Compressor and refrigerant circulation system

Abstract

The compressor of the present application includes: a housing, a stator, a rotor, a radial static pressure bearing, a bearing seat and a diffuser, wherein the housing is provided with an air outlet, the radial static pressure bearing is axially movably mounted on the rotor, and a first gap is provided between the radial static pressure bearing and the outer surface of the rotor, and the compressor further includes at least one of the following: a first exhaust chamber and a first groove, wherein the first exhaust chamber is located between the first end face of the radial static pressure bearing and the first surface of the bearing seat, which are opposite to each other, and the first groove is located on the first end face and / or the first surface, and connects the first exhaust chamber and the air outlet; a second exhaust chamber and a second groove, wherein the second exhaust chamber is located between the second end face of the radial static pressure bearing and the second surface of the diffuser, and the second groove is located on the second end face and / or the second surface, and connects the second exhaust chamber and the air outlet. Based on this, the exhaust smoothness can be improved and the operating reliability of the compressor can be improved.

Description

Technical Field

[0001] The present application relates to the technical field of compressors, and in particular to a compressor and a refrigerant circulation system. Background Art

[0002] Hydrostatic gas bearings are widely used in compressors due to their low operating resistance, high mechanical precision, strong load-bearing capacity, and zero dry friction during start-up and shutdown. For example, some compressors use radial hydrostatic bearings to support the rotor. Furthermore, to reduce the risk of shaft seizure, these bearings are also designed to be axially movable.

[0003] However, in practice, it is found that when the radial static pressure bearing is axially movable, the gas used to form the air film in the radial static pressure bearing has a problem of poor discharge, which affects the load-bearing capacity of the radial static pressure bearing and reduces the operating reliability of the compressor. Summary of the Invention

[0004] A technical problem to be solved by the present application is to improve the exhaust smoothness of the axially movable radial static pressure bearing and enhance the operational reliability of the compressor.

[0005] In order to solve the above technical problems, the present application provides a compressor, comprising:

[0006] case;

[0007] A stator is fixedly disposed in the housing;

[0008] The rotor is rotatably disposed in the stator;

[0009] A bearing assembly comprising a radial static pressure bearing, a bearing seat, and a diffuser. The radial static pressure bearing is axially movably sleeved on the rotor and has a first gap between it and the outer surface of the rotor for allowing gas to pass through to form a gas film. The bearing seat is sleeved outside the radial static pressure bearing. The diffuser is sleeved on the rotor and is located on a side of the radial static pressure bearing away from the stator.

[0010] An exhaust gas path is used to discharge the gas in the first gap to the outside of the shell, and includes an exhaust hole, the exhaust hole is provided on the shell and communicates with the outside of the shell, and the exhaust gas path further includes at least one of the following:

[0011] a first exhaust cavity and a first groove, wherein the first exhaust cavity is located between a first end surface of the radial static pressure bearing facing the stator and a first surface of the bearing seat opposite to the first end surface, and the first groove is located on the first end surface and / or the first surface and communicates with the first exhaust cavity and the air outlet;

[0012] A second exhaust cavity and a second groove, the second exhaust cavity is located between the second end surface of the radial static pressure bearing facing the diffuser and the second surface of the diffuser opposite to the second end surface, the second groove is located on the second end surface and / or the second surface, and connects the second exhaust cavity and the outlet hole.

[0013] In some embodiments, the exhaust gas path includes at least two first grooves, which are arranged at intervals along the circumference of the rotor; and / or the exhaust gas path includes at least two second grooves, which are arranged at intervals along the circumference of the rotor.

[0014] In some embodiments, the exhaust gas path includes a first exhaust chamber, a first groove, a second exhaust chamber and a second groove, and the exhaust gas path also includes a connecting hole, the connecting hole connects the first groove and the second exhaust chamber or the second groove, and the second groove connects the second exhaust chamber and the air outlet.

[0015] In some embodiments, the radial static pressure bearing includes a sleeve and a carrier, the sleeve is sleeved outside the carrier, the first gap is located between the carrier and the rotor, and the communicating hole is located on the sleeve.

[0016] In some embodiments, the air outlet is located on a side of the bearing seat away from the diffuser, and the exhaust gas path also includes an air bleed hole, which is arranged on the bearing seat and / or the shell, and connects the first exhaust cavity and / or the second exhaust cavity with the air outlet.

[0017] In some embodiments, the compressor includes a first air supply path, which is connected to the first gap and supplies air to the first gap to form an air film.

[0018] In some embodiments, the first air supply path includes an air inlet hole, a first air supply channel and a first air inlet channel. The air inlet hole is arranged on the shell and is connected to the outside of the shell. The first air supply channel is arranged on the bearing seat and is connected to the air inlet hole. The first air inlet channel is arranged on the radial static pressure bearing and is connected to the first air supply channel and the first gap.

[0019] In some embodiments, the radial static pressure bearing includes a sleeve and a carrier, the sleeve is arranged outside the carrier, the first gap is located between the carrier and the outer surface of the rotor, the first air inlet channel includes a first channel section and a second channel section, the first channel section is arranged on the sleeve and is connected to the first air supply channel, and the second channel section is arranged on the carrier and is connected to the first channel section and the first gap.

[0020] In some embodiments, the first channel section includes a first annular groove and an air vent, the first annular groove is arranged on the outer surface of the sleeve and is connected to the first air supply channel, and the air vent is arranged at the bottom of the first annular groove and is connected to the first annular groove and the second channel section; and / or, the second channel section includes a second annular groove and a first throttling hole, the second annular groove is arranged on the outer surface of the carrier and is connected to the first channel section, and the first throttling hole is arranged at the bottom of the second annular groove and is connected to the second annular groove and the first gap.

[0021] In some embodiments, the first channel segment includes at least two ventilation holes, which are arranged at intervals along the circumference of the first annular groove; and / or, the second channel segment includes at least two first throttling holes, which are arranged at intervals along the axial direction and / or circumferential direction of the second annular groove.

[0022] In some embodiments, the compressor includes two bearing assemblies, which are disposed at both axial ends of the rotor.

[0023] In some embodiments, the air supply path includes two first air supply paths, and the two first air supply paths respectively supply air to the first gaps of the radial static pressure bearings of the two bearing assemblies.

[0024] In some embodiments, a thrust plate is provided on the rotor, and the thrust plate is located on a side of the radial static pressure bearing away from the diffuser. In addition, the compressor further comprises at least one of the following:

[0025] a first static pressure thrust bearing sleeved on the rotor and disposed on a side of the thrust plate adjacent to the radial static pressure bearing; a second gap being defined between the first static pressure thrust bearing and adjacent axial end surfaces of the thrust plate; and a second air supply path communicating with the second gap to supply air to the second gap to form an air film; and the second gap communicating with a first exhaust chamber of the exhaust path;

[0026] The second hydrostatic thrust bearing is sleeved on the rotor and arranged on the side of the thrust plate away from the radial hydrostatic bearing. A third gap is provided between the second hydrostatic thrust bearing and the adjacent axial end faces of the thrust plate. The compressor includes a third air supply path, which is connected to the third gap to supply air to the third gap to form an air film. The third gap is connected to the air outlet.

[0027] In some embodiments, the second air supply path includes a second air supply channel, which is arranged on the bearing seat and connects the first air supply channel and the second gap of the first air supply path of the compressor; and / or, the third air supply path includes a third air supply channel, which is arranged on the bearing seat and connects the first air supply channel and the third gap of the first air supply path of the compressor.

[0028] In some embodiments, the second air supply path also includes a first air supply chamber and a second throttle hole, the first air supply chamber is located between the adjacent axial end faces of the first hydrostatic thrust bearing and the bearing seat, and is connected to the second air supply channel, the second throttle hole is arranged on the first hydrostatic thrust bearing, and is connected to the first air supply chamber and the second gap; and / or, the third air supply path includes a second air supply chamber and a third throttle hole, the second air supply chamber is located between the adjacent axial end faces of the second hydrostatic thrust bearing and the cover, and is connected to the third air supply channel, the third throttle hole is arranged on the second hydrostatic thrust bearing, and is connected to the second air supply chamber and the third gap, the cover is sleeved on the rotor, and is located on the side of the second hydrostatic thrust bearing away from the radial hydrostatic bearing.

[0029] In addition, the present application also provides a refrigerant circulation system, which includes the compressor of any embodiment of the present application.

[0030] In some embodiments, the refrigerant circulation system is an air conditioning system.

[0031] By providing at least one of the first exhaust chamber and the first groove and the second exhaust chamber and the second groove, the exhaust smoothness can be effectively improved, the bearing load capacity and load stability can be enhanced, and the operating reliability of the compressor can be improved.

[0032] Other features and advantages of the present application will become apparent from the following detailed description of exemplary embodiments of the present application with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0034] Figure 1 This is a schematic diagram of the structure of the compressor in an embodiment of the present application.

[0035] Figure 2 for Figure 1 A partial enlarged schematic diagram of the left radial hydrostatic bearing, the first hydrostatic thrust bearing, and the second hydrostatic thrust bearing.

[0036] Figure 3 It is a three-dimensional schematic diagram of the left radial hydrostatic bearing in an embodiment of the present application.

[0037] Figure 4 It is a cutaway perspective view of the left radial hydrostatic bearing in the embodiment of the present application.

[0038] Figure 5This is a schematic structural diagram of the sleeve of the left radial hydrostatic bearing in an embodiment of the present application.

[0039] Figure 6 This is a schematic structural diagram of the carrier of the left radial hydrostatic bearing in an embodiment of the present application.

[0040] Figure 7 This is a three-dimensional schematic diagram of the left bearing seat in the embodiment of the present application.

[0041] Figure 8 This is a right side view of the left diffuser in the implementation of this application.

[0042] Description of reference numerals:

[0043] 10. Compressor;

[0044] 1. Shell;

[0045] 2. Stator;

[0046] 3. Rotor; 31. Thrust plate;

[0047] 4. Bearing assembly; 41. Radial static pressure bearing; 411. Sleeve; 412. Carrier; 413. Cylinder; 414. Limiting flange; 415. Main body; 416. Stop ring; 417. First end face; 418. Second end face; 419. First gap; 42. Bearing seat; 421. Seat body; 422. First boss; 423. Second boss; 424. First mounting groove; 425. Second mounting groove; 426. First surface; 43. Diffuser; 431. Second surface;

[0048] 5. First hydrostatic thrust bearing; 51. Second gap; 52. First gap;

[0049] 6. Second hydrostatic thrust bearing; 61. Third gap; 62. Second gap;

[0050] 7. Air supply path; 71. First air supply path; 711. Air inlet; 712. First air supply channel; 713. First air inlet channel; 714. First channel section; 715. Second channel section; 716. First annular groove; 717. Air vent; 718. Second annular groove; 719. First throttle hole; 72. Second air supply path; 721. Second air supply channel; 722. First air supply cavity; 723. Third annular groove; 724. Second throttle hole; 73. Third air supply path; 731. Third air supply channel; 732. Second air supply cavity; 733. Fourth annular groove; 734. Third throttle hole;

[0051] 8. Exhaust gas path; 81. First exhaust cavity; 82. Second exhaust cavity; 83. Communication hole; 84. Air outlet; 85. First groove; 86. Second groove; 87. Air inlet hole;

[0052] 91. Seal; 92. Impeller; 93. Volute; 94. Locking piece; 95. Bearing cavity; 96. Motor cavity; 97. Cover. DETAILED DESCRIPTION

[0053] 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 only part of the embodiments of the present application, not all of the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is in no way intended to limit the present application and its application or use. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without carrying out creative work are within the scope of protection of this application.

[0054] Technologies, methods, and equipment known to ordinary technicians in the relevant art may not be discussed in detail, but where appropriate, the technologies, methods, and equipment should be considered part of the specification.

[0055] In the description of this application, it should be understood that the use of words such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. Unless otherwise stated, the above words have no special meaning and therefore cannot be understood as limiting the scope of protection of this application.

[0056] In addition, the technical features involved in the different embodiments of the present application described below can be combined with each other as long as they do not conflict with each other.

[0057] The compressor is a crucial component of refrigerant circulation systems, such as those used in air conditioners. It connects to the condenser, evaporator, and throttling element to form the refrigerant circulation circuit. During operation, the compressor draws in relatively low-pressure working fluid vapor from the evaporator, raises its pressure, and then feeds it into the condenser, where it condenses into a higher-pressure liquid. After being throttled by the throttling element, the lower-pressure liquid is then fed into the evaporator, where it absorbs heat and evaporates into a lower-pressure vapor. This vapor is then fed into the compressor's inlet, completing the refrigeration cycle.

[0058] See also Figure 1 The compressor 10 generally includes a housing 1, a stator 2, a rotor 3, and the like.

[0059] A chamber is provided inside the housing 1 to provide installation space for other structural components such as the stator 2 and the rotor 3 .

[0060] Both the stator 2 and the rotor 3 are mounted within the housing 1. The stator 2 is fixedly mounted within the housing 1. For example, the stator 2 can be shrink-fitted onto the inner surface of the housing 1. The rotor 3 is rotatably mounted within the housing 1 and passes through the stator 2. In other words, the rotor 3 rotatably penetrates the stator 2.

[0061] The rotor 3 rotates at high speed during operation and, by cooperating with the stator 2 , realizes the conversion of electrical energy into mechanical energy.

[0062] In order to reliably support the rotor 3 , some rotors 3 are provided with gas bearings.

[0063] Gas bearings utilize a gas film to support loads. Compared to other types of bearings, they offer numerous advantages, including oil-free operation, pollution-free operation, low operating resistance, simple structure, high mechanical precision, low heat generation, and long life. They can overcome the shortcomings of traditional liquid bearings, sliding bearings, and rolling bearings, and are therefore widely used in high-speed rotating machinery and precision machining equipment.

[0064] Among them, according to the different working principles of the bearings, gas bearings can be divided into multiple types such as static pressure gas bearings, dynamic pressure gas bearings and dynamic and static pressure hybrid bearings. Among them, dynamic pressure gas bearings use high-speed moving rotors to drive fluid movement to form a dynamic pressure gas film. The air film has a relatively small carrying capacity. At the same time, due to insufficient carrying capacity in the low-speed stages of starting and stopping, dry friction is prone to occur. Static pressure gas bearings use external high-pressure gas to pass through a throttle to form a static pressure gas film. Dry friction will not occur during the start and stop stages, and the static pressure gas film has a strong carrying capacity. Compared with dynamic pressure gas bearings, static pressure gas bearings have significant characteristics and are currently widely used in compressors such as centrifugal compressors.

[0065] In addition, based on the direction in which the bearing bears the load, hydrostatic gas bearings can be further divided into radial hydrostatic bearings and axial hydrostatic bearings. Radial hydrostatic bearings primarily bear radial loads, while axial hydrostatic bearings primarily bear axial loads and are also called hydrostatic thrust bearings.

[0066] In traditional solutions, the radial static pressure bearing in the compressor is usually an integrated structure, and the gap between it and the outer surface of the rotor 3 is usually small, and it cannot move axially on the rotor 3. In this case, assembly is difficult, and the shaft is prone to jamming during assembly and operation.

[0067] In view of the above situation, in order to reduce the difficulty of assembly and the risk of shaft sticking, some related technologies set the radial static pressure bearing to be movable in the axial direction on the rotor 3.

[0068] However, practice has found that setting the radial hydrostatic bearing to be axially movable can indeed reduce the difficulty of assembly and the risk of shaft jamming, but it also brings the problem of poor exhaust.

[0069] As mentioned earlier, radial static pressure bearings require external air supply to form an air film. After the corresponding gas forms an air film, it needs to be discharged. If the exhaust is not smooth, it will affect the pressure difference distribution, affect the bearing load, and reduce the reliability of the compressor operation. In the case of radial static pressure bearings that can move axially, when the radial static pressure bearings move axially to the two extreme positions, they will abut against the bearing seats and diffusers on both sides of the radial static pressure bearings, blocking the exhaust gas path and causing poor exhaust. In this case, after the gas forms an air film, it cannot be discharged in time, which will cause the pressure to rise, affect the bearing load, and reduce the operational reliability.

[0070] It can be seen that the above-mentioned solution of axially movable radial static pressure bearing will affect the operating reliability of the compressor by affecting the smoothness of exhaust.

[0071] Based on the above findings, the present application provides a compressor to solve the problems of poor exhaust and low operating reliability when the radial static pressure bearing can move axially.

[0072] Figures 1-8 The structure of the compressor in this application is shown as an example.

[0073] See also Figures 1-8 In the present application, the compressor 10 includes a shell 1, a stator 2, a rotor 3, a bearing assembly 4 and an exhaust gas path 8. Among them, the stator 2 is fixedly arranged in the shell 1. The rotor 3 is rotatably arranged in the stator 2. The bearing assembly 4 includes a radial static pressure bearing 41, a bearing seat 42 and a diffuser 43. The radial static pressure bearing 41 is axially movably mounted on the rotor 3, and a first gap 419 is provided between the radial static pressure bearing 41 and the outer surface of the rotor 3 to allow gas to pass through and form an air film. The bearing seat 42 is mounted outside the radial static pressure bearing 41. The diffuser 43 is mounted on the rotor 3 and is located on the side of the radial static pressure bearing 41 away from the stator 2. The exhaust gas path 8 is used to discharge the gas in the first gap 419 to the outside of the shell 1, and includes an air outlet 84. The air outlet 84 is provided on the shell 1 and is connected to the outside of the shell 1, and the exhaust gas path 8 also includes at least one of the following:

[0074] A first exhaust cavity 81 and a first groove 85. The first exhaust cavity 81 is located between a first end surface 417 of the radial static pressure bearing 41 facing the stator 2 and a first surface 426 of the bearing seat 42 opposite to the first end surface 417. The first groove 85 is located on the first end surface 417 and / or the first surface 426 and connects the first exhaust cavity 81 with the exhaust hole 84.

[0075] The second exhaust chamber 82 and the second groove 86, the second exhaust chamber 82 is located between the second end face 418 of the radial static pressure bearing 41 facing the diffuser 43 and the second surface 431 of the diffuser 43 opposite to the second end face 418, the second groove 86 is located on the second end face 418 and / or the second surface 431, and connects the second exhaust chamber 82 and the outlet hole 84.

[0076] Based on the provision of the first groove 85 and / or the second groove 86 , the exhaust smoothness can be effectively improved, thereby enhancing the bearing capacity and bearing stability, and improving the operational reliability of the compressor 10 .

[0077] Among them, based on the set first groove 85, when the radial static pressure bearing 41 moves axially to its first end face 417 and abuts against the first surface 426 of the bearing seat 42, the gas in the first exhaust chamber 81 will not be blocked, but can still flow outward through the recessed first groove 85, thereby effectively preventing the radial static pressure bearing 41 from abutting against the bearing seat 42 and causing poor exhaust, so that even if the radial static pressure bearing 41 moves to the extreme position toward the side of the stator 2, the gas in the first gap 419 can still be discharged smoothly and in time, which is conducive to improving the exhaust smoothness, enhancing the bearing load capacity and load stability, and improving the operating reliability of the compressor 10.

[0078] In addition, based on the second groove 86 provided, when the radial static pressure bearing 41 moves axially to its second end face 418 and abuts against the second surface 431 of the diffuser 43, the gas in the second exhaust chamber 82 will not be blocked, but can still flow outward through the recessed second groove 86, thereby effectively preventing the radial static pressure bearing 41 from abutting against the diffuser 43 and causing poor exhaust, so that even if the radial static pressure bearing 41 moves to the extreme position toward the side of the diffuser 43, the gas in the first gap 419 can still be discharged smoothly and in time, which is conducive to improving the exhaust smoothness, enhancing the bearing load capacity and load stability, and improving the operating reliability of the compressor 10.

[0079] It can be seen that by providing at least one of the first exhaust chamber 81 and the first groove 85 and the second exhaust chamber 82 and the second groove 86, the exhaust smoothness can be effectively improved, the bearing load capacity and load stability can be improved, and the operating reliability of the compressor 10 can be improved.

[0080] Specifically, only the first exhaust chamber 81 and the first groove 85 may be provided, or only the second exhaust chamber 82 and the second groove 86 may be provided. Alternatively, the first exhaust chamber 81, the first groove 85, and both the second exhaust chamber 82 and the second groove 86 may be provided. When only the first exhaust chamber 81 and the first groove 85 or the second exhaust chamber 82 and the second groove 86 are provided, the gas in the first gap 419 is discharged only from one of the two axial sides of the radial static pressure bearing 41. When both the first exhaust chamber 81 and the first groove 85 and the second exhaust chamber 82 and the second groove 86 are provided, the gas in the first gap 419 can be discharged from both axial sides of the radial static pressure bearing 41, resulting in higher exhaust efficiency and smoother exhaust, which is more conducive to improving the operational reliability of the compressor 10.

[0081] When the exhaust gas path 8 includes the first exhaust chamber 81, the first groove 85, the second exhaust chamber 82 and the second groove 86 at the same time, the first exhaust chamber 81 and the first groove 85 and the second exhaust chamber 82 and the second groove 86 located on both sides of the axial direction of the radial static pressure bearing 41 can be two independent exhaust gas paths, both of which are connected to the air outlet 84 respectively, or the two exhaust gas paths can also be connected to each other, and one of them is connected to the air outlet 84 through the other.

[0082] For example, see Figure 1 and Figure 2 In some embodiments, the exhaust gas circuit 8 includes a first exhaust chamber 81, a first groove 85, a second exhaust chamber 82, and a second groove 86, and the exhaust gas circuit 8 also includes a connecting hole 83, the connecting hole 83 connects the first groove 85 and the second exhaust chamber 82 or the second groove 86, and the second groove 86 connects the second exhaust chamber 82 and the air outlet hole 84.

[0083] In the above scheme, the first exhaust gas path (the first exhaust chamber 81 and the first groove 85) and the second exhaust gas path (the second exhaust chamber 82 and the second groove 86) located on both sides of the radial static pressure bearing 41 are not independent of each other, but are connected to each other. Specifically, the first exhaust gas path is connected to the second exhaust gas path, and is connected to the outlet hole 84 through the second exhaust gas path. At this time, the first groove 85 is connected to the outlet hole 84 through the connecting hole 83 and the second exhaust gas path. In this way, see Figure 2 As shown by the arrows in the figure, the gas entering the first gap 419 to form an air film will flow in two paths, one of which flows toward the side of the stator 2, flows to the first exhaust gas path, and enters the first exhaust chamber 81, and the other flows toward the side of the diffuser 43, flows to the second exhaust gas path, and enters the second exhaust chamber 82. Moreover, the gas entering the first exhaust chamber 81 will merge with the gas entering the second exhaust chamber 82 through the first groove 85 and the connecting hole 83, and flow out together through the second groove 86, flow to the outlet hole 84, and be discharged to the outside of the shell 1.

[0084] During the exhaust process, since the first and second exhaust paths include the first and second grooves 85 and 86, respectively, neither the first nor the second exhaust path is blocked by the movement of the radial static pressure bearing. Therefore, smooth exhaust can be achieved during the axial movement of the radial static pressure bearing 41. Furthermore, since the first and second exhaust paths are connected via the connecting hole 83, they do not need to be connected to the outlet hole 84 separately. This effectively simplifies the structure of the entire exhaust path 8.

[0085] It can be seen that the above solution can improve the exhaust smoothness and enhance the operating reliability of the compressor 10 based on a relatively simple structure.

[0086] The connecting hole 83 can be provided on the radial static pressure bearing 41. As an example, see Figure 1 and Figure 2 In some embodiments, the radial static pressure bearing 41 includes a sleeve 411 and a carrier 412. The sleeve 411 is sleeved over the carrier 412, with the first gap 419 located between the carrier 412 and the rotor 3. The connecting hole 83 is located on the sleeve 411. In this case, the radial static pressure bearing 41 is no longer a single-piece structure, but a split-piece structure, which facilitates axial movement and reduces the risk of shaft sticking. Providing the connecting hole 83 on the sleeve 411, located on the exterior of the split-piece radial static pressure bearing 41, facilitates communication between the first groove 85 and the second exhaust gas path.

[0087] In the aforementioned embodiments, the air outlet 84 may be located on the side of the bearing seat 42 close to the diffuser 43, or may be located on the side of the bearing seat 42 away from the diffuser 43. Figure 1 and Figure 2 When the air outlet 84 is located on the side of the bearing housing 42 away from the diffuser 43, the exhaust gas path 8 may further include an air inlet 87. The air inlet 87 is provided on the bearing housing 42 and / or the housing 1 and connects the first exhaust chamber 81 and / or the second exhaust chamber 82 with the air outlet 84. In this case, the gas flowing out of the bearing assembly 4 can flow smoothly through the air inlet 87 to the air outlet 84 located on the side of the bearing housing 42 away from the diffuser 43, thereby achieving exhaust.

[0088] In the aforementioned embodiments, the number of the first groove 85 and / or the second groove 86 is not limited to one, but may be two or more.

[0089] For example, see Figure 7 In some embodiments, the exhaust gas path 8 includes at least two first grooves 85, which are spaced apart along the circumference of the rotor 3. This facilitates faster and more reliable exhaust, thereby more effectively improving the operating reliability of the compressor 10.

[0090] For example, see Figure 8 In some embodiments, the exhaust gas path 8 includes at least two second grooves 86, which are spaced apart along the circumference of the rotor 3. This facilitates faster and more reliable exhaust, thereby more effectively improving the operating reliability of the compressor 10.

[0091] In order to realize the air supply to the radial static pressure bearing 41 in the above embodiments, see Figure 1 and Figure 2 The compressor 10 includes a first air supply path 71 , which is connected to the first gap 419 and supplies air to the first gap 419 to form an air film.

[0092] Specifically, see Figure 2 In some embodiments, the first air supply path 71 includes an air inlet 711, a first air supply channel 712, and a first air inlet channel 713. The air inlet 711 is provided on the housing 1 and communicates with the exterior of the housing 1. The first air supply channel 712 is provided on the bearing seat 42 and communicates with the air inlet 711. The first air inlet channel 713 is provided on the radial static pressure bearing 41 and communicates with the first air supply channel 712 and the first gap 419. In this way, gas can sequentially pass through the air inlet 711 on the housing 1, the first air supply channel 712 on the bearing seat 42, and the first air supply channel 712 on the radial static pressure bearing 41, and enter the first gap 419 between the radial static pressure bearing 41 and the rotor 3, forming an air film that supports the rotor 3 and enables the radial static pressure bearing 41 to support the rotor 3. In this case, since it is only necessary to set up channels on the housing 1, the bearing seat 42 and the radial hydrostatic bearing 41, the air supply to the radial hydrostatic bearing 41 can be achieved without setting up a complex air path. Therefore, it is beneficial to simplify the structure of the air supply path and to prevent the risk of gas leakage from increasing due to the complexity of the air supply path.

[0093] When the radial static pressure bearing 41 is the aforementioned split bearing comprising a sleeve 411 and a carrier 412, see Figure 2 In some embodiments, the first air inlet channel 713 includes a first channel section 714 and a second channel section 715. The first channel section 714 is disposed on the sleeve 411 and communicates with the first air supply channel 712. The second channel section 715 is disposed on the carrier 412 and communicates with the first channel section 714 and the first gap 419. In this case, the first air inlet channel 713 penetrates the sleeve 411 and the carrier 412 and includes the first channel section 714 on the sleeve 411 and the second channel section 715 on the carrier 412. The first air supply channel 712 sequentially passes through the first channel section 714 on the sleeve 411 and the second channel section 715 on the carrier 412 to communicate with the first gap 419, resulting in a relatively simple air path.

[0094] Specifically, see Figure 2 As an example, the first channel section 714 includes a first annular groove 716 and a vent hole 717. The first annular groove 716 is provided on the outer surface of the sleeve 411 and communicates with the first gas supply channel 712. The vent hole 717 is provided at the bottom of the first annular groove 716 and connects the first annular groove 716 with the second channel section 715. In this case, the first channel section 714 includes the first annular groove 716 and the vent hole 717, which are connected to each other. The first channel section 714 communicates with the first gas supply channel 712 and the second channel section 715 through the first annular groove 716 and the vent hole 717, respectively. This allows the gas flowing out of the first gas supply channel 712 to flow through the first annular groove 716 and the vent hole 717 in sequence, then into the second channel section 715 and ultimately reach the first gap 419. Due to the provision of the first annular groove 716 , the first annular groove 716 can guide the gas flowing out of the first gas supply channel 712 to flow along the circumferential direction of the sleeve 411 to achieve circumferential uniform distribution of the gas. Therefore, it is beneficial to improve the uniformity of gas supply and form a more uniform gas film in the first gap 419 .

[0095] The number of the vent holes 717 can be one, two or more. Figure 5 In some embodiments, the first channel section 714 includes at least two vent holes 717, which are spaced apart along the circumference of the first annular groove 716. This helps to further improve the uniformity of gas supply.

[0096] In addition, back to Figure 2 As an example, the second channel section 715 includes a second annular groove 718 and a first throttle hole 719. The second annular groove 718 is provided on the outer surface of the carrier 412 and communicates with the first channel section 714. The first throttle hole 719 is provided at the bottom of the second annular groove 718 and communicates with the second annular groove 718 and the first gap 419. In this case, the second channel section 715 includes the second annular groove 718 and the first throttle hole 719, which are connected to each other. The second channel section 715 is connected to the first channel section 714 and the first gap 419 through the second annular groove 718 and the first throttle hole 719, respectively. This allows the gas flowing out of the first channel section 714 to flow through the second annular groove 718 and the first throttle hole 719 in sequence before flowing into the first gap 419. The second annular groove 718 guides the gas flowing out of the first channel section 714 along the circumference of the carrier 412, achieving uniform circumferential distribution of the gas. This improves gas supply uniformity and forms a more uniform gas film within the first gap 419. Furthermore, the first throttle hole 719 acts as a throttling mechanism, facilitating the flow of gas through the first throttle hole 719 into the first gap 419, where it forms a gas film to support the rotor 3.

[0097] The number of the first throttle holes 719 can be one, two or more. Figure 6 In some embodiments, the second channel section 715 includes at least two first throttle holes 719, which are spaced apart along the axial and / or circumferential directions of the second annular groove 718. This helps further improve the uniformity of gas supply and facilitates faster establishment of a pressure difference and formation of an air film.

[0098] In the above embodiments, the number of the bearing assembly 4 can be one, or more than one. Figure 1 In some embodiments, the compressor 10 includes two bearing assemblies 4, which are disposed at both axial ends of the rotor 3. In this case, the two axial ends of the rotor 3 can be effectively supported by the two radial static pressure bearings 41. Moreover, both radial static pressure bearings 41 can be exhausted smoothly, thereby improving the operating reliability of the compressor 10.

[0099] When the compressor 10 includes two bearing assemblies 4, the two bearing assemblies 4 can be supplied with air by the same air supply path, or can be supplied with air by different air supply paths. Figure 1 In some embodiments, the compressor 10 includes two first air supply paths 71 , each of which supplies air to the first gaps 419 of the radial static pressure bearings 41 of the two bearing assemblies 4 . In this case, the two bearing assemblies 4 are supplied with air by different first air supply paths 71 , which improves air supply reliability.

[0100] As a further improvement to the above embodiments, in some embodiments, the compressor 10 includes not only the radial static pressure bearing 41 but also a static pressure thrust bearing. Figure 1 and Figure 2 A thrust plate 31 is provided on the rotor 3 , and the thrust plate 31 is located on a side of the radial static pressure bearing 41 away from the diffuser 43 , and the compressor 10 further includes at least one of a first static pressure thrust bearing 5 and a second static pressure thrust bearing 6 .

[0101] Among them, see Figure 1 and Figure 2 The first static pressure thrust bearing 5 is sleeved on the rotor 3 and disposed on the side of the thrust plate 31 proximal to the radial static pressure bearing 41. A second gap 51 is defined between the adjacent axial end surfaces of the first static pressure thrust bearing 5 and the thrust plate 31. The compressor 10 includes a second air supply path 72, which communicates with the second gap 51 to supply air to the second gap 51 and form an air film. The second gap 51 communicates with the first exhaust chamber 81.

[0102] In the above solution, the first static thrust bearing 5 can work together with the radial static bearing 41 to support the rotor 3, ensuring smoother operation. Furthermore, because the second gap 51 between the first static thrust bearing 5 and the thrust plate 31, used for inflation to form an air film, is connected to the first exhaust chamber 81, the gas within the second gap 51 can flow into the first exhaust chamber 81 and, together with the gas flowing from the first gap 419 into the first exhaust chamber 81, flow outward through the first groove 85 for exhaust. Because the first static thrust bearing 5 and the radial static bearing 41 can share part of the exhaust gas path, this helps simplify the structure of the exhaust gas path 8. Furthermore, because the first groove 85 can improve exhaust smoothness, exhausting the first static thrust bearing 5 through the first groove 85 also improves exhaust smoothness of the first static thrust bearing 5. In particular, the exhaust gas of the first hydrostatic thrust bearing 5 and the radial hydrostatic bearing 41 flows into the first exhaust chamber 81 together, and the amount of gas is large. In this case, the role of the first groove 85 is more prominent, which can realize the timely discharge of the two parts of gas and effectively prevent the accumulation of the two parts of gas, affecting the bearing load and the reliability of the compressor operation.

[0103] The second air supply path 72 for supplying air to the first static pressure thrust bearing 5 can be independent of or connected to the first air supply path 71 for supplying air to the radial static pressure bearing 41. Figure 1 and Figure 2 In some embodiments, the second air supply path 72 includes a second air supply channel 721 disposed on the bearing housing 42 and connecting the first air supply channel 712 of the first air supply path 71 with the second gap 51. In this case, the second air supply path 72 is connected to the first air supply path 71 and can share a portion of the first air supply channel 712 and the air inlet 711 with the first air supply path 71, thereby simplifying the structure.

[0104] Continue to see Figure 1 and Figure 2 In some embodiments, the second air supply path 72 includes not only the second air supply channel 721, but also a first air supply cavity 722 and a second throttle hole 724. The first air supply cavity 722 is located between the adjacent axial end surfaces of the first hydrostatic thrust bearing 5 and the bearing seat 42 and communicates with the second air supply channel 721. The second throttle hole 724 is provided on the first hydrostatic thrust bearing 5 and communicates with the first air supply cavity 722 and the second gap 51. In this way, gas outside the housing 1 can flow into the second gap 51 through the air inlet 711, the first air supply channel 712, the second air supply channel 721, the first air supply cavity 722, and the second throttle hole 724 in sequence, forming the air film required by the first hydrostatic thrust bearing 5, thereby enabling the first hydrostatic thrust bearing 5 to support the rotor 3. This simplifies the air path and facilitates air supply.

[0105] Also, see Figure 1 and Figure 2 The second static pressure thrust bearing 6 is sleeved on the rotor 3 and disposed on the side of the thrust plate 31 away from the radial static pressure bearing 41. A third gap 61 is defined between the adjacent axial end surfaces of the second static pressure thrust bearing 6 and the thrust plate 31. The compressor 10 includes a third air supply path 73, which communicates with the third gap 61 to supply air to form an air film. The third gap 61 is connected to the air outlet 84.

[0106] In the above solution, the second static thrust bearing 6 can work together with the radial static bearing 41 to support the rotor 3, ensuring smoother operation. Because the third gap 61 between the second static thrust bearing 6 and the thrust plate 31, used for inflating and forming an air film, is connected to the air outlet 84, gas, after forming an air film in the third gap 61, can flow out of the third gap 61 and toward the air outlet 84 for exhaust. Because the third gap 61 bypasses the exhaust path of the radial static bearing 41 and instead connects to the air outlet 84, the exhaust path of the second static thrust bearing 6 is shorter, resulting in smoother exhaust.

[0107] The third air supply path 73 for supplying air to the second static thrust bearing 6 can be independent of or connected to the first air supply path 71 for supplying air to the radial static bearing 41. Figure 1 and Figure 2 In some embodiments, the third air supply path 73 includes a third air supply channel 731 disposed on the bearing housing 42 and connecting the first air supply channel 712 of the first air supply path 71 with the third gap 61. In this case, the third air supply path 73 is connected to the first air supply path 71 and can share a portion of the first air supply channel 712 and the air inlet 711 with the first air supply path 71, thereby simplifying the structure.

[0108] Continue to see Figure 1 and Figure 2In some embodiments, the third air supply path 73 includes not only a third air supply channel 731, but also a second air supply cavity 732 and a third throttle hole 734. The second air supply cavity 732 is located between the adjacent axial end surfaces of the second hydrostatic thrust bearing 6 and the cover 97 and communicates with the third air supply channel 731. The third throttle hole 734 is provided on the second hydrostatic thrust bearing 6 and connects the second air supply cavity 732 with the third gap 61. The cover 97 is sleeved on the rotor 3 and is located on the side of the second hydrostatic thrust bearing 6 away from the radial hydrostatic bearing 41. In this way, gas outside the housing 1 can flow sequentially through the air inlet 711, the first air supply channel 712, the third air supply channel 731, the second air supply cavity 732, and the third throttle hole 734 into the third gap 61, forming the air film required by the second hydrostatic thrust bearing 6 and enabling the second hydrostatic thrust bearing 6 to support the rotor 3. This simplifies the air path and facilitates air supply.

[0109] Next, Figures 1-8 The illustrated embodiment is further described.

[0110] like Figures 1-8 As shown, in this embodiment, the compressor 10 is a centrifugal compressor, which includes a casing 1, a stator 2, a rotor 3, two bearing assemblies 4, a first static thrust bearing 5, a second static thrust bearing 6, an air supply line 7, an exhaust line 8, a seal 91, an impeller 92, a volute 93, a locking member 94 and a cover 97.

[0111] The housing 1 is cylindrical and has a chamber inside, which provides installation space for other components such as the stator 2 and the rotor 3.

[0112] The stator 2 is fixedly disposed in the housing 1 .

[0113] The rotor 3 is rotatably mounted within the housing 1 and extends through the stator 2, cooperating with the stator 2 to convert electrical energy into mechanical energy. The rotor 3 extends axially from the housing 1 at either end, and is equipped with an impeller 92 at each axial end. Impellers 92 are secured to the rotor 3 by locking members 94 (e.g., locknuts), allowing them to rotate with the rotor 3. Volutes 93 are located on the outer sides of both impellers 92 (the sides facing away from the stator 2). These volutes 93 are connected to the housing 1 at both axial ends.

[0114] Two bearing assemblies 4 are disposed at either axial end of the rotor 3 and are located inside the two impellers 92 (on the side closest to the stator 2). Each bearing assembly 4 includes a radial static pressure bearing 41, a bearing seat 42, and a diffuser 43. The radial static pressure bearing 41 fits over the rotor 3. The bearing seat 42 fits over the radial static pressure bearing 41. The diffuser 43 fits over the rotor 3 and is located on the side of the radial static pressure bearing 41 away from the stator 2.

[0115] The two bearing seats 42 separate the interior space of the housing 1 , so that the interior of the housing 1 is divided into a motor cavity 96 located between the two bearing seats 42 and a bearing cavity 95 located between the bearing seats 42 on both sides and the corresponding diffusers 43 .

[0116] For the convenience of description, the axial direction of the rotor 3 is defined as the left and right direction. Figure 1 Thus, the volute 93, impeller 92, diffuser 43, radial static pressure bearing 41, and bearing seat 42 on the left side can be respectively referred to as the left volute, left impeller, left diffuser, left radial static pressure bearing, and left bearing seat, while the volute 93, impeller 92, diffuser 43, radial static pressure bearing 41, and bearing seat 42 on the right side can be respectively referred to as the right volute, right impeller, right diffuser, right radial static pressure bearing, and right bearing seat, and the two bearing assemblies 4 on the left and right sides can be respectively referred to as the left bearing assembly and the right bearing assembly for easy distinction.

[0117] In this embodiment, the left bearing assembly and the right bearing assembly have many similarities. Therefore, in order to simplify the description, the following will focus on only the left bearing assembly, and for the right bearing assembly, only the differences between it and the left bearing assembly will be mainly introduced. For any parts not described, please refer to the description of the left bearing assembly for understanding.

[0118] Figure 3-Figure 6 The structure of the radial static pressure bearing 41 (i.e., the left radial static pressure bearing) in the left bearing assembly is further shown. Figure 3-Figure 6 as well as Figure 1 and Figure 2 As can be seen, in this embodiment, the left radial hydrostatic bearing adopts a split structure, comprising a carrier 412 and a sleeve 411. Carrier 412 is generally hollow cylindrical and fits over rotor 3. A first gap 419 is defined between its inner surface and the outer surface of rotor 3 for ventilation and forming an air film. Sleeve 411 is generally hollow cylindrical and fits over carrier 412. A seal 91 (e.g., an O-ring, V-ring, or U-ring) is provided between its inner surface and the outer surface of carrier 412 to prevent leakage.

[0119] Specifically, if Figure 3-Figure 6As shown, in this embodiment, the sleeve 411 includes a cylinder 413 and a limiting flange 414. The carrier 412 includes a main body 415 and a stop ring 416. The limiting flange 414 is connected to one axial end of the cylinder 413 and protrudes radially outward from the cylinder 413. The main body 415 is located in the sleeve 411. The stop ring 416 is connected to one axial end of the main body 415 and protrudes radially outward from the main body 415. The limiting flange 414 and the stop ring 416 are located on both axial sides of the cylinder 413. The stop ring 416 abuts against the axial end face of the cylinder 413 facing the stator 2 to limit the relative displacement of the sleeve 411 and the carrier 412. The limiting flange 414 faces the diffuser 43 (i.e., the left diffuser) of the left bearing assembly and is used to extend between the left diffuser and the left bearing seat to perform stop and limit. The surface of the stop ring 416 facing the stator 2 and the surface of the limiting flange 414 facing the left diffuser respectively form two axial end faces of the radial static pressure bearing 41 , ie, a first end face 417 and a second end face 418 .

[0120] Figure 7 The structure of the bearing seat 42 (i.e., the left bearing seat) in the left bearing assembly is further shown. Figure 7 and Figure 2 It can be seen that in this embodiment, the left bearing seat is not only used to support the radial hydrostatic bearing 41 , but also used to support the first hydrostatic thrust bearing 5 and the second hydrostatic thrust bearing 6 .

[0121] Specifically, if Figure 2 and Figure 7As shown, in this embodiment, the left bearing seat includes a seat body 421, a first boss 422, and a second boss 423. The first and second bosses 422, 423 are connected to opposite axial end surfaces of the seat body 421 and each have an outer diameter smaller than that of the seat body 421. The first boss 422 is connected to the surface of the seat body 421 facing the left diffuser and is configured to engage with the retaining flange 414 of the left radial hydrostatic bearing. The second boss 423 is connected to the surface of the seat body 421 facing the stator 2. A first mounting groove 424 for accommodating the left radial hydrostatic bearing is defined within the first boss 422 and the seat body 421. A second mounting groove 425 for accommodating the first and second hydrostatic thrust bearings 5, 6 is defined within the second boss 423. The first mounting groove 424 is smaller than the second mounting groove 425. Both the first and second mounting grooves 424, 425 have a bottom. The bottom of the first mounting groove 424 forms a portion of the bottom of the second mounting groove 425. The surface of the bottom of the first mounting groove 424 that faces the left radial static pressure bearing is the inner surface. This surface, opposite the first end surface 417 of the left radial static pressure bearing, forms the first surface 426 of the left bearing seat. The left radial static pressure bearing is disposed in the first mounting groove 424, with its first end surface 417 facing the first surface 426 of the left bearing seat. Furthermore, a plurality of seals 91 are provided on the outer surface of the cylindrical body 413 of the left radial static pressure bearing to seal the gap between the left radial static pressure bearing and the left bearing seat to prevent air leakage. Seals 91 are also provided between the outer surface of the left bearing seat and the inner surface of the housing 1 to seal the gap between the left bearing seat and the housing 1 to prevent air leakage.

[0122] Figure 8 The structure of the diffuser 43 (left diffuser) in the left bearing assembly is further shown. Figure 8 and Figure 2 As can be seen, in this embodiment, the left diffuser is generally hollow cylindrical, with a shoulder provided for engaging and retaining the housing 1. The smaller end of the diffuser 43 is inserted into the housing 1, with its surface facing the left radial static pressure bearing facing the second end surface 418 of the left radial static pressure bearing, forming a second surface 431.

[0123] The first static pressure thrust bearing 5 and the second static pressure thrust bearing 6 are both arranged in the second mounting groove 425 of the left bearing seat and supported by the left bearing seat. Figure 1 and Figure 2As shown, in this embodiment, a thrust plate 31 is provided on the rotor 3. The thrust plate 31 is located between the left radial static pressure bearing and the stator 2 and extends into the second mounting groove 425. A first static pressure thrust bearing 5 and a second static pressure thrust bearing 6 are disposed on opposite sides of the thrust plate 31. The first static pressure thrust bearing 5 is disposed on the side of the thrust plate 31 closest to the left radial static pressure bearing and serves as the left static pressure thrust bearing. The second static pressure thrust bearing 6 is disposed on the side of the thrust plate 31 away from the left radial static pressure bearing and serves as the right static pressure thrust bearing. A second gap 51 is provided between the first static pressure thrust bearing 5 and the left end surface of the thrust plate 31 for allowing gas to form an air film. A third gap 61 is provided between the second static pressure thrust bearing 6 and the right end surface of the thrust plate 31 for allowing gas to form an air film. Furthermore, a cover 97 is provided on the side of the second static pressure thrust bearing 6 away from the left radial static pressure bearing. Seals 91 are provided between the first hydrostatic thrust bearing 5 and the left bearing seat, between the second hydrostatic thrust bearing 6 and the cover 97 , and between the first hydrostatic thrust bearing 5 and the second hydrostatic thrust bearing 6 .

[0124] The left radial static pressure bearing, the first static pressure thrust bearing 5 and the second static pressure thrust bearing 6 together support the left end of the rotor 3 .

[0125] In order to realize the support function of the left radial static pressure bearing, the first static pressure thrust bearing 5 and the second static pressure thrust bearing 6 on the rotor 3, as shown in FIG. Figure 1 and Figure 2 As shown, in this embodiment, the compressor 10 includes an air supply path 7, and the air supply path 7 includes a first air supply path 71, a second air supply path 72 and a third air supply path 73 arranged on the left side.

[0126] The first air supply path 71 is used to supply air to the left radial static pressure bearing. Figure 1-Figure 7As shown, in this embodiment, the first air supply path 71 includes an air inlet hole 711, a first air supply channel 712, and a first air inlet channel 713, which are connected in sequence. The first air inlet channel 713 includes a first channel section 714 and a second channel section 715, which are connected in sequence. The first channel section 714 includes a first annular groove 716 and an air vent 717, which are connected in sequence. The second channel section 715 includes a second annular groove 718 and a first throttle hole 719, which are connected in sequence. The air inlet hole 711 is provided on the housing 1 and extends radially, connecting the interior and exterior of the housing 1. The first air supply channel 712 is provided on the left bearing seat, specifically on the seat body 421 of the left bearing seat, and extends radially, connecting the air inlet hole 711 with the first annular groove 716. A first annular groove 716 is provided on the sleeve 411 of the left radial static pressure bearing, specifically on the body 413 of the sleeve 411. It is recessed inward from the outer surface of the body 413 and completely surrounds the body 413, circumferentially distributing the airflow. Three vents 717 are evenly arranged circumferentially at the bottom of the first annular groove 716 and extend radially, connecting the first annular groove 716 with the second annular groove 718. A second annular groove 718 is provided on the carrier 412 of the left radial static pressure bearing, specifically on the body 415 of the carrier 412. It is recessed inward from the outer surface of the body 415 and completely surrounds the body 415, storing air and distributing it circumferentially. Multiple first throttle holes 719 are arranged in rows and columns at the bottom of the second annular groove 718. These first throttle holes 719 extend radially, connecting the second annular groove 718 with the first gap 419 to throttle the gas flow, allowing it to enter the first gap 419 and form an air film on the left radial hydrostatic bearing. This ensures air supply to the left radial hydrostatic bearing.

[0127] The second air supply path 72 is used to supply air to the first static pressure thrust bearing 5. Specifically, Figure 1 and Figure 2As shown, in this embodiment, the second air supply path 72 includes a second air supply channel 721, a first air supply cavity 722, and a second throttle hole 724. The second air supply channel 721 is arranged on the left bearing seat, specifically on the seat body 421 of the left bearing seat. It is led out from the first air supply channel 712 and extends axially to connect the first air supply channel 712 with the first air supply cavity 722. At this time, the second air supply channel 721 forms a branch of the first air supply channel 712. The first air supply cavity 722 is located between the first hydrostatic thrust bearing 5 and the surface of the second mounting groove 425 facing the first hydrostatic thrust bearing 5, and is specifically formed by providing a third annular groove 723 on the left end face of the first hydrostatic thrust bearing 5. Multiple second throttle holes 724 are provided at the bottom of the third annular groove 723 and extend axially through the first hydrostatic thrust bearing 5, connecting the third annular groove 723 with the second gap 51. This allows gas to enter the second gap 51 after throttling, forming an air film around the first hydrostatic thrust bearing 5. This ensures air supply to the first hydrostatic thrust bearing 5.

[0128] The third air supply path 73 is used to supply air to the second static pressure thrust bearing 6. Specifically, Figure 1 and Figure 2 As shown, in this embodiment, the third air supply path 73 includes a third air supply channel 731, a second air supply cavity 732, and a third throttle hole 734. The third air supply channel 731 is provided on the left bearing seat, specifically on the seat body 421 of the left bearing seat. It is led out from the first air supply channel 712 and extends axially, connecting the first air supply channel 712 with the second air supply cavity 732. At this time, the third air supply channel 731 forms another branch of the first air supply channel 712, arranged radially side by side with the second air supply channel 721, and specifically located radially outward of the second air supply channel 721. The second air supply cavity 732 is located between the second hydrostatic thrust bearing 6 and the surface of the cover 97 facing the second hydrostatic thrust bearing 6, and is specifically formed by providing a fourth annular groove 733 on the right end surface of the second hydrostatic thrust bearing 6. A plurality of third throttle holes 734 are provided at the bottom of the fourth annular groove 733 and extend axially through the second hydrostatic thrust bearing 6, connecting the fourth annular groove 733 with the third gap 61. This allows gas to enter the third gap 61 after throttling, forming an air film around the second hydrostatic thrust bearing 6. This ensures air supply to the second hydrostatic thrust bearing 6.

[0129] It can be seen that in this embodiment, the left radial hydrostatic bearing, the first hydrostatic thrust bearing 5 and the second hydrostatic thrust bearing 6 share the same air inlet hole 711, and the structure is relatively simple, which is conducive to avoiding the leakage risk caused by a complex air supply path.

[0130] In this embodiment, the left radial hydrostatic bearing can move left and right. When it moves to the right to its limit position, the first end face 417 abuts against the first surface 426. When it moves to the left to its limit position, the second end face 418 abuts against the second surface 431. To prevent this from affecting exhaust smoothness, this embodiment provides an exhaust gas path 8 and designs the exhaust gas path 8.

[0131] Next, the structure of the exhaust gas passage 8 will be described.

[0132] like Figure 1 and Figure 2 As shown, in this embodiment, the exhaust gas path 8 includes a first exhaust chamber 81 , a second exhaust chamber 82 , a connecting hole 83 , an air outlet 84 , a first groove 85 , a second groove 86 and an air inlet 87 .

[0133] The air outlet 84 is provided on the housing 1 , and specifically on a portion of the housing 1 between the stator 2 and the right bearing assembly. The air outlet 84 extends radially to connect the interior and exterior of the housing 1 .

[0134] The air duct 87 is provided on the left bearing seat, specifically on the seat body 421 of the left bearing seat, and extends axially to connect the bearing cavity 95 located on the left side of the left bearing seat with the motor cavity 96 located on the right side of the left bearing seat.

[0135] The first exhaust chamber 81 and the second exhaust chamber 82 are disposed on the left and right sides of the left radial static pressure bearing, specifically between the first end surface 417 of the left radial static pressure bearing and the first surface 426 of the left bearing seat, and between the second end surface 418 of the left radial static pressure bearing and the second surface 431 of the left diffuser, respectively. Both the first exhaust chamber 81 and the second exhaust chamber 82 are connected to the first gap 419, allowing the gas within the first gap 419 to be divided into two paths, flowing to the left and right, and then into the second exhaust chamber 82 and the first exhaust chamber 81.

[0136] The first groove 85 is provided on the first surface 426 of the left bearing seat and is recessed from the first surface 426 toward the side away from the first end surface 417. Furthermore, the first groove 85 is located radially outward of the first exhaust cavity 81. A plurality of first grooves 85 are evenly arranged along the circumference and are all connected to the first exhaust cavity 81.

[0137] Communication holes 83 are provided on the sleeve 411 of the left radial static pressure bearing. Multiple communication holes 83 are evenly spaced along the circumference of the sleeve 411. Each communication hole 83 extends axially through both axial ends of the sleeve 411, connecting the first groove 85 on the right side of the left radial static pressure bearing with the second exhaust chamber 82 on the left side of the left radial static pressure bearing.

[0138] The second groove 86 is provided on the second surface 431 of the left diffuser and is recessed from the second surface 431 toward a side away from the second end surface 418. Furthermore, the second groove 86 is located radially outward of the second exhaust cavity 82. Multiple second grooves 86 are evenly arranged along the circumference and each connects the second exhaust cavity 82 to the bearing cavity 95 located between the left bearing seat and the left diffuser.

[0139] Since the bearing cavity 95 located between the left bearing seat and the left diffuser is connected to the air bleed hole 87, and the air bleed hole 87 is connected to the air outlet hole 84, the second groove 86 connected to the bearing cavity 95 located between the left bearing seat and the left diffuser can be connected to the air outlet hole 84 through the air bleed hole 87.

[0140] Moreover, since the second exhaust chamber 82 is connected with the second groove 86, and the first exhaust chamber 81 is connected with the second exhaust chamber 82 through the first groove 85 and the connecting hole 83, the second exhaust chamber 82 and the first exhaust chamber 81 can both be connected with the air outlet 84, so that the gas in the first gap 419 can be divided into two paths and flow into the first exhaust chamber 81 and the second exhaust chamber 82, and the gas flowing into the first exhaust chamber 81 can flow into the second exhaust chamber 82 through the first groove 85 and the connecting hole 83, and merge with the gas flowing to the left from the first gap 419 to the second exhaust chamber 82, and flow through the second groove 86 and the air duct 87 together, and then flow out to the outside of the shell 1 through the air outlet 84 for discharge, thereby realizing the exhaust of the left radial static pressure bearing.

[0141] In addition, in order to achieve the exhaust of the first static pressure thrust bearing 5, as shown in FIG. Figure 2 As shown, in this embodiment, the second gap 51 of the first static thrust bearing 5 communicates with the first exhaust chamber 81 via the first gap 52 between the inner surface of the first static thrust bearing 5 and the outer surface of the rotor 3. Thus, the gas in the second gap 51 can flow into the first exhaust chamber 81 via the first gap 52. Thereafter, together with the gas flowing from the first gap 419 into the first exhaust chamber 81, it flows sequentially through the first groove 85, the communicating hole 83, the second exhaust chamber 82, the second groove 86, and the air inlet hole 87, to the exhaust hole 84, where it is discharged, thereby exhausting the first static thrust bearing 5.

[0142] Due to the provision of the first groove 85, even if the left radial static pressure bearing moves to the right to the extreme position, the first exhaust chamber 81 can still be connected with the connecting hole 83 through the first groove 85, so that the gas collected in the first exhaust chamber 81 by the first gap 419 and the second gap 51 will not be blocked, but can still be discharged in time. In this way, it is possible to effectively prevent gas accumulation from causing pressure increase here, affecting the pressure difference between the right part of the left radial static pressure bearing and the second annular groove 718 and the pressure distribution in the third annular groove 723 of the first static pressure thrust bearing 5, so as not to affect the load-bearing capacity of the left radial static pressure bearing and the first static pressure thrust bearing 5, resulting in reduced operational reliability.

[0143] Moreover, due to the provision of the second groove 86, even if the left radial static pressure bearing moves to the left to the extreme position, the second exhaust chamber 82 can still be connected with the air outlet 84 through the second groove 86, so that the gas entering the second exhaust chamber 82 from the first gap 419 and the gas converging into the second exhaust chamber 82 from the first gap 419 and the second gap 51 via the first exhaust chamber 81 will not be blocked, but can still be discharged in time. In this way, it is possible to effectively prevent gas accumulation from causing pressure increase here, so as not to affect the load-bearing capacity of the left radial static pressure bearing and the first static pressure thrust bearing 5, resulting in reduced operational reliability.

[0144] It can be seen that by providing the first groove 85 and the second groove 86 , the exhaust smoothness can be effectively improved, the bearing capacity can be improved, and the operating reliability of the compressor 10 can be improved.

[0145] In addition, in order to achieve the exhaust of the second static pressure thrust bearing 6, as shown in FIG. Figure 2 As shown, in this embodiment, a second gap 62 is defined between the inner surface of the second hydrostatic thrust bearing 6, the inner surface of the cover 97, and the outer surface of the rotor 3. Furthermore, the third gap 61 of the second hydrostatic thrust bearing 6 communicates with the motor cavity 96 through the second gap 62. Because the motor cavity 96 is connected to the air outlet 84, the third gap 61, which is connected to the motor cavity 96, is also connected to the air outlet 84. This allows gas within the third gap 61 to flow through the second gap 62 to the air outlet 84, and then out of the housing 1 through the air outlet 84, thereby exhausting the second hydrostatic thrust bearing 6.

[0146] It can be seen that the exhaust gas path 9 of this embodiment can achieve smooth exhaust of the left radial hydrostatic bearing, the first hydrostatic thrust bearing 5 and the second hydrostatic thrust bearing 6 based on a relatively simple structure, effectively improving the operating reliability of the compressor 10.

[0147] The left bearing assembly has been introduced above. Next, the difference between the right bearing assembly and the left bearing assembly will be mainly introduced.

[0148] like Figure 1As shown, in this embodiment, the main difference between the right and left bearing assemblies is that the bearing seat 42 (i.e., the right bearing seat) of the right bearing assembly is used only to support the right radial hydrostatic bearing 41 (i.e., the right radial hydrostatic bearing) of the right bearing assembly, and no longer supports the hydrostatic thrust bearing. Therefore, the right bearing seat includes only a first mounting groove 424 for accommodating the right radial hydrostatic bearing, and does not include a second mounting groove 425 for accommodating the hydrostatic thrust bearing. Moreover, the first mounting groove 424 of the right bearing seat does not have a groove bottom, but is directly open toward one end of the stator 2, communicating with the motor cavity 96. In this case, the right radial hydrostatic bearing is provided with only the second exhaust chamber 82 and the second groove 86 on the right side, while the left side does not include the first exhaust chamber 81 and the first groove 85. The second exhaust chamber 82 communicates with the motor cavity 96 via the second groove 86 and the connecting hole 83 located on the sleeve 411 of the right radial hydrostatic bearing.

[0149] At the same time, since the right bearing seat is only used to support the right radial static pressure bearing and no longer supports the static pressure thrust bearing, in this embodiment, the right bearing assembly is only equipped with a first air supply path 71 for supplying air to the right radial static pressure bearing, and is not equipped with the second air supply path 72 and the third air supply path 73 mentioned above. That is to say, in this embodiment, the air supply path 7 includes two first air supply paths 71, one second air supply path 72 and one third air supply path 73. Among them, one first air supply path 71, one second air supply path 72 and one third air supply path 73 constitute the left air supply path, which is used to supply air to the left radial static pressure bearing, the first static pressure thrust bearing 5 and the second static pressure thrust bearing 6, and the other first air supply path 71 constitutes the right air supply path, which is used to supply air to the right radial static pressure bearing.

[0150] Next, combine Figure 1 and Figure 2 The air supply and exhaust processes of the left radial static pressure bearing, the first static pressure thrust bearing 5 , the second static pressure thrust bearing 6 , and the right radial static pressure bearing will be described.

[0151] First, the air supply and exhaust processes of the left radial static pressure bearing, the first static pressure thrust bearing 5 and the second static pressure thrust bearing 6 are introduced.

[0152] like Figure 1 and Figure 2 As shown, in this embodiment, the gas outside the shell 1 enters the first air supply channel 712 through the air inlet 711 of the left air supply path, and then is divided into three parts, supplying air to the left radial static pressure bearing, the first static pressure thrust bearing 5 and the second static pressure thrust bearing 6 respectively.

[0153] The gas supplied to the left radial static pressure bearing flows from the first gas supply channel 712 through the first annular groove 716, the vent hole 717, the second annular groove 718, and the first throttle hole 719 of the left radial static pressure bearing, and flows into the first gap 419 between the left radial static pressure bearing and the rotor 3, forming an air film. Afterwards, the gas in the first gap 419 flows in two directions, with one part flowing directly to the left toward the second exhaust chamber 82, and the other part flowing to the right toward the first exhaust chamber 81, and then passing through the first groove 85 and the connecting hole 83 that penetrates the sleeve 411 of the left radial static pressure bearing, reaching the second exhaust chamber 82.

[0154] The gas supplying the first static pressure thrust bearing 5 flows out from the first gas supply channel 712, and flows through the second gas supply channel 721, the first gas supply cavity 722, and the second throttle hole 724 in sequence, and flows to the second gap 51 between the first static pressure thrust bearing 5 and the thrust plate 31, forming an air film. Thereafter, the gas passes through the first gap 52 between the first static pressure thrust bearing 5 and the rotor 3 to reach the first exhaust cavity 81, and converges with the gas discharged from the right side of the first gap 419. Thereafter, the gas passes through the first groove 85 and the connecting hole 83 to reach the second exhaust cavity 82, and converges with the gas discharged from the left side of the first gap 419. The gas passes through the second groove 86 located radially outside the second exhaust cavity 82, reaches the air inlet hole 87, and flows to the air outlet hole 84 for discharge.

[0155] The gas supplying the second hydrostatic thrust bearing 6 flows out from the first gas supply channel 712, and passes through the third gas supply channel 731, the second gas supply cavity 732 and the third throttle hole 734 in sequence, flows into the third gap 61 between the second hydrostatic thrust bearing 6 and the thrust plate 31, forms an air film, and then reaches the left part of the motor cavity 96 through the second hydrostatic thrust bearing 6 and the second gap 62 between the cover 97 and the rotor 3, and reaches the right part of the motor cavity 96 through the air gap between the stator 2 and the rotor 3, and is finally discharged through the air outlet 84.

[0156] Next, the air supply and exhaust process of the right radial static pressure bearing is introduced.

[0157] like Figure 1 and Figure 2As shown, in this embodiment, the gas outside the shell 1 flows to the first gap 419 between the right radial static pressure bearing and the rotor 3 through the air inlet 711, the first air supply channel 712, the first annular groove 716, the air vent 717, the second annular groove 718 and the first throttle hole 719 of the right air supply path in sequence, forming an air film. After that, the gas in the first gap 419 flows to both sides, one part flows directly to the left to the motor cavity 96, and the other part flows to the right to reach the second exhaust cavity 82 between the right radial static pressure bearing and the right diffuser, and then passes through the second groove 86 located radially outside the second exhaust cavity 82 and the connecting hole 83 passing through the right radial static pressure bearing sleeve 411 in sequence to reach the motor cavity 96, and finally is discharged through the air outlet 84 provided on the shell 1.

[0158] It can be seen that this embodiment adopts a "two-inlet and one-outlet" air circuit to supply and exhaust air for the left and right bearings and the left and right static pressure thrust bearings. The air circuits are relatively simple, which can effectively simplify the air circuit structure while meeting the air supply and exhaust requirements, reduce the risk of leakage, and improve the operating reliability of the gas bearings and the compressor 10.

[0159] Moreover, this embodiment optimizes the exhaust gas path. By providing the first groove 85 and the second groove 86, the problem of poor exhaust caused by the axial movement of the radial static pressure bearing can be cleverly solved, the exhaust smoothness of the gas bearing in the compressor 10 can be effectively improved, the load-bearing capacity and load-bearing stability of the gas bearing can be enhanced, and the operating reliability of the compressor 10 can be improved.

[0160] It can be seen that the compressor 10 of this embodiment has the characteristics of simple gas circuit and reliable air supply and exhaust.

[0161] Applying the compressor 10 of the present application to a refrigerant circulation system can effectively enhance the operational reliability of the refrigerant circulation system and improve the performance of the refrigerant circulation system.

[0162] Therefore, the present application also provides a refrigerant circulation system, which includes the compressor 10 of any embodiment of the present application. Exemplarily, the refrigerant circulation system is an air conditioning system.

[0163] The above description is merely an exemplary embodiment of the present application and is not intended to limit the present application. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present application shall be included in the scope of protection of the present application.

Claims

1. A compressor (10), characterized in that: include: housing (1); A stator (2) is fixedly disposed in the housing (1); A rotor (3) rotatably inserted into the stator (2); A bearing assembly (4) comprising a radial static pressure bearing (41), a bearing seat (42) and a diffuser (43), wherein the radial static pressure bearing (41) is axially movably sleeved on the rotor (3) and a first gap (419) is provided between the radial static pressure bearing (41) and the outer surface of the rotor (3) for allowing gas to pass through to form a gas film, the bearing seat (42) is sleeved outside the radial static pressure bearing (41), and the diffuser (43) is sleeved on the rotor (3) and is located on a side of the radial static pressure bearing (41) away from the stator (2); and An exhaust gas path (8) is used to discharge the gas in the first gap (419) to the outside of the housing (1), and includes an exhaust hole (84), the exhaust hole (84) is provided on the housing (1) and communicates with the outside of the housing (1), the exhaust hole (84) is located on a side of the bearing seat (42) away from the diffuser (43), and the exhaust gas path (8) further includes: a first exhaust cavity (81) and a first groove (85), wherein the first exhaust cavity (81) is located between a first end surface (417) of the radial static pressure bearing (41) facing the stator (2) and a first surface (426) of the bearing seat (42) opposite to the first end surface (417), and the first groove (85) is located on the first end surface (417) and / or the first surface (426) and communicates with the first exhaust cavity (81) and the air outlet hole (84); a second exhaust cavity (82) and a second groove (86), wherein the second exhaust cavity (82) is located between a second end surface (418) of the radial static pressure bearing (41) facing the diffuser (43) and a second surface (431) of the diffuser (43) opposite to the second end surface (418), and the second groove (86) is located on the second end surface (418) and / or the second surface (431) and communicates with the second exhaust cavity (82) and the air outlet hole (84); a connecting hole (83) connecting the first groove (85) and the second exhaust cavity (82), or connecting the first groove (85) and the second groove (86), wherein the second groove (86) connects the second exhaust cavity (82) and the air outlet hole (84); and An air inlet hole (87) is provided on the bearing seat (42) and / or the housing (1), and connects the second groove (86) with the air outlet hole (84).

2. The compressor (10) according to claim 1, characterized in that The exhaust gas path (8) comprises at least two first grooves (85), and the at least two first grooves (85) are arranged at intervals along the circumference of the rotor (3); and / or the exhaust gas path (8) comprises at least two second grooves (86), and the at least two second grooves (86) are arranged at intervals along the circumference of the rotor (3).

3. The compressor (10) according to claim 1, characterized in that The radial static pressure bearing (41) comprises a sleeve (411) and a carrier (412), the sleeve (411) is sleeved outside the carrier (412), the first gap (419) is located between the carrier (412) and the rotor (3), and the communicating hole (83) is located on the sleeve (411).

4. The compressor (10) according to claim 1, characterized in that The compressor (10) comprises a first air supply path (71), the first air supply path (71) being in communication with the first gap (419) and supplying air to the first gap (419) to form an air film.

5. The compressor (10) according to claim 4, characterized in that The first air supply path (71) includes an air inlet hole (711), a first air supply channel (712) and a first air inlet channel (713); the air inlet hole (711) is provided on the housing (1) and is in communication with the outside of the housing (1); the first air supply channel (712) is provided on the bearing seat (42) and is in communication with the air inlet hole (711); the first air inlet channel (713) is provided on the radial static pressure bearing (41) and is in communication with the first air supply channel (712) and the first gap (419).

6. The compressor (10) according to claim 5, characterized in that The radial static pressure bearing (41) includes a sleeve (411) and a carrier (412), wherein the sleeve (411) is sleeved outside the carrier (412), and the first gap (419) is located between the carrier (412) and the outer surface of the rotor (3). The first air inlet channel (713) includes a first channel section (714) and a second channel section (715), wherein the first channel section (714) is arranged on the sleeve (411) and communicates with the first air supply channel (712), and the second channel section (715) is arranged on the carrier (412) and communicates with the first channel section (714) and the first gap (419).

7. The compressor (10) according to claim 6, characterized in that The first channel section (714) includes a first annular groove (716) and a vent hole (717), wherein the first annular groove (716) is arranged on the outer surface of the sleeve (411) and is in communication with the first air supply channel (712), and the vent hole (717) is arranged at the bottom of the first annular groove (716) and is in communication with the first annular groove (716) and the second channel section (715); and / or, the second channel section (715) includes a second annular groove (718) and a first throttle hole (719), wherein the second annular groove (718) is arranged on the outer surface of the carrier (412) and is in communication with the first channel section (714), and the first throttle hole (719) is arranged at the bottom of the second annular groove (718) and is in communication with the second annular groove (718) and the first gap (419).

8. The compressor (10) according to claim 7, characterized in that The first channel section (714) includes at least two ventilation holes (717), and the at least two ventilation holes (717) are arranged at intervals along the circumference of the first annular groove (716); and / or the second channel section (715) includes at least two first throttling holes (719), and the at least two first throttling holes (719) are arranged at intervals along the axial direction and / or circumferential direction of the second annular groove (718).

9. The compressor (10) according to any one of claims 1 to 8, characterized in that The compressor (10) comprises two bearing assemblies (4), and the two bearing assemblies (4) are arranged at both axial ends of the rotor (3).

10. The compressor (10) according to claim 9, characterized in that The compressor (10) comprises two first air supply paths (71), and the two first air supply paths (71) respectively supply air to first gaps (419) of radial static pressure bearings (41) of the two bearing assemblies (4).

11. The compressor (10) according to any one of claims 1 to 4, characterized in that: The rotor (3) is provided with a thrust disk (31), and the thrust disk (31) is located on a side of the radial static pressure bearing (41) away from the diffuser (43), and the compressor (10) further includes at least one of the following: A first static pressure thrust bearing (5) is sleeved on the rotor (3) and is arranged on a side of the thrust plate (31) close to the radial static pressure bearing (41); a second gap (51) is provided between the first static pressure thrust bearing (5) and the adjacent axial end surface of the thrust plate (31); the compressor (10) includes a second air supply path (72); the second air supply path (72) is communicated with the second gap (51) to supply air to the second gap (51) to form an air film; the second gap (51) is communicated with a first exhaust chamber (81) of the exhaust path (8); A second static pressure thrust bearing (6) is sleeved on the rotor (3) and is arranged on a side of the thrust plate (31) away from the radial static pressure bearing (41). A third gap (61) is provided between the second static pressure thrust bearing (6) and the adjacent axial end faces of the thrust plate (31). The compressor (10) includes a third air supply path (73). The third air supply path (73) is connected to the third gap (61) to supply air to the third gap (61) to form an air film. The third gap (61) is connected to the air outlet (84).

12. The compressor (10) according to any one of claims 5 to 8, characterized in that: The rotor (3) is provided with a thrust disk (31), and the thrust disk (31) is located on a side of the radial static pressure bearing (41) away from the diffuser (43), and the compressor (10) further includes at least one of the following: A first static pressure thrust bearing (5) is sleeved on the rotor (3) and is arranged on a side of the thrust plate (31) close to the radial static pressure bearing (41); a second gap (51) is provided between the first static pressure thrust bearing (5) and the adjacent axial end surface of the thrust plate (31); the compressor (10) includes a second air supply path (72); the second air supply path (72) is communicated with the second gap (51) to supply air to the second gap (51) to form an air film; the second gap (51) is communicated with a first exhaust chamber (81) of the exhaust path (8); A second static pressure thrust bearing (6) is sleeved on the rotor (3) and is arranged on a side of the thrust plate (31) away from the radial static pressure bearing (41). A third gap (61) is provided between the second static pressure thrust bearing (6) and the adjacent axial end faces of the thrust plate (31). The compressor (10) includes a third air supply path (73). The third air supply path (73) is connected to the third gap (61) to supply air to the third gap (61) to form an air film. The third gap (61) is connected to the air outlet (84).

13. The compressor (10) according to claim 12, characterized in that The second air supply path (72) includes a second air supply channel (721), which is arranged on the bearing seat (42) and connects the first air supply channel (712) of the first air supply path (71) of the compressor (10) and the second gap (51); and / or the third air supply path (73) includes a third air supply channel (731), which is arranged on the bearing seat (42) and connects the first air supply channel (712) of the first air supply path (71) of the compressor (10) and the third gap (61).

14. The compressor (10) according to claim 13, characterized in that The second air supply path (72) further comprises a first air supply cavity (722) and a second throttle hole (724), wherein the first air supply cavity (722) is located between the adjacent axial end faces of the first static thrust bearing (5) and the bearing seat (42), and is communicated with the second air supply channel (721), and the second throttle hole (724) is provided on the first static thrust bearing (5) and is communicated with the first air supply cavity (722) and the second gap (51); and / or the third air supply path (73) comprises a second air supply cavity (732) ) and a third throttling hole (734), the second air supply cavity (732) is located between the adjacent axial end faces of the second hydrostatic thrust bearing (6) and the cover (97), and is connected to the third air supply channel (731), the third throttling hole (734) is provided on the second hydrostatic thrust bearing (6), and is connected to the second air supply cavity (732) and the third gap (61), the cover (97) is sleeved on the rotor (3), and is located on the side of the second hydrostatic thrust bearing (6) away from the radial hydrostatic bearing (41).

15. A refrigerant circulation system, characterized in that: Comprising a compressor (10) as described in any one of claims 1 to 14.

16. The refrigerant circulation system according to claim 15, characterized in that: The refrigerant circulation system is an air-conditioning system.

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