Gas bearing assembly, compressor and air conditioner

Abstract

The present disclosure relates to a gas bearing assembly, a compressor, and an air conditioner. The gas bearing assembly includes: a bearing plate (10) including at least one hydrostatic bearing section (12) and at least one shallow cavity bearing section (13) arranged radially, the at least one hydrostatic bearing section (12) and the at least one shallow cavity bearing section (13) being located on an end face of the bearing plate (10) on one side along the axial direction; a thrust disc (20) axially located on a side of the bearing plate (10) adjacent to the at least one hydrostatic bearing section (12) and the at least one shallow cavity bearing section (13), wherein a distance d1 between the at least one hydrostatic bearing section (12) and the thrust disc (20) is greater than a distance d2 between the at least one shallow cavity bearing section (13) and the thrust disc (20). Embodiments of the present disclosure can provide good support for rotors in a larger speed range, improving service life and working stability.

Description

Technical Field

[0001] The present disclosure relates to the field of bearings, and particularly to a gas bearing assembly, a compressor, and an air conditioner. Background Art

[0002] A centrifugal chiller is a large-scale central air-conditioning refrigeration device, and its core is a centrifugal compressor. The centrifugal compressor compresses the refrigerant by using the centrifugal force generated by the rotation of the impeller, and mainly includes fixed-frequency, variable-frequency, magnetic levitation, and air suspension centrifugal compressors. The air suspension centrifugal compressor has become the development trend of future centrifugal compressors due to its advantages such as simple structure, oil-free, frictionless, and low cost.

[0003] Since a centrifugal compressor is a device for compressing refrigerant, the forces on both ends of the rotor are usually not the same, resulting in the rotor inevitably moving forward or backward. At this time, in the related art, a thrust bearing is arranged in the rotor system to balance the forward or backward force of the rotor. The air suspension centrifugal compressor usually uses a gas thrust bearing to support the rotor and balance the axial force received by the rotor.

[0004] In the related art, gas bearings mainly include hydrodynamic gas bearings and hydrostatic gas bearings. The hydrodynamic gas bearing belongs to a self-supporting bearing, which does not require an additional air supply system for air supply and mainly works using the hydrodynamic principle. The hydrostatic gas bearing generates an air film for supporting the rotor by means of active ventilation. Summary of the Invention

[0005] After research, it is found that since the air suspension centrifugal compressor generally has a high rotational speed and a large pressure ratio, when using a hydrodynamic gas bearing to support the rotor, the load-carrying capacity of the hydrodynamic gas bearing is insufficient, it is difficult to achieve a good balance of the axial force, and a certain starting rotational speed is required, making it difficult to support the rotor takeoff at a low rotational speed of the rotor. During the start-stop stage, friction occurs between the rotor and the bearing, reducing the service life; when using a hydrostatic gas bearing to support the rotor, the hydrostatic gas bearing lacks adaptability, and at a high rotational speed of the rotor, it is easy to cause the rotor to run unstably, and a large air supply pressure is required. When the air supply pressure difference is large, the hydrostatic gas bearing may generate a water hammer, resulting in the rotor running unstably.

[0006] In view of this, the embodiments of the present disclosure provide a gas bearing assembly, a compressor, and an air conditioner, which can provide good support for rotors in a larger rotational speed range, improving the service life and working stability.

[0007] In one aspect of the present disclosure, a gas bearing assembly is provided, including:

[0008] The bearing piece includes at least one hydrostatic bearing section and at least one shallow cavity bearing section arranged radially, and the at least one hydrostatic bearing section and the at least one shallow cavity bearing section are located on the end face of one side of the bearing piece along the axial direction;

[0009] The thrust disk is located axially on one side of the bearing piece adjacent to the at least one hydrostatic bearing section and the at least one shallow cavity bearing section,

[0010] wherein, the distance d1 between the at least one hydrostatic bearing section and the thrust disk is greater than the distance d2 between the at least one shallow cavity bearing section and the thrust disk.

[0011] In some embodiments, the at least one hydrostatic bearing section includes at least two hydrostatic bearing sections, a part of the at least two hydrostatic bearing sections is located radially on one side of the at least one shallow cavity bearing section, and another part of the at least two hydrostatic bearing sections is located radially on the other side of the at least one shallow cavity bearing section.

[0012] In some embodiments, the at least two hydrostatic bearing sections include two hydrostatic bearing sections, and the at least one shallow cavity bearing section includes one shallow cavity bearing section, which is located between the two hydrostatic bearing sections.

[0013] In some embodiments, the distance d1 between the at least one hydrostatic bearing section and the thrust disk is 0.03 - 0.07 mm, and the distance d2 between the at least one shallow cavity bearing section and the thrust disk is 0.005 - 0.015 mm.

[0014] In some embodiments, the distance d1 between the at least one hydrostatic bearing section and the thrust disk is 0.05 mm, and the distance d2 between the at least one shallow cavity bearing section and the thrust disk is 0.01 mm.

[0015] In some embodiments, the hydrostatic bearing section includes:

[0016] A first annular sheet body having a plurality of air supply through holes axially penetrating the first annular sheet body;

[0017] A plurality of porous material blocks are arranged at intervals in the circumferential direction on the end face of the first annular sheet body on the first side along the axial direction, and are respectively aligned with the plurality of air supply through holes;

[0018] wherein, the distance d1 between the hydrostatic bearing section and the thrust disk is the distance between the porous material block and the thrust disk.

[0019] In some embodiments, the end face of the first annular sheet body on the first axial side has a plurality of mounting grooves, the plurality of porous material blocks are respectively embedded in the plurality of mounting grooves, the plurality of air supply through holes are respectively communicated with the bottoms of the plurality of mounting grooves, the end face of the first annular sheet body on the second axial side opposite to the first side has a first annular air groove, and the plurality of air supply through holes are all communicated with the first annular air groove.

[0020] In some embodiments, the at least one hydrostatic bearing section includes a first hydrostatic bearing section and a second hydrostatic bearing section, and the plurality of porous material blocks included in the first hydrostatic bearing section are circumferentially offset from the plurality of porous material blocks included in the second hydrostatic bearing section.

[0021] In some embodiments, the shallow cavity bearing section includes:

[0022] A second annular sheet body having a plurality of grooves, the plurality of grooves being located on the end face of the second annular sheet body on the first axial side and being circumferentially spaced apart.

[0023] Wherein, the distance d2 between the shallow cavity bearing section and the thrust disk is the distance between the end face of the second annular sheet body on the first side and the thrust disk.

[0024] In some embodiments, there are a plurality of air intake through holes on the end face of the second annular sheet body on the second axial side opposite to the first side, which are respectively opposite to and communicated with the plurality of grooves, the end face of the second annular sheet body on the second axial side has a second annular air groove, and the plurality of air intake through holes are all communicated with the second annular air groove.

[0025] In some embodiments, the bottom of the groove is wedge-shaped, the depth of the groove is configured to be from deep to shallow along the rotation direction of the rotor supported by the gas bearing assembly, and the air intake through hole is opposite to the deeper part in the groove.

[0026] In some embodiments, the depth of the groove is 0.01 - 0.03 mm, and the aperture of the air intake through hole is 0.6 - 1 mm.

[0027] In some embodiments, the thrust disk has a plurality of parts radially divided and respectively corresponding to at least one hydrostatic bearing section and at least one shallow cavity bearing section, and the part of the thrust disk corresponding to at least one hydrostatic bearing section is recessed away from the bearing sheet side relative to the part of the thrust disk corresponding to at least one shallow cavity bearing section.

[0028] In some embodiments, the at least one hydrostatic bearing segment includes a plurality of hydrostatic bearing segments, and the distances d1 between the plurality of hydrostatic bearing segments and the thrust disc are all the same, and / or, the at least one shallow cavity bearing segment includes a plurality of shallow cavity bearing segments, and the distances d2 between the plurality of shallow cavity bearing segments and the thrust disc are all the same.

[0029] In one aspect of the present disclosure, there is provided a compressor including the aforementioned gas bearing assembly.

[0030] In one aspect of the present disclosure, there is provided an air conditioner including the aforementioned compressor.

[0031] Therefore, according to the embodiments of the present disclosure, by arranging at least one hydrostatic bearing segment and at least one shallow cavity bearing segment radially on the bearing piece, and setting the distance between the hydrostatic bearing segment and the thrust disc to be greater than the distance between the shallow cavity bearing segment and the thrust disc, the gas bearing assembly can provide good support for the rotor in a larger speed range, improving the service life and working stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] The drawings forming a part of the specification depict embodiments of the present disclosure and, together with the description, are used to explain the principles of the present disclosure.

[0033] Referring to the drawings, the present disclosure can be more clearly understood from the following detailed description, wherein:

[0034] Figure 1 is a schematic structural diagram of some embodiments of the gas bearing assembly according to the present disclosure;

[0035] Figure 2 is a schematic longitudinal sectional view along the axial direction of some embodiments of the gas bearing assembly according to the present disclosure;

[0036] Figure 3 is Figure 2 an enlarged schematic view of ellipse A in

[0037] Figure 4 is a schematic structural diagram of one side of the bearing piece adjacent to the thrust disc in some embodiments of the gas bearing assembly according to the present disclosure;

[0038] Figure 5 is a schematic structural diagram of one side of the bearing piece away from the thrust disc in some embodiments of the gas bearing assembly according to the present disclosure;

[0039] Figure 6 is Figure 5 an enlarged schematic view of ellipse B in.

[0040] It should be understood that the dimensions of the various parts shown in the drawings are not drawn in actual proportional relationship. In addition, the same or similar reference numerals represent the same or similar components. Detailed Embodiments

[0041] Various exemplary embodiments of the present disclosure will now be described in detail with reference to the accompanying drawings. The description of the exemplary embodiments is merely illustrative and in no way limits the present disclosure or its application or use. The present disclosure can be implemented in many different forms and is not limited to the embodiments described herein. These embodiments are provided to make the present disclosure thorough and complete, and to fully convey the scope of the present disclosure to those skilled in the art. It should be noted that: unless otherwise specifically stated, the relative arrangements of components and steps, the compositions of materials, numerical expressions, and numerical values set forth in these embodiments should be construed as merely exemplary and not as limitations.

[0042] The terms "first", "second", and similar terms used in the present disclosure do not denote any order, quantity, or importance, but are merely used to distinguish different parts. Words such as "comprising" or "including" mean that the elements before the word cover the elements listed after the word, and do not exclude the possibility of also covering other elements. Terms such as "upper", "lower", "left", "right", etc. are only used to represent relative positional relationships, and when the absolute position of the object being described changes, the relative positional relationship may also change accordingly.

[0043] In the present disclosure, when it is described that a specific device is located between a first device and a second device, there may or may not be an intermediate device between the specific device and the first device or the second device. When it is described that a specific device is connected to other devices, the specific device may be directly connected to the other devices without an intermediate device, or may not be directly connected to the other devices and have an intermediate device.

[0044] All terms used in the present disclosure (including technical terms or scientific terms) have the same meaning as understood by those of ordinary skill in the art to which the present disclosure pertains, unless otherwise specifically defined. It should also be understood that terms defined in a general dictionary, such as those in a general dictionary, should be construed to have a meaning consistent with their meaning in the context of the relevant art, and should not be interpreted in an idealized or overly formal sense, unless specifically defined as such here.

[0045] Techniques, methods, and devices known to those of ordinary skill in the relevant art may not be discussed in detail, but where appropriate, the techniques, methods, and devices should be regarded as part of the specification.

[0046] Figure 1 is a schematic structural diagram of some embodiments of the gas bearing assembly according to the present disclosure. Refer to Figure 1, in some embodiments, the gas bearing assembly includes: a bearing plate 10 and a thrust disk 20. The bearing plate 10 includes at least one hydrostatic bearing section 12 and at least one shallow cavity bearing section 13 arranged radially. The at least one hydrostatic bearing section 12 and the at least one shallow cavity bearing section 13 are located on the end face of the bearing plate 10 on one side along the axial direction. The thrust disk 20 is axially located on one side of the bearing plate 10 adjacent to the at least one hydrostatic bearing section 12 and the at least one shallow cavity bearing section 13. The distance d1 between the at least one hydrostatic bearing section 12 and the thrust disk 20 is greater than the distance d2 between the at least one shallow cavity bearing section 13 and the thrust disk 20.

[0047] In this embodiment, by arranging at least one hydrostatic bearing section and at least one shallow cavity bearing section radially on the bearing plate, the hydrostatic bearing section can achieve the supporting effect of the hydrostatic gas bearing on the rotor, and the shallow cavity bearing section can at least achieve the supporting effect of the hydrodynamic gas bearing on the rotor, so that the gas bearing assembly has the advantages of large load-bearing capacity and high stability of both the hydrostatic gas bearing and the hydrodynamic gas bearing.

[0048] As mentioned above, for an air suspension centrifugal compressor, due to the high rotor speed and large pressure ratio, when using a hydrodynamic gas bearing to support the rotor, the hydrodynamic gas bearing has deficiencies in load-bearing capacity and take-off speed. In this embodiment, by setting the distance between the hydrostatic bearing section and the thrust disk to be greater than the distance between the shallow cavity bearing section and the thrust disk, the hydrostatic bearing section can play a major role during the start-stop stage or the low-speed stage of the rotor, enabling the rotor to float without reaching a high take-off speed and reducing the difficulty of frequency converter program control. Accordingly, the problem of reducing the service life due to friction between the rotor and the bearing during the start-stop or low-speed stage is avoided or reduced.

[0049] In addition, as mentioned above, when using a hydrostatic gas bearing to support the rotor, the hydrostatic gas bearing is prone to generating water hammers due to a large supply air pressure difference at high rotor speeds, which may lead to unstable rotor operation. In this embodiment, by setting the distance between the hydrostatic bearing section and the thrust disk to be greater than the distance between the shallow cavity bearing section and the thrust disk, the shallow cavity bearing section can play a major role when the rotor is at a high-speed state, achieving a good hydrodynamic effect, thereby reducing the requirement for the supply air pressure difference of the hydrostatic bearing section, reducing the load and power consumption of the external air supply system, reducing water hammer vibration, and making the rotor operation more stable.

[0050] In addition, at least one hydrostatic bearing section 12 and at least one shallow cavity bearing section 13 of the bearing piece 10 are arranged radially, that is, the hydrostatic bearing section 12 and the shallow cavity bearing section 13 correspond to different radial positions respectively. In some embodiments, there is no overlapping range between the hydrostatic bearing section 12 and the shallow cavity bearing section 13 in the radial direction. Compared with the arrangement mode of arranging both the hydrostatic bearing section and the shallow cavity bearing section in the circular ring area at the same radial position, this embodiment is easier to control the reasonable distance between the hydrostatic bearing section and the shallow cavity bearing section and the thrust plate respectively, so as to obtain better bearing performance.

[0051] In Figure 1 , a through hole 21 may be provided at the center of the thrust plate 20 for connecting with the rotor. A through hole 11 may also be provided at the center of the bearing piece 10 for the rotor to pass through. Correspondingly, each hydrostatic bearing section 12 and shallow cavity bearing section 13 is annular.

[0052] Referring to Figure 1 , in some embodiments, at least one hydrostatic bearing section 12 includes at least two hydrostatic bearing sections 12. A part of the at least two hydrostatic bearing sections 12 is located on one side of the at least one shallow cavity bearing section 13 in the radial direction, and another part of the at least two hydrostatic bearing sections 12 is located on the other side of the at least one shallow cavity bearing section 13 in the radial direction. By arranging the hydrostatic bearing sections on both sides of the shallow cavity bearing section 13 in the radial direction, a more balanced hydrostatic support effect on the rotor can be achieved in the radial direction.

[0053] It should be noted that two adjacent hydrostatic bearing sections in the radial direction can also be regarded as a wider hydrostatic bearing section in the radial direction, and two adjacent shallow cavity bearing sections in the radial direction can also be regarded as a wider shallow cavity bearing section in the radial direction. In this way, Figure 1 the shown arrangement mode can be regarded as a gas bearing assembly with a combination mode of hydrostatic - shallow cavity - hydrostatic. In other embodiments, the gas bearing assembly can also adopt a combination mode of hydrostatic - shallow cavity or shallow cavity - hydrostatic, or a combination mode of shallow cavity - hydrostatic - shallow cavity, etc. The gas bearing assembly adopting the combination mode of hydrostatic - shallow cavity - hydrostatic can provide a reliable support for the rotor during the startup or low - speed working conditions of the rotor, so as to support a lower rotor take - off speed.

[0054] In Figure 1 , at least two hydrostatic bearing sections 12 include two hydrostatic bearing sections 12, and the at least one shallow cavity bearing section 13 includes one shallow cavity bearing section 13, which is located between the two hydrostatic bearing sections 12. By setting a reasonable quantity ratio of the hydrostatic bearing section 12 and the shallow cavity bearing section 13, materials can be saved, the component size can be reduced, and the support requirements of various rotors at different speeds can be met.

[0055] Referring to Figure 1, in some embodiments, the distance d1 between at least one hydrostatic bearing section 12 and the thrust disk 20 is 0.03 - 0.07 mm, and more preferably 0.05 mm. The distance d2 between at least one shallow cavity bearing section 13 and the thrust disk 20 is 0.005 - 0.015 mm, and more preferably 0.01 mm. By adopting suitable distances d1 and d2, on the one hand, the action sequence of the hydrostatic bearing section and the shallow cavity bearing section at different rotor speeds can be realized, and on the other hand, the rotor support performance of the hydrostatic bearing section and the shallow cavity bearing section can be further improved.

[0056] In some embodiments, the at least one hydrostatic bearing section 12 includes a plurality of hydrostatic bearing sections 12, and the distances d1 between the plurality of hydrostatic bearing sections 12 and the thrust disk 20 are the same, so as to keep the hydrostatic effects achieved by each hydrostatic bearing section 12 consistent. In some embodiments, the at least one shallow cavity bearing section 13 includes a plurality of shallow cavity bearing sections 13, and the distances d2 between the plurality of shallow cavity bearing sections 13 and the thrust disk 20 are the same, so as to keep the hybrid hydrodynamic and hydrostatic effects achieved by each shallow cavity bearing section 13 consistent.

[0057] Figure 2 is a schematic longitudinal sectional view along the axial direction of some embodiments of the gas bearing assembly according to the present disclosure. Figure 3 is Figure 2 an enlarged schematic view of ellipse A in Figure 4 is a schematic structural view of one side of the bearing piece adjacent to the thrust disk in some embodiments of the gas bearing assembly according to the present disclosure. Figure 5 is a schematic structural view of one side of the bearing piece away from the thrust disk in some embodiments of the gas bearing assembly according to the present disclosure. Figure 6 is Figure 5 an enlarged schematic view of ellipse B in

[0058] Reference Figures 2 - 6 , in some embodiments, the hydrostatic bearing section 12 includes: a first annular sheet body 12a and a plurality of porous material blocks 12b. The first annular sheet body 12a has a plurality of air supply through holes 12c axially penetrating the first annular sheet body 12a. The plurality of porous material blocks 12b are circumferentially arranged at intervals on the end face of the first annular sheet body 12a on the first axial side and are respectively aligned with the plurality of air supply through holes 12c. The distance d1 between the hydrostatic bearing section 12 and the thrust disk 20 is the distance between the porous material block 12b and the thrust disk 20.

[0059] Considering the starting and stopping stages or low-speed stages of the rotor, the load on the gas bearing is small. Using multiple porous material blocks 12b arranged locally discretely can meet the usage requirements, thereby reducing the amount of porous material used and lowering costs. In some embodiments, the porous material is graphite material. The first annular sheet 12a can be made of materials such as metal or alloy, such as aluminum alloy, which is easy to process and has high strength.

[0060] When a certain porous material block 12b is damaged, only the damaged porous material block 12b needs to be replaced. In some other embodiments, the hydrostatic bearing section 12 may also include a porous material ring in a closed annular shape to obtain a better hydrostatic bearing effect.

[0061] Reference Figure 3 and Figure 4 , in some embodiments, the end face of the first annular sheet 12a on the first axial side has a plurality of mounting grooves, and the plurality of porous material blocks 12b are respectively embedded in the plurality of mounting grooves. The plurality of air supply through holes 12c are respectively communicated with the bottoms 12e of the plurality of mounting grooves. In Figure 5 and Figure 6 , the end face of the first annular sheet 12a on the second axial side opposite to the first side has a first annular air groove 12d, and the plurality of air supply through holes 12c are all communicated with the first annular air groove 12d.

[0062] By embedding and fixing the porous material blocks in the mounting grooves, the structure of the hydrostatic bearing section can be made more stable and reliable, while the first annular air groove on the back side and the air supply through holes connecting the first annular air groove and the mounting grooves can make the high-pressure air supply input from the external system be applied more evenly to each porous material block, and then be applied more evenly to the thrust disk fixed to the rotor. Without increasing the complexity of the external air supply system, it can supply air to each porous material block well.

[0063] Reference Figure 1 and Figure 4 , in some embodiments, at least one hydrostatic bearing section 12 includes a first hydrostatic bearing section 121 and a second hydrostatic bearing section 122. The plurality of porous material blocks 12b included in the first hydrostatic bearing section 121 are circumferentially offset from the plurality of porous material blocks 12b included in the second hydrostatic bearing section 12. This circumferential offset arrangement can make the load-bearing of the gas bearing assembly more balanced, thereby achieving a greater load-bearing capacity.

[0064] In Figure 4Among them, the hydrostatic bearing section 12 (i.e., the first hydrostatic bearing section 121) located in the inner circle has four porous material blocks 12b, which are respectively located at positions of 45°, 135°, 225° and 315° based on the axis of the gas bearing assembly. The hydrostatic bearing section 12 (i.e., the first hydrostatic bearing section 122) located in the outer circle also has four porous material blocks 12b, which are respectively located at positions of 0°, 90°, 180° and 270° based on the axis of the gas bearing assembly, so as to realize the staggered arrangement of the porous material blocks in different circles in the circumferential angle.

[0065] Reference Figure 4 , in some embodiments, the shallow cavity bearing section 13 includes: a second annular sheet body 13a having a plurality of grooves 13b. The plurality of grooves 13b are located on the end surface of the second annular sheet body 13a on the first axial side, and are arranged at intervals in the circumferential direction. The distance d2 between the shallow cavity bearing section 13 and the thrust disc 20 is the distance between the end surface of the second annular sheet body 13a on the first side and the thrust disc 20.

[0066] The bottom of each groove 13b in the shallow cavity bearing section 13 can be set in a wedge shape, and the depth of the groove 13b can be configured to be from deep to shallow along the rotation direction of the rotor supported by the gas bearing assembly. In this way, when the rotor rotates at a higher speed, along the rotation direction of the rotor, each groove 13b of the shallow cavity bearing section 13 can gradually generate a wedge-shaped gas film to achieve a better hydrodynamic effect.

[0067] The plurality of grooves 13b in the shallow cavity bearing section 13 can be arranged at equal angles in the circumferential direction to make the load bearing of the gas bearing assembly more balanced. In Figure 4 , the groove edge profile of the groove in the axial direction of the gas bearing assembly can be fan-shaped, that is, the two sides in the radial direction are arcs, and the center of the circle is located at the axis of the gas bearing assembly, and the extension lines of the two sides in the circumferential direction both pass through the axis of the gas bearing assembly. In some embodiments, the orthographic projection of the plurality of grooves 13b in the shallow cavity bearing section 13 on a plane perpendicular to the axis of the gas bearing assembly is half of the orthographic projection of the entire shallow cavity bearing section 13 on this plane.

[0068] Reference Figures 4 - 6, in some embodiments, the second annular sheet 13a has a plurality of air inlet through holes 13c on the end face of the second side along the axial direction opposite to the first side, which are respectively opposite to and communicated with the plurality of grooves 13b. With this structure, a secondary throttling effect can be produced in the shallow cavity bearing section. When the air supply enters the air inlet through holes 13c with a smaller aperture (for example, 0.6 - 1 mm) from the second side of the second annular sheet 13a, the air inlet through holes 13c can produce a first throttling effect on the air supply. Then, when passing through the relatively shallow grooves (for example, the depth is 0.01 - 0.03 mm, preferably 0.02 mm), a greater resistance will be generated to the air supply, thereby producing a second throttling effect, and further forming a stronger hydrostatic support effect. In this way, the shallow cavity bearing section realizes the combined action of hydrodynamic and hydrostatic bearings.

[0069] When setting the air inlet through holes, the air inlet through holes 13c can be made to face the deeper part in the grooves 13b. In this way, when the air supply enters the grooves through the air inlet through holes 13c, it can flow from the deeper part of the grooves to the shallower part of the grooves, thereby producing an extrusion effect on the thrust disk and floating up the thrust disk.

[0070] The end face of the second annular sheet 13a on the second side along the axial direction has a second annular air groove 13d, and the plurality of air inlet through holes 13c are all communicated with the second annular air groove 13d. Each air inlet through hole 13c can be communicated with an air supply source inside or outside the compressor through the second annular air groove 13d, so that the air inlet pressure of each air inlet through hole 13c can be kept consistent. Without increasing the complexity of the external air supply system, the second annular air groove 13d can supply air to each groove well.

[0071] Reference Figure 2 and Figure 3 , in some embodiments, the first annular sheet of the hydrostatic bearing section and the second annular sheet of the shallow cavity bearing section can be integrally formed to obtain better strength, machining accuracy and a more compact structure. In other embodiments, the first annular sheet of the hydrostatic bearing section and the second annular sheet of the shallow cavity bearing section can be separately prepared and then connected radially through a connecting member. The connecting member can be a bolt, a clamping structure or an adhesive, etc.

[0072] In Figure 2 and Figure 3Among them, the thrust disk 20 has a plurality of parts that are radially divided and respectively correspond to at least one hydrostatic bearing section 12 and at least one shallow cavity bearing section 13. The part of the thrust disk 20 corresponding to at least one hydrostatic bearing section 12 is recessed away from the bearing piece 10 side relative to the part of the thrust disk 20 corresponding to at least one shallow cavity bearing section 13. In some other embodiments, the surface of the thrust disk adjacent to the bearing piece can be a plane, and the hydrostatic bearing section and the shallow cavity bearing section are arranged in a thickness structure with different convex and concave shapes, as long as the spacing relationship between the aforementioned hydrostatic bearing section and shallow cavity bearing section and the thrust disk is satisfied.

[0073] The above gas bearing assembly is applicable to various devices that need to use a thrust bearing to support a rotor, such as a compressor. Correspondingly, the embodiments of the present disclosure provide a compressor, including any one of the above embodiments of the gas bearing assembly. The compressor can be a gas-bearing centrifugal compressor or a compressor in other ways.

[0074] The embodiments of the compressor of the present disclosure can be used in various devices that need to perform working fluid compression, such as refrigerators, air conditioners, etc. Correspondingly, the embodiments of the present disclosure provide an air conditioner, including any one of the above embodiments of the compressor. The air conditioner can be a centrifugal chiller for central air conditioning.

[0075] So far, the embodiments of the present disclosure have been described in detail. To avoid obscuring the concept of the present disclosure, some details well known in the art have not been described. Those skilled in the art can fully understand how to implement the technical solutions disclosed here based on the above description.

[0076] Although some specific embodiments of the present disclosure have been described in detail by way of examples, those skilled in the art should understand that the above examples are only for illustration and not for limiting the scope of the present disclosure. Those skilled in the art should understand that the above embodiments can be modified or some technical features can be equivalently replaced without departing from the scope and spirit of the present disclosure. The scope of the present disclosure is defined by the appended claims.

Claims

1. A gas bearing assembly, characterized in that, it comprises: a bearing plate (10) including at least one hydrostatic bearing section (12) and at least one shallow cavity bearing section (13) arranged radially, and the at least one hydrostatic bearing section (12) and the at least one shallow cavity bearing section (13) are located on an end face of the bearing plate (10) on one axial side; a thrust disc (20) axially located on one side of the bearing plate (10) adjacent to the at least one hydrostatic bearing section (12) and the at least one shallow cavity bearing section (13), wherein, a distance d1 between the at least one hydrostatic bearing section (12) and the thrust disc (20) is greater than a distance d2 between the at least one shallow cavity bearing section (13) and the thrust disc (20); the shallow cavity bearing section (13) includes a second annular sheet body (13a), the second annular sheet body (13a) has a plurality of grooves (13b), the plurality of grooves (13b) are located on an end face of the second annular sheet body (13a) on a first axial side, and are arranged at intervals in the circumferential direction; there are a plurality of air inlet through holes (13c) on an end face of the second annular sheet body (13a) on a second axial side opposite to the first side, and are respectively opposite to and communicated with the plurality of grooves (13b); a bottom of the groove (13b) is wedge-shaped, a depth of the groove (13b) is configured to be from deep to shallow along a rotation direction of a rotor supported by the gas bearing assembly, and the air inlet through hole (13c) is opposite to a deeper part in the groove (13b).

2. The gas bearing assembly according to claim 1, characterized in that, the at least one hydrostatic bearing section (12) includes at least two hydrostatic bearing sections (12), a part of the at least two hydrostatic bearing sections (12) is radially located on one side of the at least one shallow cavity bearing section (13), and another part of the at least two hydrostatic bearing sections (12) is radially located on the other side of the at least one shallow cavity bearing section (13).

3. The gas bearing assembly according to claim 2, characterized in that, the at least two hydrostatic bearing sections (12) include two hydrostatic bearing sections (12), the at least one shallow cavity bearing section (13) includes one shallow cavity bearing section (13), and is located between the two hydrostatic bearing sections (12).

4. The gas bearing assembly according to claim 1, characterized in that, the distance d1 between the at least one hydrostatic bearing section (12) and the thrust disc (20) is 0.03 - 0.07 mm, and the distance d2 between the at least one shallow cavity bearing section (13) and the thrust disc (20) is 0.005 - 0.015 mm.

5. The gas bearing assembly according to claim 4, characterized in that, the distance d1 between the at least one hydrostatic bearing section (12) and the thrust disc (20) is 0.05 mm, and the distance d2 between the at least one shallow cavity bearing section (13) and the thrust disc (20) is 0.01 mm.

6. The gas bearing assembly according to claim 1, characterized in that, the hydrostatic bearing section (12) includes: A first annular sheet body (12a) having a plurality of air supply through holes (12c) axially penetrating the first annular sheet body (12a); A plurality of porous material blocks (12b) arranged at intervals in the circumferential direction on the end face of the first annular sheet body (12a) on the first axial side and respectively facing the plurality of air supply through holes (12c); Wherein, the distance d1 between the hydrostatic bearing section (12) and the thrust disk (20) is the distance between the porous material block (12b) and the thrust disk (20).

7. The gas bearing assembly according to claim 6, Characterized in that, The end face of the first annular sheet body (12a) on the first axial side has a plurality of mounting grooves, the plurality of porous material blocks (12b) are respectively embedded in the plurality of mounting grooves, the plurality of air supply through holes (12c) are respectively communicated with the bottoms (12e) of the plurality of mounting grooves, the end face of the first annular sheet body (12a) on the second axial side opposite to the first side has a first annular air groove (12d), and the plurality of air supply through holes (12c) are all communicated with the first annular air groove (12d).

8. The gas bearing assembly according to claim 6, Characterized in that, The at least one hydrostatic bearing section (12) includes a first hydrostatic bearing section (121) and a second hydrostatic bearing section (122), and the plurality of porous material blocks (12b) included in the first hydrostatic bearing section (121) are staggered from the plurality of porous material blocks (12b) included in the second hydrostatic bearing section (122) in the circumferential angle.

9. The gas bearing assembly according to claim 1, Characterized in that, The distance d2 between the shallow cavity bearing section (13) and the thrust disk (20) is the distance between the end face of the second annular sheet body (13a) on the first side and the thrust disk (20).

10. The gas bearing assembly according to claim 9, Characterized in that, The end face of the second annular sheet body (13a) on the second axial side has a second annular air groove (13d), and the plurality of air intake through holes (13c) are all communicated with the second annular air groove (13d).

11. The gas bearing assembly according to claim 10, Characterized in that, The depth of the groove (13b) is 0.01 - 0.03 mm, and the aperture of the air intake through hole (13c) is 0.6 - 1 mm.

12. The gas bearing assembly according to claim 1, Characterized in that, The thrust disk (20) has a plurality of parts radially divided and respectively corresponding to at least one hydrostatic bearing section (12) and at least one shallow cavity bearing section (13), and the part of the thrust disk (20) corresponding to at least one hydrostatic bearing section (12) is recessed away from the bearing sheet (10) side relative to the part of the thrust disk (20) corresponding to at least one shallow cavity bearing section (13).

13. The gas bearing assembly according to claim 1, Characterized in that, The at least one hydrostatic bearing segment (12) includes a plurality of hydrostatic bearing segments (12), and the distances d1 between the plurality of hydrostatic bearing segments (12) and the thrust disk (20) are all the same, and / or, the at least one shallow cavity bearing segment (13) includes a plurality of shallow cavity bearing segments (13), and the distances d2 between the plurality of shallow cavity bearing segments (13) and the thrust disk (20) are all the same.

14. A compressor, characterized in that it includes: The gas bearing assembly according to any one of claims 1 to 13.

15. An air conditioner, characterized in that it includes: The compressor according to claim 14.

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