Air static pressure radial and thrust integrated bearing based on micropore throttling

Abstract

The invention discloses an air static pressure radial and thrust integrated bearing based on micropore throttling, and relates to the technical field of air bearings. The problems that an existing air static pressure bearing is low in bearing capacity and rigidity and generates thermal deformation under the ultra-high-speed working condition are solved. The air static pressure radial bearing comprises an air static pressure radial bearing body and an air static pressure thrust bearing body, the air static pressure thrust bearing body is coaxially and fixedly connected to the front end of the air static pressure radial bearing body, the air static pressure radial bearing body comprises a radial bearing body and a plurality of throttlers, and an airflow channel is formed in the radial bearing body; a plurality of throttlers are evenly distributed and embedded in the inner side wall of the radial bearing body in the circumferential direction, a plurality of throttling assemblies are evenly distributed in the front end face of the air static pressure thrust bearing in the circumferential direction, and the air inlet ends of the throttlers and the air inlet ends of the throttling assemblies communicate with the airflow channel. The invention is used for the ultra-high-speed air static pressure electric spindle system.

Description

Technical Field

[0001] The invention relates to the technical field of air-floating bearings, and in particular to an air static pressure radial and thrust integrated bearing based on micropore throttling. Background Art

[0002] Aerostatic bearings use high-pressure air to form an air film within the bearing gap, supporting rotating components. These bearings offer advantages such as high rotational precision, long service life, and zero pollution. As key support components, they are crucial for ultra-high-speed electric spindles. However, existing aerostatic bearings generally have low load-bearing capacity and stiffness. Furthermore, under ultra-high-speed operating conditions, the lubricating medium in aerostatic bearings is subjected to strong shear and compression. The viscous stagnation of the air causes intense friction within the air film, resulting in frictional heating of the aerostatic bearing and thermal deformation of the bearing. Summary of the Invention

[0003] In order to solve the problems of low load-bearing capacity and rigidity of existing aerostatic bearings and thermal deformation under ultra-high-speed working conditions, the present invention proposes an aerostatic radial and thrust integrated bearing based on micropore throttling.

[0004] The technical solution adopted by the present invention to solve the above technical problems is:

[0005] An integrated air static pressure radial and thrust bearing based on micropore throttling includes an air static pressure radial bearing and an air static pressure thrust bearing. The air static pressure thrust bearing is coaxially fixed to the front end of the air static pressure radial bearing. The air static pressure radial bearing includes a radial bearing body and multiple throttles. An air flow channel is provided inside the radial bearing body. Multiple throttles are evenly embedded in the inner side wall of the radial bearing body along the circumferential direction. Multiple throttle components are evenly distributed in the circumferential direction on the front end surface of the air static pressure thrust bearing. The air inlet ends of the throttle and the throttle component are respectively connected to the air flow channel.

[0006] Furthermore, the air flow channel includes an air inlet hole, a radial air inlet groove, an air outlet hole, a long through hole and a long air inlet channel. The air inlet hole and the air outlet hole are respectively arranged in the disk surface of the radial bearing body in the radial direction. The radial air inlet groove is opened on the front end surface of the disk surface of the radial bearing body along the circumferential direction. The radial air inlet groove is connected with the outside of the radial bearing body through the air inlet hole. The groove bottom of the radial air inlet groove is evenly distributed with a plurality of long air inlet channels along the circumferential direction. Each long air inlet channel is arranged in the axial direction. A plurality of throttle mounting holes are opened on the inner side of the long air inlet channel along the length direction. Each throttle mounting hole is arranged in the radial direction. The long air inlet channel is connected with the inner side of the radial bearing body through the throttle mounting hole. A throttle is respectively installed in each throttle mounting hole. The inner and outer sides of the radial bearing body are connected through the air outlet hole. The long through hole is arranged on the rear end surface of the radial bearing body along the axial direction. The air inlet end of the long through hole is connected with the air outlet hole.

[0007] Furthermore, the radial bearing body is provided with a water cooling groove.

[0008] Furthermore, the water cooling groove includes a disk water cooling groove and a serpentine water cooling groove. The disk water cooling groove is opened on the front end face of the radial bearing body along the circumferential direction and is arranged on the outside of the radial air inlet groove. The serpentine water cooling groove is opened on the outer side wall of the radial bearing body along the circumferential direction.

[0009] Furthermore, a thrust-stop air groove is provided on the rear end surface of the air static thrust bearing in the circumferential direction. The thrust-stop air groove is arranged corresponding to the radial air inlet groove. The throttling assembly is connected to the air flow channel through the thrust-stop air groove.

[0010] Furthermore, the throttling assembly includes a plurality of thrust air cavities and a plurality of thrust throttling microholes, the plurality of thrust throttling microholes are arranged in parallel along the radial direction on the front end surface of the air static thrust bearing, the plurality of thrust air cavities are arranged in parallel along the radial direction at the bottom of the thrust air groove, and each thrust throttling microhole is connected to a thrust throttling thrust air cavity through a thrust pre-drilled hole.

[0011] Furthermore, a sealing assembly is provided between the aerostatic radial bearing and the aerostatic thrust bearing.

[0012] Furthermore, the sealing assembly includes a radial sealing ring groove and two thrust sealing ring grooves. The radial sealing ring groove is opened on the front end face of the radial bearing body and is arranged on the inner side of the radial air inlet groove. The thrust sealing ring groove is opened on the rear end face of the air static pressure thrust bearing. One thrust sealing ring groove is arranged between the thrust air inlet groove and the disk water cooling groove, and the other thrust sealing ring groove is arranged on the outer side of the disk water cooling groove. Sealing rings are provided in the radial sealing ring groove and the two thrust sealing ring grooves.

[0013] Furthermore, the throttle is cylindrical in shape, the outer end face of the throttle is flush with the inner wall of the radial bearing body, a radial air cavity is opened in the middle of the inner end face of the throttle, and a plurality of radial throttling microholes are opened along the axial direction on the outer end face of the throttle, and each radial throttling microhole is connected to the radial air cavity through a radial pre-drilled hole.

[0014] Furthermore, the outer diameter of the inner end surface of the throttle is smaller than the outer diameter of the outer end surface.

[0015] Compared with the prior art, the present invention has the following beneficial effects:

[0016] 1. In the present invention, the radial bearing and the thrust bearing are connected and then processed as an integrated whole, which can ensure the perpendicularity between the thrust bearing surface and the radial bearing inner surface, and greatly improve the processing accuracy.

[0017] 2. The thrust bearing surface of the present invention is connected to the radial bearing disc surface, and air can be supplied to the radial bearing and the thrust bearing at the same time, making the structure simpler and more compact and reducing costs.

[0018] 3. The present invention does not directly process micro-holes on the radial bearing curved surface, but installs the processed throttle on the throttle mounting hole on the radial bearing, which greatly reduces the processing difficulty.

[0019] 4. The throttle in the present invention is designed as a throttling form with two to three throttling holes as a group, and the bearing adopts a throttling form with double rows of holes. The load-bearing capacity and stiffness of the bearing are improved by increasing the throttling holes; the throttling micropore form is adopted, which can increase the bearing capacity of the bearing and improve the supporting characteristics of the bearing compared to small hole throttling.

[0020] 5. The water cooling grooves on the outer surface of the bearing body of the present invention are serpentine, thereby increasing the effective area of ​​water cooling. The radial bearing disc is provided with water cooling grooves to cool the thrust bearing, making the overall structure simple and compact. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic cross-sectional structural diagram of the present invention as a whole;

[0022] Figure 2 It is a schematic diagram of the overall structure of the air static pressure radial bearing in the present invention;

[0023] Figure 3 Schematic diagram of the cross-sectional structure of the air flow channel of the air static pressure radial bearing in the present invention;

[0024] Figure 4 It is a schematic cross-sectional view of the throttle in the present invention;

[0025] Figure 5 It is a structural schematic diagram of the rear end surface of the air static pressure thrust bearing in the present invention;

[0026] Figure 6 It is a gas supply diagram of the overall structure of the present invention;

[0027] Figure 7 yes Figure 6 A magnified view of part A

[0028] Figure 8 It is a curve diagram of the bearing capacity of small hole throttling and micro hole throttling at different eccentricities. DETAILED DESCRIPTION

[0029] In order to make the technical problems, technical solutions and beneficial effects solved by the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0030] Specific implementation method 1: Combination Figures 1 to 7 To explain this embodiment, the present embodiment describes an integrated air static pressure radial and thrust bearing based on micropore throttling, including an air static pressure radial bearing 1 and an air static pressure thrust bearing 2. The air static pressure thrust bearing 2 is coaxially fixed to the front end of the air static pressure radial bearing 1. The air static pressure radial bearing 1 includes a radial bearing body 11 and a plurality of throttles 12. An air flow channel is provided inside the radial bearing body 11. A plurality of throttles 12 are evenly embedded in the circumferential direction on the inner side wall of the radial bearing body 11. A plurality of throttle components 24 are evenly distributed in the circumferential direction on the inner front end surface of the air static pressure thrust bearing 2. The air inlet ends of the throttle 12 and the throttle component 24 are respectively connected to the air flow channel.

[0031] In this embodiment, the air static pressure radial bearing 1 and the air static pressure thrust bearing 2 are fixedly connected by bolts. A plurality of radial threaded holes 117 are provided on the disk surface of the radial bearing body 11 in the circumferential direction, and a plurality of thrust threaded holes 23 are correspondingly provided on the disk surface of the air static pressure thrust bearing 2. The radial threaded holes 117 and the thrust threaded holes 23 are arranged in a one-to-one correspondence, and bolts are provided in the holes to achieve a fixed connection between the air static pressure radial bearing 1 and the air static pressure thrust bearing 2 and a connection and fixation between the integrated bearing and other related components.

[0032] When machining the aerostatic radial bearing 1 and the aerostatic thrust bearing 2, allowances are left on the working surfaces of the aerostatic radial bearing 1 and the aerostatic thrust bearing 2, respectively. After the machined bearings are connected with bolts, the inner surface of the aerostatic radial bearing 1 and the working plane of the aerostatic thrust bearing 2 are ground and finished, thereby ensuring the verticality of the two and improving the machining accuracy.

[0033] Specific implementation method 2: Combination Figures 1 to 3 and Figure 6Describing this embodiment, the air flow channel in this embodiment includes an air inlet hole 111, a radial air inlet groove 112, an air outlet hole 113, a long through hole 114 and a long air inlet channel 115. The air inlet hole 111 and the air outlet hole 113 are respectively arranged in the disk surface of the radial bearing body 11 in the radial direction, and the radial air inlet groove 112 is opened on the front end surface of the disk surface of the radial bearing body 11 in the circumferential direction. The radial air inlet groove 112 is connected to the outside of the radial bearing body 11 through the air inlet hole 111. The bottom of the radial air inlet groove 112 is evenly distributed with a plurality of long air inlet channels 115 in the circumferential direction. The channels 115 are all arranged in the axial direction, and a plurality of throttle mounting holes 116 are opened on the inner side of the long air inlet channel 115 along the length direction. Each throttle mounting hole 116 is arranged in the radial direction. The long air inlet channel 115 is connected with the inner side of the radial bearing body 11 through the throttle mounting hole 116. A throttle 12 is respectively installed in each throttle mounting hole 116. The inner and outer sides of the radial bearing body 11 are connected through the air outlet hole 113. The long through hole 114 is arranged on the rear end surface of the radial bearing body 11 along the axial direction, and the air inlet end of the long through hole 114 is connected with the air outlet hole 113.

[0034] The undisclosed technical features in this embodiment are the same as those in the first embodiment.

[0035] The radial air inlet groove 112 is an annular groove. The air inlet end of the air inlet hole 111 is arranged on the outer side wall of the disk surface of the radial bearing body 11 , and the air outlet end of the air inlet hole 111 is connected to the radial air inlet groove 112 .

[0036] The long air inlet channel 115 is arranged around the central axis of the aerostatic radial bearing 1. The central angles between any two adjacent long air inlet channels 115 are equal. The diameter of the long air inlet channel 115 is slightly smaller than the width of the radial air inlet groove 112. The long air inlet channel 115 is connected to the radial air inlet groove 112.

[0037] The long air inlet passage 115 is provided with a throttle mounting hole 116, the central axis of which passes through the central axis of the air static pressure radial bearing 1. Each long air inlet passage 115 has two throttle mounting holes 116, that is, the throttle mounting holes 116 are in a double row.

[0038] Specific implementation method three: Combination Figure 1 and Figure 2 To describe this embodiment, the radial bearing body 11 of this embodiment is provided with a water cooling groove 118 .

[0039] The undisclosed technical features in this embodiment are the same as those in the second embodiment.

[0040] Specific implementation method four: Combination Figure 1 and Figure 2To describe this embodiment, the water-cooling groove 118 described in this embodiment includes a disk water-cooling groove 118a and a serpentine water-cooling groove 118b. The disk water-cooling groove 118a is opened on the front end face of the radial bearing body 11 along the circumferential direction and is arranged on the outside of the radial air inlet groove 112. The serpentine water-cooling groove 118b is opened on the outer side wall of the radial bearing body 11 along the circumferential direction.

[0041] The undisclosed technical features in this embodiment are the same as those in the third embodiment.

[0042] The serpentine water-cooling groove 118b is distributed over the outer surface of the radial bearing body 11, thereby increasing the effective area of ​​water cooling and better cooling the radial bearing. When in use, a shell 4 is provided on the outside of the radial bearing body 11 to achieve support. The radial bearing body 11 is inserted into the shell 4. A sealing structure is provided between the shell 4 and the radial bearing body 11. The sealing structure is provided on both sides of the serpentine water-cooling groove 118b to prevent the cooling water from flowing out. A water inlet is provided on one side of the shell 4, and a water outlet is provided on the other side. The cooling water enters the water inlet and flows through the serpentine water-cooling groove 118b to cool the air static pressure radial bearing 1, and is then discharged through the water outlet.

[0043] The surface of the aerostatic radial bearing 1 is equipped with a water-cooling groove 118a, an annular, C-shaped groove. A cooling water inlet and outlet are located on one side of the aerostatic radial bearing 1. Cooling water flows through the inlet, makes a circuit of the groove, and then exits through the outlet on the other side, cooling the aerostatic thrust bearing 2 connected to the aerostatic radial bearing 1. The design of the water-cooling groove 118 effectively solves the problem of bearing heating under ultra-high-speed operating conditions, resulting in a simple and compact overall structure and significantly reducing manufacturing costs.

[0044] Specific implementation method five: Combination Figure 1 、 Figure 5 and Figure 6 To illustrate this embodiment, a thrust-stop air groove 21 is provided on the rear end face of the air static thrust bearing 2 in the circumferential direction. The thrust-stop air groove 21 is arranged corresponding to the radial air inlet groove 112, and the throttling assembly 24 is connected to the air flow channel through the thrust-stop air groove 21.

[0045] The undisclosed technical features in this embodiment are the same as those in the fourth embodiment.

[0046] The anti-thrust air groove 21 is an annular groove, and multiple throttling components 24 are evenly distributed into multiple groups. Each group of throttling components 24 includes multiple throttling components 24 evenly distributed along the circumferential direction. Multiple groups of throttling components 24 are coaxially arranged from the inside to the outside, and each adjacent two groups of throttling components 24 are staggered.

[0047] Specific implementation method six: combination Figure 1 、 Figure 5 and Figure 7 To illustrate this embodiment, the throttling assembly 24 described in this embodiment includes a plurality of thrust air cavities 241 and a plurality of thrust throttling micropores 243. The plurality of thrust throttling micropores 243 are arranged in parallel along the radial direction on the front end surface of the air static pressure thrust bearing 2, and the plurality of thrust air cavities 241 are arranged in parallel along the radial direction at the bottom of the thrust air groove 21. Each thrust throttling micropore 243 is connected to a thrust throttling thrust air cavity 241 through a thrust pre-drilled hole 242.

[0048] The undisclosed technical features in this embodiment are the same as those in the fifth embodiment.

[0049] The number of the thrust throttling micro-holes 243 is two.

[0050] The thrust-stop air groove 21 of the aerostatic thrust bearing 2 houses three throttle assemblies 24. Because the work surface is flat, machining is relatively easy, so the throttle assemblies 24 are machined directly on the bearing. From top to bottom, the throttle assemblies 24 consist of a thrust-stop air cavity 241, a thrust pre-drilled hole 242, and a thrust-stop micro-hole 243. Their configuration is identical to the throttle 12 of the aerostatic radial bearing 1. These assemblies are machined using laser or high-speed micro-drilling.

[0051] like Figure 1 and 4 As shown, each row of circumference is provided with 24 throttles 12, and each throttle 12 has 3 radial throttling micropores 123. Under different eccentricities, the bearing capacity of the air film with 48 micropores and 24×3 micropores is much better than that of the air film with 8 micropores, as shown in FIG. Figure 8 It is shown that micropore throttling can improve the bearing's support characteristics and enhance the bearing's comprehensive performance.

[0052] Specific implementation method seven: combination Figure 1 and Figure 4 To describe this embodiment, a sealing assembly is provided between the static air pressure radial bearing 1 and the static air pressure thrust bearing 2 in this embodiment.

[0053] The undisclosed technical features in this embodiment are the same as those in the fifth embodiment.

[0054] Specific implementation method eight: combination Figures 1 to 3To describe this embodiment, the sealing assembly described in this embodiment includes a radial sealing ring groove 119 and two thrust sealing ring grooves 22. The radial sealing ring groove 119 is opened on the front end face of the radial bearing body 11 and is arranged on the inner side of the radial air inlet groove 112. The thrust sealing ring groove 22 is opened on the rear end face of the air static pressure thrust bearing 2. One thrust sealing ring groove 22 is arranged between the anti-thrust air groove 21 and the disk surface water-cooling groove 118a, and the other thrust sealing ring groove 22 is arranged on the outer side of the disk surface water-cooling groove 118a. Sealing rings 3 are provided in the radial sealing ring groove 119 and the two thrust sealing ring grooves 22.

[0055] The undisclosed technical features in this embodiment are the same as those in the seventh embodiment.

[0056] The provision of the sealing ring 3 can effectively prevent gas and liquid leakage.

[0057] Specific implementation method nine: combination Figure 1 and Figure 4 To describe this embodiment, the throttle 12 described in this embodiment is cylindrical in shape, the outer end face of the throttle 12 is flush with the inner wall of the radial bearing body 11, a radial air cavity 121 is provided in the middle of the inner end face of the throttle 12, and a plurality of radial throttling microholes 123 are provided on the outer end face of the throttle 12 along the axial direction, and each radial throttling microhole 123 is connected to the radial air cavity 121 through a radial pre-drilled hole 122.

[0058] The undisclosed technical features in this embodiment are the same as those in the first embodiment.

[0059] The restrictor 12 is provided with three radial throttling micropores 123 . Each radial throttling micropore 123 has a diameter less than 0.1 mm and an aspect ratio less than or equal to 10. Each radial throttling micropore 123 has a corresponding radial pre-drilled hole 122 above it. The diameter of the radial pre-drilled hole 122 is much larger than that of the radial throttling micropore 123 .

[0060] The throttle 12 has a radial air cavity 121 at its upper end and three radial throttling microholes 123 with a diameter of 0.05 mm at its lower end. Above each radial throttling microhole 123 is a radial pre-drilled hole 122 with a diameter much larger than the radial throttling microhole 123. The diameter of the radial pre-drilled holes 122 is much larger than the radial throttling holes 123, preventing throttling during operation. The radial pre-drilled holes 122 also reduce the aspect ratio of the radial throttling microholes 123, effectively simplifying their machining.

[0061] Specific implementation method ten: Combination Figure 1 and Figure 4 To explain this embodiment, the outer diameter of the inner end surface of the restrictor 12 in this embodiment is smaller than the outer diameter of the outer end surface.

[0062] The undisclosed technical features in this embodiment are the same as those in the ninth embodiment.

[0063] The throttle 12 is a miniature stepped shaft.

[0064] For microporous radial air bearings, the throttle hole diameter is small, and it is difficult to process on the curved surface of the radial air bearing. Therefore, the processed throttle is installed in the radial air bearing for throttling, which greatly reduces the processing difficulty. Figure 1 As shown, the throttle 12 is interference-fitted into the throttle mounting hole. The throttle 12 is a miniature stepped shaft with a top diameter slightly smaller than the bottom diameter, so that it can be easily placed into the corresponding mounting hole during installation. The throttle 12 is installed from the inner wall of the aerostatic radial bearing 1 and embedded into the throttle mounting hole 116 until the lower surface of the throttle 12 is flush with the arc surface of the inner wall of the aerostatic radial bearing 1. After the throttle 12 is embedded, the inner wall of the aerostatic radial bearing 1 is finely ground so that the lower surface of the throttle 12 is coplanar with the inner wall of the aerostatic radial bearing 1. Finally, high-pressure gas is introduced to blow out the chips in the air path to prevent the aerostatic radial bearing 1 from being blocked during operation.

[0065] Working process

[0066] When the bearing is operating, filtered, external, high-pressure air enters through the air inlet 111 and then flows to both sides. On one side, it passes through the radial air inlet groove 112, then into the long air inlet channel 115. It then passes through the throttle 12, where it is throttled by the radial throttling micropores 123, before entering the bearing gap and forming a load-bearing air film. Finally, the air is discharged through the long through-hole 114 and the air outlet 113. On the other side, it flows into the thrust air groove 21 of the aerostatic thrust bearing 2, then passes through the thrust air cavity 241, the thrust pre-drilled hole 242, and the thrust throttling micropores 243, before entering the bearing gap and forming a load-bearing air film. This improves the bearing's load-bearing capacity and bearing characteristics.

[0067] The basic principles, main features, and advantages of the present invention are shown and described above. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The above embodiments and descriptions are merely illustrative of the principles of the present invention. Various changes and modifications may be made to the present invention without departing from the spirit and scope of the present invention. Such changes and modifications are intended to fall within the scope of the present invention. The scope of protection claimed in the present invention is defined by the appended claims and their equivalents.

Claims

1. An air static pressure radial and thrust integrated bearing based on micropore throttling, characterized by: The invention comprises an air static pressure radial bearing (1) and an air static pressure thrust bearing (2), wherein the air static pressure thrust bearing (2) is coaxially fixed to the front end of the air static pressure radial bearing (1), and the air static pressure radial bearing (1) comprises a radial bearing body (11) and a plurality of throttles (12), an air flow channel is provided inside the radial bearing body (11), a plurality of throttles (12) are evenly embedded on the inner side wall of the radial bearing body (11) along the circumferential direction, a plurality of throttle components (24) are evenly distributed on the inner side surface of the front end of the air static pressure thrust bearing (2), and the air inlet ends of the throttles (12) and the throttle components (24) are respectively connected to the air flow channel.

2. The micropore throttling-based aerostatic radial and thrust integrated bearing according to claim 1, characterized in that: The air flow channel includes an air inlet hole (111), a radial air inlet groove (112), an air outlet hole (113), a long through hole (114) and a long air inlet channel (115). The air inlet hole (111) and the air outlet hole (113) are respectively arranged in the disk surface of the radial bearing body (11) along the radial direction. The radial air inlet groove (112) is opened on the front end surface of the disk surface of the radial bearing body (11) along the circumferential direction. The radial air inlet groove (112) is connected to the outside of the radial bearing body (11) through the air inlet hole (111). The groove bottom of the radial air inlet groove (112) is uniformly provided with a plurality of long air inlet channels (115) along the circumferential direction. Each long air inlet channel (115) is arranged along the circumferential direction. The long air inlet channel (115) is arranged in the axial direction, and a plurality of throttle mounting holes (116) are provided on the inner side of the long air inlet channel (115) along the length direction. Each throttle mounting hole (116) is arranged in the radial direction. The long air inlet channel (115) is connected to the inner side of the radial bearing body (11) through the throttle mounting hole (116). A throttle (12) is respectively installed in each throttle mounting hole (116). The inner and outer sides of the radial bearing body (11) are connected through the air outlet hole (113). The long through hole (114) is arranged on the rear end surface of the radial bearing body (11) along the axial direction. The air inlet end of the long through hole (114) is connected to the air outlet hole (113).

3. The micropore throttling-based aerostatic radial and thrust integrated bearing according to claim 2, characterized in that: The radial bearing body (11) is provided with a water cooling groove (118).

4. The micropore throttling-based aerostatic radial and thrust integrated bearing according to claim 3, characterized in that: The water cooling groove (118) includes a disk surface water cooling groove (118a) and a serpentine water cooling groove (118b). The disk surface water cooling groove (118a) is opened on the front end surface of the radial bearing body (11) along the circumferential direction and is arranged on the outside of the radial air inlet groove (112). The serpentine water cooling groove (118b) is opened on the outer side wall of the radial bearing body (11) along the circumferential direction.

5. The micropore throttling-based aerostatic radial and thrust integrated bearing according to claim 4, characterized in that: A thrust-stop air groove (21) is provided on the rear end surface of the air static thrust bearing (2) along the circumferential direction. The thrust-stop air groove (21) is arranged corresponding to the radial air inlet groove (112). The throttle assembly (24) is connected to the air flow channel through the thrust-stop air groove (21).

6. The micropore throttling-based aerostatic radial and thrust integrated bearing according to claim 5, characterized in that: The throttling assembly (24) includes a plurality of thrust air chambers (241) and a plurality of thrust throttling micropores (243). The plurality of thrust throttling micropores (243) are arranged in parallel along the radial direction on the front end surface of the air static pressure thrust bearing (2). The plurality of thrust air chambers (241) are arranged in parallel along the radial direction at the bottom of the thrust air groove (21). Each thrust throttling micropore (243) is connected to a thrust throttling thrust air chamber (241) through a thrust pre-drilled hole (242).

7. The micropore throttling-based aerostatic radial and thrust integrated bearing according to claim 5, characterized in that: A sealing assembly is provided between the air static pressure radial bearing (1) and the air static pressure thrust bearing (2).

8. The micropore throttling-based aerostatic radial and thrust integrated bearing according to claim 7, characterized in that: The sealing assembly includes a radial sealing ring groove (119) and two thrust sealing ring grooves (22). The radial sealing ring groove (119) is provided on the front end surface of the radial bearing body (11) and is arranged on the inner side of the radial air inlet groove (112). The thrust sealing ring groove (22) is provided on the rear end surface of the air static pressure thrust bearing (2). One thrust sealing ring groove (22) is provided between the thrust air inlet groove (21) and the disk surface water cooling groove (118a), and the other thrust sealing ring groove (22) is provided on the outer side of the disk surface water cooling groove (118a). Sealing rings (3) are provided in the radial sealing ring groove (119) and the two thrust sealing ring grooves (22).

9. The micropore throttling-based aerostatic radial and thrust integrated bearing according to claim 1, characterized in that: The throttle (12) is cylindrical in shape, and the outer end surface of the throttle (12) is flush with the inner wall of the radial bearing body (11). A radial air cavity (121) is provided in the middle of the inner end surface of the throttle (12). A plurality of radial throttling micropores (123) are provided on the outer end surface of the throttle (12) along the axial direction, and each radial throttling micropore (123) is connected to the radial air cavity (121) through a radial pre-drilled hole (122).

10. The micropore throttling-based aerostatic radial and thrust integrated bearing according to claim 9, characterized in that: The outer diameter of the inner end surface of the throttle (12) is smaller than the outer diameter of the outer end surface.

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