Rotating machinery, thrust gas bearing and processing method thereof

Abstract

The present application belongs to the technical field of gas bearings, and specifically relates to a rotating machine, a thrust gas bearing and a processing method thereof. The thrust gas bearing comprises a top foil and a support assembly, wherein the top foil is superimposed and connected to the support assembly, and the top foil comprises a plurality of thrust units distributed at intervals along the circumference of the top foil, and any two adjacent thrust units are separately arranged; at least part of the thrust unit is tilted relative to the support assembly to form a wedge-shaped convergence space between the thrust disk of the rotor and the thrust unit, and the thrust unit comprises a first end and a second end distributed along the circumference of the top foil, wherein the first end is lower than the second end, and the first end can move relative to the support assembly; the thrust unit is separated from the support assembly and a first gas space is formed between the two, and the first gas space can avoid the thrust unit to allow the thrust unit to undergo elastic deformation in the direction close to the support assembly. The present application can reduce the production cost of the thrust gas bearing.

Description

Technical Field

[0001] The present application belongs to the technical field of gas bearings, and specifically relates to a rotating machine, a thrust gas bearing and a processing method thereof. Background Art

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

[0003] In the related art, the thrust gas bearing includes a top foil, and the top foil is supported by a corrugated foil. However, the production cost of the corrugated foil is relatively high, so the production cost of the thrust gas bearing in the related art is relatively high. Summary of the invention

[0004] The purpose of the present application is to provide a rotating machine, a thrust gas bearing and a processing method thereof, which can reduce the production cost of the thrust gas bearing.

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

[0006] In a first aspect, the present application provides a thrust gas bearing, comprising a top foil and a support assembly, wherein the top foil is stacked and connected to the support assembly, the top foil comprises a plurality of thrust units spaced apart along the circumference of the top foil, and any two adjacent thrust units are separately arranged;

[0007] At least a portion of the thrust unit is tilted relative to the support assembly to form a wedge-shaped convergence space between the thrust plate of the rotor and the thrust unit, the thrust unit comprising a first end and a second end distributed along the circumference of the top foil, the first end being lower than the second end, and the first end being movable relative to the support assembly;

[0008] The thrust unit is separated from the support assembly and a first gas space is formed therebetween. The first gas space can avoid the thrust unit to allow the thrust unit to elastically deform in a direction close to the support assembly.

[0009] In a second aspect, the present application provides a method for processing a thrust gas bearing, which is used to process the thrust gas bearing, comprising:

[0010] Overlaying and connecting a top foil sheet on the support assembly, the top foil sheet comprising an inner ring body;

[0011] A plurality of slits are provided on the inner ring body and are spaced apart along the circumference of the inner ring body to divide the inner ring body into a plurality of thrust units;

[0012] The first end of the thrust unit is pressed down in a direction close to the support assembly so that the thrust unit is tilted relative to the support assembly.

[0013] In a third aspect, the present application provides a rotating machine including the above-mentioned thrust gas bearing.

[0014] The beneficial technical effects of this application are as follows:

[0015] Since the thrust unit of the present application is separated from the support assembly and a first gas space is formed between the two, during operation, the high-speed rotating rotor will continuously draw in air from the outside of the thrust gas bearing, and the air drawn into the thrust gas bearing from the outside will enter the first gas space. The gas entering the first gas space will cause the first gas space to have a certain pressure, thereby supporting the thrust unit; and the gas in the first gas space will also impact the thrust unit to exert an upward force on the thrust unit, thereby supporting the thrust unit.

[0016] Since the first end of the thrust unit is movable relative to the support assembly, and the first gas space can avoid the thrust unit, when the air film between the thrust plate and the thrust unit is compressed to increase the air pressure between the thrust plate and the thrust unit, the thrust unit can be deformed in the direction close to the support assembly, so that the thrust unit enters the first gas space and compresses the volume of the first gas space. This can not only increase the gas pressure in the first gas space, thereby improving the support performance of the thrust unit, but also increase the windward angle of the thrust unit after the thrust unit is deformed and enters the first gas space. In this way, the impact of the gas on the thrust unit will be stronger, and the upward force exerted on the thrust unit will be greater, so as to improve the support performance of the thrust unit, thereby meeting the support performance requirements for the thrust unit.

[0017] In summary, the present application separates two adjacent thrust units and sets a first gas space below the thrust unit that can avoid the thrust unit, so that the thrust unit can reach or even exceed the supporting performance of the corrugated foil in the related art, so as to replace the corrugated foil in the related art, thereby saving the production cost of the thrust gas bearing. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 The structure of the thrust gas bearing disclosed in the embodiment of the present application is schematically shown in FIG. Figure 1 ;

[0019] Figure 2 An exploded schematic diagram of a thrust gas bearing disclosed in an embodiment of the present application;

[0020] Figure 3 The structure of the thrust gas bearing disclosed in the embodiment of the present application is schematically shown in FIG. Figure 2 ;

[0021] Figure 4 For this application Figure 3 The enlarged schematic diagram of point A in the middle;

[0022] Figure 5 A schematic diagram of the cooperation between the top foil and the spacer disclosed in the embodiment of the present application;

[0023] Figure 6 A cross-sectional view of a thrust gas bearing disclosed in an embodiment of the present application;

[0024] Figure 7 For this application Figure 6 The enlarged schematic diagram of point B in the middle;

[0025] Figure 8 A schematic diagram of the structure of a top foil disclosed in another embodiment of the present application;

[0026] Fig. 9 This is a schematic diagram of the structure of the two-layer foil disclosed in the embodiment of the present application;

[0027] Fig.10 It is a schematic diagram of the structure of the bottom foil disclosed in the embodiment of the present application;

[0028] Fig.11 This is an assembly diagram between the rotor and the thrust gas bearing disclosed in an embodiment of the present application.

[0029] Description of reference numerals:

[0030] 100, top layer foil; 110, thrust unit; 111, deformation opening; 112, second section; 113, first section; 120, outer ring body; 130, connecting ribs; 200, support assembly; 210, second layer foil; 211, first support structure; 212, first support portion; 213, annular support portion; 220, third layer foil; 230, bottom layer foil; 231, second support structure; 240, base; 250, spacer; 310, first gas space; 320, second gas space; 400, rotor; 410, thrust plate. DETAILED DESCRIPTION

[0031] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0032] The terms "first", "second", etc. in the specification and claims of the present application are used to distinguish similar objects, and are not used to describe a specific order or sequence. It should be understood that the data used in this way can be interchangeable under appropriate circumstances, so that the embodiments of the present application can be implemented in an order other than those illustrated or described here, and the objects distinguished by "first", "second", etc. are generally of one type, and the number of objects is not limited. For example, the first object can be one or more. In addition, "and / or" in the specification and claims represents at least one of the connected objects, and the character " / " generally indicates that the objects associated with each other are in an "or" relationship.

[0033] The rotating machinery, thrust gas bearing and processing method thereof provided in the embodiments of the present application are described in detail below with reference to the accompanying drawings through specific embodiments and their application scenarios.

[0034] like Figures 1 to 11 As shown, an embodiment of the present application discloses a thrust gas bearing, including 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 at intervals along the circumference of the top foil 100, and any two adjacent thrust units 110 are separately arranged, that is, there is no connection relationship between the ends of the two adjacent thrust units 110, that is, there is no connection relationship between the first end of any thrust unit 110 and the second end of the adjacent thrust unit 110, and the first end and the second end here are the two ends of the thrust unit 110 along the circumference of the top foil 100.

[0035] Exemplarily, the thrust unit 110 here can extend along the circumference of the top foil 100, and can be in a fan-shaped shape. A plurality of thrust units 110 are surrounded to form a first mating hole located inside the top foil 100, and the first mating hole is used for the rotor 400 to pass through; a second mating hole is formed inside the support assembly 200, and the second mating hole is also used for the rotor 400 to pass through, and the first mating hole and the second mating hole can be coaxially arranged.

[0036] At least a portion of the thrust unit 110 is tilted relative to the support assembly 200 to form a wedge-shaped convergence space between the thrust disk 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 convergence space gradually decreases along the rotation direction of the rotor 400. That is, the height of the portion of the thrust unit 110 tilted relative to the support assembly 200 gradually increases along the rotation direction of the rotor 400. The thrust unit 110 includes a first end and a second end distributed along the circumference of the top foil 100, the first end being lower than the second end. The relative height here is Figure 1 The height of the viewing angle shown is such that the first end can move relative to the support assembly 200 .

[0037] Optionally, all parts of the thrust unit 110 may be tilted relative to the support assembly 200; or a part of the thrust unit 110 is tilted relative to the support assembly 200, and the other part is not tilted relative to the support assembly 200. In this case, the thrust unit 110 may include a second section 112 and a first section 113 connected to each other, the second section 112 is not tilted relative to the support assembly 200, and it may be parallel to the plane where the support assembly 200 is located, and an end of the first section 113 away from the second section 112 (i.e., the first end of the thrust unit 110) is bent downward relative to the second section 112, so that the first section 113 is tilted relative to the support assembly 200.

[0038] The thrust unit 110 is separated from the support assembly 200 and a first gas space 310 is formed therebetween. The first gas space 310 can avoid the thrust unit 110 to allow the thrust unit 110 to elastically deform in a direction approaching the support assembly 200. In other words, the thrust unit 110 is elastic and can elastically deform in a direction approaching the support assembly 200 and can also restore the elastic deformation in a direction away from the support assembly 200.

[0039] In the present application, at least a portion of the thrust unit 110 is tilted relative to the support assembly 200 to form a wedge-shaped convergence space between the thrust plate 410 and the thrust unit 110. When the thrust gas bearing sleeve of the present application is mounted outside the rotor 400, the high-speed rotation of the rotor 400 will generate an air film in the convergence space to support the thrust plate 410, thereby achieving axial suspension.

[0040] Since the thrust unit 110 of the present application is separated 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, and the air drawn into the thrust gas bearing from the outside will enter the first gas space 310. The gas entering the first gas space 310 will cause the first gas space 310 to have a certain pressure, thereby supporting the thrust unit 110; and the gas in the first gas space 310 will also impact the thrust unit 110 to apply an upward force to the thrust unit 110, thereby supporting the thrust unit 110.

[0041] Since the first end of the thrust unit 110 is movable relative to the support assembly 200, and the first gas space 310 can avoid the thrust unit 110, the air film between the thrust plate 410 and the thrust unit 110 will exert a downward force on the thrust unit 110. Therefore, when the air film is compressed and the air pressure between the thrust plate 410 and the thrust unit 110 increases, the force will also increase, so that the thrust unit 110 can be deformed in the direction close to the support assembly 200, so that the thrust unit 110 enters the first gas space 310. 0 thereby compressing the volume of the first gas space 310, which can not only increase the gas pressure in the first gas space 310, but also improve the support performance of the thrust unit 110; at the same time, the first end of the thrust unit 110 will move relative to the support assembly 200 to approach the second end of the thrust unit 110. It should be noted that while the thrust unit 110 is deformed in the direction of approaching the support assembly 200, the first end of the thrust unit 110 will move relative to the support assembly 200 to approach the second end of the thrust unit 110. It should be noted that since the thrust units 110 are separated, the thrust units 110 are more likely to deform, thereby improving the support performance of the thrust units 110, and when the first end of any thrust unit 110 moves, it will not pull the adjacent thrust unit 110, thereby not driving the adjacent thrust unit 110 to move, so as to prevent the position of the wedge-shaped convergence space from changing, thereby reducing the bearing capacity of the thrust gas bearing.

[0042] In addition, after the thrust unit 110 is deformed and enters the first gas space 310, the windward angle of the thrust unit 110 will increase, so that the impact of the gas on the thrust unit 110 will be stronger, and the upward force applied to the thrust unit 110 will be greater, so as to improve the support performance of the thrust unit 110, thereby meeting the support performance requirements for the thrust unit 110.

[0043] In summary, the present application separates two adjacent thrust units 110, and sets a first gas space 310 below the thrust unit 110 that can avoid the thrust unit 110, so that the thrust unit 110 reaches or even exceeds the supporting performance of the corrugated foil in the related art, so as to replace the corrugated foil in the related art, thereby saving the production cost of the thrust gas bearing.

[0044] In an optional embodiment, in any two adjacent thrust units 110, the first end of one thrust unit 110 and the second end of the other thrust unit 110 are spaced apart in the axial direction of the top foil 100, and the axial distance between the two gradually decreases from the outside to the inside. Here, the axial distance is Figure 4 For details, please refer to Figure 4 The D dimension in the figure is also Figure 4 For details, please refer to Figure 4 The x-arrow line indicates the direction.

[0045] In this embodiment, among the multiple thrust units 110, the first end of any thrust unit 110 will be lower than the second end of the adjacent thrust unit 110, and the axial distance between the first end of the thrust unit 110 and the second end of the adjacent thrust unit 110 gradually decreases from the outside to the inside, that is, the outer side of the thrust unit 110 is inclined downward relative to the inner side of the thrust unit 110, which can increase the depth and volume of the convergence space. Obviously, this will increase the thickness of the air film formed in the convergence space, thereby enhancing the support effect on the thrust unit 110.

[0046] 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 outer side of the thrust unit 110 of the present application is inclined downward relative to the inner side of the thrust unit 110, the opening size of the outer side of the first gas space 310 located below the thrust unit 110 is smaller than the opening size of the inner side of the first gas space 310, which allows the gas to 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 support effect on the thrust unit 110.

[0047] The rotor 400 will disturb the airflow during the rotation process, so that the gas will flow along the circumferential direction of the top foil 100. In order to prevent the gas flowing along the circumferential direction from entering the gap between the first end of the thrust unit 110 and the support assembly 200, the first end of the thrust unit 110 is prevented from being warped by the circumferential gas and reducing the support stability of the thrust unit 110. In an optional embodiment, among the plurality of thrust units 110, the first end of any thrust unit 110 is located below the second end of the adjacent thrust unit 110.

[0048] In this embodiment, the first end of the thrust unit 110 is located below the second end of the adjacent thrust unit 110, so that the first end of the thrust unit 110 can be hidden in the space between the second 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 second end of the adjacent thrust unit 110. After such a configuration, the circumferentially flowing gas will directly reach the surface of the first end of the thrust unit 110 after flowing out from the second end of the adjacent thrust unit 110, and flow on the surface of the thrust unit 110, thereby reducing the risk of the circumferentially flowing gas entering the gap between the first end of the thrust unit 110 and the support assembly 200, thereby reducing the risk of the first end of the thrust unit 110 being warped and reducing the support stability of the thrust unit 110.

[0049] Of course, the first end of the thrust unit 110 may also be staggered with the second end of the adjacent thrust unit 110 in the axial direction, and the present application does not limit this.

[0050] In order to separate the thrust unit 110 from the support assembly 200 to form the first gas space 310, in an optional embodiment, at least one of the support assembly 200 and the top foil 100 is formed with a first support structure 211, and the top foil 100 is supported on the support assembly 200 by the first support structure 211, 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 first support structure 211, and the thrust unit 110 is separated from the support assembly 200. Since the first support structure 211 has a high strength, the support stability of the top foil 100 can be further improved.

[0051] In an optional embodiment, the first support structure 211 includes a plurality of first support portions 212 spaced apart along the circumference of the top foil 100, and the second end of each thrust unit 110 is respectively supported on each first support portion 212. Specifically, the first support portion 212 is located at one side of the first gas space 310 below the thrust unit 110 in the circumferential direction.

[0052] The second ends of the thrust units 110 of the present embodiment are respectively supported by the first support portions 212, so that the second ends of the thrust units 110 have better rigidity performance, and the second 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.

[0053] In a further embodiment, the first support structure 211 also includes an annular support portion 213, each first support portion 212 is arranged in the annular support portion 213 and connected to the annular support portion 213, and the outer ring body 120 of the above-mentioned top foil 100 can be supported on the annular support portion 213, thereby further improving the supporting performance of the support assembly 200 for the top foil 100.

[0054] Alternatively, in an optional embodiment, the top foil 100 also includes an outer ring body 120 connected to the support assembly 200, and each thrust unit 110 is connected to the outer ring body 120 via a connecting rib 130, and the connecting rib 130 is bent upward relative to the outer ring body 120 to separate the thrust unit 110 from the support assembly 200.

[0055] In this embodiment, each thrust unit 110 is connected to the outer ring body 120 through the connecting rib 130, and the outer ring body 120 is connected to the support assembly 200, so that 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, so that the thrust unit 110 connected to the connecting rib 130 can be lifted upward, thereby separating the thrust unit 110 from the support assembly 200, so that the thrust unit 110 is tilted relative to the support assembly 200, and the first gas space 310 is formed. It can be seen that in this embodiment, the thrust unit 110 is separated from the support assembly 200 by the structure of the top foil 100 itself, so that the above-mentioned first support structure 211 can be selected not to be provided, so that the structure of the thrust gas bearing can be simplified.

[0056] See also Figure 2 In an optional embodiment, the support assembly 200 includes a second-layer foil 210, a third-layer foil 220 and a bottom foil 230 stacked in sequence from top to bottom, a first support structure 211 is formed on the second-layer foil 210, a plurality of second support structures 231 spaced along its own circumferential direction are formed on the bottom foil 230, the third-layer foil 220 is supported on the second support structure 231, and the first end of the thrust unit 110 passes through the gap between two adjacent first support portions 212 and contacts the third-layer foil 220. Specifically, a partial area of ​​the third-layer foil 220 is exposed through the gap between two adjacent first support portions 212 of the second-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 third-layer foil 220, that is, the first gas space 310 of the present application is formed between the thrust unit 110 and the third-layer foil 220.

[0057] A second gas space 320 is formed between two adjacent second support structures 231 . The junction between the first end of the thrust unit 110 and the three-layer foil 220 is a first junction. The first junction and the middle of the second gas space 320 are arranged opposite to each other in the axial direction of the top foil 100 .

[0058] In this embodiment, the plurality of second 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 second 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 of this embodiment is arranged 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 is deformed, the first end of the thrust unit 110 will The top foil 220 applies a downward force, so that the portion of the three-layer foil 220 located between the two second support structures 231 is elastically deformed downward, so that the portion of the three-layer foil 220 invades the second gas space 320, thereby increasing the gas pressure in the second gas space 320, and further improving the support 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 this can further improve the support performance of the thrust unit 110. Of course, the first joint can also be arranged opposite to the second support structure 231 in the axial direction of the top foil 100.

[0059] Optionally, the support assembly 200 further includes a base 240 , the bottom foil is stacked on the base 240 , and the second gas space 320 is located between the base 240 and the three-layer foil 220 .

[0060] Since the air film between the thrust plate 410 and the thrust unit 110 applies a downward force to the thrust unit 110, the first end of the thrust unit 110 is pressed tightly against the support assembly 200. Since at least a portion of the thrust unit 110 is inclined relative to the support assembly 200, the portion of the thrust unit 110 that contacts the support assembly 200 is most likely the edge of the first end of the thrust unit 110. Therefore, 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.

[0061] To prevent damage to the support assembly 200, refer to Figure 8In an optional embodiment, the first end of the thrust unit 110 is provided with a deformation opening 111, and the deformation opening 111 passes through from one plate surface of the thrust unit 110 to another 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 a deformation opening 111, which can reduce the rigidity of the first end of the thrust unit 110, so that under the action of the air film between the thrust plate 410 and the thrust unit 110, the first end of the thrust unit 110 will be elastically deformed, so that the plate surface of the first end of the thrust unit 110 fits with the support assembly 200, and then 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 will be increased to reduce the risk of damage to the support assembly 200. Of course, the first end of the thrust unit 110 may not be provided with a deformation opening 111, and this application is not limited to this.

[0062] And / or, in an optional embodiment, a padding member 250 is connected below the first end of the thrust unit 110, and the padding member 250 is stacked on the support assembly 200, that is, the first end of the thrust unit 110 is indirectly in contact with the support assembly 200. In this embodiment, the first end of the thrust unit 110 is padded by the padding member 250, so that the thrust unit 110 is more likely to elastically deform; and after the first end of the thrust unit 110 is padded, the volume of the first gas space 310 below the thrust unit 110 will be increased, so that the first gas space 310 can allow the thrust unit 110 to deform to a greater extent, thereby further improving the support effect of the thrust unit 110. Of course, the padding member 250 may not be provided below the thrust unit 110, and in this case, the first end of the thrust unit 110 may directly contact the support assembly 200.

[0063] In an optional embodiment, the pad 250 is a sheet-like structural member, and at least one of the outer edge of the thrust unit 110 and the inner edge of the thrust unit 110 radially protrudes beyond the pad 250. In this way, the risk of the thrust unit 110 protruding beyond the inner edge and / or outer edge of the pad 250 can be reduced during the sliding process of the thrust unit 110 relative to the pad 250, thereby reducing the risk of the inner edge and / or outer edge of the pad 250 scratching the thrust unit 110 and reducing the structural strength of the thrust unit 110.

[0064] And / or, in an optional embodiment, the raising member 250 is a sheet-like structural member, the outer side of the thrust unit 110 is supported on the raising member 250, and there is an avoidance gap between the inner side of the thrust unit 110 and the raising member 250, that is, the raising member 250 does not support all parts of the first end of the thrust unit 110, so that the thrust unit 110 is more easily deformed downward, thereby further improving the support performance of the thrust unit 110.

[0065] The embodiment of the present application further discloses a method for processing a thrust gas bearing, which is used to process the thrust gas bearing described in any of the above embodiments, comprising:

[0066] S100 , stacking and connecting the top foil 100 on the support assembly 200 , wherein the top foil 100 includes an inner ring body spaced apart from the support assembly 200 .

[0067] S200, a plurality of slits are provided on the inner ring body at intervals along the circumference of the inner ring body to divide the inner ring body into a plurality of thrust units 110. Specifically, the slits extend from the inner edge of the inner ring body to the outer edge of the inner ring body, and an independent thrust unit 110 is formed between two adjacent slits.

[0068] S300, the first end of the thrust unit 110 is pressed down in a direction close to the support assembly 200, so that the thrust unit 110 is tilted relative to the support assembly 200. Here, a punching device can be used to press down the first ends of multiple thrust units 110 at the same time, or the first end of each thrust unit 110 can be pressed down manually. After the thrust unit 110 is tilted relative to the support assembly 200, a convergence space and a first gas space 310 can be formed.

[0069] It can be seen that the present application only needs to set a plurality of slits on the inner ring body and then press down the first end of the thrust unit 110 to form a support structure for the top foil 100 , and the processing is simple.

[0070] The embodiment of the present application also discloses a rotary machine, including the thrust gas bearing described in any of the above embodiments, so that the rotary machine has the beneficial effects of the thrust gas bearing structure, which will not be repeated here. Optionally, the rotary machine also includes a rotor 400, the rotor 400 is sleeved in the thrust gas bearing, the rotor 400 includes a radially protruding thrust disk 410, the number of thrust gas bearings includes two, the two thrust gas bearings are spaced and arranged in opposite directions along the axial direction of the rotor 400, and the thrust disk 410 is located between the two thrust gas bearings, so as to use the two thrust gas bearings to achieve bidirectional suspension of the thrust disk 410.

[0071] The above embodiments of the present application focus on the differences between the various embodiments. As long as the different optimization features between the various embodiments are not contradictory, they can be combined to form a better embodiment. Considering the simplicity of the text, they will not be repeated here. The embodiments of the present application are described above in conjunction with the accompanying drawings, but the present application is not limited to the above-mentioned specific implementation methods. The above-mentioned specific implementation methods are merely illustrative and not restrictive. Under the enlightenment of the present application, ordinary technicians in this field can also make many forms without departing from the scope of protection of the purpose of the present application and the claims, all of which are within the protection of the present application.

Claims

1. A thrust gas bearing, characterized in that: The invention comprises a top foil (100) and a support assembly (200), wherein the top foil (100) is superimposed and connected to the support assembly (200), and the top foil (100) comprises a plurality of thrust units (110) distributed at intervals along the circumference of the top foil (100), and any two adjacent thrust units (110) are separately arranged; At least a portion of the thrust unit (110) is tilted relative to the support assembly (200) to form a wedge-shaped convergent space between the thrust disk (410) of the rotor (400) and the thrust unit (110), the thrust unit (110) comprising a first end and a second end distributed along the circumference of the top foil (100), the first end being lower than the second end, and the first end being movable relative to the support assembly (200); The thrust unit (110) is separated from the support assembly (200) and a first gas space (310) is formed therebetween, and the first gas space (310) is capable of avoiding the thrust unit (110) to allow the thrust unit (110) to undergo elastic deformation in a direction approaching the support assembly (200); At least one of the support assembly (200) and the top foil (100) is formed with a first support structure (211), and the top foil (100) is supported on the support assembly (200) by the first support structure (211) so that the thrust unit (110) is separated from the support assembly (200); The first support structure (211) comprises a plurality of first support portions (212) spaced apart along the circumference of the top foil (100), and the second end of each thrust stop unit (110) is supported on each first support portion (212).

2. The thrust gas bearing according to claim 1, characterized in that: In any two adjacent thrust units (110), the first end of one thrust unit (110) and the second end of the other thrust unit (110) are spaced apart in the axial direction of the top foil (100), and the axial distance between the two gradually decreases from the outside to the inside.

3. The thrust gas bearing according to claim 1, characterized in that: Among the plurality of thrust units (110), the first end of any one of the thrust units (110) is located below the second end of an adjacent thrust unit (110).

4. The thrust gas bearing according to claim 1, characterized in that: The top foil (100) further comprises an outer ring body (120) connected to the support assembly (200), each of the thrust units (110) being connected to the outer ring body (120) via a connecting rib (130), and the connecting rib (130) being bent upward relative to the outer ring body (120) so as to separate the thrust unit (110) from the support assembly (200).

5. The thrust gas bearing according to claim 1, characterized in that: The support assembly (200) comprises a second-layer foil (210), a third-layer foil (220) and a bottom-layer foil (230) stacked in sequence from top to bottom, the second-layer foil (210) being provided with the first support structure (211), the bottom-layer foil (230) being provided with a plurality of second support structures (231) spaced apart along its circumference, the third-layer foil (220) being supported on the second support structures (231), and the first end of the thrust stop unit (110) passing through a gap between two adjacent first support portions (212) and contacting the third-layer foil (220); A second gas space (320) is formed between two adjacent second support structures (231); a 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 a middle portion of the second gas space (320) are arranged opposite to each other in the axial direction of the top foil (100).

6. The thrust gas bearing according to claim 1, characterized in that: 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 another plate surface, and the deformation opening (111) extends to the end surface of the first end of the top foil (100); and / or, A cushioning member (250) is connected below the first end of the thrust unit (110), and the cushioning member (250) is stacked on the support assembly (200).

7. The thrust gas bearing according to claim 6, characterized in that: The cushioning member (250) is a sheet-like structural member; At least one of the outer edge of the thrust unit (110) and the inner edge of the thrust unit (110) radially protrudes beyond the padding member (250); and / or the outer side of the thrust unit (110) is supported on the padding member (250), and an avoidance gap is provided between the inner side of the thrust unit (110) and the padding member (250).

8. A method for processing a thrust gas bearing, characterized in that: Used to manufacture a thrust gas bearing as claimed in any one of claims 1 to 7, comprising: The top foil (100) is stacked and connected to the support assembly (200), wherein the top foil (100) comprises an inner ring body which is spaced apart from the support assembly (200); A plurality of slits are provided on the inner ring body and are spaced apart from each other along the circumference of the inner ring body, so as to divide the inner ring body into a plurality of thrust units (110); The first end of the thrust unit (110) is pressed down in a direction close to the support assembly (200), so that the thrust unit (110) is tilted relative to the support assembly (200).

9. A rotating machine, characterized in that: Comprising the thrust gas bearing according to any one of claims 1 to 7.

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