wear of foil piece, improves the air input of outside air at foil piece edge part, avoids local temperature rise serious.
In order to achieve the above object, the present application provides a gas dynamic pressure thrust bearing, comprising a bearing bottom plate, a wave foil and a flat foil which are stacked one on another; the bearing bottom plate is in an annular plate shape, the wave foils and the plane foils are distributed in an annular array around the central hole of the bearing bottom plate, the outer ring boundaries of the plane foils outwards exceed the outer ring boundaries of the wave foils, and the inner ring boundaries of the plane foils inwards exceed the inner ring boundaries of the wave foils.
In some embodiments, the outer annular edge of the bearing bottom plate extends outwardly beyond the outer annular boundary of the flat foil and the inner annular edge of the bearing bottom plate extends inwardly beyond the inner annular boundary of the flat foil.
In some embodiments, the bump foil sheet comprises a plurality of fan ring bump foils, all of which are annularly distributed around the central hole of the bearing bottom plate;
the flat foil comprises a plurality of fan-shaped annular flat foils, and all the fan-shaped annular flat foils are distributed around the central hole of the bearing base plate in an annular array.
In some embodiments, the axial projection of one fan annular corrugated foil lies within the axial projection of one fan annular flat foil; the axial projections of all the fan-shaped annular wave foils correspond to the axial projections of all the fan-shaped annular flat foils one to one.
In some embodiments, the two fan ring sides of any fan ring-shaped flat foil are respectively a first flat foil side fixedly connected with the bearing bottom plate and a second flat foil side overlapped with the bearing bottom plate.
In some embodiments, the two fan ring side edges of any fan ring-shaped corrugated foil are respectively a first corrugated foil side edge fixedly connected with the bearing bottom plate and a second corrugated foil side edge lapped with the bearing bottom plate; in a pair of fan-shaped wave foil and fan-shaped flat foil which are overlapped in axial projection, the side edge of the first wave foil and the side edge of the first flat foil are positioned on different sides, and the side edge of the second wave foil and the side edge of the second flat foil are positioned on different sides.
In some embodiments, the bearing bottom plate is provided with a plurality of bottom plate grooves, any bottom plate groove is distributed along the radial direction of the bearing bottom plate, and all the bottom plates are uniformly arranged in a ring along the circumferential direction of the bearing bottom plate; the bearing bottom plate is provided with a plurality of bottom plate gaskets, and all the bottom plate gaskets are close to all the bottom plate grooves in a one-to-one correspondence manner; the number of all the bottom plate grooves and the number of all the fan-shaped annular wave foil pieces and the number of all the fan-shaped annular flat foil pieces are equal, and any one fan-shaped annular wave foil piece and any one fan-shaped annular flat foil piece are located between every two adjacent bottom plate grooves.
In some embodiments, the distance between the bearing bottom plate and any one of the fan-shaped flat foils gradually increases from the side edge of the first bump foil to the side edge of the second bump foil; in the same flat foil, the direction extending from the side edge of the first bump foil to the side edge of the second bump foil is the rotation direction of the aerodynamic thrust bearing.
In some embodiments, each fan-shaped corrugated foil is provided with a plurality of foil grooves, each foil groove is arc-shaped and extends along the circumferential direction of the fan-shaped corrugated foil, and all the foil grooves are distributed at intervals in the radial direction of the fan-shaped corrugated foil; any foil slot is open to the fan ring side edge of the fan ring-shaped wave foil;
the same fan-shaped annular wave foil is divided into a plurality of sections by all the foil grooves, and the length of each section of the same fan-shaped annular wave foil is gradually reduced from the axial middle part to the axial two ends of the bearing sleeve.
Compared with the background technology, the aerodynamic thrust bearing provided by the application comprises a bearing bottom plate, a wave foil and a flat foil which are arranged in a stacking mode; the bearing bottom plate is in an annular plate shape, and the wave foils and the foil sheets are distributed in an annular array around a central hole of the bearing bottom plate; the outer ring boundary of the flat foil extends outwardly beyond the outer ring boundary of the bump foil, and the inner ring boundary of the flat foil extends inwardly beyond the inner ring boundary of the bump foil.
In the aerodynamic thrust bearing, the bearing bottom plate directly supports the bump foil, and the bump foil directly supports the flat foil. As the inner ring boundary and the outer ring boundary of the flat foil exceed the inner ring boundary and the outer ring boundary of the wave foil respectively, the inner ring boundary and the outer ring boundary of the flat foil are suspended relative to the wave foil, so that the inner ring boundary and the outer ring boundary of the flat foil form a cantilever structure, and the inner side edge and the outer side edge of the flat foil are easier to deform. When the aerodynamic thrust bearing is started, stopped or operates under variable load, the edges of the inner side and the outer side of the flat foil can easily generate enough deformation, excessive abrasion of the edges of the inner side and the outer side of the flat foil is avoided, and the air inflow between the flat foil and the wave foil can be improved so as to improve the convection heat dissipation effect.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings used in the embodiments or the prior art descriptions will be briefly described below, it is obvious that the drawings in the following description are only the embodiments of the present application, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a gas dynamic pressure thrust bearing provided in an embodiment of the present application;
FIG. 2 is an exploded view of a gas dynamic pressure thrust bearing provided by an embodiment of the present application;
FIG. 3 is a schematic structural diagram of a bearing bottom plate according to an embodiment of the present disclosure;
FIG. 4 is a schematic view of an assembly of a fan ring corrugated foil and a fan ring flat foil according to an embodiment of the present application;
fig. 5 is a schematic assembly diagram of a bearing bottom plate, a fan-ring corrugated foil, a fan-ring flat foil, and a bottom plate spacer according to an embodiment of the present disclosure.
The bearing comprises a bearing bottom plate 1, a bottom plate 11, a 2-wave foil, a 21-fan annular wave foil, a 211-first wave foil side, a 212-second wave foil side, a 213-foil groove, a 3-flat foil, a 31-fan annular flat foil, a 311-first flat foil side, a 312-second flat foil side and a 4-bottom plate gasket.
Detailed Description
The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
In order to enable those skilled in the art to better understand the scheme of the present application, the present application will be described in further detail with reference to the accompanying drawings and the detailed description.
Referring to fig. 1 to 5, fig. 1 is a schematic structural diagram of a gas dynamic pressure thrust bearing according to an embodiment of the present disclosure; FIG. 2 is an exploded view of a gas dynamic thrust bearing provided by an embodiment of the present application; FIG. 3 is a schematic structural diagram of a bearing bottom plate according to an embodiment of the present disclosure;
FIG. 4 is a schematic view of an assembly of a fan ring corrugated foil and a fan ring flat foil according to an embodiment of the present application; fig. 5 is a schematic assembly diagram of a bearing bottom plate, a fan-ring corrugated foil, a fan-ring flat foil, and a bottom plate spacer according to an embodiment of the present disclosure.
Referring to fig. 1 and 2, the present application provides a gas dynamic pressure thrust bearing, which includes a bearing bottom plate 1, a wave foil 2 and a flat foil 3, wherein the bearing bottom plate 1, the wave foil 2 and the flat foil 3 are stacked one by one to form an annular structure through which a rotating shaft can pass. In the gas dynamic pressure thrust bearing, a bearing bottom plate 1 is in an annular plate shape, and wave foils 2 and flat foils 3 are distributed in an annular array around a central hole of the bearing bottom plate 1; the outer ring boundary of the flat foil 3 extends outward beyond the outer ring boundary of the bump foil 2, and the inner ring boundary of the flat foil 3 extends inward beyond the inner ring boundary of the bump foil 2.
When the aerodynamic thrust bearing and the rotating shaft are assembled, the rotating shaft penetrates through the central hole of the bearing base plate 1, so that the wave foils 2 and the flat foils 3 are distributed in an annular array around the central hole of the bearing base plate 1 in the embodiment, and the installation requirement of the rotating shaft is met.
The bump foil 2 is between the bearing bottom plate 1 and the flat foil 3, in other words, the flat foil 3 is supported by the bump foil 2. The outer ring boundary of the flat foil 3 outwards exceeds the outer ring boundary of the wave foil 2, so that the outer ring boundary of the flat foil 3 is suspended relative to the wave foil 2; the inner ring boundary of the flat foil 3 is inward beyond the inner ring boundary of the wave foil 2, so that the inner ring boundary of the flat foil 3 is suspended relative to the wave foil 2, and therefore, the inner and outer side edges of the flat foil 3 form cantilever structures, deformation of the inner and outer side edges of the flat foil 3 under a specific working condition is facilitated, and the purpose of reducing abrasion of the flat foil 3 is achieved. The specific working conditions are generally referred to as starting, stopping and variable load operation of the gas dynamic pressure thrust bearing.
The aerodynamic thrust bearing provided by the present application will be further described with reference to the accompanying drawings and embodiments.
In some embodiments, referring to fig. 1, the axial projection of the bump foil 2 and the axial projection of the flat foil 3 are both within the axial projection of the bearing bottom plate 1, in other words, the outer ring edge of the bearing bottom plate 1 is outward beyond the outer ring boundary of the flat foil 3, and the inner ring edge of the bearing bottom plate 1 is inward beyond the inner ring boundary of the flat foil 3. As can be seen from the foregoing, the inner and outer side edges of the flat foil 3 are suspended in the wave foil 2, so that the outer ring edge of the bearing bottom plate 1 outwardly exceeds the outer ring edge of the wave foil 2, and the inner ring edge of the bearing bottom plate 1 inwardly exceeds the inner ring edge of the wave foil 2. It can be seen that the inner diameter of the bearing bottom plate 1 is smaller than the inner diameter of the bump foil 2 and is also smaller than the inner diameter of the flat foil 3; the outer diameter of the bearing bottom plate 1 is larger than that of the bump foil 2 and that of the flat foil 3. The bump foil 2 directly supports the flat foil 3, and the bearing bottom plate 1 not only indirectly supports the flat foil 3 through the bump foil 2, but also can limit the deformation range of the edges of the inner side and the outer side of the flat foil 3, so that the influence of the excessive deformation of the flat foil 3 on the normal operation characteristic of the flat foil 3 is avoided.
Referring to fig. 1 to 4, the bump foil 2 may include a plurality of fan-shaped ring-shaped bump foils 2, and all the fan-shaped ring-shaped bump foils 2 are distributed around the central hole of the bearing base plate 1; in general, the inner ring edges of all the fan-ring wave foils 2 of the wave foils 2 are located at the same circumference, and the outer ring edges of all the fan-ring wave foils 2 of the wave foils 2 are located at the same circumference. Similar to the bump foil 2, the flat foil 3 may include a plurality of fan-shaped annular flat foils 31, all the fan-shaped annular flat foils 31 are distributed around the central hole of the bearing base plate 1; generally, the inner ring edges of all the fan-shaped flat foils 31 of the flat foil 3 are at the same circumference, and the outer ring edges of all the fan-shaped flat foils 31 of the flat foil 3 are at the same circumference.
The single fan-shaped annular flat foil 31 of the flat foil 3 is in a fan-shaped ring shape and small in size, so that the deformation of the inner ring edge and the outer ring edge under a specific working condition is facilitated, and the abrasion is reduced and the gas suction amount is increased by means of the deformation, so that the convection heat dissipation effect is improved.
On the basis of the above embodiment, all the fan-shaped corrugated foils 21 and all the fan-shaped flat foils 31 are installed in pairs, and it is obvious that the number of all the fan-shaped corrugated foils 21 is the same as that of all the fan-shaped flat foils 31. When one fan ring wave foil 21 and one fan ring flat foil 31 in a pair are mounted on the bearing base plate 1, the axial projection of the fan ring wave foil 21 is within the axial projection of the fan ring flat foil 31.
According to the relationship between the shapes and the sizes of the fan ring wave foil 21 and the fan ring flat foil 31, the following situations can be included when the axial projection of the fan ring wave foil 21 is within the axial projection of the fan ring flat foil 31:
the central angle of the fan-shaped corrugated foil 21 is equal to the central angle of the fan-shaped flat foil 31, and therefore when one fan-shaped corrugated foil 21 and one fan-shaped flat foil 31 which are paired are mounted on the bearing base plate 1, two fan-shaped ring side edges of the fan-shaped corrugated foil 21 are respectively aligned with two fan-shaped ring side edges of the fan-shaped flat foil 31; of course, as can be seen from the foregoing, the two sides inside and outside the ring of the fan-shaped flat foil 31 respectively exceed the two sides inside and outside the ring of the fan-shaped corrugated foil 21.
The central angle of the fan-shaped wave foil 21 is smaller than the central angle of the fan-shaped flat foil 31, when one fan-shaped wave foil 21 and one fan-shaped flat foil 31 are paired and mounted on the bearing base plate 1, both fan-shaped sides of the fan-shaped flat foil 31 can exceed both fan-shaped sides of the fan-shaped wave foil 21, and in addition, only one fan-shaped side of the fan-shaped flat foil 31 can exceed the fan-shaped side of the fan-shaped wave foil 21.
When a fan-shaped corrugated foil 21 and a fan-shaped flat foil 31 are installed in a pair on the bearing base plate 1, two fan-shaped sides of the fan-shaped flat foil 31 are a first flat foil side 311 and a second flat foil side 312, respectively, the first flat foil side 311 is fixedly connected to the bearing base plate 1, and the second flat foil side 312 is lapped on the bearing base plate 1.
When the fan-shaped flat foil 31 is connected to the bearing bottom plate 1 by the above-mentioned installation method, the fan-shaped corrugated foil 21 can be clamped between the fan-shaped corrugated foil 21 and the bearing bottom plate 1. In addition, the fan-ring corrugated foil 21 may also be connected to the bearing bottom plate 1 in a similar installation manner as the fan-ring flat foil 31, for example, two fan-ring sides of any fan-ring corrugated foil 21 are a first corrugated foil side 211 and a second corrugated foil side 212, respectively, the first corrugated foil side 211 is fixedly connected to the bearing bottom plate 1, and the second corrugated foil side 212 is connected to the bearing bottom plate 1. Among the pair of fan-ring-shaped corrugated foils 21 and fan-ring-shaped flat foils 31, the first corrugated foil side 211 and the first flat foil side 311 are located on opposite sides, and the second corrugated foil side 212 and the second flat foil side 312 are located on opposite sides.
On the basis of the above embodiment, the aerodynamic thrust bearing provided by the present application further includes a plurality of bottom plate spacers 4, and any one of the bottom plate spacers 4 may be in the form of a long and thin strip; the bearing bottom plate 1 is provided with a plurality of bottom plate grooves 11, any one bottom plate groove 11 extends along the radial direction of the bearing bottom plate 1, and all the bottom plates are uniformly arranged in a circular manner along the circumferential direction of the bearing bottom plate 1; all the baseplate gaskets 4 are adjacent to all the baseplate grooves 11 in a one-to-one correspondence, and any one baseplate gasket 4 is fixed on the bearing baseplate 1. In addition, in the aerodynamic thrust bearing, the number of all the bottom plate grooves 11, the number of all the fan-shaped annular corrugated foils 21 and the number of all the fan-shaped annular flat foils 31 are equal; any one of the fan-shaped corrugated foils 21 is located between the adjacent bottom plate grooves 11 and between the adjacent bottom plate spacers 4, and any one of the fan-shaped flat foils 31 is located between the adjacent bottom plate grooves 11 and between the adjacent bottom plate spacers 4.
In some embodiments, the distance between any one of the fan-shaped flat foils 31 and the bearing bottom plate 1 gradually increases from the first bump foil side 211 to the second bump foil side 212, so that the fan-shaped flat foil 31 forms a wedge surface, as shown in fig. 5. The transition direction of any fan-shaped annular flat foil 31 from the first bump foil side 211 to the second bump foil side 212 along the circumferential direction is also the rotation direction of the aerodynamic thrust bearing, so that the wedge surface is beneficial to forming a high-pressure air film during the operation of the aerodynamic thrust bearing.
Referring to fig. 4, in other embodiments provided in the present application, any one of the fan-shaped corrugated foils 21 is provided with a plurality of foil grooves 213, each of the foil grooves 213 is arc-shaped and extends along the circumferential direction of the fan-shaped corrugated foil 21, and all of the foil grooves 213 are spaced apart from each other in the radial direction of the fan-shaped corrugated foil 21. Of course, any one of the above-mentioned foil grooves 213 is opened to at most one of the fan-ring sides of the fan-ring wave foil 21, for example, two fan-ring sides of the fan-ring wave foil 21 include the first wave foil side 211 and the second wave foil side 212, and all the foil grooves 213 may be opened to the second wave foil side 212 of the fan-ring wave foil 21.
For the same fan ring wave foil 21, it is divided into multiple sections by all the foil slots 213, for example, if one fan ring wave foil 21 includes four foil slots 213, then one fan ring wave foil 21 is divided into five sections by the four foil slots 213; the length of each segment of the same fan-shaped corrugated foil 21 is gradually reduced from the axial middle portion of the bearing sleeve to the axial two ends, that is, the closer to the fan-shaped ring inner side and the fan-shaped ring outer side of the fan-shaped corrugated foil 21, the smaller the distance between two adjacent foil grooves 213, and vice versa. The segmented characteristics of the fan-shaped corrugated foil 21 can greatly reduce the rigidity of the radial two ends of the fan-shaped corrugated foil 21, thereby being beneficial to reducing the deformation difficulty of the inner side and the outer side of the fan ring of the fan-shaped corrugated foil 21, enabling the inner side and the outer side of the fan ring of the fan-shaped corrugated foil 21 to generate elastic deformation more easily, and further ensuring that the inner side and the outer side of the fan ring of the fan-shaped flat foil 31 can generate enough large deformation under specific working conditions.
The aerodynamic thrust bearing provided by the present application is described in detail above. The principles and embodiments of the present application are described herein using specific examples, which are only used to help understand the method and its core idea of the present application. It should be noted that, for those skilled in the art, it is possible to make several improvements and modifications to the present application without departing from the principle of the present application, and such improvements and modifications also fall within the scope of the claims of the present application.
Claims (9)
1. A gas dynamic pressure thrust bearing is characterized by comprising a bearing bottom plate (1), a wave foil (2) and a flat foil (3) which are arranged in a stacking mode; the bearing bottom plate (1) is in an annular plate shape, the wave foil (2) and the flat foil (3) are distributed in an annular array mode around a center hole of the bearing bottom plate (1), the outer ring boundary of the flat foil (3) outwards exceeds the outer ring boundary of the wave foil (2), and the inner ring boundary of the flat foil (3) inwards exceeds the inner ring boundary of the wave foil (2).
2. Aerodynamic thrust bearing according to claim 1, characterized in that the outer circumferential edge of the bearing bottom plate (1) extends outwardly beyond the outer circumferential boundary of the flat foil (3) and the inner circumferential edge of the bearing bottom plate (1) extends inwardly beyond the inner circumferential boundary of the flat foil (3).
3. A gas dynamic pressure thrust bearing according to claim 1,
the bump foil (2) comprises a plurality of fan-shaped ring-shaped bump foils (21), and all the fan-shaped ring-shaped bump foils (21) are distributed around the central hole of the bearing bottom plate (1) in an annular array;
the flat foil (3) comprises a plurality of fan-shaped annular flat foils (31), and all the fan-shaped annular flat foils (31) are distributed around the central hole of the bearing base plate (1) in an annular array.
4. Aerodynamic thrust bearing according to claim 3, characterized in that the axial projection of one of said fan-shaped corrugated foils (21) lies within the axial projection of one of said fan-shaped flat foils (31); the axial projections of all the fan-shaped annular wave foils (21) correspond to the axial projections of all the fan-shaped annular flat foils (31) one by one.
5. The aerodynamic thrust bearing according to claim 3, wherein the two fan ring sides of any one of the fan ring shaped flat foils (31) are a first flat foil side (311) fixedly connected to the bearing bottom plate (1) and a second flat foil side (312) overlapping the bearing bottom plate (1), respectively.
6. The aerodynamic thrust bearing according to claim 5, wherein the two fan ring sides of any one of the fan ring-shaped bump foils (21) are a first bump foil side (211) fixedly connected with the bearing bottom plate (1) and a second bump foil side (212) overlapped with the bearing bottom plate (1); in a pair of the fan-shaped annular corrugated foil (21) and the fan-shaped annular flat foil (31) which are overlapped in axial projection, the first corrugated foil side (211) and the first flat foil side (311) are located on the opposite side, and the second corrugated foil side (212) and the second flat foil side (312) are located on the opposite side.
7. The aerodynamic thrust bearing according to claim 6, characterized in that the bearing bottom plate (1) is provided with a plurality of bottom plate grooves (11), any one of the bottom plate grooves (11) is distributed along the radial direction of the bearing bottom plate (1), and all the bottom plates (11) are uniformly arranged in a circular manner along the circumferential direction of the bearing bottom plate (1); the bearing bottom plate (1) is provided with a plurality of bottom plate gaskets (4), and all the bottom plate gaskets (4) are close to all the bottom plate grooves (11) in a one-to-one correspondence manner; the number of all the bottom plate grooves (11), the number of all the fan-shaped annular wave foil pieces (21) and the number of all the fan-shaped annular flat foil pieces (31) are equal, and any one of the fan-shaped annular wave foil pieces (21) and any one of the fan-shaped annular flat foil pieces (31) are located between every two adjacent bottom plate grooves (11).
8. The aerodynamic thrust bearing according to any one of claims 4 to 7, wherein a distance between the bearing bottom plate (1) and any one of the fan-shaped flat foils (31) is gradually raised from the first bump foil side (211) toward the second bump foil side (212); in the same flat foil (3), a direction extending from the first bump foil side (211) to the second bump foil side (212) is a rotation direction of the aerodynamic thrust bearing.
9. The gas dynamic pressure thrust bearing according to any one of claims 4 to 7, wherein any one of the fan-shaped bump foils (21) is provided with a plurality of foil grooves (213), any one of the foil grooves (213) is arc-shaped and extends along a circumferential direction of the fan-shaped bump foil (21), and all the foil grooves (213) are spaced apart in a radial direction of the fan-shaped bump foil (21); any one of the foil slots (213) is open to the fan ring side of the fan ring wave foil (21); the same fan-shaped annular wave foil (21) is divided into a plurality of sections by all the foil grooves (213), and the length of each section of the same fan-shaped annular wave foil (21) is gradually reduced from the axial middle part to the axial two ends of the bearing sleeve (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211089544.0A CN115654021A (en) | 2022-09-07 | 2022-09-07 | Gas dynamic pressure thrust bearing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211089544.0A CN115654021A (en) | 2022-09-07 | 2022-09-07 | Gas dynamic pressure thrust bearing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115654021A true CN115654021A (en) | 2023-01-31 |
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ID=84983177
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211089544.0A Pending CN115654021A (en) | 2022-09-07 | 2022-09-07 | Gas dynamic pressure thrust bearing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115654021A (en) |
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2022
- 2022-09-07 CN CN202211089544.0A patent/CN115654021A/en active Pending
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