Thrust gas bearing and rotating machinery

Abstract

This application belongs to the technical field of gas bearings, and particularly relates to a thrust gas bearing and a rotating machine. The thrust gas bearing includes a top foil and a support assembly. The top foil is stacked and connected to the support assembly. The top foil includes a plurality of thrust units sequentially distributed along the circumferential direction of the top foil. At least a part of the thrust unit is inclined relative to the support assembly to form a wedge-shaped converging space between the thrust disk of the rotor and the thrust unit. The inclined part of the thrust unit relative to the support assembly is spaced apart from the support assembly to form a first gas space therebetween. The first gas space can avoid the thrust unit to allow the thrust unit to elastically deform in the direction close to the support assembly. In the circumferential direction of the top foil, the inclined part of the thrust unit relative to the support assembly has a higher end, and a ventilation hole is provided at the higher end. The ventilation hole is communicated with the first gas space. This application can solve the problem of unsatisfactory heat dissipation effect of the current thrust gas bearing.

Description

Technical Field

[0001] This application belongs to the technical field of gas bearings, and particularly relates to a thrust gas bearing and a rotating machine. Background Art

[0002] A thrust gas bearing is a mechanical component that supports and balances axial loads through the reaction force generated by gas compression. It utilizes the compressibility and fluidity of gas to form a pressure gas film on the bearing surface, and supports the load through the pressure gas film, thus avoiding direct contact between solids in traditional bearings and greatly reducing friction and wear.

[0003] In related technologies, a thrust gas bearing includes a top foil. The top foil can form a wedge-shaped convergent space between itself and the thrust disk of the rotor, thereby realizing the axial suspension of the rotor. To improve the heat dissipation performance of the thrust gas bearing, ventilation holes are provided in the top foil in related technologies, and a cooling channel is formed between the upper and lower sides of the top foil through the ventilation holes to better dissipate heat from the thrust gas bearing. However, in practice, even with the ventilation holes provided, the heat dissipation effect of the thrust gas bearing is still not ideal. Summary of the Invention

[0004] The purpose of this application is to provide a thrust gas bearing and a rotating machine, which can solve the problem of the unsatisfactory heat dissipation effect of the current thrust gas bearing.

[0005] To solve the above technical problems, this application is implemented as follows:

[0006] In a first aspect, this application provides a thrust gas bearing, including a top foil and a support assembly. The top foil is stacked and connected to the support assembly. The top foil includes a plurality of thrust units sequentially distributed along the circumference of the top foil;

[0007] At least a part of the thrust unit is inclined relative to the support assembly to form a wedge-shaped convergent space between the thrust disk of the rotor and the thrust unit. The inclined part of the thrust unit relative to the support assembly is spaced apart from the support assembly to form a first gas space therebetween. The first gas space can avoid the thrust unit to allow the thrust unit to elastically deform in the direction close to the support assembly;

[0008] In the circumferential direction of the top foil, the inclined part of the thrust unit relative to the support assembly has a higher end, and a ventilation hole is provided at the higher end. The ventilation hole is connected to the first gas space.

[0009] In a second aspect, this application provides a rotating machine, including the above-mentioned thrust gas bearing.

[0010] The beneficial technical effects of this application are as follows:

[0011] In this application, the ventilation holes on the thrust unit are provided at the higher end of the inclined portion of the thrust unit relative to the support assembly, and the distance between the higher end of the inclined portion of the thrust unit and the support assembly is greater than the distance between the lower end of the inclined portion of the thrust unit and the support assembly. Therefore, a greater deformation is required at the higher end of the inclined portion of the thrust unit to come into contact with the support assembly. Thus, by arranging the ventilation holes at the higher end of the inclined portion of the thrust unit in this application, the risk of the ventilation holes coming into contact with the support assembly and being blocked can be reduced, thereby preventing the cooling channel between the upper and lower sides of the top foil from being truncated, so as to ensure that the thrust gas bearing has a better heat dissipation effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 is a schematic structural diagram of a thrust gas bearing disclosed in an embodiment of this application Figure 1 ;

[0013] Figure 2 is an exploded schematic diagram of a thrust gas bearing disclosed in an embodiment of this application;

[0014] Figure 3 is a schematic structural diagram of a thrust gas bearing disclosed in an embodiment of this application Figure 2 ;

[0015] Figure 4 is for this application Figure 3 an enlarged schematic diagram of part A;

[0016] Figure 5 is a schematic diagram of the cooperation between the top foil and the spacer disclosed in an embodiment of this application;

[0017] Figure 6 is a cross-sectional view of a thrust gas bearing disclosed in an embodiment of this application;

[0018] Figure 7 is for this application Figure 6 an enlarged schematic diagram of part B;

[0019] Figure 8 is a schematic structural diagram of a top foil disclosed in another embodiment of this application;

[0020] Figure 9 is a schematic structural diagram of a top foil disclosed in yet another embodiment of this application;

[0021] Figure 10 is for this application Figure 9 an enlarged schematic diagram of part C;

[0022] Figure 11 is a schematic structural diagram of a top foil disclosed in yet another embodiment of this application;

[0023] Figure 12 is for this applicationFigure 11 Enlarged schematic view at D in the [specific context];

[0024] Figure 13 Schematic structural view of the two - layer foil disclosed in the embodiment of the present application;

[0025] Figure 14 Schematic structural view of the bottom - layer foil disclosed in the embodiment of the present application;

[0026] Figure 15 Assembly drawing between the rotor and the thrust gas bearing disclosed in the embodiment of the present application.

[0027] Explanation of reference numerals:

[0028] 100, top - layer foil; 110, thrust unit; 111, deformation opening; 112, second section; 113, first section; 120, outer ring body; 130, connecting rib; 140, ventilation hole; 141, first ventilation hole; 142, second ventilation hole; 150, recess; 151, air - guiding edge; 200, support assembly; 210, two - layer foil; 211, second support structure; 212, first support portion; 213, annular support portion; 220, three - layer foil; 230, bottom - layer foil; 231, third support structure; 240, base; 250, height - increasing member; 310, first gas space; 320, second gas space; 400, rotor; 410, thrust disc. Detailed implementation manners

[0029] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all of them. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present application.

[0030] The terms "first", "second", etc. in the specification and claims of the present application are used to distinguish similar objects, rather than to describe a specific order or sequence. It should be understood that such data can be interchanged under appropriate circumstances so that the embodiments of the present application can be implemented in an order other than those illustrated or described herein, and the objects distinguished by "first", "second", etc. generally belong to the same category, and do not limit the number of objects. For example, the first object can be one or more. In addition, "and / or" in the specification and claims means at least one of the connected objects, and the character " / ", generally represents an "or" relationship between the associated objects.

[0031] Next, in combination with Figures 1 to 15, the thrust gas bearing and the rotating machine provided by the embodiments of the present application are described in detail through specific embodiments and their application scenarios.

[0032] In the related art, the thrust gas bearing includes a top foil and a support assembly. The top foil includes a plurality of thrust units sequentially distributed along the circumference of the top foil. The thrust units are inclined relative to the support assembly to form a wedge-shaped convergent space between the thrust disk of the rotor and the thrust units. The inclined part of the thrust unit relative to the support assembly is spaced apart from the support assembly to form a first gas space therebetween, and ventilation holes are provided on the thrust units. In this way, the gas above the thrust units can enter below the thrust units through the ventilation holes, thereby improving the gas flow performance to dissipate heat from the thrust gas bearing.

[0033] The inventors have found through research that the ventilation holes in the related art are opened at the lower end of the two ends of the thrust unit. Since no other support structure is provided below the thrust unit to support the thrust unit, and the gas above the thrust unit has a large impact force, the gas may squeeze and deform the thrust unit in the direction close to the first gas space when contacting the thrust unit, so that the lower end of the thrust unit fits with the support assembly. At this time, the support assembly will block the ventilation holes, thereby truncating the cooling channel formed between the upper and lower parts of the top foil. Obviously, this will lead to an unsatisfactory heat dissipation effect of the thrust gas bearing.

[0034] Please refer to Figure 1 , Figure 2 , Figure 6 and Figure 7 , an embodiment of the present application discloses a thrust gas bearing, including a top foil 100 and a support assembly 200. The top foil 100 is stacked and connected to the support assembly 200. The top foil 100 includes a plurality of thrust units 110 sequentially distributed along the circumference of the top foil 100. Exemplarily, here the thrust units 110 can extend along the circumference of the top foil 100, and it can be fan-shaped. The plurality of thrust units 110 surround to form a first fitting hole located inside the top foil 100 for the rotor 400 to pass through; a second fitting hole is formed inside the support assembly 200, and the second fitting hole is also used for the rotor 400 to pass through. The first fitting hole and the second fitting hole can be coaxially arranged.

[0035] At least a part of the thrust unit 110 is inclined relative to the support assembly 200 to form a wedge-shaped convergent space between the thrust disc 410 of the rotor 400 and the thrust unit 110. Specifically, when the thrust gas bearing is used in conjunction with the rotor 400, the width of the convergent space gradually decreases along the rotation direction of the rotor 400. That is to say, the height of the inclined part of the thrust unit 110 relative to the support assembly 200 gradually increases along the rotation direction of the rotor 400. The inclined part of the thrust unit 110 relative to the support assembly 200 is spaced apart from the support assembly 200 to form a first gas space 310 therebetween. The first gas space 310 can avoid the thrust unit 110 to allow the thrust unit 110 to elastically deform in the direction close to the support assembly 200. That is to say, the thrust unit 110 has elasticity. The thrust unit 110 can elastically deform in the direction close to the support assembly 200 and can also recover the elastic deformation in the direction away from the support assembly 200.

[0036] In the circumferential direction of the top foil 100, the inclined part of the thrust unit 110 relative to the support assembly 200 has a higher end, and a ventilation hole 140 is provided at the higher end. The ventilation hole 140 is communicated with the first gas space 310. It should be noted that the higher end of the two ends in the circumferential direction of the inclined part of the thrust unit 110 relative to the support assembly 200 along the top foil 100 is the higher end, and the lower end is the lower end. Here, the higher and lower refer to the relative height comparison of the two ends of the inclined part of the thrust unit 110, and the relative height here is the height in the Figure 1 displayed perspective.

[0037] Since the thrust unit 110 of the present application is spaced apart from the support assembly 200 and a first gas space 310 is formed therebetween, during operation, the high-speed rotating rotor 400 will continuously draw in air from the outside of the thrust gas bearing. The air drawn in from the outside into the thrust gas bearing will enter the first gas space 310. The gas entering the first gas space 310 will make the first gas space 310 have a certain pressure to support the thrust unit 110; and the gas in the first gas space 310 will also impact the thrust unit 110 to apply an upward acting force on the thrust unit 110, thereby supporting the thrust unit 110.

[0038] Moreover, since the first gas space 310 can accommodate the thrust unit 110, when the air film between the thrust disk 410 and the thrust unit 110 is compressed to increase the air pressure between the thrust disk 410 and the thrust unit 110, the thrust unit 110 can deform in the 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. This can not only increase the gas pressure in the first gas space 310, thereby improving the support performance for the thrust unit 110, but also increase the windward angle of the thrust unit 110 after the thrust unit 110 deforms and enters the first gas space 310. In this way, the impact of the gas on the thrust unit 110 will be stronger, and the upward acting force exerted on the thrust unit 110 will be greater, so as to improve the support performance for the thrust unit 110, thus meeting the support performance requirements for the thrust unit 110. In this way, there is no need to additionally provide support components such as wave foils 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.

[0039] In addition, the ventilation holes 140 on the thrust unit 110 are provided at the higher end of the inclined part of the thrust unit 110 relative to the support assembly 200, and the distance between the higher end of the inclined part of the thrust unit 110 and the support assembly 200 is greater than the distance between the lower end of the inclined part of the thrust unit 110 and the support assembly 200. Therefore, a greater deformation is required at the higher end of the inclined part of the thrust unit 110 to contact the support assembly 200. Therefore, setting the ventilation holes 140 at the higher end of the inclined part of the thrust unit 110 in this application can reduce the risk of the ventilation holes 140 being blocked by contacting the support assembly 200, thereby preventing the cooling channels above and below the top foil 100 from being truncated, so as to ensure that the thrust gas bearing has a better heat dissipation effect. And the gas above the top foil 100 can enter the first gas space 310 through the ventilation holes 140 to provide gas supply for the first gas space 310. In this way, a greater gas pressure can be ensured in the first gas space 310, so as to ensure the support performance for the thrust unit 110.

[0040] Please refer to Figure 7 , in an alternative embodiment, the thrust unit 110 includes a first section 113 and a second section 112 that are bent relative to each other. The first section 113 is inclined relative to the support assembly 200 to cooperate with the thrust disk 410 to form a converging space. The first section 113 also has a lower end distributed along the circumference of the top foil 100, and the ventilation holes 140 are provided at the higher end. The higher end is bent relative to the second section 112, so that the first section 113 is inclined relative to the support assembly 200. Optionally, the second section 112 here is not inclined relative to the support assembly 200 and can be parallel to the plane where the support assembly 200 is located.

[0041] In this embodiment, the first section 113 of the thrust unit 110 is bent relative to the second section 112, and the bent portion between the first section 113 and the second section 112 is located at the joint of the higher end of the first section 113 and the second section 112. After the plate member is bent, the structural strength at the bent portion will increase. That is to say, the strength and stiffness of the bent portion between the first section 113 and the second section 112 are both large. The ventilation hole 140 is provided at the higher end of the first section 113, that is, the ventilation hole 140 is arranged adjacent to the bent portion between the first section 113 and the second section 112. In this way, the part of the thrust unit 110 provided with the ventilation hole 140 is less likely to collapse downward, which can further prevent the ventilation hole 140 from being blocked by the support assembly 200.

[0042] and / or, please refer to Figure 3 and Figure 4 , in an alternative embodiment, any two adjacent thrust units 110 are separated, that is to say, there is no connection relationship between the ends of two adjacent thrust units 110. The thrust unit 110 also has a lower end distributed along the circumference of the top foil 100, and the lower end can move relative to the support assembly 200. In this embodiment, two adjacent thrust units 110 are separated, which can make the thrust unit 110 more likely to deform, thereby improving the support performance of the thrust unit 110. And during the process of the thrust unit 110 deforming in the direction close to the support assembly 200, the lower end will move relative to the support assembly 200, so that the lower end is closer to the higher end. In addition, since two adjacent thrust units 110 are separated, this can prevent the lower end from driving the adjacent thrust unit 110 to move during the movement, that is, when the first end of any one thrust unit 110 moves, it will not pull the adjacent thrust unit 110, so as not to drive the adjacent thrust unit 110 to move, so as to prevent the position of the wedge-shaped convergence space from changing, thereby reducing the load-bearing capacity of the thrust gas bearing. Of course, two adjacent thrust units 110 can also be connected, that is, each thrust unit 110 can be integrated into one body, and the present application does not limit this.

[0043] In some embodiments, the second section 112 includes a first end away from the first section 113, and the first section 113 also includes a lower end. Among any two adjacent thrust units 110, the first end of one thrust unit 110 and the lower end of the other thrust unit 110 are spaced apart axially on the top foil 100, and the axial distance between them gradually decreases from outside to inside. The axial distance here is shown in Figure 4 and can be specifically referred to Figure 4 as the D dimension in, and the direction from outside to inside is also shown in Figure 4 and can be specifically referred to Figure 4 as the direction indicated by the x arrow line in.

[0044] In this embodiment, among the multiple 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 this thrust unit 110 and the lower end of the adjacent thrust unit 110 gradually decreases from the outside to the inside. That is to say, the outside of the thrust unit 110 is inclined downward relative to the inside of the thrust unit 110. In this way, the depth and volume of the convergence space can be increased. Obviously, this will increase the thickness of the air film formed in the convergence space, thereby improving the supporting effect on the thrust unit 110.

[0045] In addition, since the gas in the external environment enters from the outside to the 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, and the outside of the thrust unit 110 of the present application is inclined downward relative to the inside of the thrust unit 110, the opening size of the outside of the first gas space 310 located below the thrust unit 110 is smaller than the opening size of the inside of the first gas space 310. This can make the gas pass through the first gas space 310 at a high flow rate, which can improve the fluidity of the gas in the first gas space 310, thereby further improving the supporting effect on the thrust unit 110.

[0046] During the rotation of the rotor 400, the air flow will be disturbed, so that the gas will flow circumferentially along the top foil 100. In order to prevent the gas flowing circumferentially from entering 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 warping under the action of the circumferential gas and reducing the supporting stability of the thrust unit 110. In some embodiments, among the multiple thrust units 110, the first end of any one thrust unit 110 is located above the lower end of the adjacent thrust unit 110.

[0047] In this embodiment, the first end of the thrust unit 110 is located above the lower end of the adjacent thrust unit 110. In this way, the first end of this thrust unit 110 can be hidden in the space between the lower end of the adjacent thrust unit 110 and the support assembly 200. That is to say, the gap between the first end of this thrust unit 110 and the support assembly 200 is covered by the lower end of the adjacent thrust unit 110. After such a setting, the gas flowing circumferentially will directly reach the surface of the first end of this thrust unit 110 after flowing out from the lower end of the adjacent thrust unit 110 and flow on the surface of this thrust unit 110, thereby reducing the risk of the gas flowing circumferentially entering the gap between the first end of this thrust unit 110 and the support assembly 200, so as to reduce the risk of the first end of the thrust unit 110 warping and reducing the supporting stability of the thrust unit 110.

[0048] Of course, the first end of the thrust unit 110 can also be axially staggered from the lower end of the adjacent thrust unit 110, and the present application does not limit this.

[0049] In order 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. The top foil 100 is supported on the support assembly 200 through the third support structure 231, so that the thrust unit 110 is separated from the support assembly 200. In this embodiment, the top foil 100 is supported on the support assembly 200 by additionally providing the third support structure 231, and the thrust unit 110 is separated from the support assembly 200. Since the strength of the third support structure 231 is relatively high, the support stability of the top foil 100 can be further improved.

[0050] In an alternative embodiment, the third support structure 231 includes a plurality of first support portions 212 that are circumferentially spaced apart along the top foil 100. The lower ends of the respective thrust units 110 are respectively supported on the respective first support portions 212. Specifically, the first support portion 212 is located on one side in the circumferential direction of the first gas space 310 below the thrust unit 110.

[0051] In this embodiment, the lower ends of the respective thrust units 110 are respectively supported by the first support portions 212. In this way, the lower ends of the thrust units 110 can have better stiffness performance, and the lower ends of the thrust units 110 are not easily deformed under the action of gas pressure, which makes it easier for other parts of the thrust units 110 to deform in a specific direction, thereby further improving the support performance of the thrust units 110.

[0052] In a further embodiment, the second support structure 211 further includes an annular support portion 213. Each of the first support portions 212 is disposed within and connected to the annular support portion 213. The outer ring body 120 of the top foil 100 described above can be supported on the annular support portion 213, thereby further improving the support performance of the support assembly 200 for the top foil 100.

[0053] Alternatively, in an alternative embodiment, the top foil 100 further includes an outer ring body 120 connected to the support assembly 200. Each of the thrust units 110 is connected to the outer ring body 120 through a connecting rib 130. The connecting rib 130 is bent upward relative to the outer ring body 120 so that the thrust unit 110 is separated from the support assembly 200.

[0054] In this embodiment, each thrust unit 110 is connected to the outer ring body 120 through a connecting rib 130, and the outer ring body 120 is further connected to the support assembly 200. In this way, the thrust unit 110 can be indirectly connected to the support assembly 200; and the connecting rib 130 of this embodiment is bent upward relative to the outer ring body 120. In this way, the thrust unit 110 connected to the connecting rib 130 can be lifted upward, so as to separate the thrust unit 110 from the support assembly 200, which facilitates tilting the thrust unit 110 relative to the support assembly 200 and facilitates the formation of the first gas space 310. It can be seen that this embodiment uses the structure of the top foil 100 itself to separate the thrust unit 110 from the support assembly 200. In this way, the above-mentioned second support structure 211 can be selectively not provided, so as to simplify the structure of the thrust gas bearing.

[0055] Please refer to Figure 2 、 Figure 13 and Figure 14 , in an alternative embodiment, the support assembly 200 includes a two-layer foil 210, a three-layer foil 220, and a bottom foil 230 stacked in sequence from top to bottom. The second support structure 211 is formed on the two-layer foil 210, and a plurality of third support structures 231 are formed on the bottom foil 230 and are distributed at intervals along its circumferential direction. The three-layer foil 220 is supported on the third support structures 231. The first end of the thrust unit 110 passes through the gap between two adjacent first support portions 212 and contacts the three-layer foil 220. Specifically, a part of the three-layer foil 220 is exposed through the gap between two adjacent first support portions 212 of the two-layer foil 210, which enables 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 to say, the first gas space 310 of this application is formed between the thrust unit 110 and the three-layer foil 220.

[0056] A second gas space 320 is formed between two adjacent third support structures 231. The connection between the first end of the thrust unit 110 and the three-layer foil 220 is the first connection. The first connection and the middle of the second gas space 320 are oppositely arranged in the axial direction of the top foil 100.

[0057] In this embodiment, a plurality of third support structures 231 on the bottom foil 230 support the three-layer foil 220, and a second gas space 320 is formed between two adjacent third support structures 231. After the external air enters the second gas space 320, the second gas space 320 will have a certain pressure. The first end of the thrust unit 110 in this embodiment is disposed opposite to the middle part of the second gas space 320 along the circumference of the thrust gas bearing. In this way, when the thrust unit 110 deforms, the first end of the thrust unit 110 will apply a downward force to the three-layer foil 220, so that the part of the three-layer foil 220 located between the two third support structures 231 will elastically deform downward, so that this part of the three-layer foil 220 will intrude into the second gas space 320, thereby increasing the gas pressure in the second gas space 320, and further improving the support performance of this part of the three-layer foil 220. And the first end of the thrust unit 110 is in contact with this part of the three-layer foil 220, so this can further improve the support performance of the thrust unit 110. Of course, the first contact can also be disposed opposite to the third support structure 231 in the axial direction of the top foil 100.

[0058] Optionally, the support assembly 200 further includes a base 240, the bottom foil 230 is stacked on the base 240, and the above-mentioned second gas space 320 is located between the base 240 and the three-layer foil 220.

[0059] Since the air film between the thrust disc 410 and the thrust unit 110 will apply a downward force to the thrust unit 110, the first end of the thrust unit 110 will be tightly pressed against the support assembly 200. Since at least part of the thrust unit 110 is inclined relative to the support assembly 200, the part of the thrust unit 110 in contact with the support assembly 200 is very likely to be the edge of the first end of the thrust unit 110. In this way, when the thrust unit 110 moves relative to the support assembly 200, the edge of the first end of the thrust unit 110 may scratch the support assembly 200, thereby causing damage to the support assembly 200.

[0060] To prevent damage to the support assembly 200, please refer to Figure 8, in an alternative embodiment, a deformation opening 111 is provided at the first end of the thrust unit 110. 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 deformation opening 111 is provided at the first end of the thrust unit 110, which can reduce the stiffness of the first end of the thrust unit 110. Thus, under the action of the air film between the thrust disk 410 and the thrust unit 110, the first end of the thrust unit 110 will undergo elastic deformation, so that the plate surface of the first end of the thrust unit 110 fits with the support assembly 200, and further converts the contact between the thrust unit 110 and the support assembly 200 from line contact to surface contact. In this way, the contact area between the thrust unit 110 and the support assembly 200 will increase to reduce 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, and the present application does not limit this.

[0061] and / or, please refer to Figure 5 , in an alternative embodiment, a heightening member 250 is connected below the first end of the thrust unit 110. The heightening member 250 is stacked on the support assembly 200, that is to say, the first end of the thrust unit 110 is in indirect contact with the support assembly 200. In this embodiment, the first end of the thrust unit 110 is heightened by the heightening member 250, so that the thrust unit 110 is more likely to undergo elastic deformation; and after the first end of the thrust unit 110 is heightened, the volume of the first gas space 310 below the thrust unit 110 will be increased. In this way, the first gas space 310 can allow a greater degree of deformation of the thrust unit 110, thereby further enhancing the support effect on the thrust unit 110. Of course, the heightening member 250 may not be provided below the thrust unit 110, and at this time, the first end of the thrust unit 110 can be directly in contact with the support assembly 200.

[0062] In an alternative embodiment, the heightening member 250 is a sheet-like structural member, and at least one of the outer edge and the inner edge of the thrust unit 110 radially extends beyond the heightening member 250. In this way, during the sliding process of the thrust unit 110 relative to the heightening member 250, the risk that the thrust unit 110 extends beyond the inner edge and / or outer edge of the heightening member 250 can be reduced, thereby reducing the inner edge and / or outer edge of the heightening member 250 from scratching the thrust unit 110 and reducing the structural strength of the thrust unit 110.

[0063] And / or, in an alternative embodiment, the spacer 250 is a sheet-like structural member. The outer side of the thrust unit 110 is supported on the spacer 250, and there is a clearance between the inner side of the thrust unit 110 and the spacer 250. That is to say, the spacer 250 does not support all parts of the first end of the thrust unit 110. In this way, the thrust unit 110 is more likely to deform downward, thereby further improving the support performance for the thrust unit 110.

[0064] Please refer to Figures 9 to 12 , in order to prevent the higher end of the inclined part of the thrust unit 110 from fitting with the support assembly 200 under a large air pressure to block the ventilation hole 140, in an alternative embodiment, a first support structure is connected to one of the thrust unit 110 and the support assembly 200. The first support structure is located between the thrust unit 110 and the support assembly 200, and there is a gap between the first support structure and the other of the thrust unit 110 and the support assembly 200. When one end of the thrust unit 110 provided with the ventilation hole 140 is in limit fit with the support assembly 200 through the first support structure, a fluid passage is formed between the ventilation hole 140 and the first gas space 310.

[0065] In this embodiment, there is a gap between the first support structure and the other of the thrust unit 110 and the support assembly 200, which allows the thrust unit 110 to elastically deform towards the first gas space 310. And even when a large air pressure acts on the higher end of the thrust unit 110 to cause the higher end to elastically deform downward, the first support structure between the higher end and the support assembly 200 will limit the higher end to prevent it from further deforming downward, so as to avoid the support assembly 200 closing all parts of the ventilation hole 140. At this time, the gas located above the thrust unit 110 can enter the first gas space 310 through the fluid passage between the first gas space 310 and the ventilation hole 140, thereby ensuring that the thrust gas bearing has better heat dissipation effect and better support performance. Of course, the above first support structure may not be provided between the thrust unit 110 and the support assembly 200, and the present application does not limit this.

[0066] Please refer to Figure 10 and Figure 12 , in an alternative embodiment, the ventilation hole 140 includes a first ventilation hole 141, the thrust unit 110 includes a first region, the first region is recessed towards the direction close to the first gas space 310 to form a recess 150, and the first ventilation hole 141 is formed in the recess 150. The first support structure includes the recess 150.

[0067] In this embodiment, applying a downward stamping force to the first region of the thrust unit 110 can cause the first region to be recessed downward to form a recess 150, and a first ventilation hole 141 is formed in the recess 150. This can increase the hole depth of the first ventilation hole 141, so that the flow path of the gas entering the first gas space 310 from above the thrust unit 110 is longer, to provide a more uniform gas distribution. And in this embodiment, the recess 150 used to form the first ventilation hole 141 is used to support the higher end of the thrust unit 110. This can not only achieve the purpose of multi-purpose use of one object, but also does not require additional support structures, thus simplifying the structure of the gas thrust bearing.

[0068] In some embodiments, the ventilation hole 140 may only include the first ventilation hole 141. At this time, in order to form the above-mentioned fluid passage when the end of the thrust unit 110 provided with the ventilation hole 140 is in limit fit with the support assembly 200 through the first support structure, a first air outlet (not shown in the figure) may be provided on the side wall of the recess 150. The first air outlet faces the lower end of the two ends of the inclined part of the thrust unit 110 relative to the support assembly 200. After the gas enters the first ventilation hole 141, it can flow out from the first air outlet to enter the first gas space 310.

[0069] Please continue to refer to Figure 10 and Figure 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 plate surfaces of the thrust unit 110, and the two hole edges of the second ventilation hole 142 are flush with the two opposite plate surfaces of the thrust unit 110 respectively.

[0070] In addition to the first ventilation hole 141, this embodiment additionally provides a second ventilation hole 142. This 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 support performance of the thrust gas bearing. And the lower hole edge of the second ventilation hole 142 in this embodiment is higher than the lower hole edge of the first ventilation hole 141. Therefore, 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 will not be blocked by the support assembly 200, so as to stably introduce gas into the first gas space 310. That is, after adopting the structure of this embodiment, even if the first air outlet is not provided on the recess 150, the above-mentioned fluid passage can be established.

[0071] In some embodiments, the number of the first ventilation hole 141 and the second ventilation hole 142 may also be only one. At this time, both the first ventilation hole 141 and the second ventilation hole 142 can be strip-shaped holes.

[0072] Please continue to refer to Figure 10 and Figure 12In an optional embodiment, there are multiple first ventilation holes 141 and multiple second ventilation holes 142, and the first ventilation holes 141 and the second ventilation holes 142 are arranged alternately, that is, there is a second ventilation hole 142 between two adjacent first ventilation holes 141, and there is also a first ventilation hole 141 between two adjacent second ventilation holes 142.

[0073] In this embodiment, the first ventilation holes 141 and the second ventilation holes 142 are arranged alternately. This allows the second ventilation holes 142 to correspond to various radial portions of the first gas space 310. That is, the second ventilation holes 142 are more evenly distributed in the radial direction of the gas thrust bearing. Therefore, even if the first ventilation holes 141 are blocked by the support assembly 200, uniform gas supply to the first gas space 310 can be ensured through the second ventilation holes 142 alone, thereby improving the support effect on the thrust unit 110. Of course, the first ventilation holes 141 and the second ventilation holes 142 do not need to be arranged alternately, and this application does not limit the arrangement of the first ventilation holes 141 and the second ventilation holes 142.

[0074] In order to prevent the first ventilation hole 141 from being blocked by the support assembly 200 when the recess 150 contacts the support assembly 200, in an optional embodiment, the end of the recess 150 facing away from the thrust unit 110 is an open end, and the recess 150 is provided with a plurality of deformation notches (not shown in the figure) that pass through the side wall of the recess 150. The plurality of deformation notches are distributed at intervals along the circumference of the recess 150, and the deformation notches extend to the end face of the open end of the recess 150.

[0075] Under the action of greater gas pressure, the higher end of the thrust unit 110 will deform downward to a greater extent, which may cause the open end of the recessed portion 150 to be blocked by the support assembly 200, thereby preventing the gas above the thrust unit 110 from entering the first gas space 310; therefore, in this embodiment, a plurality of deformation notches are provided on the recessed portion 150, and the deformation notches extend to the end surface of the open end of the recessed portion 150, so that the open end of the recessed portion 150 can be divided into multiple sub-support portions. After the recessed portion 150 contacts the support assembly 200, if the thrust unit 110 is further deformed toward the first gas space 310, the sub-support portions will elastically bend, and the gap between two adjacent sub-support portions will increase, that is, the width of the deformation notches will increase, thereby allowing the gas in the first ventilation hole 141 to flow out from the deformation notches and enter the first gas space 310, thereby establishing the above-mentioned fluid channel.

[0076] In an alternative embodiment, the side wall of the recess 150 is provided with a second air outlet (not shown in the figure). The second air outlet faces away from the lower end of the two ends of the part where the thrust unit 110 is inclined relative to the support assembly 200. In this way, the gas will be guided to the higher end of the thrust unit 110 to maintain the gas pressure below the higher end of the thrust unit 110, reduce the risk of downward deformation of the higher end of the thrust unit 110, and further prevent the ventilation hole 140 provided at the higher end from being blocked by the support assembly 200.

[0077] Please continue to refer to Figure 12 , in an alternative embodiment, one 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 a wind guiding edge 151. In this embodiment, the wind guiding edge 151 can guide the gas in all directions, thereby improving the uniformity of gas distribution; and the gas will be guided by the wind guiding edge 151 to the higher end of the thrust unit 110 to maintain the gas pressure below the higher end of the thrust unit 110, reduce the risk of downward deformation of the higher end of the thrust unit 110, and further prevent the ventilation hole 140 provided at the higher end from being blocked by the support assembly 200.

[0078] The embodiment of the present application also discloses a rotating machine, including the thrust gas bearing described in any of the above embodiments. In this way, the rotating machine has the beneficial effects of the above thrust gas bearing, which will not be elaborated here. Optionally, please refer to Figure 15 , the rotating machine further includes a rotor 400. The rotor 400 is sleeved inside the thrust gas bearing. The rotor 400 includes a thrust disk 410 protruding radially. The number of thrust gas bearings is two. The two thrust gas bearings are spaced along the axial direction of the rotor 400 and are arranged in opposite directions. The thrust disk 410 is located between the two thrust gas bearings to achieve the two-way suspension of the thrust disk 410 by using the two thrust gas bearings.

[0079] In the above embodiments of the present application, the differences between the various embodiments are mainly described. As long as the different optimization features between the various embodiments are not contradictory, they can be combined to form a more optimal embodiment. For the sake of brevity of the text, it will not be elaborated here. The embodiments of the present application have been described above with reference to the drawings. However, the present application is not limited to the above specific embodiments. The above specific embodiments are only illustrative and not restrictive. Under the inspiration of the present application, those of ordinary skill in the art can also make many forms without departing from the purpose of the present application and the scope protected by the claims, and all of them belong to the protection scope of the present application.

Claims

1. A thrust gas bearing, characterized in that, Comprising a top foil (100) and a support assembly (200), 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) sequentially distributed along the circumferential direction of the top foil (100); At least a part of the thrust unit (110) is inclined relative to the support assembly (200) to form a wedge-shaped converging space between the thrust disc (410) of the rotor (400) and the thrust unit (110). The inclined part of the thrust unit (110) relative to the support assembly (200) is spaced apart from the support assembly (200) to form a first gas space (310) therebetween. The first gas space (310) can avoid the thrust unit (110) to allow the thrust unit (110) to elastically deform in the direction close to the support assembly (200); In the circumferential direction of the top foil (100), the inclined part of the thrust unit (110) relative to the support assembly (200) has a higher end, and a ventilation hole (140) is provided at the higher end. The ventilation hole (140) is communicated with the first gas space (310); 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), and there is a gap between the first support structure and the other of the thrust unit (110) and the support assembly (200); When the end of the thrust unit (110) provided with the ventilation hole (140) is in limit fit with the support assembly (200) through the first support structure, a fluid channel is formed between the ventilation hole (140) and the first gas space (310).

2. The thrust gas bearing according to claim 1, characterized in that, The thrust unit (110) includes a first section (113) and a second section (112) that are bent relative to each other. The first section (113) is inclined relative to the support assembly (200) to cooperate with the thrust disc (410) to form the converging space. The first section (113) also has a lower end distributed along the circumferential direction of the top foil (100). The ventilation hole (140) is provided at the higher end, and the higher end is bent relative to the second section (112); and / or, Any two adjacent thrust units (110) are separated, and the thrust unit (110) also has a lower end distributed along the circumferential direction of the top foil (100), and the lower end can move relative to the support assembly (200).

3. The thrust gas bearing according to claim 1, wherein The ventilation hole (140) includes a first ventilation hole (141). The thrust unit (110) includes a first region, and the first region is recessed toward the first gas space (310) to form a recess (150). The first ventilation hole (141) is formed in the recess (150), and the first support structure includes the recess (150).

4. The thrust gas bearing according to claim 3, wherein The ventilation hole (140) further includes a second ventilation hole (142) that penetrates through two opposite plate surfaces of the thrust unit (110), and two hole edges of the second ventilation hole (142) are flush with the two opposite plate surfaces of the thrust unit (110), respectively.

5. The thrust gas bearing according to claim 4, characterized in that, 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 arranged alternately.

6. The thrust gas bearing according to claim 3, characterized in that, One end of the recessed portion (150) facing away from the thrust unit (110) is an open end. A plurality of deformation notches penetrating through the side wall of the recessed portion (150) are provided on the recessed portion (150). The plurality of deformation notches are spaced apart along the circumferential direction of the recessed portion (150), and the deformation notches extend to the end surface of the open end of the recessed portion (150).

7. The thrust gas bearing according to claim 3, characterized in that, A first air outlet is provided on the side wall of the recessed portion (150), and the first air outlet faces the lower end of the two ends of the inclined portion of the thrust unit (110) relative to the support assembly (200); and / or A second air outlet is provided on the side wall of the recessed portion (150), and the second air outlet faces away from the lower end of the two ends of the inclined portion of the thrust unit (110) relative to the support assembly (200).

8. The thrust gas bearing according to claim 3, wherein, One end of the recessed portion (150) facing away from the thrust unit (110) is an open end, and the open end of the recessed portion (150) is turned outwards to form a wind guiding edge (151).

9. A rotating machine, characterized in that, It includes the thrust gas bearing according to any one of claims 1 to 8.

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