Thrust gas bearing and rotating machine

Abstract

The invention belongs to the technical field of gas bearings, and particularly relates to a thrust gas bearing and a rotating machine. The thrust gas bearing comprises a top-layer foil piece and a supporting assembly, the top-layer foil piece is connected to the supporting assembly in an overlapped mode, and the top-layer foil piece comprises a plurality of thrust units which are sequentially distributed in the circumferential direction of the top-layer foil piece; at least part of the thrust unit is obliquely arranged relative to the supporting assembly so that a wedge-shaped convergence space can be formed between a thrust disc of the rotor and the thrust unit, the part, oblique relative to the supporting assembly, of the thrust unit is separated from the supporting assembly so that a first gas space can be formed between the thrust unit and the supporting assembly, and the first gas space can avoid the thrust unit. The thrust unit is allowed to elastically deform in the direction close to the supporting assembly; in the circumferential direction of the top-layer foil, the part, inclined relative to the supporting assembly, of the thrust unit is provided with a high end, the high end is provided with a ventilation hole, and the ventilation hole communicates with the first gas space. The thrust gas bearing can solve the problem that the heat dissipation effect of an existing thrust gas bearing is not ideal.

Description

Technical Field

[0001] The present application belongs to the technical field of gas bearings, and in particular relates to a thrust gas bearing and a rotating machine. 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, which can form a wedge-shaped convergence space between itself and the thrust disk of the rotor, thereby realizing the axial suspension of the rotor; in order to improve the heat dissipation performance of the thrust gas bearing, the related art provides ventilation holes on the top foil, and forms a cooling channel between the top and bottom of the top foil through the ventilation holes to better dissipate the heat of the thrust gas bearing. However, in practice, even with the ventilation holes, the heat dissipation effect of the thrust gas bearing is still not ideal. Summary of the invention

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

[0005] In order to solve the above technical problems, this application is implemented as follows: 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, and the top foil comprises a plurality of thrust units sequentially distributed along the circumference of the top foil; At least part 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, and the part of the thrust unit tilted relative to the support assembly is separated from the support assembly to form a first gas space therebetween, and 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; In the circumferential direction of the top foil, a portion of the thrust unit that is inclined relative to the support assembly has a higher end, and a ventilation hole is provided at the higher end, and the ventilation hole is communicated with the first gas space.

[0006] In a second aspect, the present application provides a rotating machine, comprising the above-mentioned thrust gas bearing.

[0007] The beneficial technical effects of this application are as follows: In the present application, the ventilation holes on the thrust unit are arranged at the higher end of the portion of the thrust unit that is inclined 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, the higher end of the inclined portion of the thrust unit requires a larger deformation to contact the support assembly. Therefore, the present application arranges the ventilation holes at the higher end of the inclined portion of the thrust unit to reduce the risk of the ventilation holes contacting the support assembly and blocking the ventilation holes, thereby preventing the cooling channel between the top and bottom of the top foil from being cut off, so as to ensure that the thrust gas bearing has a better heat dissipation effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0008] Figure 1 The structure of the thrust gas bearing disclosed in the embodiment of the present application is schematically shown in FIG. Figure 1 ; Figure 2 An exploded schematic diagram of a thrust gas bearing disclosed in an embodiment of the present application; Figure 3 The structure of the thrust gas bearing disclosed in the embodiment of the present application is schematically shown in FIG. Figure 2 ; Figure 4 For this application Figure 3 The enlarged schematic diagram of point A in the middle; Figure 5 A schematic diagram of the cooperation between the top foil and the spacer disclosed in the embodiment of the present application; Figure 6 A cross-sectional view of a thrust gas bearing disclosed in an embodiment of the present application; Figure 7 For this application Figure 6 The enlarged schematic diagram of point B in the middle; Figure 8 A schematic diagram of the structure of a top foil disclosed in another embodiment of the present application; Fig. 9 A schematic diagram of the structure of a top foil disclosed in another embodiment of the present application; Fig.10 For this application Fig. 9 The enlarged schematic diagram of the center C; Fig.11 A schematic diagram of the structure of a top foil disclosed in another embodiment of the present application; Fig.12 For this application Fig.11 The enlarged schematic diagram of point D in the middle; Fig.13 This is a schematic diagram of the structure of the two-layer foil disclosed in the embodiment of the present application; Fig.14 It is a schematic diagram of the structure of the bottom foil disclosed in the embodiment of the present application; Fig.15This is an assembly diagram between the rotor and the thrust gas bearing disclosed in an embodiment of the present application.

[0009] Description of reference numerals: 100, top layer foil; 110, thrust unit; 111, deformation opening; 112, second section; 113, first section; 120, outer ring body; 130, connecting ribs; 140, ventilation holes; 141, first ventilation holes; 142, second ventilation holes; 150, recessed portion; 151, wind guide edge; 200, support assembly; 210, second layer foil; 211, second support structure; 212, first support portion; 213, annular support portion; 220, third layer foil; 230, bottom layer foil; 231, third support structure; 240, base; 250, padding member; 310, first gas space; 320, second gas space; 400, rotor; 410, thrust plate. DETAILED DESCRIPTION

[0010] 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.

[0011] 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.

[0012] Combine the following Figures 1 to 15 , the thrust gas bearing and rotating machinery provided in the embodiments of the present application are described in detail through specific embodiments and their application scenarios.

[0013] In the related art, a 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 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 portion of the thrust unit tilted relative to the support assembly is separated from the support assembly to form a first gas space therebetween, and ventilation holes are provided on the thrust unit, so that the gas above the thrust unit can enter the bottom of the thrust unit through the ventilation holes, thereby improving the gas flow performance to dissipate heat for the thrust gas bearing.

[0014] The inventors have found that the ventilation hole in the related art is opened at the lower end of the two ends of the thrust unit. Since no other supporting structure is arranged 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 hole, thereby cutting off the cooling channel formed between the top and bottom of the top foil. Obviously, this will lead to unsatisfactory heat dissipation effect of the thrust gas bearing.

[0015] See also Figure 1 , Figure 2 , Figure 6 and Figure 7 The embodiment of the present application discloses a thrust gas bearing, comprising 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 comprises a plurality of thrust units 110 sequentially distributed along the circumference of the top foil 100. Exemplarily, the thrust units 110 here may extend along the circumference of the top foil 100, and may be in a fan-shaped shape, and the plurality of thrust units 110 surround and form a first matching hole located inside the top foil 100, and the first matching hole is used for the rotor 400 to pass through; a second matching hole is formed inside the support assembly 200, and the second matching hole is also used for the rotor 400 to pass through, and the first matching hole and the second matching hole may be coaxially arranged.

[0016] 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 portion of the thrust unit 110 tilted relative to the support assembly 200 is separated 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 a direction approaching the support assembly 200. That is, the thrust unit 110 is elastic, and the thrust unit 110 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.

[0017] In the circumferential direction of the top foil 100, the portion of the thrust unit 110 that is inclined relative to the support assembly 200 has a higher end, and the higher end is provided with a ventilation hole 140, and the ventilation hole 140 is connected to the first gas space 310. It should be noted that the higher end of the two ends of the portion of the thrust unit 110 that is inclined relative to the support assembly 200 along the circumferential direction of the top foil 100 is the higher end, and the lower end is the lower end. The higher and lower here are comparisons of the relative heights of the two ends of the inclined portion of the thrust unit 110, and the relative heights here are Figure 1 The height of the perspective displayed.

[0018] 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.

[0019] Furthermore, since the first gas space 310 can avoid the thrust unit 110, when the air film between the thrust plate 410 and the thrust unit 110 is compressed to increase the air pressure between the thrust plate 410 and the thrust unit 110, 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 and compresses 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 of the thrust unit 110, but also increase the windward angle of the thrust unit 110 after the thrust unit 110 is deformed 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 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. In this way, there is no need to provide additional supporting components such as corrugated 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.

[0020] In addition, the ventilation hole 140 on the thrust unit 110 is arranged at the higher end of the portion of the thrust unit 110 that is inclined relative to the support assembly 200, and the distance between the higher 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 the higher end of the inclined portion of the thrust unit 110 requires a larger deformation to contact the support assembly 200. Therefore, the present application arranges the ventilation hole 140 at the higher end of the inclined portion of the thrust unit 110 to reduce the risk of the ventilation hole 140 contacting the support assembly 200 and blocking the ventilation hole 140, thereby preventing the cooling channel between the top and bottom of the top foil 100 from being cut off, so as to ensure that the thrust gas bearing has a better heat dissipation effect. Furthermore, the gas above the top foil 100 can enter the first gas space 310 through the ventilation holes 140 and provide gas supply to the first gas space 310 , thereby ensuring a higher gas pressure in the first gas space 310 , thereby ensuring the support performance of the thrust unit 110 .

[0021] See also Figure 7 In an optional 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 tilted relative to the support assembly 200 to cooperate with the thrust plate 410 to form a convergence space. The first section 113 also has a lower end distributed along the circumference of the top foil 100. The ventilation holes 140 are provided at the higher end, and the higher end is bent relative to the second section 112, so that the first section 113 is tilted relative to the support assembly 200. Optionally, the second section 112 here is not tilted relative to the support assembly 200, and it can be parallel to the plane where the support assembly 200 is located.

[0022] In the present embodiment, the first section 113 of the thrust unit 110 is bent relative to the second section 112, and the bending point between the first section 113 and the second section 112 is located at the higher end of the first section 113 and the junction of the second section 112, and the structural strength of the bending point of the plate will increase after being bent, that is, the strength and rigidity of the bending point between the first section 113 and the second section 112 are both relatively large, and the ventilation hole 140 is arranged at the higher end of the first section 113, that is, the ventilation hole 140 is arranged adjacent to the bending point between the first section 113 and the second section 112, so that the portion 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.

[0023] and / or, see Figure 3 and Figure 4 In an optional embodiment, any two adjacent thrust units 110 are separately arranged, that is, the ends of the two adjacent thrust units 110 are not connected, and 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, the two adjacent thrust units 110 are separated, which can make the thrust unit 110 more easily deformed, thereby improving the support performance of the thrust unit 110, and in the process of the thrust unit 110 deforming in the direction of approaching the support assembly 200, the lower end will move relative to the support assembly 200, so that the lower end is closer to the upper end. In addition, since the 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 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. Of course, the two adjacent thrust units 110 can also be connected, that is, each thrust unit 110 can be connected as a whole, and this application is not limited to this.

[0024] 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. In 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 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.

[0025] In this embodiment, among the multiple thrust units 110, the first end of any thrust unit 110 will be 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 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.

[0026] 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.

[0027] 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 some embodiments, among the plurality of thrust units 110, the first end of any thrust unit 110 is located above the lower end of the adjacent thrust unit 110.

[0028] 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 can be 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. After such arrangement, the circumferentially flowing gas will directly reach the surface of the first end of the thrust unit 110 after flowing out from the lower 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.

[0029] Of course, the first end of the thrust unit 110 may also be staggered with the lower end of the adjacent thrust unit 110 in the axial direction, and the present application is not limited to this.

[0030] 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 third support structure 231, and the top foil 100 is supported on the support assembly 200 by 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 third support structure 231 has a high strength, the support stability of the top foil 100 can be further improved.

[0031] In an optional embodiment, the third support structure 231 includes a plurality of first support portions 212 spaced apart along the circumference 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 portion 212 is located on one side of the first gas space 310 below the thrust unit 110 in the circumferential direction.

[0032] The lower ends of the thrust units 110 of the present embodiment are supported by the first support portions 212, respectively. This allows the lower ends of the thrust units 110 to have better rigidity performance, and the lower ends of the thrust units 110 are less likely to deform 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.

[0033] In a further embodiment, the second 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.

[0034] 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.

[0035] 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 second support structure 211 can be selected not to be provided, so that the structure of the thrust gas bearing can be simplified.

[0036] See also Figure 2 , Fig.13 and Fig.14 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 second support structure 211 is formed on the second-layer foil 210, a plurality of third 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 third 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.

[0037] A second gas space 320 is formed between two adjacent third 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 .

[0038] In this embodiment, a plurality of third support structures 231 on the bottom foil sheet 230 support the three-layer foil sheet 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 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 third 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 third support structure 231 in the axial direction of the top foil 100.

[0039] Optionally, the support assembly 200 further includes a base 240 , 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 .

[0040] 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.

[0041] 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.

[0042] and / or, see Figure 5 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 undergo elastic deformation; 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.

[0043] 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.

[0044] 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.

[0045] See also Figures 9 to 12 In order to prevent the higher end of the inclined portion of the thrust unit 110 from fitting against the support assembly 200 under a higher air pressure and thereby blocking the ventilation hole 140, in an optional 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, and a gap is provided 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 limitedly matched 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.

[0046] 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 toward the first gas space 310, and even if a large gas 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 from 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 channel between the first gas space 310 and the ventilation hole 140, thereby ensuring that the thrust gas bearing has a better heat dissipation effect and better support performance. Of course, the above-mentioned first support structure may not be provided between the thrust unit 110 and the support assembly 200, and this application is not limited to this.

[0047] See also Fig.10 and Fig.12 In an optional embodiment, the ventilation hole 140 includes a first ventilation hole 141, the thrust unit 110 includes a first area, the first area is recessed in a direction close to the first gas space 310 to form a recessed portion 150, the first ventilation hole 141 is formed in the recessed portion 150, and the first support structure includes the recessed portion 150.

[0048] In this embodiment, a downward pressing force is applied to the first area of ​​the thrust unit 110 so that the first area is depressed downward to form a depression 150, and a first ventilation hole 141 is formed in the depression 150, which can increase the hole depth of the first ventilation hole 141, thereby making the flow path of the gas from the top of the thrust unit 110 into the first gas space 310 longer, so as to provide a more uniform gas distribution. In addition, in this embodiment, the depression 150 used to form the first ventilation hole 141 is used to support the higher end of the thrust unit 110, which not only achieves the purpose of one object for multiple uses, but also does not need to set up other additional support structures, thereby simplifying the structure of the gas thrust bearing.

[0049] In some embodiments, the ventilation hole 140 may only include the first ventilation hole 141. In this case, in order to form the above-mentioned fluid channel when the end of the thrust unit 110 provided with the ventilation hole 140 is limitedly matched 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 recessed portion 150. The first air outlet faces the lower end of the two ends of the portion of the thrust unit 110 that is inclined relative to the support assembly 200. After entering the first ventilation hole 141, the gas can flow out from the first air outlet to enter the first gas space 310.

[0050] Please continue reading Fig.10 and Fig.12 In an optional embodiment, the ventilation hole 140 further includes a second ventilation hole 142 , the second ventilation hole 142 passes through two opposite plate surfaces of the thrust unit 110 , and two hole edges of the second ventilation hole 142 are respectively flush with the two opposite plate surfaces of the thrust unit 110 .

[0051] In addition to the first ventilation hole 141, the present embodiment also has a second ventilation hole 142, which can increase the flow of gas entering the first gas space 310 from the top of the thrust unit 110, thereby further improving the heat dissipation effect and support performance of the thrust gas bearing. In addition, the lower hole edge of the second ventilation hole 142 of the present embodiment is higher than the lower hole edge of the first ventilation hole 141, so when the recessed portion 150 contacts 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 that gas can be stably introduced into the first gas space 310, that is, after adopting the structure of the present embodiment, even if the first gas outlet is not provided on the recessed portion 150, the above-mentioned fluid channel can be established.

[0052] In some embodiments, the number of the first ventilation hole 141 and the second ventilation hole 142 may be only one, and in this case, the first ventilation hole 141 and the second ventilation hole 142 may both be bar-shaped holes.

[0053] Please continue reading Fig.10 and Fig.12In an optional embodiment, the number of the first ventilation holes 141 and the second ventilation holes 142 are both multiple, 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.

[0054] In this embodiment, the first ventilation holes 141 and the second ventilation holes 142 are arranged alternately, so that the second ventilation holes 142 can be arranged corresponding to various parts of the first gas space 310 in the radial direction, that is, in the radial direction of the gas thrust bearing, the second ventilation holes 142 are distributed more evenly, so even if the first ventilation holes 141 are blocked by the support assembly 200, the uniformity of gas supply to the first gas space 310 can be ensured only through the second ventilation holes 142, so as to improve the support effect of the thrust unit 110. Of course, the first ventilation holes 141 and the second ventilation holes 142 may not be arranged alternately, and the present application does not limit the arrangement of the first ventilation holes 141 and the second ventilation holes 142.

[0055] In order to prevent the first ventilation hole 141 from being blocked by the support assembly 200 when the recessed portion 150 contacts the support assembly 200, in an optional embodiment, the end of the recessed portion 150 facing away from the thrust unit 110 is an open end, and the recessed portion 150 is provided with a plurality of deformation notches (not shown in the figure) penetrating the side wall of the recessed portion 150, and the plurality of deformation notches are distributed at intervals along the circumference of the recessed portion 150, and the deformation notches extend to the end face of the open end of the recessed portion 150.

[0056] Under the action of the 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 portion will be elastically bent, and the gap between two adjacent sub-support portions will be increased, that is, the width of the deformation notch will be increased, thereby allowing the gas in the first ventilation hole 141 to flow out from the deformation notch to enter the first gas space 310, thereby establishing the above-mentioned fluid channel.

[0057] In an optional embodiment, a second air outlet (not shown in the figure) is provided on the side wall of the recessed portion 150, and the second air outlet is away from the lower end of the portion of the thrust unit 110 that is inclined relative to the support assembly 200, so that the gas will be directed 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 the higher end of the thrust unit 110 deforming downward, and further prevent the ventilation hole 140 provided at the higher end from being blocked by the support assembly 200.

[0058] Please continue reading Fig.12 In an optional embodiment, the end of the recessed portion 150 away from the thrust unit 110 is an open end, and the open end of the recessed portion 150 is folded outward to form a wind guide edge 151. In this embodiment, the wind guide edge 151 can guide the gas to the surroundings, thereby improving the uniformity of gas distribution; and the gas will be guided to the higher end of the thrust unit 110 by the wind guide edge 151 to maintain the gas pressure below the higher end of the thrust unit 110, reduce the risk of the higher end of the thrust unit 110 deforming downward, and further prevent the ventilation hole 140 provided at the higher end from being blocked by the support assembly 200.

[0059] 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, which will not be described in detail here. Fig.15 The rotating machine also includes a rotor 400, which is sleeved in a 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. The thrust disk 410 is located between the two thrust gas bearings to achieve bidirectional suspension of the thrust disk 410 by using the two thrust gas bearings.

[0060] 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 in sequence along the circumference of the top foil (100); At least a portion of the thrust unit (110) is arranged to be tilted relative to the support assembly (200) to form a wedge-shaped convergent space between the thrust plate (410) of the rotor (400) and the thrust unit (110); the portion of the thrust unit (110) tilted relative to the support assembly (200) is arranged to be separated 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 undergo elastic deformation in a direction close to the support assembly (200); In the circumferential direction of the top foil (100), the portion of the thrust unit (110) inclined relative to the support assembly (200) has a higher end, and a ventilation hole (140) is provided at the higher end, and the ventilation hole (140) is connected to the first gas space (310).

2. The thrust gas bearing according to claim 1, characterized in that: The thrust unit (110) comprises a first section (113) and a second section (112) which are bent relative to each other, the first section (113) being arranged obliquely relative to the support assembly (200) so as to cooperate with the thrust plate (410) to form the convergence space, the first section (113) also having a lower end distributed along the circumference of the top foil (100), the ventilation hole (140) being arranged at the higher end, and the higher end being bent relative to the second section (112); and / or, Any two adjacent thrust units (110) are arranged separately, and the thrust unit (110) further comprises a lower end distributed along the circumference of the top foil (100), and the lower end is movable relative to the support assembly (200).

3. The thrust gas bearing according to claim 1, characterized in that: One of the thrust unit (110) and the support assembly (200) is connected to a first support structure, the first support structure is located between the thrust unit (110) and the support assembly (200), and a gap is formed 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 limitedly matched 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).

4. The thrust gas bearing according to claim 3, characterized in that: The ventilation hole (140) comprises a first ventilation hole (141), the thrust unit (110) comprises a first region, the first region is recessed in a direction close to the first gas space (310) to form a recessed portion (150), the first ventilation hole (141) is formed in the recessed portion (150), and the first support structure comprises the recessed portion (150).

5. The thrust gas bearing according to claim 4, characterized in that: The ventilation hole (140) further comprises a second ventilation hole (142), the second ventilation hole (142) penetrating two opposite plate surfaces of the thrust unit (110), and two hole edges of the second ventilation hole (142) are respectively flush with the two opposite plate surfaces of the thrust unit (110).

6. The thrust gas bearing according to claim 5, characterized in that: The number of the first ventilation holes (141) and the number of the second ventilation holes (142) are both multiple, and the first ventilation holes (141) and the second ventilation holes (142) are arranged alternately.

7. The thrust gas bearing according to claim 4, characterized in that: One end of the recessed portion (150) facing away from the thrust unit (110) is an open end, and the recessed portion (150) is provided with a plurality of deformation notches penetrating the side wall of the recessed portion (150), the plurality of deformation notches are distributed at intervals along the circumference of the recessed portion (150), and the deformation notches extend to the end surface of the open end of the recessed portion (150).

8. The thrust gas bearing according to claim 4, characterized in that: A first air outlet is provided on a side wall of the recessed portion (150), the first air outlet facing the lower end of two ends of a portion of the thrust unit (110) inclined relative to the support assembly (200); and / or, A second air outlet is provided on the side wall of the recessed portion (150), the second air outlet being away from the lower end of the two ends of the portion of the thrust unit (110) that is inclined relative to the support assembly (200).

9. The thrust gas bearing according to claim 4, characterized in that: One end of the recessed portion (150) that faces away from the thrust unit (110) is an open end, and the open end of the recessed portion (150) is folded outwards to form a wind guide edge (151).

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

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