CN114688164A

CN114688164A - Gas bearing assembly, compressor and air conditioner

Info

Publication number: CN114688164A
Application number: CN202011568293.5A
Authority: CN
Inventors: 董明珠; 刘华; 张治平; 钟瑞兴; 陈玉辉
Original assignee: Gree Electric Appliances Inc of Zhuhai
Current assignee: Gree Electric Appliances Inc of Zhuhai
Priority date: 2020-12-25
Filing date: 2020-12-25
Publication date: 2022-07-01

Abstract

The present disclosure relates to a gas bearing assembly, a compressor and an air conditioner. The gas bearing assembly includes: the bearing sheet (10) comprises at least one static pressure bearing section (12) and at least one shallow cavity bearing section (13) which are arranged along the radial direction, and the at least one static pressure bearing section (12) and the at least one shallow cavity bearing section (13) are positioned on the end face of one side of the bearing sheet (10) along the axial direction; a thrust disk (20) located axially on a side of the bearing sheet (10) adjacent to the at least one hydrostatic bearing segment (12) and the at least one shallow-cavity bearing segment (13), wherein a separation d1 of the at least one hydrostatic bearing segment (12) from the thrust disk (20) is greater than a separation d2 of the at least one shallow-cavity bearing segment (13) from the thrust disk (20). The embodiment of the disclosure can provide good support for the rotor with a larger rotating speed range, and improve the service life and the working stability.

Description

Gas bearing assembly, compressor and air conditioner

Technical Field

The disclosure relates to the field of bearings, in particular to a gas bearing assembly, a compressor and an air conditioner.

Background

The centrifugal water chilling unit is a large central air-conditioning refrigeration equipment, and its core is centrifugal compressor. The centrifugal compressor compresses a refrigerant by utilizing centrifugal force generated by rotation of an impeller, and mainly comprises a fixed-frequency centrifugal compressor, a variable-frequency centrifugal compressor, a magnetic suspension centrifugal compressor and an air suspension centrifugal compressor. The air suspension centrifugal compressor has the advantages of simple structure, no oil, no friction, low cost and the like, and becomes a development trend of the centrifugal compressor in the future.

Because the centrifugal compressor is a device for compressing the refrigerant, the stress on the two ends of the rotor is usually different, so that the rotor inevitably moves forwards or backwards. At this time, in the related art, a thrust bearing is disposed in the rotor system to balance the forward or backward force of the rotor. Gas-suspension centrifugal compressors typically employ gas thrust bearings to support the rotor and balance the axial forces experienced by the rotor.

In the related art, the gas bearing mainly includes a dynamic pressure gas bearing and a static pressure gas bearing. The dynamic pressure gas bearing belongs to a self-supporting bearing, does not need an additional gas supply system for supplying gas, and mainly works by adopting a dynamic pressure principle. The hydrostatic gas bearings generate a gas film supporting the rotor by means of active ventilation.

Disclosure of Invention

Research shows that because the air suspension centrifugal compressor generally has higher rotating speed and larger pressure ratio, when a dynamic pressure gas bearing is adopted to support a rotor, the bearing capacity of the dynamic pressure gas bearing is insufficient, better balance axial force is difficult to achieve, a certain takeoff rotating speed is required, the rotor is difficult to support to take off in a low rotating speed state of the rotor, and friction is generated between the rotor and the bearing in a start-stop stage to reduce the service life; when the static pressure gas bearing is adopted to support the rotor, the static pressure gas bearing lacks self-adaptability, the rotor is easy to operate and unstable in operation under the high rotating speed state of the rotor, and large gas supply pressure is needed, and when the gas supply pressure difference is large, the static pressure gas bearing can generate a gas hammer to cause the operation and instability of the rotor.

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 a rotor with a larger rotation speed range, and improve service life and working stability.

In one aspect of the present disclosure, there is provided a gas bearing assembly comprising:

the bearing sheet comprises at least one static pressure bearing section and at least one shallow cavity bearing section which are arranged along the radial direction, and the at least one static pressure bearing section and the at least one shallow cavity bearing section are positioned on the end surface of one side of the bearing sheet along the axial direction;

a thrust disk axially located on a side of the bearing plate adjacent the at least one hydrostatic bearing segment and the at least one shallow bore bearing segment,

wherein a spacing d1 of the at least one hydrostatic bearing segment from the thrust disk is greater than a spacing d2 of the at least one shallow cavity bearing segment from the thrust disk.

In some embodiments, the at least one hydrostatic bearing segment comprises at least two hydrostatic bearing segments, a portion of the at least two hydrostatic bearing segments being located radially on one side of the at least one shallow cavity bearing segment, another portion of the at least two hydrostatic bearing segments being located radially on another side of the at least one shallow cavity bearing segment.

In some embodiments, the at least two hydrostatic bearing segments comprise two hydrostatic bearing segments, and the at least one shallow cavity bearing segment comprises one shallow cavity bearing segment located between the two hydrostatic bearing segments.

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

In some embodiments, the at least one hydrostatic bearing segment is spaced from the thrust disk by a distance d1 of 0.05mm, and the at least one shallow cavity bearing segment is spaced from the thrust disk by a distance d2 of 0.01 mm.

In some embodiments, the hydrostatic bearing segment comprises:

the first annular sheet body is provided with a plurality of air supply through holes which axially penetrate through the first annular sheet body;

the plurality of porous material blocks are arranged on the end face of the first annular sheet body along the axial direction at intervals along the circumferential direction and are respectively opposite to the plurality of air supply through holes;

and the distance d1 between the static pressure bearing section and the thrust disk is the distance between the porous material block and the thrust disk.

In some embodiments, the first annular sheet has a plurality of mounting grooves along an end surface of an axial first side, the plurality of porous material blocks are respectively embedded in the plurality of mounting grooves, the plurality of gas supply through holes are respectively communicated with groove bottoms of the plurality of mounting grooves, the end surface of a second side of the first annular sheet opposite to the first side along the axial direction has a first annular gas groove, and the plurality of gas supply through holes are all communicated with the first annular gas groove.

In some embodiments, the at least one hydrostatic bearing segment comprises a first hydrostatic bearing segment and a second hydrostatic bearing segment, the first hydrostatic bearing segment comprising a plurality of porous material blocks angularly offset in a circumferential direction from the plurality of porous material blocks of the second hydrostatic bearing segment.

In some embodiments, the shallow cavity bearing segment comprises:

a second annular sheet body which is provided with a plurality of grooves, the grooves are positioned on the end surface of the first side of the second annular sheet body along the axial direction and are arranged at intervals along the circumferential direction,

and the distance d2 between the shallow cavity bearing segment 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.

In some embodiments, a plurality of air inlet through holes are formed in an end surface of a second side, opposite to the first side, of the second annular sheet body in the axial direction, and are respectively opposite to and communicated with the grooves, a second annular air groove is formed in the end surface of the second side, in the axial direction, of the second annular sheet body, and the air inlet through holes are all communicated with the second annular air groove.

In some embodiments, the bottom of the groove is wedge-shaped, the depth of the groove is configured to be from deep to shallow in the direction of rotation of a rotor supported by the gas bearing assembly, and the air inlet through-hole faces a deeper portion within the groove.

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

In some embodiments, the thrust disk has a plurality of portions divided in the radial direction and corresponding to the at least one hydrostatic bearing segment and the at least one shallow-cavity bearing segment, respectively, and the portion of the thrust disk corresponding to the at least one hydrostatic bearing segment is recessed away from the bearing plate relative to the portion of the thrust disk corresponding to the at least one shallow-cavity bearing segment.

In some embodiments, the at least one hydrostatic bearing segment comprises a plurality of hydrostatic bearing segments and the spacing d1 of the plurality of hydrostatic bearing segments and the thrust disk are the same, and/or the at least one shallow cavity bearing segment comprises a plurality of shallow cavity bearing segments and the spacing d2 of the plurality of shallow cavity bearing segments and the thrust disk are the same.

In one aspect of the present disclosure, there is provided a compressor comprising the aforementioned gas bearing assembly.

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

Therefore, according to the embodiment of the disclosure, by arranging at least one static pressure bearing section and at least one shallow cavity bearing section on the bearing plate in the radial direction and setting the distance between the static pressure bearing section and the thrust disk to be larger than the distance between the shallow cavity bearing section and the thrust disk, the gas bearing assembly can provide good support for a rotor with a larger rotating speed range, and the service life and the working stability are improved.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the disclosure and together with the description, serve to explain the principles of the disclosure.

The present disclosure may be more clearly understood from the following detailed description, taken with reference to the accompanying drawings, in which:

FIG. 1 is a schematic structural view of some embodiments of a gas bearing assembly according to the present disclosure;

FIG. 2 is a schematic longitudinal cross-sectional view along an axial direction of some embodiments of a gas bearing assembly according to the present disclosure;

FIG. 3 is an enlarged schematic view of ellipse A of FIG. 2;

FIG. 4 is a schematic view of a bearing plate adjacent a side of a thrust plate in accordance with some embodiments of the gas bearing assembly of the present disclosure;

FIG. 5 is a schematic view of a bearing plate side facing away from a thrust plate in accordance with some embodiments of the gas bearing assembly of the present disclosure;

fig. 6 is an enlarged schematic view of the ellipse B in fig. 5.

It should be understood that the dimensions of the various parts shown in the figures are not drawn to scale. Further, the same or similar reference numerals denote the same or similar components.

Detailed Description

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 is in no way intended to limit the disclosure, its application, or uses. The present disclosure may be embodied in many different forms and is not limited to the embodiments described herein. These embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that: the relative arrangement of parts and steps, the composition of materials, numerical expressions and numerical values set forth in these embodiments are to be construed as merely illustrative, and not as limitative, unless specifically stated otherwise.

The use of "first," "second," and similar terms in this disclosure is not intended to indicate any order, quantity, or importance, but rather are used to distinguish one element from another. The word "comprising" or "comprises", and the like, means that the element preceding the word covers the element listed after the word, and does not exclude the possibility that other elements are also covered. "upper", "lower", "left", "right", and the like are used merely to indicate relative positional relationships, and when the absolute position of the object being described is changed, the relative positional relationships may also be changed accordingly.

In the present disclosure, when a particular device is described as being located between a first device and a second device, intervening devices may or may not be present between the particular device and the first device or the second device. When a particular device is described as being coupled to other devices, that particular device may be directly coupled to the other devices without intervening devices or may be directly coupled to the other devices with intervening devices.

All terms (including technical or scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this disclosure belongs unless specifically defined otherwise. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the relevant art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.

Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate.

FIG. 1 is a schematic structural view of some embodiments of a gas bearing assembly according to the present disclosure. Referring to fig. 1, in some embodiments, a gas bearing assembly includes: bearing plate 10 and thrust plate 20. The bearing sheet 10 comprises at least one static pressure bearing section 12 and at least one shallow cavity bearing section 13 which are arranged along the radial direction, and the at least one static pressure bearing section 12 and the at least one shallow cavity bearing section 13 are positioned on the end surface of one side of the bearing sheet 10 along the axial direction. A thrust disk 20 is located axially on a side of the bearing sheet 10 adjacent to the at least one hydrostatic bearing segment 12 and the at least one shallow bore bearing segment 13. The distance d1 between the at least one hydrostatic bearing segment 12 and the thrust disk 20 is greater than the distance d2 between the at least one shallow cavity bearing segment 13 and the thrust disk 20.

In the embodiment, at least one static pressure bearing section and at least one shallow cavity bearing section are arranged on the bearing sheet along the radial direction, the static pressure bearing section can realize the supporting effect of the static pressure gas bearing on the rotor, and the shallow cavity bearing section can at least realize the supporting effect of the dynamic pressure gas bearing on the rotor, so that the gas bearing assembly has the advantages of larger bearing capacity and higher stability of the static pressure gas bearing and the dynamic pressure gas bearing.

As mentioned above, for the air-suspension centrifugal compressor, because the rotor speed is high and the pressure ratio is large, when the rotor is supported by the dynamic pressure gas bearing, the dynamic pressure gas bearing is insufficient in the aspects of bearing capacity and takeoff speed, in this embodiment, the distance between the static pressure bearing section and the thrust disk is set to be larger than the distance between the shallow cavity bearing section and the thrust disk, so that the static pressure bearing section can play a main role in the start-stop stage or the low-speed stage of the rotor, so that the rotor can float without reaching the high takeoff speed, and the difficulty of the program control of the frequency converter can be reduced. Accordingly, the problem that the service life is reduced due to the friction between the rotor and the bearing in the start-stop or low-speed stage is avoided or reduced.

In addition, when the rotor is supported by the static pressure gas bearing, the static pressure gas bearing is easy to generate air hammer due to large air supply pressure difference in a high rotating speed state of the rotor, and further the running instability of the rotor is caused. In the embodiment, the distance between the static pressure bearing section and the thrust disc is set to be larger than the distance between the shallow cavity bearing section and the thrust disc, so that the shallow cavity bearing section can play a main role when the rotor is in a high rotating speed state, a good dynamic pressure effect is realized, the requirement on the air supply pressure difference of the static pressure bearing section is reduced, the load and the power consumption of an external air supply system are further reduced, the vibration of an air hammer is reduced, and the rotor runs more stably.

In addition, at least one hydrostatic bearing segment 12 and at least one shallow cavity bearing segment 13 of the bearing sheet 10 are radially arranged, i.e. the hydrostatic bearing segment 12 and the shallow cavity bearing segment 13 correspond to different radial positions, respectively. In some embodiments, the static pressure bearing section 12 and the shallow cavity bearing section 13 do not have an overlapping range in the radial direction, and compared with the arrangement mode that both the static pressure bearing section and the shallow cavity bearing section are arranged in the annular ring area at the same radial position, the embodiment is easier to control the reasonable distance between each of the static pressure bearing section and the shallow cavity bearing section and the thrust disk so as to obtain better bearing performance.

In fig. 1, the thrust disk 20 may have a through hole 21 in the center for connection with the rotor. The bearing sheet 10 may also have a through hole 11 in the center for the rotor to pass through. Accordingly, each of the hydrostatic bearing segments 12 and the shallow cavity bearing segments 13 is annular.

Referring to fig. 1, in some embodiments, the at least one hydrostatic bearing segment 12 includes at least two hydrostatic bearing segments 12, a portion of the at least two hydrostatic bearing segments 12 being located radially on one side of the at least one shallow cavity bearing segment 13, another portion of the at least two hydrostatic bearing segments 12 being located radially on another side of the at least one shallow cavity bearing segment 13. By respectively arranging static pressure bearing sections at the two radial sides of the shallow cavity bearing section 13, a more balanced static pressure supporting effect on the rotor can be realized in the radial direction.

It should be noted that two radially adjacent hydrostatic bearing segments may also be considered as one radially wider hydrostatic bearing segment, and two radially adjacent shallow bearing segments may also be considered as one radially wider shallow bearing segment. Thus, the arrangement shown in FIG. 1 can be considered to be a gas bearing assembly having a combination of hydrostatic-shallow-hydrostatic pressure. In other embodiments, the gas bearing assembly may also employ hydrostatic-shallow cavity or combination of shallow cavity-hydrostatic, or combination of shallow cavity-hydrostatic-shallow cavity, etc. The gas bearing assembly adopting the static pressure-shallow cavity-static pressure combined mode can provide reliable supporting effect for the rotor under the starting or low-speed working condition of the rotor so as to support the lower takeoff rotating speed of the rotor.

In fig. 1, the at least two hydrostatic bearing segments 12 comprise two hydrostatic bearing segments 12, and the at least one shallow bearing segment 13 comprises one shallow bearing segment 13, located between the two hydrostatic bearing segments 12. Through setting up reasonable static pressure bearing section 12 and the quantity proportion of shallow chamber bearing section 13, can save material, reduce the subassembly size, satisfy the support demand of various rotors under different rotational speeds.

Referring to fig. 1, in some embodiments, the distance d1 between at least one hydrostatic bearing segment 12 and the thrust disk 20 is 0.03-0.07 mm, and more preferably 0.05 mm. The distance d2 between the 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 the proper distances d1 and d2, the acting sequence of the static pressure bearing section and the shallow cavity bearing section at different rotating speeds of the rotor can be realized, and the respective rotor supporting performance of the static pressure bearing section and the shallow cavity bearing section can be further improved.

In some embodiments, the at least one hydrostatic bearing segment 12 includes a plurality of hydrostatic bearing segments 12, and the spacing d1 between the plurality of hydrostatic bearing segments 12 and the thrust disk 20 is the same to maintain a uniform hydrostatic pressure effect achieved by each hydrostatic bearing segment 12. In some embodiments, the at least one shallow cavity bearing segment 13 includes a plurality of shallow cavity bearing segments 13, and the distance d2 between the shallow cavity bearing segments 13 and the thrust disk 20 is the same, so as to keep the mixing effect of the dynamic and static pressure of each shallow cavity bearing segment 13 consistent.

Fig. 2 is a schematic longitudinal sectional view along an axial direction of some embodiments of a gas bearing assembly according to the present disclosure. Fig. 3 is an enlarged schematic view of ellipse a in fig. 2. FIG. 4 is a schematic view of a bearing plate adjacent a side of a thrust plate in some embodiments of a gas bearing assembly according to the present disclosure. FIG. 5 is a schematic view of a side of a bearing plate distal from a thrust plate in some embodiments of a gas bearing assembly according to the present disclosure. Fig. 6 is an enlarged schematic view of the ellipse B in fig. 5.

Referring to fig. 2-6, in some embodiments, the hydrostatic bearing segment 12 includes: a first annular sheet 12a and a plurality of porous material blocks 12 b. The first annular sheet body 12a has a plurality of air supply through holes 12c that axially penetrate the first annular sheet body 12 a. The plurality of porous material blocks 12b are circumferentially arranged on the end surface of the first annular sheet body 12a on the first side in the axial direction at intervals, and are respectively opposite to the plurality of air supply through holes 12 c. The distance d1 between the hydrostatic bearing segment 12 and the thrust disk 20 is the distance between the porous material block 12b and the thrust disk 20.

Considering that the load of the gas bearing is small in the starting and stopping stage or the low rotating speed stage of the rotor, the use requirement can be met by adopting a plurality of porous material blocks 12b which are locally and discretely arranged, so that the using amount of the porous material is reduced, and the cost is reduced. In some embodiments, the porous material is a graphite material. The first annular sheet 12a may be made of metal or alloy, such as aluminum alloy, which is easy to machine and has high strength.

When a certain porous material block 12b is damaged, the damaged porous material block 12b may be replaced. In other embodiments, the hydrostatic bearing segment 12 may also include a ring of porous material in the shape of a closed ring to achieve better hydrostatic bearing effect.

Referring to fig. 3 and 4, in some embodiments, the first annular sheet 12a has a plurality of mounting grooves along an end surface of the first side in the axial direction, and the plurality of porous material pieces 12b are respectively embedded in the plurality of mounting grooves. The plurality of air supply through holes 12c are respectively communicated with the groove bottoms 12e of the plurality of mounting grooves. In fig. 5 and 6, an end surface of a second side of the first annular sheet body 12a opposite to the first side in the axial direction 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 12 d.

The porous material blocks are embedded and fixed in the mounting groove, so that the structure of the static pressure bearing section is more stable and reliable, and the first annular air groove at the back side and the air supply through hole for communicating the first annular air groove and the mounting groove can enable high-pressure air supply input by an external system to be more uniformly applied to each porous material block and further to be more uniformly applied to the thrust disc fixed to the rotor. The air can be well supplied to each porous material block under the condition of not increasing the complexity of an external air supply system.

Referring to fig. 1 and 4, in some embodiments, at least one hydrostatic bearing segment 12 includes a first hydrostatic bearing segment 121 and a second hydrostatic bearing segment 122, the first hydrostatic bearing segment 121 including a plurality of porous material blocks 12b angularly offset circumferentially from the second hydrostatic bearing segment 12 including a plurality of porous material blocks 12 b. This circumferentially staggered arrangement allows for more balanced loading of the gas bearing assembly, thereby achieving greater load bearing capacity.

In fig. 4, the hydrostatic bearing section 12 located at the inner ring (i.e., the first hydrostatic bearing section 121) has four porous material blocks 12b located at positions of 45 °, 135 °, 225 °, and 315 ° based on the axial center of the gas bearing assembly, respectively, while the hydrostatic bearing section 12 located at the outer ring (i.e., the first hydrostatic bearing section 122) also has four porous material blocks 12b located at positions of 0 °, 90 °, 180 °, and 270 ° based on the axial center of the gas bearing assembly, respectively, so as to realize the staggered arrangement of the porous material blocks of different rings in the circumferential angle.

Referring to fig. 4, in some embodiments, the shallow cavity bearing segment 13 includes: a second annular blade 13a having a plurality of grooves 13 b. The grooves 13b are located on the end face of the second annular sheet body 13a on the first side in the axial direction and are arranged at intervals in the circumferential direction. The distance d2 between the shallow-cavity bearing segment 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.

The bottom of each groove 13b in the shallow cavity bearing section 13 may be provided with a wedge shape, and the depth of the groove 13b may be configured to be deep to shallow in the direction of rotation of the rotor supported by the gas bearing assembly. Thus, when the rotor rotates at a high rotating speed, the grooves 13b of the shallow cavity bearing section 13 can gradually generate a wedge-shaped air film along the rotating direction of the rotor, and a good dynamic pressure effect is realized.

The plurality of grooves 13b in the shallow cavity bearing section 13 may be equiangularly disposed in the circumferential direction to provide more uniform loading of the gas bearing assembly. In fig. 4, the groove may have a fan-shaped profile along the axial direction of the gas bearing assembly, that is, two edges along the radial direction are arcs, the center of the circle is located at the axial center of the gas bearing assembly, and the extension lines of the two edges along the circumferential direction both pass through the axial center of the gas bearing assembly. In some embodiments, the orthographic projection of the plurality of grooves 13b in the shallow cavity bearing segment 13 on a plane perpendicular to the axis of the gas bearing assembly is half of the orthographic projection of the shallow cavity bearing segment 13 as a whole on that plane.

Referring to fig. 4-6, in some embodiments, a second annular blade 13a has a plurality of air inlet through holes 13c on an end surface of a second side axially opposite to the first side, and the air inlet through holes are respectively opposite to and communicated with the grooves 13 b. Through the structure, the bearing section with the shallow cavity can generate a secondary throttling effect. When the air feed enters the air inlet through hole 13c with a small aperture (for example, 0.6-1 mm) from the second side of the second annular sheet body 13a, the air inlet through hole 13c can generate a first throttling effect on the air feed, and then generates a large resistance to the air feed when passing through a shallow groove (for example, the depth is 0.01-0.03 mm, preferably 0.02mm), so that a second throttling effect is generated, and a strong static pressure supporting effect is formed. Thus, the hybrid action of the hybrid bearing is realized by the shallow cavity bearing section.

When the air inlet through hole is provided, the air inlet through hole 13c may be made to face a deeper portion in the groove 13 b. Thus, when the supplied air enters the recess through the air intake through-hole 13c, it can flow from the deeper recess portion to the shallower recess portion, thereby generating a pressing effect on the thrust disk to float the thrust disk.

The end face of the second annular sheet body 13a along the second side in the axial direction is provided with a second annular air groove 13d, and the plurality of air inlet through holes 13c are communicated with the second annular air groove 13 d. Each of the air inlet through holes 13c may communicate with an air supply source inside or outside the compressor through the second annular air groove 13d, thereby maintaining the inlet pressure of each of the air inlet through holes 13c to be uniform. The second annular gas groove 13d is able to supply gas to the respective grooves well without increasing the complexity of the external gas supply system.

Referring to fig. 2 and 3, in some embodiments, the first annular lobe of the hydrostatic bearing segment and the second annular lobe of the shallow cavity bearing segment may be integrally formed for better strength, machining accuracy and a more compact structure. In other embodiments, the first annular sheet body of the hydrostatic bearing segment and the second annular sheet body of the shallow cavity bearing segment can be prepared separately and then connected in the radial direction through a connecting piece, wherein the connecting piece can be a bolt, a clamping structure or an adhesive.

In fig. 2 and 3, the thrust disk 20 has a plurality of portions divided in the radial direction and corresponding to the at least one hydrostatic bearing segment 12 and the at least one shallow-cavity bearing segment 13, respectively, and the portion of the thrust disk 20 corresponding to the at least one hydrostatic bearing segment 12 is recessed toward the side away from the bearing plate 10 with respect to the portion of the thrust disk 20 corresponding to the at least one shallow-cavity bearing segment 13. In other embodiments, the surface of the thrust plate adjacent to the side of the bearing plate may be a plane, and the hydrostatic bearing segment and the shallow bearing segment may be configured to have different thicknesses, so long as the distance relationship between the hydrostatic bearing segment and the shallow bearing segment and the thrust plate is satisfied.

The gas bearing assembly described above is suitable for use in a variety of devices that require the use of a thrust bearing to support the rotor, such as a compressor. Accordingly, embodiments of the present disclosure provide a compressor including embodiments of any of the foregoing gas bearing assemblies. The compressor may be an air-suspension centrifugal compressor, or other compressor.

The embodiments of the compressor disclosed by the disclosure can be applied to various devices which need to perform working medium compression, such as refrigerators, air conditioners and the like. Accordingly, embodiments of the present disclosure provide an air conditioner including embodiments of any one of the aforementioned compressors. The air conditioner may be a centrifugal chiller for a central air conditioner.

Thus far, various embodiments of the present disclosure have been described in detail. Some details that are well known in the art have not been described in order to avoid obscuring the concepts of the present disclosure. It will be fully apparent to those skilled in the art from the foregoing description how to practice the presently disclosed embodiments.

Although some specific embodiments of the present disclosure have been described in detail by way of example, it should be understood by those skilled in the art that the foregoing examples are for purposes of illustration only and are not intended to limit the scope of the present disclosure. It will be understood by those skilled in the art that various changes may be made in the above embodiments or equivalents may be substituted for elements thereof 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, comprising:

the bearing sheet (10) comprises at least one static pressure bearing section (12) and at least one shallow cavity bearing section (13) which are arranged along the radial direction, and the at least one static pressure bearing section (12) and the at least one shallow cavity bearing section (13) are positioned on the end face of one side of the bearing sheet (10) along the axial direction;

a thrust disk (20) located axially on a side of the bearing sheet (10) adjacent to the at least one hydrostatic bearing segment (12) and the at least one shallow-bore bearing segment (13),

wherein 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).

2. A gas bearing assembly according to claim 1, characterized in that the at least one hydrostatic bearing segment (12) comprises at least two hydrostatic bearing segments (12), a part of the at least two hydrostatic bearing segments (12) being located radially on one side of the at least one shallow cavity bearing segment (13) and another part of the at least two hydrostatic bearing segments (12) being located radially on the other side of the at least one shallow cavity bearing segment (13).

3. A gas bearing assembly according to claim 2, characterised in that the at least two hydrostatic bearing segments (12) comprise two hydrostatic bearing segments (12) and the at least one shallow cavity bearing segment (13) comprises one shallow cavity bearing segment (13) located between the two hydrostatic bearing segments (12).

4. The gas bearing assembly of claim 1, wherein the at least one hydrostatic bearing segment (12) is spaced from the thrust disk (20) by a distance d1 of 0.03 to 0.07mm, and the at least one shallow cavity bearing segment (13) is spaced from the thrust disk (20) by a distance d2 of 0.005 to 0.015 mm.

5. A gas bearing assembly according to claim 4, characterised in that the spacing d1 of the at least one hydrostatic bearing segment (12) from the thrust disk (20) is 0.05mm and the spacing d2 of the at least one shallow bore bearing segment (13) from the thrust disk (20) is 0.01 mm.

6. A gas bearing assembly according to claim 1, characterized in that the hydrostatic bearing segment (12) comprises:

a first annular sheet (12a) having a plurality of air supply through-holes (12c) that axially penetrate the first annular sheet (12 a);

a plurality of porous material blocks (12b) which are arranged on the end surface of the first annular sheet body (12a) along the axial direction at intervals along the circumferential direction and are respectively opposite to the plurality of air supply through holes (12 c);

wherein the distance d1 between the static pressure 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 first annular sheet body (12a) has a plurality of mounting grooves in an end surface of a first side in the axial direction, the plurality of porous material pieces (12b) are respectively embedded in the plurality of mounting grooves, the plurality of gas supply through holes (12c) are respectively communicated with groove bottoms (12e) of the plurality of mounting grooves, the first annular sheet body (12a) has a first annular gas groove (12d) in an end surface of a second side opposite to the first side in the axial direction, and the plurality of gas supply through holes (12c) are all communicated with the first annular gas groove (12 d).

8. The gas bearing assembly according to claim 6, wherein the at least one hydrostatic bearing segment (12) comprises a first hydrostatic bearing segment (121) and a second hydrostatic bearing segment (122), the first hydrostatic bearing segment (121) comprising a plurality of porous material blocks (12b) being angularly circumferentially offset from the second hydrostatic bearing segment (122) comprising a plurality of porous material blocks (12 b).

9. A gas bearing assembly according to claim 1, characterized in that the shallow cavity bearing segment (13) comprises:

a second annular sheet body (13a) provided with a plurality of grooves (13b), wherein the grooves (13b) are positioned on the end surface of the first side of the second annular sheet body (13a) along the axial direction and are arranged at intervals along the circumferential direction,

wherein 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. A gas bearing assembly according to claim 9, characterized in that the second annular blade (13a) has, on the end face of a second side axially opposite to said first side, a plurality of gas inlet through holes (13c) respectively aligned and communicating with said plurality of grooves (13b), said second annular blade (13a) has, on the end face of the second side axially, a second annular gas groove (13d), said plurality of gas inlet through holes (13c) each communicating with said second annular gas groove (13 d).

11. A gas bearing assembly according to claim 10, characterized in that the bottom of the groove (13b) is wedge-shaped, the depth of the groove (13b) being configured to be deep to shallow in the direction of rotation of a rotor supported by the gas bearing assembly, the gas inlet through hole (13c) facing a deeper portion in the groove (13 b).

12. A gas bearing assembly according to claim 10, characterised in that the depth of the grooves (13b) is 0.01-0.03 mm and the aperture of the air inlet through holes (13c) is 0.6-1 mm.

13. A gas bearing assembly according to claim 1, characterized in that the thrust disk (20) has a plurality of portions divided in a radial direction and corresponding to at least one hydrostatic bearing segment (12) and at least one shallow-cavity bearing segment (13), respectively, the portion of the thrust disk (20) corresponding to at least one hydrostatic bearing segment (12) being recessed to the side remote from the bearing plate (10) with respect to the portion of the thrust disk (20) corresponding to at least one shallow-cavity bearing segment (13).

14. The gas bearing assembly of claim 1, wherein the at least one hydrostatic bearing segment (12) comprises a plurality of hydrostatic bearing segments (12) and the spacing d1 of the plurality of hydrostatic bearing segments (12) from the thrust disk (20) is the same, and/or wherein the at least one shallow cavity bearing segment (13) comprises a plurality of shallow cavity bearing segments (13) and the spacing d2 of the plurality of shallow cavity bearing segments (13) from the thrust disk (20) is the same.

15. A compressor, comprising:

a gas bearing assembly according to any of claims 1 to 14.

16. An air conditioner, comprising:

the compressor of claim 15.