CN119333473B - Thrust gas bearing and rotary machine - Google Patents
Thrust gas bearing and rotary machineInfo
- Publication number
- CN119333473B CN119333473B CN202411407067.7A CN202411407067A CN119333473B CN 119333473 B CN119333473 B CN 119333473B CN 202411407067 A CN202411407067 A CN 202411407067A CN 119333473 B CN119333473 B CN 119333473B
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- CN
- China
- Prior art keywords
- thrust
- thrust unit
- support assembly
- gas
- top foil
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C32/00—Bearings not otherwise provided for
- F16C32/06—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings
- F16C32/0603—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings supported by a gas cushion, e.g. an air cushion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C37/00—Cooling of bearings
- F16C37/002—Cooling of bearings of fluid bearings
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Support Of The Bearing (AREA)
Abstract
The application belongs to the technical field of gas bearings, and particularly relates to a thrust gas bearing and a rotary machine. The thrust gas bearing comprises a top foil and a supporting component, wherein the top foil is connected to the supporting component in a stacked mode, the top foil comprises a plurality of thrust units which are distributed in sequence along the circumferential direction of the top foil, at least part of each thrust unit is obliquely arranged relative to the supporting component so as to form a wedge-shaped convergence space between a thrust disc of a rotor and each thrust unit, the inclined part of each thrust unit relative to the supporting component is separated from the supporting component so as to form a first gas space between the thrust units and the supporting component, the first gas space can avoid the thrust units to allow the thrust units to elastically deform in the direction close to the supporting component, the inclined part of each thrust unit is provided with a higher end in the circumferential direction of the top foil, the higher end of each thrust unit is provided with a vent hole, and the vent hole is communicated with the first gas space. The application can solve the problem that the existing thrust gas bearing has unsatisfactory heat dissipation effect.
Description
Technical Field
The application belongs to the technical field of gas bearings, and particularly relates to a thrust gas bearing and a rotary machine.
Background
The thrust gas bearing is a mechanical element for supporting and balancing axial load by the reaction force generated by gas compression, and forms a layer of pressure gas film on the surface of the bearing by utilizing the compressibility and flowability of the gas, and supports the load by the pressure gas film, thereby avoiding direct contact between solids in the traditional bearing and greatly reducing friction and abrasion.
In order to improve the heat dissipation performance of the thrust gas bearing, the related art is provided with vent holes on the top foil, and a cooling channel is formed between the upper side and the lower side of the top foil through the vent holes so as to better dissipate heat of the thrust gas bearing. However, in practice, even if the vent holes are provided, the heat radiation effect of the thrust gas bearing is still not ideal.
Disclosure of Invention
The application aims to provide a thrust gas bearing and a rotary machine, which can solve the problem that the existing thrust gas bearing is not ideal in heat dissipation effect.
In order to solve the technical problems, the application is realized as follows:
In a first aspect, the present application provides a thrust gas bearing, including a top foil and a support assembly, the top foil being stacked and connected to the support assembly, the top foil including a plurality of thrust units distributed sequentially along a circumferential direction of the top foil;
At least part of the thrust unit is obliquely arranged relative to the support assembly so as to form a wedge-shaped convergence space between the thrust disc of the rotor and the thrust unit, and the oblique part of the thrust unit relative to the support assembly is arranged at a distance from the support assembly so as to form a first gas space between the thrust unit and the support assembly, wherein the first gas space can avoid the thrust unit so as to allow the thrust unit to elastically deform towards the direction approaching the support assembly;
In the circumferential direction of the top foil, the inclined part of the thrust unit relative to the support assembly is provided with a higher end, and the higher end is provided with a vent hole which is communicated with the first gas space.
In a second aspect, the present application provides a rotary machine comprising a thrust gas bearing as described above.
The beneficial technical effects of the application are as follows:
In the application, the vent hole on the thrust unit is arranged at the higher end of the inclined part of the thrust unit relative to the supporting component, and the distance between the higher end of the inclined part of the thrust unit and the supporting component is larger than the distance between the lower end of the inclined part of the thrust unit and the supporting component, so that the higher end of the inclined part of the thrust unit needs larger deformation to be contacted with the supporting component.
Drawings
FIG. 1 is a schematic diagram of a thrust gas bearing according to an embodiment of the present application;
FIG. 2 is an exploded schematic view of a thrust gas bearing according to an embodiment of the present application;
FIG. 3 is a schematic diagram of a thrust gas bearing according to an embodiment of the present application;
FIG. 4 is an enlarged schematic view of the application at A in FIG. 3;
FIG. 5 is a schematic illustration of the cooperation between a top foil and a spacer according to an embodiment of the present application;
FIG. 6 is a cross-sectional view of a thrust gas bearing disclosed in an embodiment of the present application;
FIG. 7 is an enlarged schematic view of the present application at B in FIG. 6;
FIG. 8 is a schematic view of a top foil structure according to another embodiment of the present application;
FIG. 9 is a schematic view of a top foil structure according to a further embodiment of the present application;
FIG. 10 is an enlarged schematic view of the present application at C in FIG. 9;
FIG. 11 is a schematic view of a top foil structure according to a further embodiment of the present application;
FIG. 12 is an enlarged schematic view of the application at D in FIG. 11;
FIG. 13 is a schematic view of a two-layer foil structure according to an embodiment of the present application;
FIG. 14 is a schematic view of the structure of a bottom foil disclosed in an embodiment of the present application;
Fig. 15 is an assembly view of a rotor and a thrust gas bearing according to an embodiment of the present application.
Reference numerals illustrate:
100. Top foil, 110, thrust unit, 111, deformation mouth, 112, second section, 113, first section, 120, outer ring, 130, connection rib, 140, vent hole, 141, first vent hole, 142, second vent hole, 150, recess, 151, wind guiding edge, 200, support component, 210, two-layer foil, 211, second support structure, 212, first support, 213, annular support, 220, three-layer foil, 230, bottom foil, 231, third support structure, 240, base, 250, spacer, 310, first gas space, 320, second gas space, 400, rotor, 410, thrust disk.
Detailed Description
The following description of the embodiments of the present application will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that some, but not all embodiments of the application are described. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
The terms first, second and the like in the description and in the claims, are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged, as appropriate, such that embodiments of the present application may be implemented in sequences other than those illustrated or described herein, and that the objects identified by "first," "second," etc. are generally of a type, and are not limited to the number of objects, such as the first object may be one or more. Furthermore, in the description and claims, "and/or" means at least one of the connected objects, and the character "/", generally means that the associated object is an "or" relationship.
The thrust gas bearing and the rotary machine according to the embodiments of the present application will be described in detail below with reference to fig. 1 to 15 by way of specific embodiments and application scenarios thereof.
In the related art, the thrust gas bearing comprises a top foil and a supporting component, the top foil comprises a plurality of thrust units which are distributed along the circumference of the top foil in sequence, the thrust units are obliquely arranged relative to the supporting component so as to form a wedge-shaped convergence space between a thrust disc of a rotor and the thrust units, the inclined part of the thrust units relative to the supporting component is separated from the supporting component so as to form a first gas space between the thrust units and the supporting component, and ventilation holes are formed in the thrust units, so that gas above the thrust units can enter the lower part of the thrust units through the ventilation holes, and the circulation performance of the gas is improved so as to radiate the thrust gas bearing.
The inventor researches and discovers that the vent holes in the related art are formed in the lower end of the two ends of the thrust unit, and because other supporting structures are not arranged below the thrust unit to support the thrust unit, and the air above the thrust unit has a larger impact force, the air possibly presses and deforms the thrust unit towards the direction close to the first air space when contacting with the thrust unit, so that the lower end of the thrust unit is attached to the supporting component, and the supporting component can seal the vent holes at the moment, so that a cooling channel is formed between the upper side and the lower side of the top foil, and obviously, the heat dissipation effect of the thrust air bearing is not ideal.
Referring to fig. 1,2, 6 and 7, an embodiment of the present application discloses a thrust gas bearing, which includes a top foil 100 and a support assembly 200, wherein the top foil 100 is stacked and connected to the support assembly 200, and the top foil 100 includes a plurality of thrust units 110 distributed in sequence along the circumferential direction of the top foil 100. For example, the thrust units 110 may extend along the circumferential direction of the top foil 100, and may have a fan shape, and the plurality of thrust units 110 may surround a first coupling hole formed in the top foil 100 for the rotor 400 to pass therethrough, and a second coupling hole formed in the support assembly 200 for the rotor 400 to pass therethrough, and the first coupling hole and the second coupling hole may be coaxially disposed.
At least a portion of the thrust unit 110 is disposed obliquely with respect to the support assembly 200 to form a wedge-shaped convergence space between the thrust disc 410 of the rotor 400 and the thrust unit 110, and in particular, when the thrust gas bearing is used with the rotor 400, the width of the convergence space gradually decreases in the rotation direction of the rotor 400, that is, the height of the portion of the thrust unit 110 that is inclined with respect to the support assembly 200 gradually increases in the rotation direction of the rotor 400, and the portion of the thrust unit 110 that is inclined with respect to the support assembly 200 is disposed apart from the support assembly 200 to form a first gas space 310 therebetween, the first gas space 310 being capable of avoiding the thrust unit 110 to allow the thrust unit 110 to be elastically deformed in a direction approaching the support assembly 200, that is, the thrust unit 110 being elastically deformed in a direction approaching the support assembly 200, and being capable of recovering the elastic deformation in a direction departing from the support assembly 200.
In the circumferential direction of the top foil 100, the portion of the thrust unit 110 inclined with respect to the support assembly 200 has a higher end provided with a ventilation hole 140, and the ventilation hole 140 communicates with the first gas space 310. It should be noted that the higher end of the inclined portion of the thrust unit 110 with respect to the support assembly 200 is a higher end, the lower end is a lower end, and the higher and lower ends are comparisons of the relative heights of the two ends of the inclined portion of the thrust unit 110, and the relative heights are the heights in the view shown in fig. 1.
Since the thrust unit 110 and the support assembly 200 of the present application are spaced apart from each other with the first gas space 310 formed therebetween, in operation, the rotor 400 rotating at a high speed continuously draws in air from the outside of the thrust gas bearing, the air drawn into the thrust gas bearing from the outside enters the first gas space 310, the air entering the first gas space 310 causes the first gas space 310 to have a certain pressure to support the thrust unit 110, and the air in the first gas space 310 also impacts the thrust unit 110 to apply an upward force to the thrust unit 110 to support the thrust unit 110.
Moreover, since the first gas space 310 can avoid the thrust unit 110, when the gas film between the thrust disc 410 and the thrust unit 110 is compressed to increase the gas pressure between the thrust disc 410 and the thrust unit 110, the thrust unit 110 can deform in a direction close to the support assembly 200, so that the thrust unit 110 enters the first gas space 310 to compress the volume of the first gas space 310, which not only can increase the gas pressure in the first gas space 310, thereby improving the supporting performance of the thrust unit 110, but also can increase the windward angle of the thrust unit 110 after the thrust unit 110 is deformed into the first gas space 310, so that the impact of the gas on the thrust unit 110 can be stronger, the upward acting force applied on the thrust unit 110 can be larger, thereby improving the supporting performance of the thrust unit 110 and meeting the supporting performance requirement on the thrust unit 110. Therefore, no support component such as a corrugated foil is required to be additionally arranged below the thrust unit 110, which can simplify the structure of the thrust gas bearing and save the production cost of the thrust gas bearing.
In addition, the vent hole 140 on the thrust unit 110 is disposed at the upper end of the inclined portion of the thrust unit 110 with respect to the support assembly 200, and the distance between the upper end of the inclined portion of the thrust unit 110 and the support assembly 200 is greater than the distance between the lower end of the inclined portion of the thrust unit 110 and the support assembly 200, so that the upper end of the inclined portion of the thrust unit 110 requires greater deformation to contact the support assembly 200, and thus the present application can reduce the risk of the vent hole 140 contacting the support assembly 200 to block the vent hole 140, thereby preventing the cooling channel between the upper and lower sides of the top foil 100 from being blocked, and ensuring that the thrust gas bearing has a superior heat dissipation effect. And, the gas above the top foil 100 can enter the first gas space 310 through the vent holes 140 and provide gas supply for the first gas space 310, so that a larger gas pressure in the first gas space 310 can be ensured, and the supporting performance of the thrust unit 110 can be ensured.
Referring to fig. 7, in an alternative embodiment, the thrust unit 110 includes a first segment 113 and a second segment 112 that are bent relatively, the first segment 113 is disposed obliquely with respect to the support assembly 200 to form a converging space in cooperation with the thrust disc 410, the first segment 113 further has a lower end distributed along the circumferential direction of the top foil 100, and the ventilation holes 140 are disposed at a higher end, and the higher end is disposed at a bent position with respect to the second segment 112, so that the first segment 113 is disposed obliquely with respect to the support assembly 200. Alternatively, the second section 112 herein is not inclined relative to the support assembly 200, and may be parallel to the plane of the support assembly 200.
In this embodiment, the first section 113 of the thrust unit 110 is bent relative to the second section 112, and the bending portion between the first section 113 and the second section 112 is located at the joint between the higher end of the first section 113 and the second section 112, and the structural strength of the bending portion of the plate member after bending is increased, that is, the strength and rigidity of the bending portion between the first section 113 and the second section 112 are both greater, and the vent hole 140 is located at the higher end of the first section 113, that is, the vent hole 140 is located adjacent to the bending portion between the first section 113 and the second section 112, so that the portion of the thrust unit 110 provided with the vent hole 140 is less prone to collapse downward, which can further prevent the vent hole 140 from being blocked by the support assembly 200.
And/or referring to fig. 3 and 4, in an alternative embodiment, any two adjacent thrust units 110 are separately disposed, that is, there is no connection between the ends of the two adjacent thrust units 110, and the thrust units 110 further have lower ends distributed along the circumferential direction of the top foil 100, and the lower ends are movable relative to the support assembly 200. In this embodiment, two adjacent thrust units 110 are separated, which makes the thrust units 110 deform more easily, so as to improve the supporting performance of the thrust units 110, and the lower end moves relative to the supporting component 200 during the deformation of the thrust units 110 toward the direction approaching to the supporting component 200, so that the lower end is closer to the upper end. In addition, since the two adjacent thrust units 110 are separated, the lower end can be prevented from driving the adjacent thrust units 110 to move in the moving process, that is, the first end of any one thrust unit 110 can not pull the adjacent thrust unit 110, so that the adjacent thrust units 110 can not be driven to move, the position of the wedge-shaped convergence space can be prevented from being changed, and the bearing capacity of the thrust gas bearing can be reduced. Of course, two adjacent thrust units 110 may be connected, that is, each thrust unit 110 may be integrally connected, which is not limited by the present application.
In some embodiments, the second segment 112 comprises a first end remote from the first segment 113, the first segment 113 further comprising a lower end, in any two adjacent thrust units 110, the first end of one thrust unit 110 being spaced apart from the lower end of the other thrust unit 110 in the axial direction of the top foil 100, and the axial distance between the two decreasing gradually from the outside inwards, wherein the axial distance is shown in fig. 4, in particular with reference to dimension D in fig. 4, and the direction from the outside inwards is also shown in fig. 4, in particular with reference to the direction indicated by the x arrow in fig. 4.
In this embodiment, in the plurality of thrust units 110, the first end of any one thrust unit 110 is higher than the lower end of the adjacent thrust unit 110, and the axial distance between the first end of the thrust unit 110 and the lower end of the adjacent thrust unit 110 is gradually reduced from outside to inside, that is, the outer side of the thrust unit 110 is inclined downward relative to the inner side of the thrust unit 110, so that the depth and volume of the convergence space can be increased, which obviously increases the thickness of the air film formed in the convergence space, thereby improving the supporting effect on the thrust unit 110.
In addition, since the gas in the external environment enters from outside to inside, that is, the gas enters from the outer opening of the first gas space 310 and flows out from the inner opening of the first gas space 310, the outer side of the thrust unit 110 of the present application is inclined downward relative to the inner side of the thrust unit 110, so that the size of the opening of the outer side of the first gas space 310 located below the thrust unit 110 is smaller than that of the opening of the inner side of the first gas space 310, which can make the gas pass through the first gas space 310 in a high flow velocity state, which can promote the flow of the gas in the first gas space 310, thereby further improving the supporting effect of the thrust unit 110.
The rotor 400 may disturb the air flow during rotation, thereby allowing the air to flow along the circumferential direction of the top foil 100, and in order to prevent the air flowing along the circumferential direction from entering into the gap between the first end of the thrust unit 110 and the support assembly 200, thereby preventing the first end of the thrust unit 110 from being warped by the circumferential air to reduce the support stability of the thrust unit 110. In some embodiments, a first end of any one thrust unit 110 is located above a lower end of an adjacent thrust unit 110 among the plurality of thrust units 110.
In this embodiment, the first end of the thrust unit 110 is located above the lower end of the adjacent thrust unit 110, so that the first end of the thrust unit 110 is hidden in the space between the lower end of the adjacent thrust unit 110 and the support assembly 200, that is, the gap between the first end of the thrust unit 110 and the support assembly 200 is covered by the lower end of the adjacent thrust unit 110, so that after the arrangement, the circumferentially flowing gas flows out from the lower end of the adjacent thrust unit 110 and directly reaches the surface of the first end of the thrust unit 110 and flows on the surface of the thrust unit 110, thereby reducing the risk that the circumferentially flowing gas enters the gap between the first end of the thrust unit 110 and the support assembly 200, so as to reduce the risk that the warpage of the first end of the thrust unit 110 occurs and the support stability of the thrust unit 110 is reduced.
Of course, the first end of the thrust unit 110 may be offset from the lower end of the adjacent thrust unit 110 in the axial direction, which is not limited by the present application.
To separate the thrust unit 110 from the support assembly 200 to form the first gas space 310, in an alternative embodiment, at least one of the support assembly 200 and the top foil 100 is formed with a third support structure 231, by which the top foil 100 is supported on the support assembly 200 such that the thrust unit 110 is separated from the support assembly 200. In this embodiment, the third supporting structure 231 is additionally provided to support the top foil 100 on the supporting component 200, and separate the thrust unit 110 from the supporting component 200, so that the supporting stability of the top foil 100 can be further improved due to the higher strength of the third supporting structure 231.
In an alternative embodiment, the third support structure 231 includes a plurality of first support portions 212 spaced apart along the circumferential direction of the top foil 100, and the lower end of each thrust unit 110 is supported on each first support portion 212. Specifically, the first support 212 is located at one side in the circumferential direction of the first gas space 310 below the thrust unit 110.
The lower ends of the thrust units 110 in this embodiment are respectively supported by the first supporting portions 212, so that the lower ends of the thrust units 110 have better rigidity performance, and the lower ends of the thrust units 110 are not easy to deform under the action of gas pressure, so that other portions of the thrust units 110 are easier to deform along a specific direction, and further the supporting performance of the thrust units 110 can be improved.
In a further embodiment, the second supporting structure 211 further includes an annular supporting portion 213, and each of the first supporting portions 212 is disposed in the annular supporting portion 213 and connected to the annular supporting portion 213, and the outer ring 120 of the top foil 100 can be supported on the annular supporting portion 213, so as to further improve the supporting performance of the supporting assembly 200 on the top foil 100.
Or in an alternative embodiment, the top foil 100 further comprises an outer ring 120 connected to the support assembly 200, each thrust unit 110 is connected to the outer ring 120 by a connecting rib 130, and the connecting rib 130 is bent upward relative to the outer ring 120 to space the thrust unit 110 from the support assembly 200.
In this embodiment, each of the thrust units 110 is connected to the outer ring 120 through the connection rib 130, and the outer ring 120 is connected to the support assembly 200, so that the thrust units 110 are indirectly connected to the support assembly 200, and the connection rib 130 of this embodiment is bent upward with respect to the outer ring 120, so that the thrust units 110 connected to the connection rib 130 are lifted upward, thereby separating the thrust units 110 from the support assembly 200, so that the thrust units 110 are inclined with respect to the support assembly 200, and the first gas space 310 is formed. It can be seen that the present embodiment uses the structure of the top foil 100 itself to separate the thrust unit 110 from the support assembly 200, so that the second support structure 211 can be optionally omitted, which can simplify the structure of the thrust gas bearing.
Referring to fig. 2, 13 and 14, in an alternative embodiment, the support assembly 200 includes a two-layer foil 210, a three-layer foil 220 and a bottom-layer foil 230 stacked sequentially from top to bottom, wherein the two-layer foil 210 is formed with a second support structure 211, the bottom-layer foil 230 is formed with a plurality of third support structures 231 circumferentially spaced apart from each other, the three-layer foil 220 is supported on the third support structures 231, and a first end of the thrust unit 110 passes through a gap between two adjacent first support portions 212 and contacts the three-layer foil 220. Specifically, a partial region of the three-layer foil 220 is exposed through a gap between two adjacent first support portions 212 of the two-layer foil 210, which allows the first end of the thrust unit 110 to pass through the gap between two adjacent first support portions 212 and contact the three-layer foil 220, that is, the first gas space 310 of the present application is formed between the thrust unit 110 and the three-layer foil 220.
A second air space 320 is formed between two adjacent third support structures 231, and the junction between the first end of the thrust unit 110 and the three-layer foil 220 is a first junction, and the first junction and the middle of the second air space 320 are oppositely arranged in the axial direction of the top-layer foil 100.
In this embodiment, the plurality of third supporting structures 231 on the bottom layer foil 230 support the three layer foil 220, and a second air space 320 is formed between two adjacent third supporting structures 231, and after the outside air enters the second air space 320, the second air space 320 has a certain pressure, and the first end of the thrust unit 110 and the middle of the second air space 320 along the circumferential direction of the thrust air bearing are opposite, so when the thrust unit 110 is deformed, the first end of the thrust unit 110 applies a downward force to the three layer foil 220, so that the portion of the three layer foil 220 between the two third supporting structures 231 is elastically deformed downward, and the portion of the three layer foil 220 invades into the second air space 320, thereby increasing the air pressure in the second air space 320, and further improving the supporting performance of the portion of the three layer foil 220, and the first end of the thrust unit 110 is in contact with the portion of the three layer foil 220, so that the supporting performance of the thrust unit 110 can be further improved. Of course, the first junction may also be arranged opposite the third support structure 231 in the axial direction of the top foil 100.
Optionally, the support assembly 200 further includes a base 240, and the bottom foil 230 is stacked on the base 240, and the second gas space 320 is located between the base 240 and the three-layer foil 220.
Because the air film between the thrust disc 410 and the thrust unit 110 applies a downward force to the thrust unit 110, the first end of the thrust unit 110 is tightly pressed against the support assembly 200, and because at least a portion of the thrust unit 110 is inclined with respect to the support assembly 200, the portion of the thrust unit 110 contacting the support assembly 200 is likely to be the edge of the first end of the thrust unit 110, so that the edge of the first end of the thrust unit 110 may scratch the support assembly 200 when the thrust unit 110 moves with respect to the support assembly 200, thereby damaging the support assembly 200.
In order to prevent the support assembly 200 from being damaged, referring to fig. 8, in an alternative embodiment, the first end of the thrust unit 110 is provided with a deformation opening 111, the deformation opening 111 penetrates from one plate surface of the thrust unit 110 to the other plate surface, and the deformation opening 111 extends to the end surface of the first end of the top foil 100. In this embodiment, the first end of the thrust unit 110 is provided with the deformation opening 111, which can reduce the rigidity of the first end of the thrust unit 110, so that the first end of the thrust unit 110 is elastically deformed under the action of the air film between the thrust disc 410 and the thrust unit 110, so that the plate surface of the first end of the thrust unit 110 is attached to the support assembly 200, and the contact between the thrust unit 110 and the support assembly 200 is converted from line contact to surface contact, so that the contact area between the thrust unit 110 and the support assembly 200 is increased, thereby reducing the risk of damage to the support assembly 200. Of course, the deformation opening 111 may not be provided at the first end of the thrust unit 110, which is not limited by the present application.
And/or referring to fig. 5, in an alternative embodiment, a lifting member 250 is connected below the first end of the thrust unit 110, and the lifting member 250 is stacked on the support assembly 200, that is, the first end of the thrust unit 110 is indirectly contacted with the support assembly 200. In this embodiment, the first end of the thrust unit 110 is lifted by the lifting member 250, so that the thrust unit 110 is more easily elastically deformed, and the volume of the first gas space 310 below the thrust unit 110 is increased after the first end of the thrust unit 110 is lifted, so that the first gas space 310 can allow the deformation of the thrust unit 110 to be greater, and the supporting effect on the thrust unit 110 is further improved. Of course, the spacer 250 may not be disposed under the thrust unit 110, and the first end of the thrust unit 110 may directly contact the support assembly 200.
In an alternative embodiment, the raised piece 250 is a sheet-like structure, and at least one of the outer edge of the thrust unit 110 and the inner edge of the thrust unit 110 extends radially beyond the raised piece 250, so that the risk of the thrust unit 110 extending beyond the inner edge and/or the outer edge of the raised piece 250 during sliding of the thrust unit 110 relative to the raised piece 250 can be reduced, thereby reducing the risk of the inner edge and/or the outer edge of the raised piece 250 scratching the thrust unit 110, and reducing the structural strength of the thrust unit 110.
And/or, in an alternative embodiment, the elevating member 250 is a sheet-shaped structure, the outer side of the thrust unit 110 is supported on the elevating member 250, and a clearance is provided between the inner side of the thrust unit 110 and the elevating member 250, that is, the elevating member 250 does not support all the parts of the first end of the thrust unit 110, so that the thrust unit 110 is easier to deform downwards, thereby further improving the supporting performance of the thrust unit 110.
Referring to fig. 9 to 12, in order to prevent the upper end of the inclined portion of the thrust unit 110 from being abutted with the support assembly 200 under a relatively large air pressure to block the vent hole 140, in an alternative embodiment, one of the thrust unit 110 and the support assembly 200 is connected with a first support structure, the first support structure is located between the thrust unit 110 and the support assembly 200, a gap is formed between the first support structure and the other of the thrust unit 110 and the support assembly 200, and a fluid channel is formed between the vent hole 140 and the first gas space 310 in a condition that one end of the thrust unit 110 provided with the vent hole 140 is in limit fit with the support assembly 200 through the first support structure.
In this embodiment, a gap is formed between the first support structure and the other one of the thrust unit 110 and the support assembly 200, which allows the thrust unit 110 to elastically deform toward the first gas space 310, and even if a larger gas pressure acts on the higher end of the thrust unit 110 to elastically deform the higher end downward, the first support structure between the higher end and the support assembly 200 limits the higher end and prevents the higher end from further deforming downward, so as to prevent the support assembly 200 from sealing all the ventilation holes 140, and at this time, the gas above the thrust unit 110 can enter the first gas space 310 through the fluid channel between the first gas space 310 and the ventilation holes 140, thereby ensuring that the thrust gas bearing has better heat dissipation effect and better support performance. Of course, the first supporting structure described above may not be disposed between the thrust unit 110 and the supporting assembly 200, which is not limited by the present application.
Referring to fig. 10 and 12, in an alternative embodiment, the vent 140 includes a first vent 141, the thrust unit 110 includes a first region, the first region is recessed toward a direction approaching the first gas space 310 to form a recess 150, the first vent 141 is formed in the recess 150, and the first support structure includes the recess 150.
In this embodiment, the first area of the thrust unit 110 is depressed downward by applying a downward pressing force to the first area to form the recess 150, and the first vent hole 141 is formed in the recess 150, which increases the hole depth of the first vent hole 141, so that the flow path of the gas entering the first gas space 310 from above the thrust unit 110 is longer, and more uniform gas distribution is provided. In addition, the recess 150 for forming the first ventilation hole 141 is used to support the upper end of the thrust unit 110, which not only achieves the purpose of multiple purposes, but also does not need to provide other support structures, thereby simplifying the structure of the gas thrust bearing.
In some embodiments, the vent 140 may include only the first vent 141, and in order to form the fluid channel in the case where the end of the thrust unit 110 provided with the vent 140 is in limited engagement with the support assembly 200 through the first support structure, a first air outlet (not shown) may be provided at a sidewall of the recess 150, and the first air outlet may face a lower end of the opposite ends of the inclined portion of the thrust unit 110 with respect to the support assembly 200, and the air may flow out of the first air outlet after entering the first vent 141 to enter the first air space 310.
With continued reference to fig. 10 and 12, in an alternative embodiment, the ventilation hole 140 further includes a second ventilation hole 142, the second ventilation hole 142 penetrates through two opposite faces of the thrust unit 110, and two hole edges of the second ventilation hole 142 are respectively aligned with two opposite faces of the thrust unit 110.
In addition to the first ventilation holes 141, the second ventilation holes 142 are additionally formed in the present embodiment, which can increase the flow rate of the gas entering the first gas space 310 from above the thrust unit 110, thereby further improving the heat dissipation effect and the supporting performance of the thrust gas bearing. In addition, the lower edge of the second ventilation hole 142 is higher than the lower edge of the first ventilation hole 141 in the present embodiment, so when the recess 150 is in contact with the support assembly 200, even if the first ventilation hole 141 is blocked by the support assembly 200, the second ventilation hole 142 is not blocked by the support assembly 200, so that the gas is stably introduced into the first gas space 310, that is, after the structure of the present embodiment is adopted, the above-mentioned fluid channel can be established even if the first gas outlet is not opened on the recess 150.
In some embodiments, the number of the first ventilation holes 141 and the second ventilation holes 142 may be only one, and in this case, each of the first ventilation holes 141 and the second ventilation holes 142 may be a bar-shaped hole.
With continued reference to fig. 10 and 12, in an alternative embodiment, the number of the first ventilation holes 141 and the second ventilation holes 142 is plural, and the first ventilation holes 141 and the second ventilation holes 142 are alternately arranged, that is, one second ventilation hole 142 is located between two adjacent first ventilation holes 141, and one first ventilation hole 141 is also located between two adjacent second ventilation holes 142.
In this embodiment, the first ventilation holes 141 and the second ventilation holes 142 are alternately arranged, so that the second ventilation holes 142 are arranged corresponding to each portion of the first gas space 310 in the radial direction, i.e. the second ventilation holes 142 are distributed more uniformly in the radial direction of the gas thrust bearing, and even if the first ventilation holes 141 are blocked by the support assembly 200, the uniformity of the gas supply to the first gas space 310 can be ensured only through the second ventilation holes 142, so as to improve the supporting effect on the thrust unit 110. Of course, the first ventilation holes 141 and the second ventilation holes 142 may not be alternately arranged, and the arrangement manner between the first ventilation holes 141 and the second ventilation holes 142 is not limited in the present application.
In order to prevent the recess 150 from being blocked by the support assembly 200 when contacting the support assembly 200, in an alternative embodiment, an end of the recess 150 facing away from the thrust unit 110 is an open end, a plurality of deformation openings (not shown in the drawings) penetrating through a sidewall of the recess 150 are formed in the recess 150, and the deformation openings are distributed at intervals along a circumference of the recess 150 and extend to an end surface of the open end of the recess 150.
The higher end of the thrust unit 110 is deformed downward under the action of the larger air pressure, which may cause the open end of the recess 150 to be blocked by the support component 200, so that the air above the thrust unit 110 cannot enter the first air space 310, so that the recess 150 is provided with a plurality of deformation openings, the deformation openings extend to the end face of the open end of the recess 150, so that the open end of the recess 150 is divided into multiple sub-support parts, after the recess 150 contacts with the support component 200, the sub-support parts are elastically bent, and the gap between two adjacent sub-support parts is increased, i.e. the width of the deformation openings is increased, so that the air in the first vent 141 is allowed to flow out from the deformation openings to enter the first air space 310, thereby establishing the fluid channel.
In an alternative embodiment, the side wall of the recess 150 is provided with a second gas outlet (not shown) facing away from the lower one of the two ends of the inclined portion of the thrust unit 110 relative to the support assembly 200, such that gas will be directed to the upper end of the thrust unit 110 to maintain the gas pressure below the upper end of the thrust unit 110, reducing the risk of the upper end of the thrust unit 110 deforming downwards to further prevent the vent 140 provided at the upper end from being blocked by the support assembly 200.
With continued reference to fig. 12, in an alternative embodiment, an end of the recess 150 facing away from the thrust unit 110 is an open end, and the open end of the recess 150 is turned outwards to form the wind guiding edge 151. In this embodiment, the air guiding edge 151 can guide the air around to improve uniformity of air distribution, and the air is guided by the air guiding edge 151 to the upper end of the anti-thrust unit 110 to maintain the air pressure below the upper end of the anti-thrust unit 110, so as to reduce the risk of downward deformation of the upper end of the anti-thrust unit 110, and further prevent the ventilation holes 140 at the upper end from being blocked by the support assembly 200.
The embodiment of the application also discloses a rotary machine, which comprises the thrust gas bearing in any one of the embodiments, so that the rotary machine has the beneficial effects of the thrust gas bearing, and the description is omitted herein. Optionally, referring to fig. 15, the rotary machine further includes a rotor 400, the rotor 400 is sleeved in a thrust gas bearing, the rotor 400 includes a radially protruding thrust disc 410, the number of the thrust gas bearings includes two thrust gas bearings, the two thrust gas bearings are distributed at intervals along the axial direction of the rotor 400 and are oppositely arranged, and the thrust disc 410 is located between the two thrust gas bearings, so that bidirectional suspension of the thrust disc 410 is achieved by using the two thrust gas bearings.
The foregoing embodiments of the present application mainly describe differences between the embodiments, and as long as there is no contradiction between different optimization features of the embodiments, the embodiments may be combined to form a better embodiment, and in view of brevity of line text, no further description is provided herein. The embodiments of the present application have been described above with reference to the accompanying drawings, but the present application is not limited to the above-described embodiments, which are merely illustrative and not restrictive, and many forms may be made by those having ordinary skill in the art without departing from the spirit of the present application and the scope of the claims, which are to be protected by the present application.
Claims (9)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411407067.7A CN119333473B (en) | 2024-10-10 | 2024-10-10 | Thrust gas bearing and rotary machine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411407067.7A CN119333473B (en) | 2024-10-10 | 2024-10-10 | Thrust gas bearing and rotary machine |
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| Publication Number | Publication Date |
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| CN119333473A CN119333473A (en) | 2025-01-21 |
| CN119333473B true CN119333473B (en) | 2025-08-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202411407067.7A Active CN119333473B (en) | 2024-10-10 | 2024-10-10 | Thrust gas bearing and rotary machine |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6702463B1 (en) * | 2000-11-15 | 2004-03-09 | Capstone Turbine Corporation | Compliant foil thrust bearing |
| CN117072549A (en) * | 2023-09-28 | 2023-11-17 | 杭州长河动力技术有限公司 | A dynamic pressure gas thrust bearing with integrated top foil and bottom foil |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3291543A (en) * | 1964-04-14 | 1966-12-13 | Gen Motors Corp | Bearing assembly |
| DE3442155A1 (en) * | 1984-11-17 | 1986-05-28 | SKF GmbH, 8720 Schweinfurt | Hydrodynamic foil bearing |
| FR3001779B1 (en) * | 2013-02-06 | 2016-06-03 | Liebherr-Aerospace Toulouse Sas | AERODYNAMIC BEARING WITH VENTILATED SHEETS |
| US9732789B2 (en) * | 2014-09-26 | 2017-08-15 | Hamilton Sundstrand Corporation | Journal air bearing with air-film-supply vent |
| KR102811284B1 (en) * | 2020-05-19 | 2025-05-22 | 한온시스템 주식회사 | Airfoil thrust bearing and housing assembly, and air compressor having the same |
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2024
- 2024-10-10 CN CN202411407067.7A patent/CN119333473B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6702463B1 (en) * | 2000-11-15 | 2004-03-09 | Capstone Turbine Corporation | Compliant foil thrust bearing |
| CN117072549A (en) * | 2023-09-28 | 2023-11-17 | 杭州长河动力技术有限公司 | A dynamic pressure gas thrust bearing with integrated top foil and bottom foil |
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| CN119333473A (en) | 2025-01-21 |
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