Compressor, refrigerant circulation system, and refrigeration device

Abstract

The present disclosure provides a compressor, a refrigerant circulation system and a refrigeration device. The compressor comprises: a housing having a containing space, comprising a cylinder, a first end of the cylinder comprising an end wall, the end wall comprising an end wall bearing chamber; a compressor rotor rotatably arranged in the containing space, comprising a thrust disc; and a gas bearing assembly for supporting the compressor rotor on the housing, the gas bearing assembly comprising a thrust bearing assembly and a first radial bearing, the thrust bearing assembly cooperating with the thrust disc, a first end of the compressor rotor being carried on the first radial bearing, the thrust bearing assembly abutting an outer end surface of the end wall, the first radial bearing being located in the end wall bearing chamber and an end surface of a first end of the first radial bearing abutting the outer end surface of the thrust bearing assembly. The compressor of the present disclosure has a compact structure, which is conducive to minimizing the length of the compressor rotor, reducing bearing load, improving the stiffness of the compressor rotor, improving the critical speed of the bending mode, and improving the stability of the bearing rotor system.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to the field of compression equipment and refrigeration equipment, in particular to a compressor, a refrigerant circulation system and a refrigeration equipment. BACKGROUND

[0002] The static pressure gas bearing is a new type of bearing which uses external pressure to form a gas film for gas lubrication. The static pressure gas bearing has the advantages of ultra-high precision, ultra-low friction, ultra-low vibration, ultra-low noise, long service life, no pollution, etc., and is suitable for high-speed and high-precision occasions, and has broad application prospects in centrifugal compressors, especially small-sized centrifugal compressors. SUMMARY

[0003] The present disclosure aims to provide a compressor, a refrigerant circulation system and a refrigeration equipment.

[0004] The first aspect of the present disclosure provides a compressor, comprising:

[0005] A housing comprising a cylinder, a first end of the cylinder comprising an end wall, the end wall comprising an end wall bearing chamber;

[0006] A compressor rotor rotatably arranged in the accommodation space, comprising a thrust disc; and

[0007] A gas bearing assembly for supporting the compressor rotor on the housing, the gas bearing assembly comprising a thrust bearing assembly cooperating with the thrust disc, a first end of the compressor rotor being supported on a first radial bearing, the thrust bearing assembly being attached to an outer side surface of the end wall, the first radial bearing being located in the end wall bearing chamber, and an end surface of a first end of the first radial bearing being attached to an outer side surface of the thrust bearing assembly.

[0008] In some embodiments,

[0009] The compressor further comprises an end wall snap ring;

[0010] The end wall further comprises an end wall ring groove, the end wall snap ring cooperating with the end wall ring groove, and the first radial bearing being axially limited between the thrust bearing assembly and the end wall snap ring.

[0011] In some embodiments, the end wall is provided with a radial bearing gas supply channel for supplying working gas to the first radial bearing and a thrust bearing gas supply channel for supplying working gas to the thrust bearing assembly.

[0012] In some embodiments, the radial bearing gas supply channel is in communication or isolation with the thrust bearing gas supply channel.

[0013] In some embodiments,

[0014] The end wall comprises a diffuser mounting port;

[0015] The compressor comprises a diffuser, the diffuser comprises a diffuser positioning stop cooperating with the diffuser mounting port, the diffuser is fixedly connected with the end wall, and an outer side end surface of the thrust bearing assembly is attached to an end surface of the diffuser.

[0016] In some embodiments, an inner hole of the diffuser cooperates with the first end of the compressor rotor, and a first shaft seal structure is arranged on a hole wall of the inner hole of the diffuser.

[0017] In some embodiments,

[0018] The gas bearing assembly further comprises a second radial bearing, and a second end of the compressor rotor is carried on the second radial bearing;

[0019] The compressor further comprises a bearing carrying component, the bearing carrying component comprises a diffuser part and a bearing seat part arranged integrally, the diffuser part is fixedly connected with the second end of the cylinder body, and the bearing seat part comprises a carrying component bearing chamber, and the second radial bearing is located in the carrying component bearing chamber.

[0020] In some embodiments, the end wall bearing chamber and the carrying component bearing chamber are formed by post-boring after the cylinder body and the bearing carrying component are fixedly connected.

[0021] In some embodiments,

[0022] The diffuser part comprises a shaft seal mounting hole;

[0023] The compressor further comprises a shaft seal component, the shaft seal component is fixed in the shaft seal mounting hole and sleeved on the second end of the compressor rotor, the shaft seal component comprises a second shaft seal structure cooperating with the second end of the compressor rotor, and a first end of the shaft seal component cooperates with an end surface of the second radial bearing.

[0024] In some embodiments, the bearing carrying component comprises a carrying component ring groove, the compressor comprises a carrying component snap ring, the carrying component snap ring cooperates with the carrying component ring groove, and the second radial bearing is axially limited between the shaft seal component and the carrying component snap ring.

[0025] In some embodiments,

[0026] The bearing carrying component comprises a fluid inlet channel communicating with the carrying component bearing chamber and a fluid outlet channel communicating with the bearing mounting hole;

[0027] The shaft seal component includes a shaft seal fluid passage that communicates between a gap between the bearing chamber of the load bearing component and the compressor rotor and the fluid outflow passage.

[0028] In some embodiments, the thrust bearing assembly includes:

[0029] a first thrust bearing that cooperates with the first end of the thrust disc;

[0030] a second thrust bearing that cooperates with the second end of the thrust disc; and

[0031] a positioning ring located radially outward of the thrust disc, two ends of the positioning ring abut the first thrust bearing and the second thrust bearing respectively, and the positioning ring is provided with a positioning ring fluid passage that communicates between a radially inner side and a radially outer side of the positioning ring.

[0032] In some embodiments, the compressor rotor includes a rotating shaft, the rotating shaft includes a permanent magnet and a first shaft segment and a second shaft segment coaxially arranged at axial two ends of the permanent magnet.

[0033] In some embodiments, the thrust bearing assembly includes a first thrust bearing that cooperates with the first end of the thrust disc and a second thrust bearing that cooperates with the second end of the thrust disc; the gas bearing assembly further includes a second radial bearing, the second end of the compressor rotor is carried on the second radial bearing; the first radial bearing, the second radial bearing, the first thrust bearing and the second thrust bearing are static pressure gas bearings.

[0034] The second aspect of the present disclosure provides a refrigerant circulation system, including the compressor of the first aspect of the present disclosure.

[0035] The third aspect of the present disclosure provides a refrigeration device, including the compressor of the first aspect of the present disclosure.

[0036] Based on the compressor provided by the present disclosure, the end wall of the cylinder body is integrated with a bearing seat for mounting the first radial bearing, and the thrust bearing assembly is abutted on the outer end face of the end wall, so that the end wall of the cylinder body is also integrated with the thrust bearing mounting function, and the thrust bearing assembly can also simultaneously axially position the first radial bearing, thereby facilitating compact structure of the compressor, facilitating maximum reduction of the length of the compressor rotor, reduction of bearing load, improvement of the rigidity of the compressor rotor, improvement of the bending mode critical speed, and improvement of the stability of the bearing rotor system.

[0037] Other features of the present disclosure and its advantages will become apparent from the following detailed description of exemplary embodiments thereof, with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0038] The accompanying drawings, which are included to provide a further understanding of the disclosure and constitute a part of the disclosure, illustrate embodiments of the disclosure and together with the description explain what the disclosure is. In the drawings:

[0039] Figure 1 A perspective view of a portion of the compressor of the embodiment shown.

[0040] Figure 2 A perspective view of a portion of the compressor of the embodiment shown. Figure 1

[0041] Figure 3 A perspective view of another portion of the compressor of the embodiment shown. Figure 1

[0042] Figure 4 A perspective view of another portion of the compressor of the embodiment shown. Figure 1 Figure 4 Figure 1

[0043] Figure 5 A perspective view of a portion of the compressor of the embodiment shown. Figure 4

[0044] Figure 6 A perspective view of the diffuser of the compressor of the embodiment shown. Figure 1

[0045] Figure 7 A perspective view of the diffuser of the embodiment shown. Figure 6

[0046] Figure 8 A perspective view of the positioning ring of the compressor of the embodiment shown. Figure 1

[0047] Figure 9 A perspective view of the shaft seal member of the compressor of the embodiment shown. Figure 1

[0048] Figure 10 A perspective view of the shaft seal member of the embodiment shown. Figure 9

[0049] Figure 11 A perspective view of the shaft seal member of the embodiment shown. Figure 9

[0050] Figure 12 A perspective view of the bearing support member of the compressor of the embodiment shown. Figure 1

[0051] ​​​​​​​​​​​​​Figure 13 for Figure 12 The end face structure diagram of the bearing support component is shown.

[0052] Figure 14 for Figure 1 A schematic diagram of the partial structure of the rotating shaft of the compressor of the illustrated embodiment.

[0053] Figure 15 for Figure 14 A schematic cross-sectional view of an alternative embodiment of a rotating shaft is shown.

[0054] Figure 16 for Figure 14 FIG2 is a schematic cross-sectional view of another alternative embodiment of a rotating shaft.

[0055] Figure 17 Schematic diagram of the cross-sectional structure of a compressor according to an embodiment of the present disclosure.

[0056] Figure 18 for Figure 17 The cross-sectional structure diagram of the rotating shaft of the compressor of the embodiment shown is a schematic diagram, in which the screw hole at the end of the shaft is not shown.

[0057] Figure 19 Schematic diagram of the cross-sectional structure of a compressor according to an embodiment of the present disclosure.

[0058] Figure 20 This is a schematic diagram of a partial cross-sectional structure of a compressor according to an embodiment of the present disclosure.

[0059] Figure 21 for Figure 20 A schematic cross-sectional view of the radial bearing of the compressor of the illustrated embodiment.

[0060] Figure 22 for Figure 21 The main structural diagram of the radial bearing is shown.

[0061] Figure 23 This is a schematic diagram of a partial cross-sectional structure of a compressor according to an embodiment of the present disclosure.

[0062] Figure 24 for Figure 23 A schematic cross-sectional view of the radial bearing of the compressor of the illustrated embodiment.

[0063] Figure 25 for Figure 24 The main structural diagram of the radial bearing is shown.

[0064] Figure 26 for Figure 23 A schematic diagram of the end surface structure of the bearing support component of the compressor in the illustrated embodiment.

[0065] Figure 27 FIG. 1 is a schematic view of a refrigerant cycle system according to an embodiment of the present disclosure. Figure 26 FIG. 2 is a cross-sectional view of a bearing support member shown in FIG. 1.

[0066] Figure 28 FIG. 3 is a cross-sectional view of a compressor according to an embodiment of the present disclosure.

[0067] Figure 29 FIG. 4 is a partial cross-sectional view of a bearing support member shown in FIG. 3. Figure 28

[0068] Figure 30 FIG. 5 is a partial cross-sectional view of a compressor according to an embodiment of the present disclosure.

[0069] Figure 31 FIG. 6 is a schematic view of a refrigerant cycle system according to an embodiment of the present disclosure.

[0070] Figure 32 FIG. 7 is a schematic view of a refrigerant cycle system according to an embodiment of the present disclosure.

[0071] Figure 33 FIG. 8 is a schematic view of a refrigerant cycle system according to an embodiment of the present disclosure.

[0072] Figure 34 FIG. 9 is a schematic view of a refrigerant cycle system according to an embodiment of the present disclosure. DETAILED DESCRIPTION

[0073] The technical solutions in the embodiments of the present disclosure will be described clearly and completely below with reference to the drawings in the embodiments of the present disclosure. Obviously, the described embodiments are only some of the embodiments of the present disclosure, rather than all the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and not intended to limit the present disclosure and its applications or uses in any way. Based on the embodiments in the present disclosure, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of the present disclosure.

[0074] The relative arrangement of components and steps, numerical expressions, and numerical values set forth in the embodiments are not intended to limit the scope of the present disclosure unless otherwise specifically stated. It should also be understood that the dimensions of the various parts shown in the drawings are not drawn to scale for the sake of convenience. Techniques, methods, and equipment known to those of ordinary skill in the relevant art can not be discussed in detail, but should be considered as part of the authorized description where appropriate. In all examples shown and discussed herein, any specific values should be interpreted as merely exemplary, and not as limiting. Thus, other examples of the exemplary embodiments can have different values. It should be noted that like reference numerals and letters represent like items throughout the drawings, and thus, once an item is defined in one drawing, it need not be discussed further in subsequent drawings.​

[0075] In the description of the present disclosure, it should be understood that the use of the words "first", "second" and the like words to define parts is only for the convenience of distinguishing the corresponding parts, and the above words have no special meaning unless otherwise stated, and therefore cannot be understood as a limitation on the protection scope of the present disclosure.

[0076] In the description of the present disclosure, it should be understood that the orientation words such as "front, back, up, down, left, right", "horizontal, vertical, perpendicular, horizontal" and "top, bottom" and the like indicated orientation or position relationship is generally based on the orientation or position relationship shown in the drawings, only for the convenience of describing the present disclosure and simplifying the description, without the opposite statement, these orientation words do not indicate and imply that the indicated device or element must have a specific orientation or be constructed and operated in a specific orientation, therefore cannot be understood as a limitation on the protection scope of the present disclosure; the orientation words "inner, outer" refer to the inner and outer of the contour of each part itself.

[0077] As shown in Figure 1 , Figure 17 , Figure 19 and Figure 28 , the present disclosure provides a compressor, comprising a housing 10, a compressor rotor 20 and a gas bearing assembly.

[0078] The housing 10 has a containing space, comprising a cylinder 11, the first end of the cylinder 11 comprises an end wall 112, the end wall 112 comprises an end wall bearing chamber. The compressor rotor 20 is rotatably arranged in the containing space, comprising a thrust disc 24. The gas bearing assembly is used to support the compressor rotor 20 on the housing 10, the gas bearing assembly comprises a thrust bearing assembly 41 and a first radial bearing 42, the thrust bearing assembly 41 cooperates with the thrust disc 24, the first end of the compressor rotor 20 is carried on the first radial bearing 42, the thrust bearing assembly 41 is attached to the outer side surface of the end wall 112, the first radial bearing 42 is located in the end wall bearing chamber and the end surface of the first end of the first radial bearing 42 is attached to the outer side surface of the thrust bearing assembly 41.

[0079] The compressor of the embodiment of the present disclosure, the end wall 112 of the cylinder 11 integrates a bearing seat for mounting the first radial bearing 42, the thrust bearing assembly 41 is attached to the outer side surface of the end wall 112, so that the end wall 112 of the cylinder 11 also integrates the thrust bearing mounting function, the thrust bearing assembly 11 can also simultaneously axially limit the first radial bearing 42, which is beneficial to make the compressor compact, beneficial to minimize the length of the compressor rotor 20, reduce the bearing load, improve the stiffness of the compressor rotor 20, improve the bending mode critical speed, and improve the stability of the bearing rotor system.

[0080] In some embodiments, the compressor further comprises an end wall snap ring 82; the end wall 112 further comprises an end wall ring groove, the end wall snap ring 82 is matched with the end wall ring groove, and the first radial bearing 42 is axially limited between the thrust bearing assembly 41 and the end wall snap ring 82.

[0081] In some embodiments, the end wall 112 is provided with a radial bearing gas supply channel 171 for supplying working gas to the first radial bearing 42 and a thrust bearing gas supply channel 172 for supplying working gas to the thrust bearing assembly 41.

[0082] In some embodiments, the radial bearing gas supply channel 171 is in communication or isolation with the thrust bearing gas supply channel 172.

[0083] In some embodiments, the end wall 112 comprises a diffuser mounting port; the compressor comprises a diffuser 50, the diffuser 50 comprises a diffuser positioning stop matched with the diffuser mounting port, the diffuser 50 is fixedly connected with the end wall 112, and the outer side end surface of the thrust bearing assembly 41 away from the end wall 112 is attached to the end surface of the diffuser 50.

[0084] In some embodiments, the inner hole of the diffuser 50 is matched with the first end of the compressor rotor 20, and the first shaft seal structure 56 is arranged on the hole wall of the inner hole of the diffuser 50.

[0085] In some embodiments, the gas bearing assembly further comprises a second radial bearing 43, and the second end of the compressor rotor 20 is carried on the second radial bearing 43; the compressor further comprises a bearing carrying component 60, the bearing carrying component 60 comprises a diffuser part and a bearing seat part arranged integrally, the diffuser part is fixedly connected with the second end of the cylinder 11, the bearing seat part comprises a bearing carrying component bearing chamber 62, and the second radial bearing 43 is located in the bearing carrying component bearing chamber 62.

[0086] Placing two radial bearings on both ends of the compressor rotor 20 to bear radial force, placing the thrust bearing assembly 41 on one end to cooperate with the thrust disc to bear axial force, and designing the bearing seat for installing the second radial bearing and the two-stage diffuser as one part make the compressor simple in assembly and compact in structure.

[0087] In some embodiments, the end wall bearing chamber and the bearing carrying component bearing chamber 62 are formed by boring after the fixed connection of the cylinder 11 and the bearing carrying component 60.

[0088] Through boring, the coaxiality of the two radial bearings and the perpendicularity of the thrust bearing assembly 41 can be ensured with high precision, the assembly efficiency and assembly precision are improved, the bearing seat for installing the second radial bearing 43 and the two-stage diffuser are designed as one part, the machining reference is consistent, which is beneficial to reducing cumulative error, improving the coaxiality of the shaft seal, and preventing wear.

[0089] In some embodiments, the diffuser portion includes a shaft seal mounting hole 67; the compressor further includes a shaft seal component 70 fixed in the shaft seal mounting hole 67 and sleeved on the second end of the compressor rotor, the shaft seal component 70 includes a second shaft seal structure 711 matched with the second end of the compressor rotor 20, and a first end of the shaft seal component 70 is matched with an end surface of the second radial bearing 43.

[0090] In some embodiments, the bearing carrier component 60 includes a carrier component ring groove 66, and the compressor includes a carrier component snap ring 81 matched with the carrier component ring groove 66, and the second radial bearing 43 is axially limited between the shaft seal component 70 and the carrier component snap ring 81.

[0091] In some embodiments, the bearing carrier component 60 includes a fluid inlet passage 63 communicated with the bearing carrier chamber 62 and a fluid outlet passage 64 communicated with the shaft mounting hole 67; the shaft seal component 70 includes a shaft seal fluid passage communicated between the bearing carrier chamber 62 and a gap between the compressor rotor 20 and the fluid outlet passage 64.

[0092] In some embodiments, the compressor rotor includes a thrust disc 24, and the thrust bearing assembly includes: a first thrust bearing 411 matched with a first end of the thrust disc 24; a second thrust bearing 412 matched with a second end of the thrust disc 24; and a positioning ring 413 located radially outside the thrust disc 24, two end surfaces of the positioning ring 413 are respectively matched with the first thrust bearing 411 and the second thrust bearing 412, and the positioning ring 413 is provided with a positioning ring fluid passage communicated between a radially inner side and a radially outer side of the positioning ring 413.

[0093] By adjusting the thickness and precision of the positioning ring 413, the thrust bearing gap can be adjusted and ensured, and the stability of the bearing rotor system can be improved. The exhaust gas of the thrust bearing assembly and the first radial bearing 42 enters the motor accommodating cavity through the positioning ring fluid passage of the positioning ring 413, and the exhaust gas of the second radial bearing 43 enters the motor accommodating cavity through the shaft seal fluid passage and the fluid outlet passage 64 of the bearing carrier component 60, which can prevent the gas bearing exhaust gas from being blocked to cause the back pressure to rise, thereby preventing the change of the gas film pressure distribution caused by the rise of the back pressure, and affecting the stability of the bearing rotor system.

[0094] In some embodiments, the compressor rotor 20 includes a rotating shaft 21, and the rotating shaft 21 includes a permanent magnet 211 and a first shaft segment 212 and a second shaft segment 213 coaxially arranged at two axial ends of the permanent magnet 211. The rotating shaft 21 simultaneously serves as a motor rotor of a permanent magnet synchronous motor of the compressor. In the case that the motor load is unchanged, the structure of the compressor can be more compact, and the weight can be lighter.

[0095] In some embodiments, the thrust bearing assembly 41 includes a first thrust bearing 411 engaged with the first end of the thrust plate 24 and a second thrust bearing 412 engaged with the second end of the thrust plate 24. The gas bearing assembly also includes a second radial bearing 43, on which the second end of the compressor rotor 20 is supported. The first radial bearing, the second radial bearing, the first thrust bearing, and the second thrust bearing are hydrostatic gas bearings. Hydrostatic gas bearings offer advantages such as ultra-high precision, ultra-low friction, ultra-low vibration, ultra-low noise, long life, and zero pollution. Their use in compressors can result in low vibration, low noise, and low pollution.

[0096] The aforementioned compressor is, for example, a centrifugal compressor.

[0097] The above description illustrates some structures of some embodiments of the present disclosure. The following describes the compressor and its components according to the embodiments of the present disclosure in more detail, along with several other possible variations of the present disclosure and a refrigerant circulation system having the compressor according to the embodiments of the present disclosure.

[0098] It should be noted that the various specific technical features described in these embodiments of the present disclosure can be combined in any appropriate manner without contradiction. To avoid unnecessary repetition, the embodiments of the present disclosure will not further describe various possible combinations.

[0099] like Figure 6 、 Figure 7 , a schematic diagram of a diffuser 50 is provided for some embodiments.

[0100] The diffuser 50 includes a diffuser body and a diffuser air supply passage 51 . The diffuser air supply passage 51 is provided in the diffuser body and is used to supply air to the gas bearing.

[0101] In some embodiments, the diffuser air supply passage 51 includes an inlet passage, an outlet passage, and a connecting passage. The inlet passage is used to introduce gas. The outlet passage is used to provide the gas introduced by the inlet passage to the gas bearing. The connecting passage connects the inlet passage and the outlet passage.

[0102] In some embodiments, the diffuser body is provided with a diffuser inner hole for allowing a rotating shaft 21 to pass through. The rotating shaft 21 may be a motor rotor of a compressor.

[0103] The diffuser inner bore includes a first bore 52 and a second bore 53. The diameter of the second bore 53 is larger than that of the first bore 52. The inner wall of the second bore 53 is used to securely connect a gas bearing. In this embodiment, it is used to connect the first thrust bearing 411 of the thrust bearing assembly 4141.

[0104] In some embodiments, a first shaft sealing structure 56 for forming a dynamic seal with the rotating shaft 21 is provided on an inner wall of the first hole 52 in the diffuser body.

[0105] In some embodiments, one end of the diffuser body is configured to include a diffuser positioning stop; the diffuser positioning stop includes a first diffuser stop portion 54 and a second diffuser stop portion 55 .

[0106] The first diffuser stop portion 54 is used to abut against the bottom of the component to be installed.

[0107] The second diffuser stop portion 55 is used to abut against the side of the component to be installed, and the second diffuser stop portion 55 is used to connect with the component to be installed; the radial dimension of the second diffuser stop portion 55 is greater than the radial dimension of the first diffuser stop portion 54.

[0108] In some embodiments, the aforementioned part to be installed is a housing of a compressor. Alternatively, the aforementioned part to be installed is a connecting portion extending inwardly from the housing of the compressor.

[0109] In this embodiment, the connecting portion is the end wall 112 of the cylinder 11. The connecting portion includes a radial bearing seat formed on the end wall 112 for mounting the first radial bearing 42. The radial bearing seat will be described in the following embodiments.

[0110] like Figure 5 FIG. 1 is a schematic diagram of a partial assembly of a compressor provided in some embodiments.

[0111] In some embodiments, the compressor includes a housing 10 , and a receiving space is formed in the housing 10 .

[0112] In some embodiments, the compressor includes a rotating shaft 21, which is rotatably disposed within the housing 10. In this embodiment, the rotating shaft 21 is equivalent to the motor rotor of the compressor. In some embodiments, the rotating shaft 21 is disposed along the inner central axis of the housing 10.

[0113] In some embodiments, the compressor includes the diffuser 50 of the above-described embodiments.

[0114] In some embodiments, the compressor includes a first thrust bearing 41 . A diffuser supply air passage 51 of the diffuser 50 is used to supply air to the first thrust bearing 41 . Furthermore, the first thrust bearing 41 includes a static pressure gas bearing. The first thrust bearing 41 is used to support the rotating shaft 21 .

[0115] In some embodiments, the diffuser 50 is disposed at the end of the rotating shaft 21. The diffuser 50 is fixedly connected to the end wall 112 of the cylinder 11 of the housing 10.

[0116] In some embodiments, as Figure 6 、 Figure 7As shown, the diffuser 50 is provided with a diffuser air supply channel 51 for supplying air to the first thrust bearing 41.

[0117] The diffuser 50 is provided with an air supply channel for supplying air to the first thrust bearing 41, which solves the air supply problem of the thrust bearing and stabilizes the pressure at the thrust bearing.

[0118] The air supply channel of the thrust bearing is integrated on the diffuser 50, which simplifies the structure of the air supply channel and prevents air leakage.

[0119] In some embodiments, the first thrust bearing 41 is fixedly connected to the diffuser 50. In some embodiments, the first thrust bearing 41 is fixed to the diffuser 50 by screws.

[0120] In some embodiments, the diffuser air supply channel 51 includes an introduction channel for introducing air. The introduction channel can directly introduce air outside the compressor to the first thrust bearing 41, or the introduction channel can also introduce air in the housing air supply channel 17 of the housing 10 of the compressor to the first thrust bearing 41 (described in detail below).

[0121] In some embodiments, the introduction channel is parallel to the rotating shaft 21 in the housing 10 of the compressor.

[0122] In some embodiments, the diffuser air supply channel 51 includes an exit channel for providing air introduced by the introduction channel to the first thrust bearing 41.

[0123] In some embodiments, the exit channel is parallel to the rotating shaft 21 in the housing 10 of the compressor.

[0124] In some embodiments, to prevent air leakage from the exit channel, sealing rings are provided on the diffuser 50 on both sides of the exit channel.

[0125] In some embodiments, the diffuser air supply channel 51 includes a communication channel that communicates the introduction channel and the exit channel.

[0126] In some embodiments, for ease of processing, the communication channel also communicates the outside of the diffuser 50, and a plug 57 can be provided at the end of the communication channel that communicates with the outside of the diffuser 50.

[0127] In some embodiments, the diffuser 50 includes a diffuser inner hole that allows the rotating shaft 21 to rotate, and the diffuser inner hole includes a first hole 52 and a second hole 53. The second hole 53 has a larger hole diameter than the first hole 52, and the second hole 53 is located on the inner side of the housing 10 relative to the first hole 52.

[0128] In some embodiments, the first thrust bearing 41 is disposed in the second hole 53 and fixedly connected with the wall of the second hole 53.

[0129] The radial dimension of the first thrust bearing 41 is smaller than the hole diameter of the second hole 53.

[0130] The diffuser 50 is fixedly connected with the first thrust bearing 41, and the diffuser 50 integrates the function of the thrust bearing fixing plate, so that the machining precision is easy to guarantee, the assembly reference is uniform, the assembly precision is improved, the perpendicularity of the thrust bearing is guaranteed, the length of the rotor and the load of the bearing are reduced, the rigidity of the rotor and the stability of the bearing-rotor system are improved.

[0131] In some embodiments, the compressor comprises a thrust disc 24. The thrust disc 24 is fixedly disposed at the end of the rotating shaft 21, and the thrust disc 24 rotates with the rotating shaft 21.

[0132] In some embodiments, the compressor comprises a second thrust bearing 412, which is disposed on the opposite side of the thrust disc 24 from the first thrust bearing 41. The second thrust bearing 412 comprises a gas bearing. Preferably, the second thrust bearing 412 comprises a static pressure gas bearing.

[0133] In some embodiments, the housing 10 extends a connecting portion in the direction of the central axis inside the housing 10, and the second thrust bearing 412 is fixedly connected with the connecting portion.

[0134] In some embodiments, the connecting portion is provided with a housing gas supply channel 17, which is used to supply gas to the second thrust bearing 412.

[0135] As shown in Figure 4 , the housing gas supply channel 17 comprises a thrust bearing gas supply channel 172, which supplies gas to the first thrust bearing and the second thrust bearing 412.

[0136] In some embodiments, the gas in the housing gas supply channel 17 is derived from outside the compressor.

[0137] In some embodiments, the diffuser gas supply channel 51 communicates with the housing gas supply channel 17, and the gas in the diffuser gas supply channel 51 is derived from the housing gas supply channel 17.

[0138] In some embodiments, the thrust disc 24 and the thrust disc mounting sleeve are integrally formed into a thrust disc component. The thrust disc mounting sleeve is disposed in the first hole 52 of the diffuser 50. The thrust disc 24 is disposed in the second hole 53 of the diffuser 50.

[0139] The radial dimension of the thrust disc 24 is smaller than the hole diameter of the second hole 53. The radial dimension of the thrust disc 24 is smaller than the radial dimension of the first thrust bearing 41 and / or the radial dimension of the second thrust bearing 412.

[0140] In some embodiments, the thrust disc 24 and the thrust disc mounting sleeve are both cylindrical, and the radial dimension of the thrust disc mounting sleeve is smaller than the radial dimension of the thrust disc 24.

[0141] In some embodiments, the inner wall of the first hole 52 of the diffuser 50 is provided with a first shaft seal structure 56, and the first shaft seal structure 56 forms a dynamic seal with the thrust disc mounting sleeve of the thrust disc component.

[0142] In some embodiments, the first shaft seal structure 56 comprises a first comb seal structure.

[0143] The shaft seal structure is integrated into the diffuser 50, and the bearing fixing plate is also integrated into the diffuser 50, that is, the diffuser 50, the shaft seal, and the thrust bearing fixing plate are integrated into one part in the embodiments of the present disclosure, so that the shaft seal which requires high coaxiality and the thrust bearing which requires high perpendicularity share one positioning, the assembly reference is unified, the assembly difficulty is reduced, the assembly precision is improved, and the problems of wear of the comb seal type shaft seal structure caused by insufficient coaxiality and the problems of performance reduction and failure of the thrust bearing caused by insufficient perpendicularity are solved.

[0144] Furthermore, the diffuser 50, the shaft seal, and the thrust bearing fixing plate are integrated into one part, the number of parts is reduced, and the quality control is improved; in the case of meeting the functional requirements, the length of the part is reduced, so that the length of the rotor is reduced, the stiffness of the rotor and the critical speed of the bending mode of the bearing-rotor system are improved, and the rotor weight and the bearing load are reduced, which together improve the stability of the bearing-rotor system.

[0145] In some embodiments, the housing 10 is provided with a connecting portion extending towards the central axis of the interior of the housing 10, and the diffuser 50 is fixedly connected with the connecting portion. In some embodiments, the diffuser 50 is fixedly connected with the connecting portion through a screw.

[0146] In some embodiments, one end of the diffuser 50 connected with the housing 10 is configured as a diffuser positioning stop, and the diffuser positioning stop is used for positioning with the connecting portion. The side of the connecting portion facing the diffuser 50 is provided with a diffuser mounting opening used for cooperating with the diffuser positioning stop.

[0147] In some embodiments, the diffuser positioning stop comprises a first diffuser stop portion 54, and the first diffuser stop portion 54 abuts against the bottom of the connecting portion.

[0148] In some embodiments, the diffuser positioning stop comprises a second diffuser stop portion 55, and the second diffuser stop portion 55 abuts against the side of the connecting portion and is connected with the end wall 112 of the housing 10.

[0149] The radial dimension of the first diffuser collar portion 54 is smaller than the radial dimension of the second diffuser collar portion 55. The second diffuser collar portion 55 is disposed around the outer periphery of the first diffuser collar portion 54.

[0150] In some embodiments, the connecting portion is provided with a housing gas flow channel 17, and the diffuser gas flow channel 51 is in communication with the housing gas flow channel 17, and the gas source of the diffuser gas flow channel 51 is derived from the housing gas flow channel 17.

[0151] In some embodiments, the compressor comprises a first radial bearing 42. The first radial bearing 42 is a gas bearing. The first radial bearing 42 is disposed on the outer periphery of the rotating shaft 21 for supporting the rotating shaft 21. In some embodiments, the first radial bearing 42 is a static pressure gas bearing.

[0152] The housing 10 is provided with a connecting portion extending towards the central axis of the interior of the housing 10, and the first radial bearing 42 is fixedly connected to the connecting portion.

[0153] The first radial bearing 42 is closer to the inner side of the housing 10 relative to the thrust bearing.

[0154] In some embodiments, the connecting portion provided on the housing 10 can be connected to the diffuser 50, the second thrust bearing 412, and the first radial bearing 42. The connecting portion provided on the housing 10 is provided with a housing gas flow channel 17 for supplying gas to the second thrust bearing 412, and can also supply gas to the first thrust bearing 41 through the diffuser gas flow channel 51 provided on the diffuser 50.

[0155] The connecting portion of the housing 10 is in a stepped shape, and the lengths of the respective portions extending towards the central axis of the interior of the housing 10 are different.

[0156] Further, the connecting portion provided on the inner wall of the housing 10 is also provided with an intermediate passage for communicating the housing gas flow channel 17 with the diffuser gas flow channel 51 provided in the diffuser 50.

[0157] The gas outside the compressor is first introduced through the housing gas flow channel 17 in the connecting portion of the housing 10 to supply the second thrust bearing 412, and then enters the diffuser gas flow channel 51 of the diffuser 50 through the intermediate passage, and is then supplied to the first thrust bearing 41 by the diffuser gas flow channel 51.

[0158] In some embodiments, a sealing ring is provided at the mating portion of the diffuser 50 and the connecting portion of the housing 10, and a sealing ring is also provided at the mating portion of the diffuser 50 and the second thrust bearing 412, and on both sides of the diffuser gas flow channel 51, to prevent gas leakage.

[0159] In some embodiments, the first thrust bearing 41 is first fixed on the diffuser 50 by screws, then the diffuser 50 is positioned on the casing 10 by the diffuser positioning stop, and then is precisely positioned by the pin. The coaxiality of the first shaft seal structure 56 on the diffuser 50 and the perpendicularity of the thrust bearing fixing surface are guaranteed on one part, which not only reduces the processing difficulty, but also greatly reduces the assembly cumulative error. The shaft seal with high coaxiality and the thrust bearing with high perpendicularity share the stop and the pin positioning, and the assembly reference is unified, which reduces the assembly difficulty, improves the assembly precision, solves the problem of comb seal wear caused by insufficient coaxiality, and solves the problem of performance reduction and failure of the thrust bearing caused by insufficient perpendicularity.

[0160] In some embodiments, the compressor includes a first impeller 22, the end of the rotating shaft 21 penetrates the end wall 112 of the casing 10, and the first impeller 22 is fixed on the end of the rotating shaft 21. The first impeller 22 is positioned in cooperation with the diffuser 50.

[0161] Further, the first impeller 22 is fixed on the rotating shaft 21 by the first impeller locking member 25.

[0162] In some embodiments, the end wall 112 of the casing 10 includes a mating surface with the diffuser 50. The diffuser 50 converts the velocity energy of the working medium at the outlet of the first impeller 22 into pressure energy. The diffuser gas supply passage 51 inside the diffuser 50 is used to supply gas to the thrust bearing. The inner hole of the diffuser 50 is provided with a first shaft seal structure 56, which cooperates with the thrust disc mounting sleeve to form a shaft seal, preventing the first impeller 22 exhaust gas from entering the motor cavity 1414 of the casing 10. The right end surface of the diffuser 50 is a thrust bearing fixing surface, and the first thrust bearing 41 is directly locked on the right end surface of the diffuser 50 by screws to bear the axial force of the compressor rotor 20.

[0163] In some embodiments, the diffuser gas supply passage 51 for supplying gas to the first thrust bearing 41 is arranged in the diffuser 50, and the functions of the diffuser, the thrust bearing fixing plate, and the shaft seal are integrated on the diffuser 50. This not only ensures the normal supply of gas to the gas bearing, but also shortens the length of the rotor, reduces the bearing load, improves the critical speed and stability of the rotor-bearingsystem bending mode, and makes it easy to ensure the machining precision and unify the assembly reference, thereby reducing the assembly technical requirements and improving the assembly precision to ensure the perpendicularity of the thrust bearing.

[0164] In some embodiments, the compressor is a centrifugal compressor.

[0165] As Figure 1 , Figure 2 and Figure 8As shown, in some embodiments, the present disclosure also provides a thrust bearing assembly 41, which is easier to adjust and ensure the clearance of the thrust bearing when the thrust bearing assembly 41 is used to bidirectionally stop the rotating shaft 21. The present disclosure also provides a compressor with the thrust bearing assembly 41.

[0166] As shown in Figure 1 , Figure 2 and Figure 8 , the thrust bearing assembly 41 of the present disclosure includes a first thrust bearing 411, a second thrust bearing 412 and a thrust bearing positioning ring 413.

[0167] The first thrust bearing 411 includes a first thrust surface 4111 and a first positioning surface 4112. The first thrust surface 4111 and the first positioning surface 4112 are arranged on the same side of the first thrust bearing 411. The first thrust surface 4111 is located radially inward of the first positioning surface 4112 and protrudes axially outward relative to the first positioning surface 4112. The second thrust bearing 412 includes a second thrust surface 4121 and a second positioning surface 4122. The second thrust surface 4121 and the second positioning surface 4122 are arranged on the same side of the second thrust bearing 412, located radially inward of the second positioning surface 4122 and protrude axially outward relative to the second positioning surface 4122. The second thrust surface 4121 is opposite to the first thrust surface 4111, and the second positioning surface 4122 is opposite to the first positioning surface 4112. The thrust bearing positioning ring 413 is arranged between the first thrust bearing 411 and the second thrust bearing 412, and includes a first matching surface 4131 abutting the first positioning surface 4112 and a second matching surface 4132 abutting the second positioning surface 4122, for limiting the interval between the first thrust surface 4111 and the second thrust surface 4121 by the interval between the first matching surface 4131 and the second matching surface 4132.

[0168] The first thrust surface 4111 of the first thrust bearing 411 and the second thrust surface 4121 of the second thrust bearing 412 are respectively used to cooperate with the mating surfaces on both sides of the thrust disc 24 of the rotating shaft 21, in Figure 1 the embodiment shown, the first thrust surface 4111 and the second thrust surface 4121 are respectively matched with the left end surface and the right end surface of the thrust disc 24 fixedly connected to the rotating shaft 21 of the compressor. The first thrust surface 4111 is used to bear the left axial force of the rotating shaft 21, and the second thrust surface 4121 is used to bear the right axial force of the rotating shaft 21.

[0169] The first positioning surface 4112 of the first thrust bearing 411 and the second positioning surface 4122 of the second thrust bearing 412 are used to determine the distance between the first thrust surface 4111 and the second thrust surface 4121. In this embodiment, the first positioning surface 4112 and the second positioning surface 4122 respectively mate with the first mating surface 4131 and the second mating surface 4132 of the thrust bearing locating ring 413. Thus, the distance between the first mating surface 4131 and the second mating surface 4132 of the thrust bearing locating ring 413 defines the distance between the first thrust bearing 411 and the second thrust bearing 412, that is, the distance between the first thrust surface 4111 and the second thrust surface 4121. In other words, the distance between the thrust plate 24, which mates with both the first thrust surface 4111 and the second thrust surface 4121, is defined as the sum of the clearance between the first thrust surface 4111 and the second thrust surface 4121. Therefore, the clearance of the thrust bearing assembly 41 during operation can be adjusted by adjusting the distance between the first mating surface 4131 and the second mating surface 4132 of the thrust bearing positioning ring 413 .

[0170] When the working clearance of the thrust bearing assembly 41 needs to be reduced, for example, Figure 1 In the illustrated compressor, the first thrust surface 4111 of the first thrust bearing 411 and / or the second thrust surface 4121 of the second thrust bearing 412 wear over time, causing the gap between the first thrust surface 4111 and the second thrust bearing 412 to increase. As a result, the sum of the clearance between the left end face of the thrust plate 24 and the first thrust surface 4111 and the clearance between the right end face and the second thrust surface 4121 increases, requiring a reduction in the clearance of the thrust bearing assembly 41. At this point, the thrust bearing assembly 41 can be removed from the compressor, and the clearance of the worn thrust bearing assembly 41 can be measured. Based on this clearance, the required adjustment amount for the thrust bearing locating ring 413 can be determined. Then the thrust bearing locating ring 413 is taken out from the thrust bearing assembly 41, and the first mating surface 4131 and / or the second mating surface 4132 of the thrust bearing locating ring 413 is processed by grinding or other processing methods according to the determined adjustment amount to reduce the distance between the first mating surface 4131 and the second mating surface 4132, and then the second thrust bearing 412 is fixed on the bearing seat of the compressor casing 10, and the second mating surface 4132 of the thrust bearing locating ring 413 is aligned with the second positioning surface 4122, and then the thrust bearing locating ring 413 is fixedly connected to the second thrust bearing 412, and then the first positioning surface 4112 of the first thrust bearing 411 is aligned with the first mating surface 4131, and the diffuser 50 at the left end of the first thrust bearing 411 is installed, and the diffuser 50 is tightened to press the first thrust bearing 411 onto the thrust bearing locating ring 413.

[0171] When the working clearance of the thrust bearing needs to be increased, a thrust bearing positioning ring 413 with a suitable distance between the first mating surface 4131 and the second mating surface 4132 can be replaced. By providing the thrust bearing positioning ring 413, the clearance of the thrust bearing assembly 41 can be easily adjusted.

[0172] The first thrust surface 4111 of the first thrust bearing 411 is located radially inward of the first positioning surface 4112, that is, the first thrust surface 4111 is located in the middle of the first thrust bearing 411, and the first positioning surface 4112 is located outside the first thrust bearing 411. The first thrust surface 4111 protrudes axially outward relative to the first positioning surface 4112, that is, the first thrust bearing 411 has a stepped shape with a protruding center on the side where the first positioning surface 4112 and the first thrust surface 4111 are located. Because the first thrust surface 4111 is a working surface that cooperates with the thrust disk 24 and requires high precision, the positioning accuracy of the first positioning surface 4112 can be adjusted by the thrust bearing positioning ring 413, so the precision requirement for the first positioning surface 4112 is relatively low. This arrangement facilitates high-precision machining of the first thrust surface 4111 of the first thrust bearing 411, such as surface grinding. Similarly, the same arrangement of the second thrust surface 4121 and the second positioning surface 4122 of the second thrust bearing 412 also helps to achieve high-precision processing of the second thrust bearing 412 .

[0173] The clearance of the thrust bearing assembly 41 of this embodiment is easy to adjust, and the first thrust bearing 411 and the second thrust bearing 412 are easy to achieve high-precision processing.

[0174] In some embodiments, the first thrust bearing 411 and the second thrust bearing 412 are gas bearings, such as static pressure gas bearings or dynamic pressure gas bearings. Gas bearings use gas to form an air film between the thrust surface of the thrust bearing and the thrust member, which has the advantages of high speed and low noise. Figure 1 In the illustrated compressor embodiment, when first thrust bearing 411 is a hydrostatic gas bearing, pressurized gas can be injected between the left end surface of the compressor's thrust plate 24 and first thrust surface 61, forming an air film between the left end surface of the thrust plate 24 and first thrust surface 61. Using hydrostatic gas bearings for first and second thrust bearings 411, 412 offers advantages such as ultra-high rotational precision, ultra-low friction, ultra-low vibration, ultra-low noise, long life, and zero pollution. These bearings are suitable for high-speed, high-precision applications, such as centrifugal compressors, particularly miniaturized centrifugal compressors.

[0175] In some embodiments, the thrust bearing locating ring 413 includes a locating ring fluid channel connecting the radially inner side and the radially outer side of the thrust bearing locating ring 413. In embodiments where the first thrust bearing 411 and the second thrust bearing 412 are gas bearings, this arrangement allows exhaust gas between the thrust disc 24 and the thrust surface of the gas bearings to be smoothly discharged from the locating ring fluid channel to the outer side of the thrust bearing locating ring 413, thereby preventing exhaust gas from being trapped between the thrust surfaces and the thrust disc 24 of the first and second thrust bearings 411, 412. This prevents increased back pressure in the gas bearings from affecting the internal air film pressure distribution of the bearings, thereby affecting the stiffness and load-bearing capacity of the gas bearings, and preventing air hammer vibration. This embodiment helps to ensure smooth exhaust of the gas bearings and improve the rotational stability of the gas bearing rotor system.

[0176] In some embodiments, the positioning ring fluid channel is located on one side end surface of the thrust bearing positioning ring 413. Figure 2 、 Figure 8 In the illustrated embodiment, the positioning ring fluid channel is provided on the left end face of the thrust bearing positioning ring 413. This arrangement facilitates machining of the positioning ring fluid channel, making the structure of the thrust bearing positioning ring 413 more compact. Compared to providing positioning ring fluid channels on both end faces, it also reduces the impact on machining of the mating surface of the thrust bearing positioning ring 413.

[0177] In some embodiments, as Figure 2 、 Figure 8 As shown, the positioning ring fluid channel includes a groove 4133 provided on the end surface of the thrust bearing positioning ring 413. This arrangement facilitates the processing of the positioning ring fluid channel, the structure of the thrust bearing positioning ring 413 is simple, and it also helps to smoothly exhaust the gas bearing.

[0178] In some embodiments, as Figure 8 As shown, the positioning ring fluid channel includes a plurality of grooves 4133 distributed along the circumference. This arrangement further facilitates the smooth exhaust of the gas bearing and improves the exhaust stability of the gas bearing.

[0179] In some embodiments, the grooves 4133 are radial grooves, and a plurality of radial grooves are evenly distributed along the circumference of the thrust bearing locating ring 413. This arrangement helps to facilitate the processing of the thrust bearing locating ring 413.

[0180] In an embodiment not shown in the figures, the positioning ring fluid passage may also be provided as a hole penetrating the radial inner side and the radial outer side of the thrust bearing positioning ring 413 .

[0181] In some embodiments, the first mating surface 4131 and the second mating surface 4132 of the thrust bearing locating ring 413 are the outermost planes of the two end surfaces of the thrust bearing locating ring 413. This arrangement facilitates adjustment and processing of the mating surfaces of the thrust bearing locating ring 413 by surface grinding, thereby improving the dimensional accuracy, shape accuracy, and positioning accuracy of the thrust bearing locating ring 413.

[0182] In some embodiments, the thrust bearing locating ring 413 is provided with a through hole for mounting the thrust bearing locating ring 413 on the first thrust bearing 411 or the second thrust bearing 412. Figure 2 、 Figure 8 As shown, a through hole is provided on the thrust bearing positioning ring 413, and the thrust bearing positioning ring 413 can be installed and fitted on the second thrust bearing 412 using screws 2, and the second thrust bearing can also be installed on the bearing seat of the compressor housing 10.

[0183] The embodiment of the present disclosure further provides a compressor, which includes a compressor rotor 20 and the aforementioned thrust bearing assembly 41. Figure 1 As shown, the compressor rotor 20 includes a rotating shaft 21 and a thrust plate 24 fixed on the rotating shaft 21; the two end surfaces of the thrust plate 24 respectively cooperate with the first thrust surface 4111 and the second thrust surface 4121 of the thrust bearing assembly 41.

[0184] like Figure 1 、 Figure 2 and Figure 8 As shown, an embodiment of the present disclosure further provides a compressor, which includes a cylinder 11 , a rotating shaft 21 , a diffuser 50 , a thrust plate 24 and a thrust bearing assembly 41 .

[0185] The cylinder 11 includes a side wall 111 and an end wall 112 connected to one end of the side wall 111 ( Figure 1 The motor stator 30 of the compressor is arranged in the cylinder 11.

[0186] The rotating shaft 21 is disposed inside the cylinder 11 and one end of the rotating shaft 21 passes through the end wall 112. The compressor rotor 20 includes the rotating shaft 21, which is used to drive the first impeller 22 and the second impeller 23 to rotate to compress the gas.

[0187] The diffuser 50 is mounted on the outside of the end wall 112, and one end ( Figure 1 and Figure 2 The left end in the middle) has a first diffuser structure, and the other end ( Figure 1 and Figure 2 A thrust bearing accommodating cavity is formed between the diffuser 50 and the end wall 112. Figure 1The mounting is shown on the outer side of the end wall 112 of the cylinder body 11, and a thrust bearing accommodating cavity can be directly formed between the end wall 112 and the mounting to accommodate the thrust bearing assembly 41. Hereinafter, the bearing chamber of the gas bearing includes the thrust bearing accommodating cavity when the gas bearing can be a thrust bearing.

[0188] As shown in Figure 1 and Figure 2 , in some embodiments, the end wall 112 includes a stepped mounting port, and the end face of the other end of the diffuser 50 is provided with a diffuser positioning stop, and the outer peripheral wall of the diffuser 50, the end face of the other end of the diffuser 50 and the diffuser positioning stop are matched with the large diameter part, the stepped surface and the small diameter part of the stepped mounting port respectively. The diffuser positioning stop is provided to facilitate ensuring the coaxiality of the diffuser and the rotating shaft 21, and also to facilitate ensuring the coaxiality of the shaft seal structure located on the diffuser 50 and the rotating shaft 21, thereby improving the sealing effect.

[0189] As shown in Figure 1 and Figure 2 , in some embodiments, the diffuser positioning stop is sealingly matched with the small diameter part of the stepped mounting port. This arrangement facilitates preventing gas from leaking between the compression cavity where the compression unit of the compressor is located and the motor accommodating cavity 14 where the motor stator is located.

[0190] The thrust disc 24 is fixed to one end (the left end in Figure 1 and Figure 2 ) of the rotating shaft 21 and located in the thrust bearing accommodating cavity. The thrust disc 24 rotates together with the rotating shaft 21 and is used to transmit axial force to the rotating shaft 21. The thrust disc 24 can be fastened to the rotating shaft 21 by means of fasteners, or can be integrally formed with the rotating shaft 21. In the present embodiment, as shown in Figure 1 and Figure 2 , the thrust disc 24 is fixedly sleeved on the end of the rotating shaft 21 by means of hot fitting.

[0191] As shown in Figure 1 and Figure 2 , the thrust bearing assembly 41 is located in the thrust bearing accommodating cavity and cooperates with the two end faces of the thrust disc 24 to bi-directionally stop the rotating shaft 21. One part of the thrust bearing assembly 41 cooperates with the left end face of the thrust disc 24 to bear the left axial force of the rotating shaft 21, and is used to rightward stop and limit the rotating shaft 21. Another part of the thrust bearing assembly 41 cooperates with the right end face of the thrust disc 24 to bear the right axial force of the rotating shaft 21, and is used to leftward stop and limit the rotating shaft 21. That is, the thrust bearing assembly 41 is used to rightward and leftward stop the rotating shaft 21.

[0192] The compressor of this embodiment forms a thrust bearing accommodating cavity between the diffuser 50 and the end wall 112 of the cylinder 11 to accommodate the thrust bearing assembly 41 for bidirectional thrust of the rotating shaft 21, thereby reducing the axial size of the compressor, making the compressor structure more compact, and helping to reduce the length of the rotating shaft 21 and improve the stiffness and bending mode critical speed of the rotating shaft 21.

[0193] In some embodiments, as Figure 1 、 Figure 2 and Figure 8 As shown, the thrust bearing assembly 41 includes a first thrust bearing 411 that mates with the left end surface of the thrust plate 24, and a second thrust bearing 412 that mates with the right end surface of the thrust plate 24. The first thrust bearing 411 mates with the inner wall of the diffuser 50, while the second thrust bearing 412 mates with the end wall 112. The first and second thrust bearings 411, 412 are directly attached to the diffuser 50 and the end wall 112, eliminating the need for intermediate mounting components, further reducing the axial dimensions of the compressor, and making the compressor structure more compact.

[0194] As previously described, the thrust bearing assembly 41 includes a first thrust bearing 411, a second thrust bearing 412, and a thrust bearing locating ring 413. The structures and mating relationships of the first thrust bearing 411, the second thrust bearing 412, and the thrust bearing locating ring 413 are as described for the thrust bearing assembly 41 in the previous embodiment and will not be repeated here.

[0195] In some embodiments, the radial inner side of the diffuser 50 is further provided with a first shaft sealing structure 56 for sealing the rotating shaft 21 or a thrust bearing mounting sleeve integrally provided with the thrust disc 24. Figure 1 or Figure 2 In the illustrated embodiment, the thrust bearing mounting sleeve and the thrust plate 24 form an integral thrust plate assembly, which is shrink-fitted onto the rotating shaft 21. A first shaft seal structure 56 is used to seal the thrust bearing mounting sleeve. Integrating the first shaft seal structure 56 with the diffuser 50 further reduces the axial dimension of the compressor, making the compressor structure more compact, and helping to reduce the length of the rotating shaft 21 and increase its rigidity.

[0196] In some embodiments, the first shaft sealing structure 56 includes a comb-teeth structure, which has a good sealing effect on gas.

[0197] In some embodiments, the compressor further includes a radial bearing seat and a first radial bearing 42. The radial bearing seat is located in the middle of the end wall 112 and is integrally formed with the end wall 112. The first radial bearing 42 is mounted on the radial bearing seat and engages with the rotating shaft 21. This arrangement helps to make the compressor structure more compact.

[0198] like Figure 1 and Figure 2As shown, in some embodiments, the compressor is a two-stage centrifugal compressor. The compressor rotor 20 of the two-stage centrifugal compressor includes the aforementioned rotating shaft 21, a thrust plate 24, and a first impeller 22 and a second impeller 23 provided at both ends of the rotating shaft 21. The compressor also includes a second radial bearing 43 and a bearing support component 60. The bearing support component 60 includes a diffuser portion and a bearing seat portion. The diffuser portion is mounted on the end of the side wall 111 opposite to the end wall 112 ( Figure 1 The right end of the cylinder (centering in the figure) has a second diffuser structure. The bearing housing is located within the cylinder 11 and is integrally formed with the diffuser. A second radial bearing 43 is mounted on the bearing housing and engages with the rotating shaft 21. A two-stage compressor can perform secondary compression on the gas, improving the gas compression ratio.

[0199] exist Figure 1 and Figure 2 In the illustrated embodiment, the first impeller 22 is a first-stage impeller, and the diffuser 50 is a first-stage diffuser; the second impeller 23 is a second-stage impeller, and the diffuser section is a second-stage diffuser. The first impeller 22 is located within the first compression chamber 15 at the left end of the diffuser 50, and the second impeller 23 is located within the second compression chamber 16 at the right end of the diffuser section. A motor stator 30 is disposed within the cylinder 11. The central portion of the rotating shaft 21 includes a permanent magnet. Therefore, the rotating shaft 21 also serves as the motor rotor. The motor stator 30, in conjunction with the rotating shaft 21, can drive the compressor rotor 20 of the centrifugal compressor.

[0200] Integrating the diffuser portion and the bearing seat portion can further reduce the axial size of the compressor and make the compressor structure compact, help reduce the length of the rotating shaft 21 and reduce the radial bearing load, and help improve the stiffness and bending mode critical speed of the rotating shaft 21.

[0201] In some embodiments, as Figure 1 As shown, the thrust bearing assembly 41 includes a first thrust bearing 411 that cooperates with the left end face of the thrust plate 24 and a second thrust bearing 412 that cooperates with the right end face of the thrust plate 24; the compressor also includes a radial bearing seat located in the middle of the end wall 112 and integrally formed with the end wall 112, and a first radial bearing 42 mounted on the radial bearing seat and cooperates with the rotating shaft 21; the first thrust bearing 411, the second thrust bearing 412, the first radial bearing 42 and the second radial bearing 43 are static pressure gas bearings, and the air supply channels of the first thrust bearing 411, the second thrust bearing 412, the first radial bearing 42 and the second radial bearing 43 are connected to each other.

[0202] like Figure 28As shown, in some embodiments, the casing gas supply channel 17 is introduced with working gas from a compressor external gas source from the casing gas supply channel inlet 101. The casing gas supply channel 17 on the cylinder 11 is divided into two parts, a total of four routes. One part includes two routes, the thrust bearing gas supply channel 172, one route is the gas supply channel for the first thrust bearing 411 through the diffuser 50, and one route is the gas supply channel for the second thrust bearing 412 through the end wall 112. The other part includes two routes, the radial bearing gas supply channel 171, one route is the gas supply channel for the first radial bearing 42 through the end wall 112, and one route is the gas supply channel for the second radial bearing 43 through the diffuser part. This way, since the gas supply channel source is only one route, the gas bearing gas supply pressure control is more simple and convenient, only the gas supply pressure on the casing gas supply channel 17 needs to be controlled, which can adjust the gas supply pressure of the first thrust bearing 411, the second thrust bearing 412, the first radial bearing 42 and the second radial bearing 43, thereby adjusting the bearing stiffness and load capacity, preventing gas hammer vibration.

[0203] In some embodiments, as shown in Figure 1 and Figure 4 The thrust bearing assembly 41 and the radial bearing can also be independently supplied with gas, as shown in Figure 4 The thrust bearing gas supply channel 172 that supplies gas to the thrust bearing of the thrust bearing assembly 41 is arranged in the end wall 112 of the cylinder 11 and in the diffuser 50. The thrust bearing gas supply channel 172 is divided into two routes, one route supplies gas to the second thrust bearing 412 through the end wall 112, and the other route enters the diffuser 50 and supplies gas to the first thrust bearing 411 through the diffuser gas supply channel 51 on the diffuser 50. The gas supply of the thrust bearing gas supply channel 172 passes through the internal throttle of the first thrust bearing 411 and the second thrust bearing 412, enters the gap between the two thrust surfaces and the mating surface of the thrust disc 24, forms a gas film with pressure, and the gas film acts on the thrust disc 24 to offset the axial force of the rotating shaft 211. During operation, the gas supply pressure of the thrust bearing gas supply channel 172 can be adjusted according to the pressure in the cylinder 11 and the vibration of the rotating shaft 21, to adjust the stiffness and load capacity of the first thrust bearing 411 and the second thrust bearing 412, and prevent gas hammer vibration.

[0204] In some embodiments, as shown in Figure 1As shown, radial bearing supply duct 171, which supplies air to the first and second radial bearings 42, 43, splits into two paths and enters the bearing chambers (hereinafter referred to as bearing mounting holes) housing the first and second radial bearings 42, 43. After throttling through the interior of the first and second radial bearings 42, 43, the air enters the gap between the first and second radial bearings 42, 43 and the rotating shaft 21, forming an air film. During operation, the air supply pressure in radial bearing supply duct 171 is adjusted based on the pressure within the motor housing chamber 14 and the vibration of the rotating shaft 21 to adjust the stiffness and load-bearing capacity of the first and second radial bearings 42, 43 and prevent air hammer vibration.

[0205] like Figure 1 and Figure 2 As shown, in some embodiments, the bearing support component 60 further includes a mounting hole. The compressor further includes a shaft seal component 70, and the bearing component is mounted in the mounting hole. The shaft seal component 70 includes a second shaft seal structure 711 for sealing the rotating shaft 21. The second shaft seal structure 711 can be, for example, a comb tooth structure. The shaft seal component 70 is connected to one end surface ( Figure 1 and Figure 2 This arrangement allows the shaft seal component 70 to not only seal the rotating shaft 21 but also provide axial positioning for the second radial bearing 43. This allows one component to serve multiple purposes, resulting in a compact compressor structure and a reduced length of the compressor rotor 20.

[0206] like Figure 1 As shown, in some embodiments, the shaft seal component 70 includes a shaft seal fluid passageway connecting the radially inner and radially outer sides of the shaft seal component 70. The bearing support component 60 includes a support component outflow passageway 64. The shaft seal fluid passageway connects the support component outflow passageway 64 with the gap between the second radial bearing 43 and the rotating shaft 21. This arrangement forms an exhaust passageway between the gap between the second radial bearing 43 and the rotating shaft 21 and the motor accommodating chamber 14 within the cylindrical body 11, which helps to ensure stable back pressure on the second radial bearing 43.

[0207] like Figure 1 As shown, the bearing bearing component 60 also includes a bearing component inflow channel 63 whose bearing structure is connected to the shell air supply channel 17 in the cylinder 11. The bearing component inflow channel 63 is connected to the bearing chamber accommodating the second radial bearing 43, thereby supplying air to the second radial bearing 43.

[0208] like Figure 1 and Figure 2As shown, the bearing carrying component 60 further comprises a carrying component positioning stop 68 arranged on the side of the diffuser component away from the second diffuser structure. The carrying component positioning stop 68 cooperates with the corresponding end of the cylinder body 11 to define the axial and circumferential positions of the bearing carrying component 60, which helps to ensure the coaxiality between the shaft seal structure on the shaft seal component 70 and the rotating shaft 21, and further ensures the sealing performance of the rotating shaft 21.

[0209] The shaft seal component 70 and the bearing carrying component 60 can each further be provided with a positioning hole and a mounting hole. The positioning hole of the shaft seal component 70 is used to cooperate with a positioning pin to limit the circumferential position of the shaft seal component 70 relative to the bearing carrying component 60, and the mounting hole of the shaft seal component 70 is used to fixedly connect the shaft seal component 70 and the bearing carrying component 60. The positioning hole of the bearing carrying component 60 is used to cooperate with a positioning pin to limit the circumferential position of the bearing carrying component 60 relative to the cylinder body 11, and the mounting hole of the bearing carrying component 60 is used to fixedly connect the bearing carrying component 60 and the cylinder body 11.

[0210] As shown in Figure 1 , Figure 3 , Figure 9 to Figure 11 The present disclosure provides a shaft seal component 70.

[0211] The shaft seal component 70 comprises a shaft seal disc body 71 and a shaft seal positioning stop 72. The shaft seal disc body 71 has a shaft hole in the center, and the hole wall of the shaft hole is provided with a shaft seal structure. The shaft seal positioning stop 72 is coaxial and integrally arranged at one axial end of the shaft seal disc body 71, and the shaft seal positioning stop 72 is provided with a shaft seal fluid passage that communicates the radially inner side and the radially outer side of the shaft seal positioning stop 72.

[0212] The shaft seal component 70 of the present disclosure has the functions of shaft sealing, positioning and discharging fluid, the shaft seal positioning stop 72 helps to improve the cooperation accuracy between the shaft seal component 70 and the sealed rotating shaft (such as the rotating shaft 21 of the compressor), which can more effectively prevent fluid leakage, the shaft seal fluid passage helps to prevent the components (such as the radial bearing) cooperating with the shaft seal component 70 from retaining fluid, which helps to stabilize the back pressure of the related components, thereby helping to improve the stability of the bearing rotor system.

[0213] As shown in Figure 1 , Figure 3 , Figure 9 to Figure 11 In some embodiments, the shaft seal structure comprises a comb structure 711. The comb structure 711 is more suitable for sealing gas and is suitable for application in a compressor, which can effectively prevent the leakage of gas under pressure.

[0214] As shown in Figure 1 , Figure 3 , Figure 9 to Figure 11As shown, in some embodiments, the end of the shaft seal positioning stop 72 away from the shaft seal disc 71 has a bearing positioning end surface 721 for axially positioning the second radial bearing 43. The bearing positioning end surface 721 enables the shaft seal component 70 to also have the axial positioning function of the radial bearing, which helps to simplify the structure of the device and shorten the length of the rotor of the device.

[0215] The structure of the shaft seal fluid channel can be various, for example, Figure 1 、 Figure 3 、 Figure 9 to Figure 11 As shown, in some embodiments, the shaft seal fluid passage includes a groove 722 that is recessed from an end away from the shaft seal disc body 71 to an end closer to the shaft seal disc body 71. In embodiments not shown, the shaft seal fluid passage may include at least one through-hole provided on the side wall 111 of the shaft seal positioning stop 72. Alternatively, both a groove and a through-hole may be provided as the shaft seal fluid passage.

[0216] like Figure 10 and Figure 11 As shown, in some embodiments, the shaft seal component 70 includes multiple shaft seal fluid channels. Providing multiple shaft seal fluid channels facilitates rapid and uniform discharge of fluid near related components, such as radial bearings, and helps prevent fluid from stagnating near related components.

[0217] like Figure 10 and Figure 11 As shown, in some embodiments, multiple shaft seal fluid channels are evenly arranged along the circumference of the shaft seal positioning stop 72. This arrangement facilitates rapid and even discharge of fluid near related components such as radial bearings, and helps prevent fluid from stagnating near related components.

[0218] In some embodiments, multiple shaft seal fluid channels are evenly spaced at 360° / n+1 intervals along the circumference of the shaft seal positioning stop 72, where n is the number of the multiple shaft seal fluid channels. The number n can be 2, 3, 4, 5, 6 or more. Figure 3 and Figure 4 In the illustrated embodiment, n = 5. The number and distribution of the shaft seal fluid passages advantageously correspond to the number and distribution of the fluid outlet passages 64 provided on the bearing support member 60. This arrangement facilitates forming fluid discharge passages in conjunction with related components, such as the bearing support member 60 described below, and also provides space for the provision of fluid inlet passages in related components.

[0219] The shaft seal component 70 comprises a shaft seal connecting hole 712 and / or a shaft seal positioning hole 713 arranged on the shaft seal disc body 71. The shaft seal positioning hole 713 can accurately determine the connecting position between the shaft seal component 70 and the relevant component, such as the bearing supporting component 60 described below, to facilitate the quick and accurate connection of the shaft seal fluid passage with the corresponding fluid passage (such as the fluid outflow passage 64 of the bearing supporting component 60). The shaft seal connecting hole 712 facilitates the detachable connection with the relevant component through a threaded connecting member.

[0220] As shown in Figure 1 , Figure 3 , Figure 9 to Figure 11 , in some embodiments, the inner circumferential surface of the shaft seal positioning stopper 72 has a diameter greater than that of the shaft hole of the shaft seal disc body 71. This arrangement facilitates the communication of the shaft seal fluid passage with the gap between the second radial bearing 43 and the rotating shaft 21, and the uniform distribution of fluid among the shaft seal fluid passages.

[0221] The embodiments of the present disclosure also provide a compressor comprising a compressor rotor 20, a second radial bearing 43 and a shaft seal component 70. The compressor rotor 20 comprises a rotating shaft 21. The second radial bearing 43 is used to support the rotating shaft 21. The shaft seal component 70 is the aforementioned shaft seal component 70. The rotating shaft 21 is arranged in the shaft hole of the shaft seal component 70. The shaft seal structure of the shaft seal component 70 cooperates with the rotating shaft 21. The shaft seal fluid passage is in communication with the gap between the second radial bearing 43 and the rotating shaft 21. This arrangement facilitates the prevention of fluid stagnation near the second radial bearing 43, the maintenance of stable back pressure of the second radial bearing 43, and the guarantee of stable operation of the compressor.

[0222] As shown in Figure 1 and Figure 3 , Figure 12 , in some embodiments, the compressor further comprises a bearing supporting component 60. The bearing supporting component 60 comprises an expander portion and a bearing seat portion. The expander portion has a mounting hole 67. The axial end (the right end of Figure 1 , Figure 5 and Figure 6 ) of the expander portion is provided with a second expander structure. The second expander structure may, for example, be an expander surface or an expander blade. The shaft seal component 70 is arranged in the mounting hole 67. The bearing seat portion is integrally arranged at the end of the expander portion away from the second expander structure. The bearing seat portion is provided with a bearing supporting component bearing chamber 62 coaxial with and in communication with the mounting hole 67. The second radial bearing 43 is arranged in the bearing supporting component bearing chamber 62. The bearing supporting component 60 simultaneously assumes the functions of the expander portion, the bearing seat portion and the shaft seal component mounting. The shaft seal component 70 cooperates to mount the second radial bearing 43 in the bearing supporting component 60, which facilitates the shortening of the length of the compressor rotor and the reduction of the weight of the compressor rotor of the compressor, and facilitates the improvement of the critical speed of the compressor rotor.

[0223] AsFigure 1 and Figure 3 、 Figure 12 As shown in FIGS. 6A and 6B, in some embodiments, the bearing carrier 60 includes a fluid inlet passage 63 that communicates the bearing carrier chamber 62 with the outside of the bearing carrier 60. The fluid inlet passage 63 can supply the second radial bearing 43 with the fluid, such as working gas, required to support the shaft 21. The fluid inlet passage 63 can be, for example, a borehole formed in the bearing carrier 60.

[0224] As shown in FIGS. 6A and 6B, in some embodiments, the bearing carrier 60 includes a fluid outlet passage 64 that communicates the mounting hole 67 with the outside of the bearing carrier 60. The seal fluid passage communicates with the fluid outlet passage 64. This arrangement helps to prevent fluid from stagnating near the second radial bearing 43, which helps to maintain a stable back pressure for the second radial bearing 43, thereby helping to stabilize the operation of the compressor. Figure 1 and Figure 3 、 Figure 12 As shown in FIGS. 6A and 6B, in some embodiments, the bearing carrier 60 includes a fluid outlet passage 64 that communicates the mounting hole 67 with the outside of the bearing carrier 60. The seal fluid passage communicates with the fluid outlet passage 64. This arrangement helps to prevent fluid from stagnating near the second radial bearing 43, which helps to maintain a stable back pressure for the second radial bearing 43, thereby helping to stabilize the operation of the compressor.

[0225] As shown in FIGS. 6A and 6B, in some embodiments, the seal carrier 70 includes a seal fluid passage in the form of a plurality of grooves 722 formed on the seal positioning stop 72. The number of grooves 722 is not limited and can be, for example, 3-12. The bearing carrier 60 includes a fluid outlet passage 64 that is equal in number to the grooves 722. The fluid outlet passage 64 can be, for example, a borehole formed in the bearing carrier 60. Figure 1 Figure 3 、 Figure 9 to Figure 11 As shown in FIGS. 6A and 6B, in some embodiments, the seal positioning stop 72 includes a bearing positioning end face 721 at the end of the seal disc 71 that is distal to the second radial bearing 43. The bearing positioning end face 721 can be configured to abut a corresponding end face of the second radial bearing 43. This arrangement allows the seal carrier 70 to simultaneously perform the function of axially positioning the second radial bearing 43, which helps to shorten the length of the compressor rotor, reduce the weight of the compressor rotor and the entire compressor, and simplify the structure of the compressor.

[0226] As shown in FIGS. 6A and 6B, in some embodiments, the seal positioning stop 72 includes a bearing positioning end face 721 at the end of the seal disc 71 that is distal to the second radial bearing 43. The bearing positioning end face 721 can be configured to abut a corresponding end face of the second radial bearing 43. This arrangement allows the seal carrier 70 to simultaneously perform the function of axially positioning the second radial bearing 43, which helps to shorten the length of the compressor rotor, reduce the weight of the compressor rotor and the entire compressor, and simplify the structure of the compressor. Figure 1 Figure 3 、

[0227] As shown in FIGS. 6A and 6B, in some embodiments, the seal positioning stop 72 includes a bearing positioning end face 721 at the end of the seal disc 71 that is distal to the second radial bearing 43. The bearing positioning end face 721 can be configured to abut a corresponding end face of the second radial bearing 43. This arrangement allows the seal carrier 70 to simultaneously perform the function of axially positioning the second radial bearing 43, which helps to shorten the length of the compressor rotor, reduce the weight of the compressor rotor and the entire compressor, and simplify the structure of the compressor. Figure 1 Figure 3 、 Figure 12 ​​​As shown, in some embodiments, the mounting hole 67 is a stepped hole, including a large-diameter section near one end of the second diffuser structure and a small-diameter section away from the other end of the second diffuser structure. The shaft seal body 71 is mounted in the large-diameter section and cooperates with the large-diameter section. The shaft seal positioning stop 72 is mounted in the small-diameter section and cooperates with the small-diameter section. A stepped positioning surface 65 is formed between the large-diameter section and the small-diameter section, and the end surface 714 of the shaft seal body 71 near the positioning ring is in clearance fit with the stepped positioning surface 65. This arrangement facilitates the axial positioning of the bearing component 70. At the same time, since the shaft seal component bears the axial positioning function of the second radial bearing 43, it also facilitates the axial positioning of the second radial bearing 43.

[0228] The following further combines Figure 1 、 Figure 3 、 Figure 9 to Figure 12 Some embodiments of the present disclosure are described in more detail.

[0229] As Figure 1 shown, the compressor mainly includes a shell 10, a compressor rotor 20, a motor stator 30, a bearing assembly, a diffuser 50, a bearing carrier component 60, and a shaft seal component 70.

[0230] The shell 10 includes a cylinder body 11 and a first-stage volute 12 and a second-stage volute 13 connected to the left and right ends of the cylinder body 11, respectively. The left end of the cylinder body 11 has an end wall, and the right end is open.

[0231] The diffuser 50, the bearing carrier component 60, and the shaft seal component 70 mounted in the mounting hole 67 of the bearing carrier component 60 are respectively arranged at the left and right ends of the cylinder body 11 and divide the internal space of the shell 10 into a motor accommodating cavity 14 located in the middle of the shell 10, a first compression cavity 15 located at the left end of the shell 10, and a second compression cavity 16 located at the right end of the shell 10.

[0232] The compressor rotor 20 mainly includes a shaft 21, a first impeller 22, a second impeller 23, and a thrust disc component including a thrust disc 24.

[0233] The motor stator 30 is fixed to the inner wall of the cylinder body 11 and has a rotor mounting hole. Spiral grooves can be provided on the inner wall of the cylinder body 11 for passing cooling fluid to cool the motor stator 30.

[0234] The shaft 21 is arranged in the motor stator 30 and penetrates the rotor mounting hole of the motor stator 30. A permanent magnet for generating a magnetic field is provided in the middle of the shaft 21, and first and second shaft sections are respectively provided at the left and right ends of the permanent magnet. Therefore, in this embodiment, the shaft 21 is also a motor rotor of the compressor. The motor stator 30 and the shaft 21 constitute a motor of the compressor. After the winding of the motor stator 30 is energized, the shaft 21 is driven to rotate, thereby driving the entire compressor rotor to rotate.

[0235] The first impeller 22 and the second impeller 23 are fixedly connected to the left and right ends of the rotating shaft 21 respectively. The first impeller 22 and the first diffuser structure of the diffuser 50 are located in the first compression chamber 15. The second impeller 23 and the second diffuser structure on the bearing carrying part 60 are located in the second compression chamber 16.

[0236] The thrust disc part is arranged close to the first impeller 22, which comprises the thrust disc 24 and a thrust disc mounting sleeve arranged integrally. The thrust disc part comprising the thrust disc 24 is fixedly sleeved on the outer periphery of the first shaft section of the rotating shaft 21. The thrust disc mounting sleeve is located between the first impeller 22 and the thrust disc. The thrust disc part comprising the thrust disc 24 can be sleeved on the first shaft section of the rotating shaft 21 by heat shrinkage.

[0237] The bearing assembly comprises a thrust bearing assembly 41, a first radial bearing 42 and a second radial bearing 43.

[0238] As shown in Figure 1 , the thrust bearing assembly 41 comprises a first thrust bearing 411, a second thrust bearing 412 and a thrust bearing positioning ring 413. The first thrust bearing 411, the second thrust bearing 412, the first radial bearing 42 and the second radial bearing 43 are all static pressure gas bearings.

[0239] The left end of the diffuser 50 has a first diffuser structure, such as a diffuser surface or a diffuser blade. The center of the diffuser 50 is provided with a shaft hole, and the shaft hole is provided with a shaft seal structure, such as a comb structure. The thrust disc mounting sleeve of the thrust disc part comprising the thrust disc 24 is located in the shaft hole of the diffuser 50 and cooperates with the shaft seal structure arranged in the shaft hole. The radially outer end of the diffuser 50 is sealingly fixed to the end wall of the cylinder 11, so that the first diffuser 50 isolates the first compression chamber 15 at the left end of the shell 10 from the motor accommodating cavity 14 in the middle of the shell 10.

[0240] As shown in Figure 1 , the right end of the diffuser 50 has a diffuser positioning stop, and the left end of the end wall 112 of the cylinder 11 has a diffuser mounting port. The diffuser positioning stop of the diffuser 50 is mounted in and cooperates with the diffuser mounting port, so as to realize the axial and radial positioning of the diffuser 50. The inside of the diffuser positioning stop of the diffuser 50 and the bottom wall of the diffuser mounting port of the cylinder 11 form a thrust bearing assembly mounting chamber.

[0241] The thrust bearing assembly 41 is arranged in the thrust bearing assembly mounting chamber. The left and right end faces of the thrust disc of the thrust disc part comprising the thrust disc 24 respectively cooperate with the first thrust surface of the first thrust bearing 411 and the second thrust surface of the second thrust bearing 412, so that the thrust disc cooperates with the first thrust bearing 411 and the second thrust bearing 412 to define the axial position of the compressor rotor 20.

[0242] The radially outer end of the first thrust surface of the first thrust bearing 411 is further provided with a first positioning surface, and the radially outer end of the second thrust surface of the second thrust bearing 412 is further provided with a second positioning surface. The left and right end surfaces of the thrust bearing locating ring 413 are clearance-matched with the first and second positioning surfaces, respectively. Thus, the distance between the left and right end surfaces of the thrust bearing locating ring 413 defines the distance between the first and second thrust surfaces, and thus defines the sum of the gaps between the thrust disc and the first thrust surface, and the gaps between the thrust disc and the second thrust surface. The thrust bearing locating ring 413 is fixedly connected to the second thrust bearing 42 and the end wall of the cylinder 11 via threaded connectors.

[0243] The thrust bearing locating ring 413 is provided with a locating ring fluid passage for connecting the radial inner side and the radial outer side thereof. The locating ring fluid passage helps to ensure the back pressure stability of the thrust bearing assembly, thereby facilitating the stable operation of the compressor.

[0244] An end wall bearing chamber is provided in the radially central portion of the end wall of the cylinder 10, housing a first radial bearing 42. The left end of the first radial bearing 42 is clearance-fitted with the side of the second thrust bearing 412 that faces away from the second thrust surface. The right end of the first radial bearing 42 is clearance-fitted with an end wall retaining ring 82 mounted within an end wall retaining groove of the end wall bearing chamber. As a result, the axial position of the first radial bearing 42 is determined by both the second thrust bearing 412 and the retaining ring 82.

[0245] The bearing support member 60 integrates the diffuser ( Figure 1 In the embodiment shown, the second radial bearing 43 is mounted in the bearing housing 62 of the bearing support member 60. The second radial bearing 43 is sleeved on the outer periphery of the second shaft section of the rotating shaft 21.

[0246] The shaft seal component 70 is fixedly mounted in the mounting hole 67 of the bearing support component 60. As previously mentioned, the bearing support component 60 is fixedly mounted on the right end of the cylinder 11. The bearing support component 60 and the cylinder 11 are sealed. After the shaft seal component 70 is mounted on the bearing support component 60 and fitted over the rotating shaft 21, a seal is formed between the shaft seal structure within the shaft hole of the bearing component 70 and the second shaft section of the rotating shaft 21. The radial outer end of the bearing component 70 is sealedly connected to the radial inner end of the bearing support component 60. As a result, the shaft seal component 70 and the bearing support component 60 isolate the second compression chamber 16 of the housing 10 from the motor accommodating chamber 14.

[0247] After the bearing carrier 60, shaft seal 70, and second radial bearing 43 are assembled, the bearing positioning end face 721 of the shaft seal 70 forms a clearance fit with the right end face of the second radial bearing 43, while the left end of the second radial bearing 43 forms a clearance fit with the carrier retaining ring 81. As a result, the axial position of the second radial bearing 43 is determined by the shaft seal 70 and the carrier retaining ring 81. Simultaneously, the shaft seal fluid passages of the shaft seal 70 communicate with the corresponding fluid outflow passages 64 of the bearing carrier 60.

[0248] like Figure 1 As shown, the cylinder 11 is provided with a housing air supply passage 17, which includes a radial bearing air supply passage 171 for supplying working gas to the first radial bearing 42 and the second radial bearing 43. The fluid inlet passage 63 of the bearing support component 60 communicates with the radial bearing air supply passage 171 via a fluid inlet provided on the end face of the diffuser portion thereof. This allows the working gas to enter the bearing chamber of the bearing support component 60, pass through the porous medium of the second radial bearing 43, enter the gap between the second radial bearing 43 and the second shaft section of the rotating shaft 21, and then enter the motor accommodating cavity of the retaining ring 72 of the shaft seal component 70. The working gas then enters the corresponding fluid outlet passage 64 of the bearing support component 60 through each shaft seal fluid passage, enters the motor accommodating cavity 14, and finally exits the housing 10 through an outlet provided on the cylinder 11.

[0249] In this embodiment, the housing air supply channel 17 of the cylindrical body 11 of the housing 10 also includes a thrust bearing air supply channel 172 for supplying working gas to the thrust bearing assembly 41. The thrust bearing air supply channel 172 is independent of the radial bearing air supply channel 171. The working gas in the thrust bearing air supply channel 172 is supplied to the interiors of the first thrust bearing 411 and the second thrust bearing 412, respectively. The working gas enters the gap between the first thrust surface and the thrust disc, and the gap between the second thrust surface and the thrust disc through the porous medium of the first thrust bearing 411 and the porous medium of the second thrust bearing 412, and then flows through the positioning ring fluid channel of the thrust bearing positioning ring 413 to the motor accommodating chamber 14. The positioning ring fluid channel of the thrust bearing positioning ring 413 facilitates the timely removal of the working gas, ensuring stable back pressure of the thrust bearing assembly 41.

[0250] In some embodiments not shown, the thrust bearing supply flow channel 172 can be connected to the radial bearing supply flow channel 171, so that working gas can be supplied to each branch flow channel and each gas bearing corresponding to the branch flow channel through the same shell air inlet and the same main flow channel.

[0251] like Figure 5As shown in the figure, the arrows indicate the flow path of the working gas supplied to the second radial bearing 43. The working gas enters the radial bearing supply channel 171 at the bottom of the cylinder 11, enters the fluid inlet channel 63 of the bearing support component 60, and the bearing chamber 62 of the support component, and is then supplied to the second radial bearing 43. The working gas enters the second radial bearing 43, passes through the porous medium of the second radial bearing 43, and enters the gap between the second radial bearing 43 and the rotating shaft 21. The working gas forms an air film in the gap between the second radial bearing 43 and the rotating shaft 21, causing the rotating shaft 21 to float. The working gas is then discharged from both ends of the gap. The working gas discharged from the left end enters the motor accommodating chamber 14 and is then discharged from the housing 10 along with the cooling gas used to cool the motor. The working gas discharged from the right end passes through the various shaft seal fluid channels in the shaft seal component 70, enters the various fluid outlet channels 64 of the bearing support component 60, enters the motor accommodating chamber 14, and is discharged from the housing 10 along with the cooling gas used to cool the motor.

[0252] Static gas bearings require very high precision, with bearing clearances typically below 10μm. The sealing clearance of the shaft seal component 70 should also be as small as possible while ensuring relative rotation. For example, the sealing clearance can be as low as 0.02mm. Such a small sealing clearance places high demands on the coaxiality between the shaft seal structure and the rotating shaft 21. The shaft seal component 70 is positioned relative to compressor components, such as the bearing support component 70 and the housing 10, through the shaft seal positioning stop 72, which helps ensure the coaxiality between the shaft seal structure and the rotating shaft 21.

[0253] The shaft seal structure is configured as a comb tooth structure, which cooperates with the rotating shaft 21 to prevent the exhaust gas of the second impeller 23 of the compressor from entering the bearing chamber 62 of the bearing bearing component 60, thereby reducing the leakage loss of the compressor and improving the energy efficiency of the compressor. At the same time, it also helps to prevent the back pressure of the bearing chamber 62 of the bearing component from increasing due to excessive leakage.

[0254] The back pressure in the bearing chamber 62 of the bearing assembly affects the distribution of air film pressure between the second radial bearing 43 and the rotating shaft 21, thereby affecting the bearing stiffness and damping. These factors, in turn, affect the rotor's dynamic stability. Furthermore, fluctuations in bearing back pressure can also cause bearing vortex motion. Therefore, maintaining stable back pressure during use in a static gas bearing is crucial for ensuring the stability of the bearing-rotor system. The seal fluid passageway 70 and the fluid outflow passageway 64 of the bearing bearing assembly 60 prevent gas exhausted from the left end from being retained within the seal 70 and bearing bearing assembly 60, effectively preventing unstable back pressure in the second radial bearing 43.

[0255] The bearing positioning end face 721 of the shaft seal component 70 is loosely matched with the right end face of the second radial bearing 43, and together with the bearing component retaining ring 81, limits the axial position of the second radial bearing 43, thereby preventing the second radial bearing 43 from moving left and right and causing bearing instability.

[0256] It can be seen that the shaft seal component 70 of the embodiment of the present disclosure is beneficial to reducing leakage losses while ensuring the stability of the working back pressure of the radial bearing adjacent to the shaft seal component 70, thereby improving the energy efficiency of the compressor and the stability of the bearing rotor system.

[0257] The bearing support component 60 of the disclosed embodiment designs the diffuser and the bearing seat into one part, and provides mounting holes, integrating the functions of the diffuser, the bearing seat and the shaft seal mounting seat, which helps to reduce the number of parts and improve assembly efficiency. At the same time, it can also reduce the length of the compressor rotor and improve the stability of the bearing rotor system.

[0258] Since the bearing support component 60 has a fluid inflow channel 63 and a fluid outflow channel 64, it is beneficial to ensure the normal operation of the second radial bearing 43 and the stability of the working back pressure, which is beneficial to improving the stability of the bearing rotor system. At the same time, it also serves as a diffuser, reduces the number of parts, reduces the length of the compressor rotor, and improves the stability of the bearing rotor system.

[0259] The bearing support component 60 is dually positioned using a support component positioning stop 68 and a diffuser positioning hole 69 in conjunction with a positioning pin. The support component positioning stop 68, along with the right end surface and inner wall of the cylinder 11, ensures the coaxiality of the bearing support component 60 and its support component bearing chamber 62 with the rotating shaft 21, thereby ensuring the coaxiality of the second radial bearing 43 with the rotating shaft 21 after assembly. The pin, in conjunction with the diffuser positioning hole 69, precisely positions the bearing support component 60 in the circumferential direction. Consequently, the bearing support component 60 improves assembly efficiency and accuracy.

[0260] Because the bearing clearance of hydrostatic gas bearings typically ranges from a few microns to tens of microns, rotating machinery supported by hydrostatic gas bearings places extremely high demands on the coaxiality of the two radial bearings. Poor coaxiality can degrade bearing performance and, in severe cases, prevent the rotor from floating. Therefore, the bearing support component 60 and its mating bearing component 70 of the disclosed embodiment are both suitable for compressors supported by hydrostatic gas bearings. Of course, while the shaft seal component 70 of the disclosed embodiment is suitable for compressors using gas bearings, such as centrifugal compressors, this does not preclude the use of the shaft seal component 70 of the disclosed embodiment in other rotating systems.

[0261] like Figure 1 、 Figure 3 、 Figure 12 and Figure 13 As shown, the embodiment of the present disclosure discloses a bearing supporting component 60 .

[0262] The bearing-carrying component 60 comprises a bearing chamber for mounting a radial bearing, a mounting hole 67 coaxial with and communicating with the bearing-carrying component bearing chamber 62, a fluid inlet passage 63 communicating the bearing-carrying component bearing chamber 62 with the outside of the bearing-carrying component 60, and a fluid outlet passage 64 communicating the mounting hole 67 with the outside of the bearing-carrying component.

[0263] The bearing-carrying component 60 comprises a bearing chamber for mounting a radial bearing, a mounting hole 67 coaxial with and communicating with the bearing-carrying component bearing chamber 62, a fluid inlet passage 63 communicating the bearing-carrying component bearing chamber 62 with the outside of the bearing-carrying component 60, and a fluid outlet passage 64 communicating the mounting hole 67 with the outside of the bearing-carrying component, so that working fluid outside the bearing-carrying component 60 can be introduced to the bearing chamber through the fluid inlet passage 63 for use by the radial bearing, and working fluid in the gap between the bearing-carrying component bearing chamber 62 and the radial bearing can be led out of the bearing-carrying component 60 through the fluid outlet passage 64, facilitating the stability of the back pressure of the radial bearing.

[0264] In some embodiments, the bearing-carrying component 60 comprises a diffuser portion and a bearing seat portion. The bearing-carrying component bearing chamber 62 is provided in the bearing seat portion. The diffuser portion is provided alongside the bearing-carrying component bearing chamber 62 in the axial direction of the bearing-carrying component bearing chamber 62 in an integral manner with the bearing seat portion, and the diffuser portion is provided with a diffuser structure at the end thereof away from the bearing seat portion. The mounting hole 67 is provided in the diffuser portion.

[0265] The bearing-carrying component 60 of the embodiments of the present disclosure designs the diffuser and the bearing seat as one part, and at the same time provides a mounting hole, integrating the functions of the diffuser, the bearing seat, and the shaft seal mounting seat, facilitating the reduction of the number of parts, the improvement of assembly efficiency, the reduction of the length of the rotor, and the improvement of the stability of the bearing-rotor system.

[0266] As shown in Figs. Figure 1 , Figure 3 , Figure 12 and Figure 13 In some embodiments, the bearing-carrying component 60 comprises a fluid inlet passage 63 communicating the bearing-carrying component bearing chamber 62 with the outside of the bearing-carrying component 60. The fluid inlet passage 63 can supply the second radial bearing 43 with fluid required for carrying the shaft 21, such as working gas. The fluid inlet passage 63 may, for example, be a hole provided inside the bearing-carrying component 60. The hole diameter of the hole may, for example, be greater than or equal to 3 mm.

[0267] As shown in Figs. Figure 1 , Figure 3 , Figure 12 and Figure 13 In some embodiments, the fluid inlet of the fluid inlet passage 63 is provided on the end face of the diffuser portion at the end thereof close to the bearing seat portion. This arrangement facilitates the introduction of fluid from the outside, such as the housing 10 of the compressor, into the fluid inlet passage 63.

[0268] like Figure 1 、 Figure 3 、 Figure 12 and Figure 13 As shown, in some embodiments, the bearing support component 60 includes a fluid outflow channel 64 connecting the mounting hole 67 with the outside of the bearing support component 60. This arrangement helps prevent fluid from being trapped near the second radial bearing 43, helps maintain a stable back pressure of the second radial bearing 43, and thus helps the compressor operate stably. The fluid outflow channel 64 is a channel provided inside the bearing support component 60. Figure 1 、 Figure 3 、 Figure 12 and Figure 13 As shown, the fluid outlet of the fluid outflow channel 64 is provided on the end surface of the axial second end of the diffuser portion and / or the outer circumferential surface of the bearing seat portion.

[0269] like Figure 1 、 Figure 3 、 Figure 12 and Figure 13 As shown, in some embodiments, the bearing support member 60 includes a plurality of fluid outflow channels 64. This arrangement facilitates rapid and uniform discharge of fluid near related components, such as the second radial bearing 43, and helps prevent fluid from stagnating near related components.

[0270] like Figure 1 、 Figure 3 、 Figure 12 and Figure 13 As shown, in some embodiments, multiple fluid outflow channels 64 are evenly distributed along the circumference of the bearing support component 60. This arrangement facilitates rapid and uniform discharge of fluid near related components, such as the second radial bearing 43, and helps prevent fluid from stagnating near related components.

[0271] like Figure 1 、 Figure 3 、 Figure 12 and Figure 13 As shown, in some embodiments, the plurality of fluid outflow channels 64 are evenly distributed along the circumference of the bearing support component 60 at intervals of 360° / (m+1), where m is the number of the plurality of fluid outflow channels 64. Figure 1 In the illustrated embodiment, m = 5. Fluid inlet channels 63 are located in locations on the circumference of the bearing support component 60 where fluid outlet channels 64 are not located. This arrangement ensures that all fluid channels in the bearing support component 60 are roughly evenly distributed, facilitating fluid channel processing and accurate positioning during assembly of the bearing support component 60. The number and distribution of the shaft seal fluid channels in the shaft seal component 70 described above correspond to the number and distribution of the fluid outlet channels 64 provided on the bearing support component 60.

[0272] like Figure 3 、 Figure 9、 Figure 1 and Figure 3 As shown, in some embodiments, the bearing carrier 60 includes a bearing positioning structure disposed at an end away from the mounting hole 67 for axially positioning the second radial bearing 43. The bearing positioning structure includes a carrier annular groove 66 for mounting a carrier retaining ring 81 for axially positioning the second radial bearing 43. The carrier annular groove 66 is disposed on a side wall of the carrier bearing chamber 62.

[0273] like Figure 9 As shown, in some embodiments, the bearing support component 60 further includes a diffuser mounting hole and / or a diffuser positioning hole 69 provided on the diffuser portion. The diffuser positioning hole 69 is used to cooperate with a positioning pin to circumferentially position the bearing support component 60. The diffuser mounting hole is used to cooperate with a threaded connector to mount the bearing support component 60 on an associated component, such as the compressor casing 10.

[0274] like Figure 1 、 Figure 3 、 Figure 9 and Figure 1 As shown, in some embodiments, the bearing carrier 60 further includes a carrier positioning stop 68 disposed at one end of the diffuser portion near the bearing seat portion. The carrier positioning stop 68 can achieve radial and axial positioning of the bearing carrier 60.

[0275] like Figure 3 、 Figure 9 、 Figure 1 and Figure 4 As shown, in some embodiments, the mounting hole 67 is a stepped hole, comprising a large-diameter section distal to the bearing chamber 62 of the bearing member and a small-diameter section proximal to the bearing chamber 62. A stepped positioning surface 65 is formed between the large-diameter and small-diameter sections. This arrangement facilitates directional and axial positioning between the shaft seal component 70 and the bearing bearing member 60. When the bearing positioning end surface 721 of the shaft seal component 70 is in clearance with the end surface of the second radial bearing 43, it also facilitates axial positioning of the second radial bearing 43.

[0276] like Figure 5 As shown, embodiments of the present disclosure also provide a compressor. The compressor includes a compressor rotor 20, a second radial bearing 43, and a bearing support member 60. The compressor rotor 20 includes a rotating shaft 21. The second radial bearing 43 supports the rotating shaft 21. The bearing support member 60 is similar to the bearing support member 60 of the aforementioned embodiment, with the second radial bearing 43 mounted within a bearing chamber 62 of the bearing support member 60. The bearing support member 60 integrates the functions of a diffuser, a bearing seat, and a shaft seal mounting seat, thereby reducing the number of parts and improving assembly efficiency. It also helps reduce the length of the compressor rotor and improves the operational stability of the compressor.

[0277] As Figure 1 , Figure 3 , Figure 12 shown, in some embodiments, the compressor further comprises a shaft seal component 70. The shaft seal component 70 is installed in the mounting hole 67 of the bearing carrier component 60. The end of the shaft seal component 70 close to the second radial bearing 43 has a bearing positioning end face 721, which is in clearance fit with the end face of the second radial bearing 43. The bearing carrier component 60 simultaneously assumes the functions of mounting the diffuser, bearing seat and shaft seal component, and the installation of the shaft seal component 70 and the second radial bearing 43 in the bearing carrier component 60 is conducive to shortening the length of the compressor rotor and reducing the weight of the compressor rotor, and is conducive to improving the critical speed of the compressor rotor. The cooperation of the bearing carrier component 60, the shaft seal component 70 and the second radial bearing 43 is conducive to making the structure and arrangement of the compressor compact, and enabling rapid and accurate assembly.

[0278] As Figure 13 , Figure 1 , Figure 14 and Figure 1 shown, in some embodiments, the bearing carrier component 60 comprises a fluid outflow channel 64 that communicates the mounting hole 67 with the outside of the bearing carrier component 60, and the shaft seal component 70 comprises a shaft seal fluid channel that communicates the fluid outflow channel 64 with the gap between the second radial bearing 43 and the shaft 21. The shaft seal fluid channel is in communication with the fluid outflow channel 64. This arrangement is conducive to preventing fluid from stagnating near the second radial bearing 43 and to maintaining the back pressure of the second radial bearing 43 stable, thereby facilitating stable operation of the compressor.

[0279] As Figure 14 , Figure 1 and Figure 14 shown, in some embodiments, the shaft seal component 70 comprises a shaft seal disc body 71 and a shaft seal positioning stop 72. The shaft seal disc body 71 has a shaft hole in the center, and the hole wall of the shaft hole is provided with a shaft seal structure. The shaft seal positioning stop 72 is coaxially and integrally arranged at the axial end of the shaft seal disc body 71, and the shaft seal positioning stop 72 is provided with a shaft seal fluid channel that communicates the radial inner side and the radial outer side of the shaft seal positioning stop 72.

[0280] The shaft seal component 70 has the functions of shaft sealing, positioning and discharging fluid, and the shaft seal positioning stop 72 is conducive to improving the cooperation accuracy between the shaft seal component 70 and the sealed shaft 21, and can more effectively prevent fluid leakage. The shaft seal fluid channel is conducive to preventing fluid from stagnating in components such as the second radial bearing 43 that cooperate with the shaft seal component 70, and is conducive to stabilizing the back pressure of the related components, thereby facilitating the improvement of the stability of the bearing rotor system.

[0281] As Figure 14 , Figure 15 and Figure 18As shown, in some embodiments, the shaft seal positioning stop 72 has a bearing positioning end face 721 for axially positioning the second radial bearing 43 at the end away from the shaft seal disc body 71. The bearing positioning end face 721 enables the shaft seal component 70 to have the axial positioning function of the second radial bearing 43, which is conducive to simplifying the structure of the device in which the shaft seal component 70 is used and shortening the rotor length of the device in which the shaft seal component 70 is used.

[0282] The structure of the shaft seal fluid passage can be various, for example, as shown in Figure 14 , Figure 15 and Figure 18 , in some embodiments, the shaft seal fluid passage includes a groove 722 recessed from the end away from the shaft seal disc body 71 to the end close to the shaft seal disc body 71. In embodiments not shown, the shaft seal fluid passage can include at least one through hole provided on the side wall of the shaft seal positioning stop 72. The groove and the through hole can also be provided simultaneously as the shaft seal fluid passage.

[0283] As shown in Figure 14 , Figure 16 and Figure 16 , in some embodiments, the shaft seal component 70 includes a plurality of shaft seal fluid passages. The plurality of shaft seal fluid passages are uniformly arranged along the circumference of the shaft seal positioning stop 72. This arrangement is conducive to the rapid and uniform discharge of fluid near the relevant components such as the second radial bearing 43, and is conducive to preventing the fluid from stagnating near the relevant components.

[0284] In some embodiments, the plurality of shaft seal fluid passages are uniformly arranged at an angle of 360° / n+1 along the circumference of the shaft seal positioning stop 72, where n is the number of the plurality of shaft seal fluid passages. The number n can be 2, 3, 4, 5, 6 or more. As shown in the embodiments of Figure 16 , Figure 17 and Figure 18 , n = 5. The number and distribution of the shaft seal fluid passages are conducive to corresponding to the number and distribution of the fluid outflow passages 64 provided on the bearing load-carrying component 60. This arrangement is conducive to the bearing load-carrying component 60 cooperating to form a fluid discharge passage, and is conducive to reserving a setting position for the fluid inlet passage of the relevant components.

[0285] In addition, the shaft seal component 70 includes a shaft seal connecting hole 712 and a shaft seal positioning hole 713 provided on the shaft seal disc body 71. The shaft seal positioning hole 713 can accurately determine the connection position between the shaft seal component 70 and the bearing load-carrying component 60, which is conducive to quickly and accurately realizing the communication between the shaft seal fluid passage and the fluid outflow passage 64 of the bearing load-carrying component 60. The shaft seal connecting hole 712 is conducive to realizing the detachable connection with the relevant components through a threaded connecting piece.

[0286] As shown in Figure 17 , Figure 18 , Figure 17 andFigure 18 As shown, in some embodiments, the mounting hole 67 is a stepped hole, including a large-diameter section near one end of the diffuser structure and a small-diameter section away from the other end of the diffuser structure. The shaft seal body 71 is mounted in the large-diameter section and cooperates with the large-diameter section. The shaft seal positioning stop 72 is mounted in the small-diameter section and cooperates with the small-diameter section. A stepped positioning surface 65 is formed between the large-diameter section and the small-diameter section. An end surface 714 of the shaft seal body 71 near the positioning ring is in clearance fit with the stepped positioning surface 65. This arrangement facilitates axial positioning of the bearing component 70. At the same time, since the shaft seal component bears the axial positioning function of the second radial bearing 43, it also facilitates axial positioning of the second radial bearing 43.

[0287] As shown, the bearing carrier component 60 further includes a carrier component positioning stop 68 arranged on the diffuser portion near the bearing seat portion, and a diffuser portion positioning hole 69 and a diffuser portion mounting hole arranged on the diffuser portion. The carrier component positioning stop 68 cooperates with the end wall 112 on the right side of the motor cylinder 11 of the shell 10 of the compressor to determine the radial and axial positions of the bearing carrier component 60. The bearing carrier component 60 is circumferentially positioned between the shell 10 by a positioning member passing through the diffuser portion positioning hole 69, and is fixedly connected to the shell 10 by a threaded connecting member passing through the diffuser portion mounting hole. Figure 17

[0288] Other details related to the bearing carrier component 60 can be referred to the relevant descriptions in the rest of this disclosure.

[0289] Figure 18 The internal structure of the rotating shaft 21 of the compressor of the embodiment shown is shown. Figure 17 The internal structure of the rotating shaft 21 of the compressor of the embodiment shown is shown.

[0290] As shown, in one embodiment of the rotating shaft 21 provided in this disclosure, the rotating shaft 21 includes a permanent magnet 211, a first shaft section 212, a second shaft section 213, and a sheath 214. The permanent magnet 211 is a solid cylinder. The permanent magnet 211 is arranged between the first shaft section 212 and the second shaft section 213. The sheath 214 is integrally arranged with the first shaft section 212 and is sleeved around the outer periphery of the permanent magnet 211 and the second shaft section 213. The sheath 214 is used to connect the first shaft section 212, the permanent magnet 211, and the second shaft section 213. Figure 18 In this embodiment, the first shaft section 212, the second shaft section 213, and the sheath 214 constitute the shaft body of the rotating shaft 21, and the permanent magnet 111 is arranged inside the shaft body.

[0291] As shown, in one embodiment of the rotating shaft 21 provided in this disclosure, the rotating shaft 21 includes a permanent magnet 211, a first shaft section 212, a second shaft section 213, and a sheath 214. The permanent magnet 211 is a solid cylinder. The permanent magnet 211 is arranged between the first shaft section 212 and the second shaft section 213. The sheath 214 is integrally arranged with the first shaft section 212 and is sleeved around the outer periphery of the permanent magnet 211 and the second shaft section 213. The sheath 214 is used to connect the first shaft section 212, the permanent magnet 211, and the second shaft section 213.

[0292] Figure 17 and Figure 17 ​​As shown, the end faces of the left and right ends of the rotating shaft 21 are respectively provided with threaded holes, and the first impeller locking member 25 and the second impeller locking member 26 matched with the threaded holes at the two ends can lock the first impeller 22 and the second impeller 23 sleeved on the left and right ends of the rotating shaft 21 on the rotating shaft 21. Figure 19 In the embodiment shown, the first impeller locking member 25 and the second impeller locking member 26 are locking screws matched with the threaded holes at the two ends of the rotating shaft 21.

[0293] In the embodiment shown, the threaded holes at the two ends of the main shaft are not drawn. Figure 19 、 16 and Figure 19 In the embodiment shown, the threaded holes at the two ends of the main shaft are not drawn.

[0294] In the embodiment not shown, external threads can also be provided at the two ends of the rotating shaft 21, and at this time, the first impeller locking member 25 and the second impeller locking member 26 are locking nuts matched with the external threads at the two ends of the rotating shaft 21.

[0295] In some embodiments, the rotating shaft 21 includes a solid permanent magnet 211, which can increase the electromagnetic intensity of the rotating shaft 21, reduce the volume of the permanent magnet 211, and be beneficial to the miniaturization of the compressor; at the same time, the linear speed of the outer surface of the permanent magnet 211 is reduced, the centrifugal force on the permanent magnet 211 and the sheath 214 is reduced, and the overall structural strength of the rotating shaft 21 is enhanced. The sheath 214 connects the first shaft section 212, the permanent magnet 211 and the second shaft section 213, which can effectively protect the permanent magnet 211, realize reliable connection of each component, and effectively improve the overall structural strength of the rotating shaft 21.

[0296] As shown, Figure 19 The sheath 214 can be integrally provided with one shaft section and is in thermal connection with the other shaft section and the permanent magnet. As shown, Figure 1 、 16 、 Figure 4 In the rotating shaft 21 shown, the sheath 214 is a separately provided component.

[0297] The rotating shaft 21 further includes a limiting structure for limiting the axial movement of the sheath 214. As shown, Figure 19 The limiting structure can be a limiting boss 2139 provided at one axial end of the sheath 214.

[0298] The limiting structure is a limiting boss, which can facilitate the close contact between the first shaft section 212, the permanent magnet 211 and the second shaft section 213, avoid the existence of gaps between the first shaft section 212, the permanent magnet 213 and the second shaft section 213 due to manufacturing errors or assembly errors, and reduce the structural strength of the rotating shaft 21.

[0299] The sheath 214 is in interference fit with the first shaft segment 212, the permanent magnet 211 and the second shaft segment 213. In this way, the sheath 214 can be tightly combined with the first shaft segment 212, the permanent magnet 211 and the second shaft segment 213 during the operation of the rotating shaft 21, and no relative movement occurs, so that the connection strength between the sheath 214 and the first shaft segment 212, the permanent magnet 211 and the second shaft segment 213 is enhanced, and the structural stability of the rotating shaft 21 during high-speed rotation is ensured.

[0300] The limiting boss 2139 can be arranged on the first shaft segment 212 and integrally formed with the first shaft segment 212. The limiting boss 2139 can also be arranged on the second shaft segment 213 and integrally formed with the second shaft segment 213.

[0301] The first shaft segment 212 includes a first large-diameter segment close to the permanent magnet 211, and the second shaft segment 213 includes a second large-diameter segment close to the permanent magnet 211. The diameters of the first large-diameter segment and the second large-diameter segment are the same as the diameter of the permanent magnet 211. In this way, the interference fit between the sheath 214 and the first shaft segment 212, the permanent magnet 211 and the second shaft segment 213 can be achieved.

[0302] The length of the permanent magnet 211 is greater than the lengths of the first large-diameter segment and the second large-diameter segment. The length of the permanent magnet 211 is increased as much as possible to increase the electromagnetic intensity.

[0303] The lengths of the first large-diameter segment and the second large-diameter segment are equal, which is conducive to ensuring the uniform stress of the rotating shaft 21.

[0304] As shown in FIG. Figure 19 In some embodiments, the first shaft segment 212 and / or the second shaft segment 213 can be provided with weight-reducing holes.

[0305] The number of weight-reducing holes can be flexibly set according to actual needs. In some embodiments, the number of weight-reducing holes arranged on the first shaft segment 212 is the same as the number of weight-reducing holes arranged on the second shaft segment 213, and the weight-reducing holes are symmetrically arranged about the permanent magnet 211.

[0306] For example, Figure 19 In the embodiment shown in FIG.

[0307] The weight-reducing holes can have various forms. For example, Figure 19 In the embodiment shown in FIG.

[0308] In an embodiment not shown, exhaust holes can also be provided on the first shaft segment 212 and / or the second shaft segment 213. By providing the exhaust holes, gaps between the first shaft segment 212 and the permanent magnet 211 and between the permanent magnet 211 and the second shaft segment 213 due to mixed gas can be prevented when the rotating shaft 21 is assembled, and the overall structural strength of the rotating shaft 21 can be reduced. The exhaust holes can also serve the purpose of weight reduction.

[0309] The exhaust holes can be provided alone so that the end faces of the first shaft segment 212 and / or the second shaft segment 213 close to the permanent magnet 211 are communicated with the external environment, and the exhaust function is achieved.

[0310] The exhaust holes can also be provided in cooperation with the weight reduction holes, for example, the first shaft segment 212 and the second shaft segment 213 are provided with weight reduction holes extending from the end faces away from the permanent magnet 211 to the direction close to the permanent magnet 211, the exhaust holes are communicated with the weight reduction holes, and the exhaust holes extend to the end faces of the first shaft segment 212 and the second shaft segment 213 close to the permanent magnet 211.

[0311] As shown in Figure 19 and Figure 19 , the rotating shaft 21 can also be provided with a cooling flow channel inside, and the cooling flow channel is used for passing cooling medium. The cooling flow channel includes a shaft segment cooling flow channel provided in the first shaft segment 212 and / or the second shaft segment 213. The cooling flow channel can also include a permanent magnet cooling flow channel provided in the permanent magnet 211. By providing the cooling flow channel, the rotating shaft 21 can be cooled, which is beneficial to prevent the rotating shaft 21 from being too high in temperature during operation, and effectively protect the rotating shaft 21.

[0312] As shown in Figure 12 and Figure 13 , the first shaft segment 212 is provided with a first cooling hole 2122; the second shaft segment 213 is provided with a second cooling hole 2132; and the permanent magnet 211 is provided with a third cooling hole 2111, and the third cooling hole 2111 is respectively communicated with the first cooling hole 2122 and the second cooling hole 2132. The cooling flow channel includes the first cooling hole 2122 and the second cooling hole 2132 as shaft cooling flow channels and the third cooling hole 2111 as a permanent magnet cooling flow channel.

[0313] As shown in Figure 19 and Figure 20 to Figure 27As shown, the plurality of first cooling holes 2122 are uniformly arranged around the circumference of the first shaft segment 212, and each first cooling hole 2122 is inclined towards the axis of the first shaft segment 212 from the end far away from the permanent magnet 211 to the end close to the permanent magnet 211. The plurality of second cooling holes 2132 are uniformly arranged around the circumference of the second shaft segment 213, and each second cooling hole 2132 is inclined towards the axis of the second shaft segment 213 from the end far away from the permanent magnet 211 to the end close to the permanent magnet 211. This arrangement can concentrate the cooling medium from the outer circumference of the rotating shaft 21 to the permanent magnet 211, achieving efficient cooling of the permanent magnet 211.

[0314] In some embodiments, the cooling flow channel can include an axial hole arranged along the axial direction of the rotating shaft 21, and a communication hole in communication with the axial hole and the circumferential surface of the rotating shaft 21. The axial hole can be arranged on at least one of the first shaft segment 212, the permanent magnet 211 and the second shaft segment 213. The communication hole can be a radial hole.

[0315] In other embodiments of the rotating shaft 21 provided by the present disclosure, the weight-reducing holes, the exhaust holes and the cooling flow channels can be freely combined, and the exhaust holes and the cooling flow channels can also serve the purpose of weight reduction.

[0316] When the rotating shaft 21 of the plurality of embodiments of the present disclosure adopts a solid permanent magnet 211, the electromagnetic intensity can be increased, and under the premise of needing to achieve the same electromagnetic intensity, the size of the rotating shaft 21 can be effectively reduced. By arranging a limiting boss, axial limiting can be achieved, and at the same time, gaps between the first shaft segment 212 and the permanent magnet 211 and between the permanent magnet 211 and the second shaft segment 213 will not occur due to manufacturing errors. By connecting the first shaft segment 212, the permanent magnet 211 and the second shaft segment 213 through the sheath 214, the permanent magnet 211 can be effectively protected, and at the same time, the structural strength of the rotating shaft 21 can be improved, ensuring safe and reliable operation of the rotating shaft 21 at high speed. The weight-reducing holes, the exhaust holes and the cooling flow channels are provided, further improving the comprehensive performance of the rotating shaft 21.

[0317] Based on the above-mentioned rotating shaft 21, the present disclosure further provides an electric machine, which includes the above-mentioned rotating shaft 21.

[0318] The present disclosure further provides a compressor. The compressor includes the above-mentioned electric machine. The compressor is a centrifugal compressor.

[0319] The following will be described in detail Figure 20 and Figure 20 The compressor with the cooling flow channel of some embodiments of the present disclosure will be described in detail.

[0320] It should be noted that Figure 20For the purpose of focusing on the cooling process of the cooling fluid inside the cooling channel of the rotating shaft 21 and in the compressor, some related content described in other embodiments of the present disclosure is not shown, but those skilled in the art can understand that the cooperation structure between the rotating shaft 21 and other components of the compressor, such as the shell 10 and the motor stator 30, of the embodiments of the present disclosure is applicable to other embodiments of the present disclosure.

[0321] As shown in Figure 20 , the rotating shaft 21 provided by the embodiments of the present disclosure comprises: a permanent magnet 211; and a shaft body arranged outside the permanent magnet 211, used for carrying the permanent magnet 211 and enabling the permanent magnet 211 to rotate around the rotating shaft of the rotating shaft 21. Wherein, the shaft body is provided with a shaft cooling channel, and two ends of the shaft cooling channel are connected to the permanent magnet 211 and the outside of the shaft body respectively, so that the cooling medium outside the shaft body can be conducted to the permanent magnet 211 through the shaft cooling channel.

[0322] Since the rotation of the rotating shaft 21 needs to rely on the magnetic field generated by the permanent magnet 211, the embodiments of the present disclosure wrap the permanent magnet 211 inside the shaft body, and open the shaft cooling channel in the shaft body, so as to realize the air flow interaction between the permanent magnet 211 and the outside of the shaft body, so that the permanent magnet 211 can be cooled by the cooling medium outside the shaft body.

[0323] After the cooling medium outside the shaft body is conducted to the permanent magnet 211, the inside of the permanent magnet 211 and the shaft body can be cooled in various ways. For example, the corresponding shaft cooling channel can be arranged on the surface of the shaft body connected with the permanent magnet 211, so that the cooling medium can flow through the outer surface of the permanent magnet 211 and the inner surface of the shaft body.

[0324] As shown in Figure 23 , Figure 20 , the shaft body has a shaft shoulder, and the shaft segment cooling channel is arranged obliquely from the shaft shoulder to the axis of the rotor.

[0325] The shaft segment cooling channel is opened from the shaft shoulder of the shaft body and extends obliquely to the permanent magnet 211, which can make the length of the shaft segment cooling channel as long as possible, and enable the inlet of the shaft segment cooling channel to simultaneously receive the cooling medium along the axial and radial directions of the rotating shaft 21.

[0326] Since the shaft segment cooling channel is opened in the rotating shaft 21, it will affect the balance of the rotating shaft 21 during operation. Based on this, in some embodiments, the number of shaft segment cooling channels is 4-8, and the shaft segment cooling channels are evenly arranged on the shaft body along the circumferential direction of the shaft body.

[0327] The cooling effect of the shaft segment cooling flow channels on the permanent magnet 211 and the shaft body is enhanced with the increase of the number of the shaft segment cooling flow channels, but the number of the shaft segment cooling flow channels is also affected by the size of the shaft shoulder end face. If too many shaft segment cooling flow channels are opened from the end face of the shaft shoulder of the shaft body, the mechanical strength of the entire shaft body will be reduced. Therefore, considering both, the number of the shaft segment cooling flow channels is selected to be 4-8, which can meet the cooling needs of the shaft segment cooling flow channels and the size strength needs of the shaft shoulder end face.

[0328] As described above, the shaft segment cooling flow channels include the first cooling hole 2122 arranged in the first shaft segment 212, and the second cooling hole 2132 arranged in the second shaft segment 213.

[0329] In some embodiments, in order to improve the rotation stability of the shaft body during rotation, and taking into account the influence of the shaft segment cooling flow channels on the rotor structural strength, in some embodiments, the number of the shaft segment cooling flow channels is even, and the aperture range of the shaft segment cooling flow channels is 3-5 mm.

[0330] In some embodiments, the permanent magnet 211 includes a permanent magnet cooling flow channel in communication with the shaft segment cooling flow channel.

[0331] The permanent magnet cooling flow channel includes at least one third cooling hole 2111 in the axial direction of the rotating shaft 21, which is in communication with the shaft segment cooling flow channel, and can make the cooling medium flow through the inside of the permanent magnet 211.

[0332] The third cooling hole 2111 in the axial direction of the rotating shaft 21 opened in the inside of the permanent magnet 211 cooperates with the shaft segment cooling flow channel to guide the cooling medium outside the shaft body to flow through the third cooling hole 2111, thereby cooling the permanent magnet 211 from the inside.

[0333] By connecting the shaft segment cooling flow channel of the shaft body through the third cooling hole 2111, a one-way cooling flow path can be formed inside the shaft body, i.e. the cooling medium can flow in from the shaft segment cooling flow channel arranged on the shaft body at one end of the permanent magnet 211, then flow out from the shaft segment cooling flow channel arranged on the shaft body at the other end of the permanent magnet 211 after passing through the third cooling hole 2111 inside the permanent magnet 211. The above-mentioned one-way cooling flow path can effectively avoid the accumulation and poor flow of the cooling medium inside the shaft body and the permanent magnet 211, and improve the cooling effect on the shaft body and the permanent magnet 211.

[0334] The shaft body includes a first shaft segment 212, a second shaft segment 213, and a sheath 214. The first shaft segment 212 has a first large-diameter segment that abuts the first end of the permanent magnet 211. The second shaft segment 213 has a second large-diameter segment that abuts the second end of the permanent magnet 211. The second large-diameter segment is provided with a first protruding ring at the end away from the permanent magnet. The sheath 214 is sleeved outside the first large-diameter segment of the first shaft segment 212, the permanent magnet 211, and the second large-diameter segment of the second shaft segment 213, and is positioned along the axial direction of the rotating shaft 21 by the first protruding ring. In this embodiment, the first protruding ring is the limiting protrusion 2139 described above.

[0335] By the shaft body composed of the first shaft segment 212, the second shaft segment 213, and the sheath 214, the shaft body and the fixed installation of the shaft body on the permanent magnet 211 can be better achieved. Specifically, first, the first shaft segment 212, the second shaft segment 213, and the permanent magnet 211 are fixed along the axial direction of the rotating shaft 21 (for example, by bonding), and then the sheath 214 is sleeved outside the first shaft segment 212, the second shaft segment 213, and the permanent magnet 211 in a hot-jacketing manner, and forms an interference fit with the first shaft segment 212, the second shaft segment 213, and the permanent magnet 211. Moreover, the sheath 214 is sleeved into the first large-diameter segment of the first shaft segment 212 and is positioned along the axial direction of the rotating shaft 21 by the first protruding ring of the second shaft segment 213.

[0336] By the above installation and fixing method, the shaft body can ensure the relative positional relationship of the components fixed during high-speed rotation of the rotating shaft 21, and enhance the integrity of the rotating shaft 21. In addition, the first shaft segment 212, the second shaft segment 213, and the sheath 214 are separately processed, which is conducive to improving the machining precision of each component and improving the production efficiency. In addition, it is also helpful to ensure that the shaft segment cooling flow channel and the third cooling hole 2111 can smoothly flow along the axial direction of the rotating shaft 21 after the first shaft segment 212, the second shaft segment 213, and the sheath 214 are assembled.

[0337] Correspondingly, in some embodiments, each shaft segment cooling flow channel is inclinedly opened to the permanent magnet 211 from the end face of the first large-diameter segment perpendicular to the shaft axis of the shaft body and away from the permanent magnet 211, and the end face of the second large-diameter segment perpendicular to the axial direction of the rotating shaft 21 and away from the permanent magnet 211.

[0338] In some embodiments, the shaft segment cooling flow channel can be inclinedly opened to the permanent magnet 211 to the axis of the rotating shaft 21. The above-mentioned shaft segment cooling flow channel inclinedly opened to the permanent magnet 211 to the axis of the rotating shaft 21 includes the case that the end of the shaft segment cooling flow channel is directly opened to the axis of the rotating shaft 21, and also includes the case that the extension line of the shaft segment cooling flow channel is opened to the axis of the rotating shaft 21, and the specific case is determined according to the length of the shaft body along the axial direction and the angle at which the shaft segment cooling flow channel is opened.

[0339] Since the rotating shaft 21 includes the permanent magnet 211, in this embodiment, the rotating shaft 21 is also the motor rotor of the compressor. In order to ensure a smooth surface of the motor rotor after assembly, in some embodiments, the outer diameter of the sheath 24 is the same as the outer diameter of the first protruding ring.

[0340] In some embodiments, the first large diameter section of the first shaft segment 212 and the second large diameter section of the second shaft segment 213 have the same outer diameter and are interference fit with the sleeve 24. Furthermore, the permanent magnet 211 and the sleeve 24 may also be interference fit to strengthen the connection between the shaft body and the permanent magnet 211 and improve the operational reliability of the compressor motor.

[0341] In order to prevent the shaft segment cooling channel and the third cooling hole 2111 from being misaligned, in some embodiments, the first shaft segment 212, the second shaft segment 213 and the permanent magnet 211 respectively have positioning grooves along the axial direction of the rotating shaft 21, and the positioning grooves can be inserted with guide rods to position the first shaft segment 212, the second shaft segment 213 and the permanent magnet 211 along the circumference of the shaft body.

[0342] like Figure 23 As shown, the embodiment of the present disclosure also provides a compressor, including: a cylinder 11; a motor stator 30, mounted on the cylinder 11; and a rotating shaft 21 as described above, rotatably mounted on the cylinder 11 and arranged inside the motor stator, capable of rotating relative to the motor stator 30 under the drive of electromagnetic force.

[0343] In some embodiments, there is a spiral cooling channel 113 extending axially along the rotating shaft 21 between the motor stator 30 and the cylinder 11, and there is a fitting gap G between the motor stator 30 and the rotating shaft 21; the refrigerant of the compressor can flow through the spiral cooling channel 113, the fitting gap G, the shaft segment cooling channel of the shaft body and the permanent magnet cooling channel in the permanent magnet 211, thereby cooling the motor stator 30 and the rotating shaft 21.

[0344] Through the spiral cooling channel 113 and the clearance G, the inner and outer surfaces of the motor stator 30 are evenly exposed to the cooling medium and effectively dissipate heat, maintaining the motor stator 30 within a suitable temperature range. Furthermore, the clearance G also cools the exterior of the rotating shaft 21. Combined with the cooling channels of the motor rotor formed by the shaft segment cooling channel and the permanent magnet cooling channel, the motor rotor can also effectively dissipate heat from both its inner and outer surfaces.

[0345] In some embodiments, the compressor includes a cooling medium inlet 114, disposed at one end of the barrel 11, for introducing the cooling medium into the spiral cooling channel 113; and a cooling medium outlet 115, disposed at the same end of the barrel 11 as the cooling medium inlet 114, for guiding the cooling medium out of the compressor after cooling the motor stator 30 and the rotating shaft 21. The cooling medium may be, for example, a working fluid compressed by the compressor, such as a refrigerant.

[0346] When the compressor is used in a refrigerant circulation system and the cooling medium is refrigerant, Figure 20 As shown, the arrows represent the flow direction and path of the cooling fluid. Based on the above-mentioned setting of the cooling medium inlet 114 and the cooling medium outlet 115, the low-temperature liquid refrigerant enters from the cooling medium inlet 114 and flows to the spiral cooling channel 113 between the cylinder 11 and the motor stator 30, and takes away the heat from the inner surface of the cylinder 11 and the outer surface of the motor stator 30; the liquid refrigerant is vaporized after fully absorbing heat in the spiral cooling channel 113, and flows out from the outlet of the spiral cooling channel 113 in the form of gas, and gathers in the motor accommodating cavity 14 formed by the first shaft section 212 and the cylinder 11; as the gaseous refrigerant accumulates in the motor accommodating cavity 14, the pressure gradually increases, and the refrigerant located in the first shaft section 212 is cooled. A portion of the gaseous refrigerant 12 flows through the gap between the motor stator 30 and the rotating shaft 21, and the other portion flows from the first cooling hole 2122 opened in the first shaft segment 212 to the third cooling hole 2111 inside the permanent magnet 211, and after sufficient heat exchange in the third cooling hole 2111, it flows out from the second cooling hole 2132 opened in the second shaft segment 213; at this time, both portions of the gaseous refrigerant are guided to the motor accommodating cavity 14 between the second shaft segment and the cylinder 11, and flow out of the compressor through the cooling medium outlet 115 opened in the cylinder 11, and take away the heat absorbed during the flow.

[0347] Based on the above technical solution, the embodiment of the present disclosure opens a shaft cooling channel connected to the permanent magnet 211 in the shaft body, so that the permanent magnet 211 can be cooled by the cooling medium outside the shaft body, thereby improving the heat dissipation effect of the shaft body and the permanent magnet 211.

[0348] In addition, the cooling channel composed of the cooling channel of the shaft main body shaft section and the permanent magnet cooling channel of the permanent magnet 211 is added to the entire heat dissipation cycle in the compressor, so that the cooling medium can continuously take away the heat of the rotating shaft 21 and maintain the rotating shaft 21 within a reasonable temperature range.

[0349] like Figure 20 As shown, the present disclosure provides compressors with modified structures according to some of the aforementioned embodiments.

[0350] like Figure 20The figure is a cross-sectional schematic view of some embodiments of a compressor according to the present disclosure. In some embodiments, the compressor comprises a housing 10, a motor stator 30, a rotating shaft 21 and a gas bearing. The motor stator 30 and the rotating shaft 21 are both disposed within the housing 10. A fit clearance G is formed between the motor stator 30 and the rotating shaft 21. At least one impeller can be included within the housing 10. The at least one impeller is fixedly connected with the rotating shaft 21 and can rotate with the rotating shaft 21. The gas bearing is disposed within the housing 10 and supports the rotating shaft 21. The rotating shaft 21 is also a motor rotor of the compressor.

[0351] In some embodiments, the compressor further comprises a housing gas supply channel 17. The housing gas supply channel 17 is disposed within the housing 10 and is used to connect an external gas source and supply working gas provided by the external gas source to the gas bearing. The external gas source can accurately and with less loss enter the gas bearing through the housing gas supply channel 17.

[0352] Reference Figure 26 In some embodiments, the gas bearing can comprise a first thrust bearing 411 and a second thrust bearing 412 and a first radial bearing 42. The first thrust bearing 411 and the second thrust bearing 412 are respectively located on the left side and the right side of a thrust disc 24 fixedly connected with the rotating shaft 21, and can realize the support function of the rotating shaft 21 in the axial direction. The first radial bearing 42 is sleeved on the rotating shaft 21 and supports the rotating shaft 21 in the radial direction.

[0353] For the above-mentioned gas bearing, the housing gas supply channel 17 can comprise a radial bearing gas supply channel 171 and a thrust bearing gas supply channel 172. The radial bearing gas supply channel 171 is disposed within the housing 10 and is used to connect an external gas source and supply working gas provided by the external gas source to the first radial bearing 42. In Figure 27 In some embodiments, the radial bearing gas supply channel 171 can be opened inside the shell wall of the housing 10 and can comprise a plurality of sub-channels in the horizontal and vertical directions. These linear sub-channels can further reduce the pressure loss of the gas along the way. The end of the radial bearing gas supply channel 171 can be directly aligned with the outer ring of the first radial bearing 42, so that the working gas of the external gas source can accurately and with less loss enter the first radial bearing 42. The working gas entering the first radial bearing 42 can penetrate into the gap between the first radial bearing 42 and the rotating shaft 21 through the porous material of the first radial bearing 42, forming a static pressure gas support effect.

[0354] The thrust bearing gas supply passage 172 is provided in the housing 10 for connecting an external gas source and supplying the working gas from the external gas source to the first thrust bearing 411 and the second thrust bearing 412. The thrust bearing gas supply passage 172 can be formed in the housing wall of the housing 10 and one end thereof is aligned with the right side end surface of the second thrust bearing 412 for supplying gas to the second thrust bearing 412, and the other end thereof is aligned with the diffuser gas supply passage 51 of the diffuser 50 for cooperating with the diffuser gas supply passage 51 to supply gas to the first thrust bearing 411. The working gas from the external gas source can be accurately and less lostly supplied to the first thrust bearing 411 and the second thrust bearing 412 by forming the thrust bearing gas supply passage 172 in the housing 10 and aligning the end thereof with the left side end surface of the first thrust bearing 411. The thrust bearing gas supply passage 172 can include a plurality of sub-paths in horizontal and vertical directions, and the linear sub-paths can further reduce the pressure loss of the gas along the path. The working gas supplied to the first thrust bearing 411 and the second thrust bearing 412 can penetrate into the gap between the first thrust bearing 411 and the thrust plate 24 and the gap between the second thrust bearing 412 and the thrust plate 24 through the porous material of the bearings to form a static pressure gas support.

[0355] Considering that the gas pressure required by the thrust bearing and the radial bearing can be different, in some embodiments, the radial bearing gas supply passage 171 and the thrust bearing gas supply passage 172 are arranged separately in the housing 10. In other words, the radial bearing gas supply passage 171 and the thrust bearing gas supply passage 172 are independent of each other and do not directly communicate with each other in the internal passage of the housing 10. For example, the first gas inlet of the radial bearing gas supply passage 171 on the outside of the housing and the second gas inlet of the thrust bearing gas supply passage 172 on the outside of the housing are arranged at different positions of the housing 10, and the radial bearing gas supply passage 171 is not directly communicated with the thrust bearing gas supply passage 172. In this way, the first gas inlet and the second gas inlet can be connected to external gas sources of different pressures, thereby meeting the working gas supply of the gas bearing more in line with the working conditions, and making the gas supply passage structure simpler.

[0356] In order to facilitate the connection of the external gas source with the gas inlet and reduce the interference problem during the connection of the external pipeline, it is preferred that the first gas inlet of the radial bearing gas supply passage 171 on the housing 10 and the second gas inlet of the thrust bearing gas supply passage 172 on the housing 10 are arranged in opposite directions of the housing 10, for example, arranged below and above the housing 10. As shown in the embodiments of Figure 20 and Figure 20 , the first gas inlet of the radial bearing gas supply passage 171 on the housing 10 and the second gas inlet of the thrust bearing gas supply passage 172 on the housing 10 are arranged at an angle of 90 degrees in the direction of the housing 10.

[0357] In some embodiments, the compressor further comprises an exhaust device. Referring to Figure 21 The suction port of the exhaust device is located on the shell 10, which is capable of sucking the working gas flowing out from the gap between the first radial bearing 42 and the rotating shaft 21 and flowing to the end of the motor stator 30 axially away from the first radial bearing 42 (i.e. Figure 22 the region B in the motor accommodating cavity 14) of the motor stator 30 via the gap between the motor stator 30 and the rotating shaft 21. In this way, the working gas inputted from outside of the compressor can be more easily exhausted from the compressor to the outside, so as to ensure the stability of the gas supply without the need of setting a special device for collecting the working gas, thereby optimizing the internal space of the compressor. In addition, the cooling effect of the motor stator 30 and the rotating shaft 21 can be achieved by the working gas flowing through the cooperation gap G between the motor stator 30 and the rotating shaft 21.

[0358] In Figure 22 the shell 10 and the motor stator 30 can be provided with a cooling gas flow channel, such as a spiral cooling flow channel 113. The outlet of the cooling gas flow channel is located at the end of the motor stator 30 axially close to the first radial bearing 42. In this way, the cooling gas entering the cooling gas flow channel can flow out from the outlet of the cooling gas flow channel and mix with the working gas flowing out from the gap between the gas bearing and the rotating shaft 21 at the end of the motor stator 30 close to the first radial bearing 42 (i.e. Figure 23 the region A in the motor accommodating cavity 14), and the mixed gas medium then flows to the end of the motor stator 30 away from the first radial bearing 42 (the region B) via the gap between the motor stator 30 and the rotating shaft 21.

[0359] After the cooling gas mixes with the working gas, the cooling effect of the motor stator 30 and the rotating shaft 21 can be achieved when the mixed gas flows through the motor stator 30 and the rotating shaft 21, and the mixed gas can also be sucked by the exhaust device to be exhausted to the outside of the shell, so as to make the circulation of the gas inside and outside of the compressor more smooth and ensure the stability of the working inside the compressor. The cooling gas and the working gas can be the same medium or different medium. Preferably, the cooling gas and the working gas are both the working substance compressed by the compressor, such as refrigerant.

[0360] Referring to Figure 23In some embodiments, the compressor includes two-stage impellers, each of which is fixedly connected to both ends of the rotating shaft 21, with each gas bearing located between the two-stage impellers. The first thrust bearing 411, the second thrust bearing 412, and the first radial bearing 42 of the gas bearing are all disposed on the rotating shaft 21 at an end near the first impeller 22. The gas bearing also includes a second radial bearing 43, which supports the rotating shaft 21 at an end near the second impeller 23. In some embodiments, the first impeller 22 is a primary impeller, and the second impeller 23 is a secondary impeller; in other embodiments, the first impeller 22 can be a primary impeller, and the second impeller 23 can be a secondary impeller.

[0361] To install the second radial bearing 43 , the second radial bearing 43 may be supported by a bearing support member 60 disposed within the housing 10 . The radial bearing air supply passage 171 is also used to supply the second radial bearing 43 with working gas provided by an external gas source.

[0362] refer to Figure 23 、 Figure 24 and Figure 25 In some embodiments, the radial bearing air supply channel 171 communicates with the second radial bearing 43 via a bearing inflow channel 63 defined in the bearing support member 60, thereby supplying working gas from an external source to the second radial bearing 43. The bearing support member 60 includes a bearing chamber 62 for supporting the second radial bearing 43. A vent group is provided between the bearing chamber 62 and the surface of the bearing support member 60 on the side proximate to the motor stator 30, serving as a bearing structure outflow channel 64. The vent group may include at least one vent 51 distributed along the circumference of the bearing support member 60. The vent group is capable of directing the working gas flowing out of the gap between the second radial bearing 43 and the rotating shaft 21 toward region B on the side of the bearing support member 60 on the side proximate to the motor stator 30. The working gas entering region B may be absorbed by the exhaust device and discharged from the housing.

[0363] refer to Figure 21 In some embodiments, the compressor further includes a shaft seal component 70 disposed between the rotating shaft 21 and the bearing support component 60 for forming a seal on one axial side of the second radial bearing 43. The bearing support component 60 and the shaft seal component 70 can be described with reference to the relevant descriptions of the previous embodiments, and will not be repeated here.

[0364] The following combination Figure 22 The bearing seat assembly structure of some embodiments of the present disclosure and the compressor having the bearing seat assembly structure are described.

[0365] like Figure 24 FIG2 is a schematic diagram of the structure of some embodiments of the bearing seat assembly structure disclosed in the present invention. Figure 25In some embodiments, the bearing housing assembly includes a bearing housing and a gas bearing. The bearing housing is internally provided with a gas supply passage which is in communication with a gas source outside or inside the device in which the bearing housing assembly is arranged. The gas bearing is arranged on the bearing housing to support the rotating shaft 21. In Figure 25 some embodiments, the gas bearing is a radial bearing which is arranged on the inner side of the bearing housing in the radial direction to support the rotating shaft 21 by static pressure gas in the radial direction. In other embodiments, the gas bearing is a thrust bearing which is arranged on the left or right side of the bearing housing in the axial direction to support the rotating shaft 21 by static pressure gas in the axial direction.

[0366] The aforementioned bearing housing and gas bearing can be, for example, a radial bearing housing arranged on the end wall 112 of the cylinder 11 and a first radial bearing 42 arranged in the radial bearing housing on the left end in Figure 21 and Figure 20 to Figure 27 . The gas supply passage at this time refers to a branch passage of the radial bearing gas supply passage 171 for supplying gas to the first radial bearing 42.

[0367] The aforementioned bearing housing and gas bearing can also be a bearing housing portion of the bearing support member 60 arranged on the right end and a second radial bearing 43 arranged in the bearing support member bearing chamber 62 of the bearing support member in Figure 1 to Figure 2 and Figure 4 to Figure 5 . The gas supply passage at this time refers to another branch passage of the radial bearing gas supply passage 171 for supplying gas to the second radial bearing 43 and the bearing support member inflow passage 63 of the bearing support member 60 which is in communication with the other branch passage.

[0368] Referring to Figure 19 , an annular intake cavity P can be arranged between the bearing housing and the gas bearing, and the annular intake cavity P is in communication with the gas supply passage. By arranging the annular intake cavity P between the gas bearing and the bearing housing and making the annular intake cavity P in communication with the gas supply passage inside the bearing housing, the working gas from the gas supply passage can be gathered in the annular intake cavity P to increase the pressure of the working gas itself, achieving the effect of pressurization to improve the stiffness and load capacity of the gas bearing. Moreover, the annular intake cavity P also makes the working gas more uniform in the circumferential direction of the gas bearing, thereby improving the working stability of the gas bearing. In this way, the working performance of the gas bearing is effectively improved.

[0369] In Figure 28 , the rotating shaft 21 can be supported by two radial bearings and corresponding bearing housings. The gas supply passage in the bearing housing can be arranged according to the shape of the bearing housing, for example, the bearing housing on the left side can include gas supply passages arranged in the vertical direction (perpendicular to the axis of the rotating shaft 21) and the horizontal direction (parallel to the axis of the rotating shaft 21) and in communication with each other. For another example, the bearing housing on the right side can include gas supply passages arranged in the horizontal direction, the vertical direction and the oblique direction (at an acute or obtuse angle to the axis of the rotating shaft 21) and in communication with each other.

[0370] In Figure 29 the right side bearing seat can also refer to Figure 2 and Figure 5 , in the embodiment, the bearing seat can be a bearing seat part of the bearing carrying part 60. In some embodiments, the bearing seat can include a bearing mounting hole. In the embodiment, the bearing mounting hole can be a bearing part chamber 62 of the bearing carrying part 60. A gas bearing is located in the bearing mounting hole to achieve radial support to the rotating shaft 21. In the embodiment, the gas bearing can be the second radial bearing 43. A plurality of gas flow channels can also be provided on the bearing seat to communicate the bearing mounting hole and the outside of the bearing seat. In the embodiment, the gas flow channel can be a bearing part outflow passage 64 of the bearing carrying part. The gas flow channel is located at the right side of the gas bearing near one end of the bearing mounting hole, and extends to the left side of the bearing seat at the other end, so that the gas at the right side of the gas bearing can flow to the left side area of the bearing seat through the gas flow channel. For example, the left side area of the bearing seat is in communication with the suction device of the compressor, and the high-pressure stage gas at the right side of the bearing seat flows to the left side of the bearing seat through the gas flow channel and is recovered by the suction device.

[0371] Referring to Figure 2 , in some embodiments, the annular gas inlet cavity P includes a first annular groove R1 provided on the hole wall of the bearing mounting hole. Since the first annular groove R1 is in communication with the gas supply flow channel in the bearing seat and is close to the circumferential outer wall of the gas bearing, the working gas entering the first annular groove R1 can be gathered at the circumferential outer wall of the gas bearing to achieve pressurization. The pressure of the working gas can form a uniform distribution on the entire circumference of the gas bearing in the first annular groove R1, improving the stability of the gas bearing operation.

[0372] Referring to Figure 1 , Figure 28 and Figure 29 , in some embodiments, the annular gas inlet cavity P further includes a gas inlet hole group H. The gas inlet hole group H is provided on the circumferential outer wall of the gas bearing and is in communication with the first annular groove R1. The gas inlet hole group H can guide the pressurized working gas gathered through the first annular groove R1 into the gas bearing to form static pressure.

[0373] In order to better guide the working gas, at least part of the orifices of the gas inlet hole group H on one side of the circumferential outer wall can be directly opposite the first annular groove R1. Preferably, all the orifices of the gas inlet hole group H on one side of the circumferential outer wall of the gas bearing are directly opposite the first annular groove R1, so that the working gas can flow more smoothly into the gas bearing.

[0374] In Figure 28In some embodiments, the group of air inlet holes H can include a plurality of air inlet holes (e.g., 5 or more) distributed along the circumference of the gas bearing. This can allow the working gas to enter the gas bearing from multiple circumferential locations, thereby improving the efficiency and uniformity of the working gas entering the gas bearing. The plurality of air inlet holes can be evenly distributed along the circumference of the gas bearing, thereby further improving the uniformity of the working gas entering the gas bearing and improving the stability of the gas bearing.

[0375] In addition to the group of air inlet holes on the gas bearing, other structures can be provided to assist in pressurizing and uniformly introducing the working gas into the gas bearing. For example, Figure 29 FIG. 6 shows a schematic diagram of another embodiment of a bearing housing assembly according to the present disclosure. Referring to FIG. 6, Figure 30 In some embodiments, the annular air inlet cavity P further includes a second annular groove R2. The second annular groove R2 is provided on the circumferential outer wall of the gas bearing and is in communication with the first annular groove R1. The second annular groove R2 and the first annular groove R1 can collectively collect the working gas from the gas supply channel and more uniformly direct the working gas into the gas bearing in the circumferential direction, thereby improving the stiffness, load capacity, and stability of the gas bearing and effectively improving the performance of the gas bearing.

[0376] To better direct the working gas, at least a portion of the slot on the side of the circumferential outer wall of the second annular groove R2 can be directly opposite the first annular groove R1. Preferably, the entire second annular groove R2 is directly opposite the first annular groove R1, so that the working gas can more smoothly enter the gas bearing.

[0377] Referring to FIG. 6, Figure 30 , Figure 30 and Figure 30 In some embodiments, the width of the second annular groove R2 can be the same as the width of the first annular groove R1, while in other embodiments, the width of the second annular groove R2 can be different from the width of the first annular groove R1. In addition, in some embodiments, the gas bearing is located in the bearing mounting hole, the annular air inlet cavity P23 can include the second annular groove R2, and the outlet of the gas supply channel is in communication with the second annular groove R2. The first annular groove R1 provided in the bearing mounting hole can be omitted, so that the second annular groove R2 can also achieve the effect of collecting and uniformly directing the working gas, and the machining of the bearing housing can be simplified.

[0378] In some embodiments, a sealing structure can be provided between the bearing housing and the gas bearing, and the sealing structure is located on at least one side of the annular air inlet cavity P. The sealing structure can prevent the working gas from leaking during the process of entering the gas bearing, thereby improving the efficiency of the working gas and the stability of the gas bearing.

[0379] Referring to FIG. 6, Figure 30 ,Figure 30 、 Figure 30 and Figure 30 In some embodiments, the sealing structure comprises a sealing ring (not shown in the figures) and a third annular groove R3 arranged on the gas bearing, and the sealing ring is arranged in the third annular groove R3. The sealing ring can be compressed between the surface of the gas bearing and the bearing seat, separating the annular gas inlet cavity P from the outside of the gas bearing and the bearing seat, and forming a gas-tight effect.

[0380] In some embodiments, the gas bearing is a radial bearing, and the sealing ring can be arranged on the radial outer side of the gas bearing. In other embodiments, the gas bearing is a thrust bearing, and the sealing ring can be arranged on the side of the gas bearing close to the bearing seat in the axial direction.

[0381] Referring to Figure 30 In some embodiments, the bearing seat comprises a bearing mounting hole, the gas bearing is arranged in the bearing mounting hole, and the sealing structure comprises a plurality of third annular grooves R3 arranged in the axial direction of the gas bearing. A sealing ring can be arranged in each third annular groove R3. Preferably, a third annular groove and a sealing ring are arranged on both sides of the annular gas inlet cavity P in the axial direction to increase the sealing effect and simplify or eliminate the arrangement of the sealing structure outside the bearing seat and the gas bearing.

[0382] According to needs, a plurality of third annular grooves R3 can be arranged in two depths respectively, and the third annular grooves R3 of the two depths are arranged in the axial direction of the gas bearing. In this way, sealing rings of different widths and thicknesses can be arranged according to needs.

[0383] Figure 30 、 22 , 24, 25, the second radial bearing 43 is taken as an example to illustrate the radial bearing, and the radial bearing structure in these figures is also applicable to the first radial bearing 42.

[0384] The above-mentioned bearing seat assembly structure of the embodiments of the present disclosure can be applied to various devices requiring assembly of a gas bearing, such as a compressor. Accordingly, the embodiments of the present disclosure also provide a compressor comprising a housing, a rotating shaft 21 and any one of the above-mentioned bearing seat assembly structure embodiments. The bearing seat assembly structure is arranged inside the housing. Here, the compressor can be a centrifugal compressor. In other embodiments, it can also be other compressors, such as a screw compressor, a sliding vane compressor, etc. In order to simplify the gas supply structure inside the housing, the gas supply flow channel arranged inside the bearing seat of the bearing seat assembly structure can be in operable communication with the gas source outside the housing.

[0385] Figure 31 to Figure 34 The parts not described in the above-mentioned embodiments can refer to the related contents of other embodiments.

[0386] The gas supply flow channel of the compressor of some embodiments of the present disclosure is described below.

[0387] As Figure 31 , Figure 31 , Figure 31 , Figure 31 and Figure 31 indicated, the compressor of some embodiments of the present disclosure comprises: a housing 10 having a receiving space; a rotating shaft 21 rotatably arranged in the receiving space; a diffuser 50; a gas thrust bearing; and a gas supply passage comprising a diffuser gas supply passage 51 formed on the diffuser 50 and used for supplying gas to the gas thrust bearing. The gas thrust bearing is, for example, a first thrust bearing 411 and a second thrust bearing 412.

[0388] The compressor of the embodiments of the present disclosure directly supplies gas to the gas thrust bearing by forming the diffuser gas supply passage 51 on the diffuser 50, which is simple in structure and convenient to process.

[0389] The compressor of the embodiments of the present disclosure further comprises a first impeller 22 connected to an end of the rotating shaft 21, the diffuser 50, a thrust disc 24, the first thrust bearing 411 and the second thrust bearing 412 respectively arranged on the axial two sides of the thrust disc 24, and a first radial bearing 42 used for rotatably supporting the rotating shaft 21 in the housing 10. The first impeller 22 and the rotating shaft 21 are fixedly connected by a first impeller locking member 25.

[0390] The gas thrust bearing and the gas radial bearing of the embodiments of the present disclosure both comprise a porous medium. The gas supply passage supplies gas to the porous medium. The gas thrust bearing comprises the first thrust bearing 411 and the second thrust bearing 412, and the gas radial bearing comprises the first radial bearing 42.

[0391] The gas supply passage of the embodiments of the present disclosure further comprises a housing gas supply passage 17 formed on the housing 10.

[0392] As Figure 31 and Figure 32 to Figure 34 indicated, in some embodiments, the housing gas supply passage 17 comprises two gas supply passages, which are respectively a radial bearing gas supply passage 171 and a thrust bearing gas supply passage 172. The radial bearing gas supply passage 171 supplies gas to the gas thrust bearing, and the thrust bearing gas supply passage 172 supplies gas to the first radial bearing 42 (as shown). Figure 32 to Figure 34 As Figure 32 to Figure 34 indicated, the radial bearing gas supply passage 171 communicates with the diffuser gas supply passage 51 to supply gas to the first thrust bearing 411, and the radial bearing gas supply passage 171 directly supplies gas to the second thrust bearing 412. The gas enters the gap between the thrust bearing and the thrust disc 24 through throttling inside the thrust bearing and forms a gas film with pressure, which acts on the thrust disc 24 to offset the system axial force. The gas enters the gap between the first radial bearing 42 and the rotating shaft 21 to form a gas film, which lubricates the support of the rotating shaft 21.

[0393] As mentioned above, the diffuser gas supply passage 51 includes an introduction passage, a communication passage and an exit passage. The communication passage is arranged in the radial direction of the compressor and its end is provided with a plug to prevent gas leakage; the introduction passage is arranged in the axial direction and its inlet is arranged on the end surface of the diffuser 50 to communicate with the thrust bearing gas supply passage 172 on the casing 10 to introduce working gas; the exit passage is arranged in the axial direction and its outlet is arranged on the end surface of the diffuser 50 opposite to the back surface of the first thrust bearing 411 to supply working gas in the diffuser gas supply passage 51 to the first thrust bearing 411.

[0394] The casing gas supply passage 17 of the present embodiment is provided with two part gas supply passages, a radial bearing gas supply passage 171 to supply gas to the radial bearing and a thrust bearing gas supply passage 172 to supply gas to the thrust bearing, that is, the thrust bearing and the radial bearing are supplied with gas separately and the gas supply pressure of the two part gas supply passages is adjustably arranged to prevent gas hammer vibration and improve system stability. Moreover, the centrifugal compressor of the present embodiment forms the gas supply passages by drilling holes on the diffuser 50 and the casing 10, which is simple in structure and convenient to process.

[0395] As shown in Figs. 1 and 2, the casing gas supply passage 17 of the present embodiment includes a radial bearing gas supply passage 171 and a thrust bearing gas supply passage 172 which are in communication with each other, and a gas supply source is provided for the gas thrust bearing and the gas radial bearing to supply gas thereto in common, so that the gas supply pressure of all the gas bearings can be adjusted by adjusting the gas supply pressure of the gas supply source, which is convenient to adjust. Figure 32 to Figure 34 Figure 32 As shown in Figs. 1 and 2, the casing gas supply passage 17 of the present embodiment includes a radial bearing gas supply passage 171 and a thrust bearing gas supply passage 172 which are in communication with each other, and a gas supply source is provided for the gas thrust bearing and the gas radial bearing to supply gas thereto in common, so that the gas supply pressure of all the gas bearings can be adjusted by adjusting the gas supply pressure of the gas supply source, which is convenient to adjust.

[0396] As shown in Figs. 1 and 2, the casing gas supply passage 17 of the present embodiment includes a radial bearing gas supply passage 171 and a thrust bearing gas supply passage 172 which are in communication with each other, and a gas supply source is provided for the gas thrust bearing and the gas radial bearing to supply gas thereto in common, so that the gas supply pressure of all the gas bearings can be adjusted by adjusting the gas supply pressure of the gas supply source, which is convenient to adjust. Figure 33 Figure 34 As shown in Figs. 1 and 2, the casing gas supply passage 17 of the present embodiment includes a radial bearing gas supply passage 171 and a thrust bearing gas supply passage 172 which are in communication with each other, and a gas supply source is provided for the gas thrust bearing and the gas radial bearing to supply gas thereto in common, so that the gas supply pressure of all the gas bearings can be adjusted by adjusting the gas supply pressure of the gas supply source, which is convenient to adjust.

[0397] ​​The air supply pressure of the casing air supply duct 17 of this embodiment is adjustable. Specifically, the air supply pressure of the casing air supply duct 17 of this embodiment is adjusted based on the pressure of the receiving space and the vibration of the main shaft. During compressor operation, the air supply pressure of the casing air supply duct 17 can be adjusted based on the pressure of the receiving space and the vibration of the main shaft, thereby adjusting the stiffness and load-bearing capacity of the bearing and preventing air hammer vibration.

[0398] In some embodiments, the compressor further includes a throttle valve connected to the casing air supply passage 17 , and the throttle valve operates to control the air supply pressure of the casing air supply passage 17 .

[0399] For parts not described in this embodiment, reference may be made to the relevant contents of other embodiments.

[0400] like Figure 32 As shown, the present disclosure also provides a compression unit having a comb-teeth sealing structure and a compressor having the compression unit.

[0401] The following combination Figure 32 The technical solution provided by the present disclosure is described in more detail. Figure 32 Only the partial structure of the compressor is shown. Figure 32 The structure shown is applicable to the compressor of any of the aforementioned embodiments.

[0402] The compression unit includes an impeller and a diffuser. The impeller and / or the pressure protector 50 include a comb-teeth seal structure for sealing the gap between the impeller and the diffuser 50. In this embodiment, the impeller may be the first impeller 22, and the diffuser 50 may be the diffuser 50. In other embodiments, the comb-teeth seal structure may also be provided on the second impeller 23 and / or the diffuser portion of the bearing support component.

[0403] like Figure 32 As shown, the compressor provided by the present disclosure includes: a casing; a rotating shaft 21 rotatably mounted on the casing; an impeller fixedly arranged on the rotating shaft 21 and capable of rotating with the rotating shaft 21; and a diffuser mounted on the casing and located on the side of the impeller away from the incoming flow direction along the axial direction of the rotating shaft 21; wherein the impeller and / or the pressure protector 50 includes: a comb tooth sealing structure for sealing the gap between the impeller and the diffuser 50.

[0404] Figure 32The disclosure is only schematically described by the structure between the first impeller 22, the rotating shaft 21 and the diffuser 50 located at the left side of the compressor in one embodiment, and only the comb seal structure arranged on the first impeller 22 is schematically shown. Based on the understanding of the following description, those skilled in the art can understand that the comb seal structure arranged on the diffuser has the same technical effect, and therefore the disclosure does not describe the comb seal structure arranged on the diffuser. Similarly, those skilled in the art can also know that for other structures of the centrifugal compressor, for example, the compressor supported by the rolling bearing, the oil film bearing or the magnetic suspension bearing, the single-stage, double-stage or multi-stage compressor, the comb seal structure arranged on the impeller and / or the diffuser to seal the gap between them can also achieve good sealing effect.

[0405] The shell is a box structure with a containing space. Based on this, the shell and the diffuser 50 jointly constitute a fixed part that does not rotate with the rotating shaft 21, and on the contrary, the first impeller 22 and the rotating shaft 21 jointly constitute a rotating part, which is a component of the compressor rotor. Therefore, the gap between the first impeller 22 and the diffuser 50 and the gap between the rotating shaft 21 and the diffuser 50 are the matching relationship between the rotating part and the fixed part.

[0406] For the first impeller 22, the airflow therein is subjected to the rotating action of the first impeller 22 to increase the pressure, and therefore the airflow in the airflow passage of the first impeller 22 will be much greater than the air pressure outside the first impeller 22. The airflow in the airflow passage of the first impeller 22 always has a tendency to leak from the gap between the first impeller 22 and the diffuser 50, and further from the gap between the rotating shaft 21 and the diffuser 50, that is, as shown in the figure, the leakage tendency from left to right along the axial direction of the rotating shaft 21. Figure 33

[0407] The embodiment of the disclosure sets the comb seal structure to seal the gap between the first impeller 22 and the diffuser 50, thereby improving the sealing performance of the first impeller 22, reducing the leakage loss, and improving the overall working efficiency of the compressor.

[0408] The comb seal structure is a sealing form in which a plurality of combs are arranged side by side, and a gap is formed between the comb tips and the surface of the diffuser 50. The principle of the comb seal is that:

[0409] Each comb and the diffuser 50 can form a small hole throttling structure. By the pressure reduction and throttling effect of the small hole throttling structure, a plurality of combs are arranged side by side at the matching gap, so that the airflow is continuously subjected to pressure reduction and throttling from the high-pressure side to the low-pressure side, and the pressure of the airflow is no longer higher than the ambient pressure, thereby forming a good sealing effect at the matching gap.

[0410] ​The small holes of the small hole throttling structure formed by the comb seal structure and the surface of the diffuser 50 are the gaps between each comb tooth tip and the surface of the diffuser 50. According to the distance of the small hole throttling, as the gap between each comb tooth tip and the diffuser 50 decreases, that is, as the size of the small hole of the small hole throttling structure decreases, the small hole throttling structure will have greater pressure reduction throttling capacity.

[0411] In addition, after passing through the gap between each comb tooth and the surface of the diffuser 50, the airflow enters the space between the combs. When entering the space between the combs, the airflow will generate a large pressure drop due to the sudden expansion effect and generate strong backflow. The backflow generated by the airflow in the space between the combs further reduces the flow-through area between the combs and the surface of the diffuser 50, further strengthening the throttling effect of the small hole throttling.

[0412] In some embodiments, the diffuser 50 is in a clearance fit with the first impeller 22 along the radial direction of the rotating shaft 21, and the comb seal structure includes: a first comb structure 221 arranged on the first impeller 22 (and / or the diffuser 50) along the radial direction of the rotating shaft 21. The first comb structure can form a clearance fit with the diffuser 50 (and / or the first impeller 22) smaller than the fit clearance between the first impeller 22 and the diffuser 50.

[0413] Since the diffuser 50 is located on the side of the first impeller 22 away from the flow direction along the axial direction of the rotating shaft 21, that is, the diffuser 50 and the rotating shaft 21 have a fit relationship along the axial direction of the rotating shaft 21. In order to make the overall structure of the compressor compact, reduce the leakage generated from the gap between the first impeller 22 and the diffuser 50 as much as possible, and ensure that there is no mechanical interference between the first impeller 22 as a rotating part and the diffuser 50 as a fixed part, the diffuser 50 is in a clearance fit with the first impeller 22 along the radial direction of the rotating shaft 21.

[0414] For this fit clearance, the first comb structure 221 is arranged to seal. In order to ensure the sealing effect, the first comb structure 221 forms a clearance with the diffuser 50 smaller than the fit clearance between the first impeller 22 and the diffuser 50. As shown in Figure 33 The first comb structure 221 is arranged on the first impeller 22.

[0415] As shown in Figure 33 A first annular groove 501 for accommodating the first comb structure 221 can be formed on the end face of the diffuser 50 opposite to the first comb structure 221 along the circumferential direction of the rotating shaft 21.

[0416] As mentioned above, for those skilled in the art, the first comb structure 221 can also be arranged on the diffuser 50. The clearance between the first comb structure 221 and the first impeller 22 can be smaller than the fit clearance between the first impeller 22 and the diffuser 50.

[0417] The first comb structure 221 arranged on the first impeller 22 is easier to process and can obtain higher processing precision, which helps to accurately control the gap size between the first comb structure 221 and the diffuser 50. Accordingly, the first comb structure 221 arranged on the diffuser 50 can obtain better stability, i.e., avoiding the change of the corresponding matching gap due to the deflection or eccentricity of the first comb structure 221 during the rotation process of the rotating shaft 21.

[0418] In some embodiments, the comb seal structure comprises a second comb structure 222 arranged on the first impeller 22 along the axial direction of the rotating shaft 21. The second comb structure 222 can form a gap matching smaller than the matching gap between the first impeller 22 and the diffuser 50 with the diffuser 50.

[0419] Due to the fact that the first impeller 22 and the diffuser 50 are both non-flat structures along the radial direction of the rotating shaft 21, a gap matching is also formed during the matching process of the first impeller 22 and the diffuser 50 along the rotating shaft 21. For this gap, the second comb structure 222 can be arranged. Similar to the first comb structure 221, the second comb structure 222 can be selectively arranged on the first impeller 22 or the diffuser 50, and the corresponding technical effects are similar to those of the first comb structure 221, which will not be described here.

[0420] In some embodiments, the diffuser 50 further comprises a second annular groove 502 arranged on the end face of the diffuser 50 close to the first impeller 22 along the circumferential direction of the rotating shaft 21, for accommodating the second comb structure 222. In some embodiments, the second comb structure 222 forms a gap matching with the side surface of the rotating shaft 21 close to the second annular groove 502.

[0421] In order to match the second comb structure 222 arranged along the axial direction of the rotating shaft 21, the diffuser 50 can be provided with a corresponding second annular groove 502 to increase the length of the matching gap between the first impeller 22 and the diffuser 50 along the axial direction of the rotating shaft 21, thereby allowing more teeth of the comb seal structure to be arranged.

[0422] When the second comb structure is arranged on the diffuser 50, the second annular groove can be arranged on the first impeller 22 accordingly. The arrangement of the second comb structure and the second annular groove in this way can reduce the weight of the first impeller 22 and the driving force required for rotating the first impeller 22. Accordingly, arranging the second comb structure 222 and the second annular groove 502 on the first impeller 22 and the diffuser 50 respectively can utilize the stability of the fixing member of the diffuser 50 to increase the depth of the second annular groove 502 as much as possible while maintaining sufficient mechanical strength.

[0423] In order to ensure that the second comb structure 222 can be accurately inserted into the second annular groove 502, in some embodiments, the width of the second annular groove 502 is greater than the thickness of the second comb structure 222 by 1-2 mm along the radial direction of the rotation shaft 21, and the depth of the second annular groove 502 is greater than the height of the second comb structure 222 by 1-2 mm along the axial direction of the rotation shaft 21.

[0424] It should be noted that the width of the second annular groove 502 being greater than the thickness of the second comb structure 222 by 1-2 mm does not mean that the fitting gap between the second comb structure 222 and the diffuser 50 is 1-2 mm. The fitting gap between the second comb structure 222 and the diffuser 50 is also affected by the radial position of the second comb structure 222 in the second annular groove 502, i.e., determined by the gap between the second comb structure 222 and the second annular groove 502.

[0425] In some embodiments, the second comb structure 222 can be arranged radially outside or radially inside the first comb structure 221.

[0426] Compared with the first impeller 22 and the diffuser 50 only having the first comb structure 221 or the second comb structure 222, the compressor provided by the embodiments of the present disclosure can also have both the first comb structure 221 and the second comb structure 222, so as to further increase the sealing length between the first impeller 22 and the diffuser 50, and improve the number of combs used to seal the gap between the first impeller 22 and the diffuser 50, thereby improving the sealing effect.

[0427] The second comb structure 222 can be arranged radially outside the first comb structure 221, so as to contact the high-pressure air in the first impeller 22 earlier than the first comb structure 221, and form the first sealing for the high-pressure air in the first impeller 22 through the tortuous path provided by the second comb structure 222 and the second annular groove 502 by using the principle of labyrinth sealing.

[0428] In order to ensure the sealing effect of the comb sealing structure, in some embodiments, the first comb structure 221 and / or the second comb structure 222 includes at least 7 combs.

[0429] And in order to enable the orifice restriction structure formed by each comb to generate greater pressure drop through the sudden expansion effect after the airflow passes through the gap, in some embodiments, the combs are inclined tooth structures, and the tooth tip of each comb is inclined to the high-pressure side of the gap between the first impeller 22 and the diffuser 50 relative to the tooth root of the same comb.

[0430] As an embodiment of the inclined tooth structure of the first comb structure 221 and / or the second comb structure 222, in some embodiments, the comb teeth are right trapezoids in the cross-sectional shape perpendicular to the circumferential direction of the rotating shaft 21, and the waist of each right trapezoid is close to the high-pressure side of the gap between the first impeller 22 and the diffuser 50.

[0431] The comb teeth with the cross-sectional shape of right trapezoids can be machined more easily as the positioning tooth surface with a waist perpendicular to the bottom surface, and ensure that the machining precision of the comb teeth meets the requirements.

[0432] In some embodiments, the diffuser 50 is in a gap fit with the rotating shaft 21; the diffuser 50 includes a first shaft seal structure 56 arranged on the side of the diffuser 50 close to the rotating shaft 21 in the axial direction of the rotating shaft 21, for sealing the gap between the diffuser 50 and the main shaft. ​ In the illustrated embodiment, the first shaft seal structure 56 is a comb structure.

[0433] The diffuser 50 is in a gap fit with the rotating shaft 21, and the first shaft seal structure 56 arranged on the fit surface of the diffuser 50 with the rotating shaft 21, so as to perform a third level of sealing on the basis of the sealing formed by the first comb structure 221 and the second comb structure 222. Considering that the diffuser 50 is a fixed part and the rotating shaft 21 is a rotating part, the comb seal structure is preferably arranged on the diffuser 50 to prevent the influence of the deflection of the rotating shaft 21 on the fit gap.

[0434] In order to ensure the sealing effect of the first shaft seal structure 56 and considering the influence of the axial space, in some embodiments, the first shaft seal structure 56 includes 8-10 comb teeth, and the tooth width of the comb teeth at both ends of the first shaft seal structure 56 is greater than or equal to 2 mm. And the two ends of the first shaft seal structure 56 can be machined into bevel angles to weaken the airflow intensity entering the first shaft seal structure 56.

[0435] Since the first shaft seal structure 56 is fixed on the diffuser 50 in an axial arrangement, the fit surface with the rotating shaft 21 needs to be ensured to be horizontal, and in some embodiments, the concentricity of the plane of the first shaft seal structure 56 fit with the rotating shaft 21 and the rotating shaft 21 is less than or equal to 0.02 mm.

[0436] In some embodiments, the compressor includes an anti-seizure member with a hardness lower than that of the diffuser 50 and the first impeller 22, and arranged in the region where the diffuser 50 and the first impeller 22 are in a gap fit.

[0437] The anti-biting member can be embedded on the diffuser 50 or the first impeller 22 to prevent the first impeller 22 and the diffuser 50 from being directly mechanically damaged due to mutual biting of the first impeller 22 and the diffuser 50 during rotation and work of the first impeller 22. For the first impeller 22 or the diffuser 50 made of aluminum material, the anti-biting member can be embedded on the aluminum material base of the first impeller 22 and / or the diffuser 50 by using a soft material to protect the area where the diffuser 50 and the first impeller 22 are in clearance fit. In addition, during installation, the second comb structure 222 on the first impeller 22 is preferably contacted and positioned before the shaft 21, which effectively prevents the second comb structure 222 from being stressed in the axial direction.

[0438] In some embodiments, the present disclosure also provides a refrigerant circulation system including the compressor described above.

[0439] The following will be described in combination with ​ Some refrigerant circulation systems of the present disclosure are described.

[0440] ​ A schematic diagram of a refrigerant circulation system of an embodiment of the present disclosure is shown. As ​ shown, the refrigerant circulation system includes a main refrigerant circuit including a main circuit compressor 100, a condenser 200, a throttling device, and an evaporator connected by a main refrigerant pipeline 900. ​ The throttling device and the evaporator are not shown in FIG. 1.

[0441] The refrigerant compressed by the main circuit compressor 100 enters the condenser 200, and the refrigerant condensed in the condenser 200 enters the evaporator after being throttled and reduced in pressure by the throttling device. The refrigerant evaporated in the evaporator returns to the suction port of the main circuit compressor 100.

[0442] The main circuit compressor 100 includes a first compression part 110 and a second compression part 120, and the exhaust port of the first compression part 110 is in communication with the intake port of the second compression part 120. The second compression part 120 is used to compress the refrigerant compressed by the first compression part 110.

[0443] The main circuit compressor 100 is, for example, the compressor of the foregoing embodiments. In combination with the accompanying drawings of the foregoing compressor, the main circuit compressor 100 includes a shaft 21 used to drive the first compression part 110 and the second compression part 120.

[0444] In this embodiment, the first compression unit 110 and the second compression unit 120 are respectively mounted at both ends of the rotating shaft 21. The first compression unit 110 includes a first impeller 22 for accelerating the refrigerant to be compressed and a first diffuser (e.g., diffuser 50) for compressing the refrigerant accelerated by the first impeller 22. The first impeller 22 is connected to the first end of the rotating shaft 21.

[0445] The second compressor 120 includes a second impeller 23 for accelerating the refrigerant compressed by the first compressor 110 and a second diffuser (e.g., the diffuser portion of the bearing support 60) for compressing the refrigerant accelerated by the second impeller 23. The second impeller 23 is connected to the second end of the rotating shaft 21.

[0446] The main circuit compressor 100 also includes a motor, which includes a motor rotor and a motor stator. The motor rotor, for example, is the compressor shaft 21 of the aforementioned embodiment, which has a built-in permanent magnet 211. The motor stator, for example, is the motor stator 30 of the aforementioned embodiment, which is fixed within the motor accommodating cavity 14 of the housing 10. The permanent magnet 211, driven by the energized windings within the motor stator 30, drives the shaft 21 and the compressor rotor 20 to rotate.

[0447] The main circuit compressor 100 further includes a gas bearing for supporting the rotating shaft 21. In some embodiments, the gas bearing is a hydrostatic air bearing.

[0448] The refrigerant circulation system further includes a main gas source flow path and a storage container 600 for providing gaseous refrigerant to the gas bearing.

[0449] like ​ As shown, in some embodiments, the main gas source flow path includes a first gas source flow path 510 for directing the refrigerant at a first position in the main refrigerant circuit to the storage container 600 and a second gas source flow path 520 for directing the refrigerant at a second position with a higher pressure than the first position in the main refrigerant circuit to the storage container 600.

[0450] In order to enable the storage container 600 to provide refrigerant with stable pressure to the gas bearing, the refrigerant circulation system also includes a regulating valve for adjusting the flow ratio of the first gas source flow path 510 and the second gas source flow path 520. The refrigerant circulation system of this embodiment adjusts the pressure in the storage container 600 by adjusting the flow ratio of the refrigerant delivered to the storage container 600 by the first gas source flow path 510 and the second gas source flow path 520, and then adjusts the pressure of the refrigerant that the storage container 600 can deliver to the gas bearing, which is beneficial to ensure the stability of the pressure of the refrigerant delivered to the gas bearing.

[0451] In this embodiment, the first gas source flow path 510 is connected to the first gas source compression chamber (e.g., the first gas source compression chamber 15 of the compressor in the aforementioned embodiment) of the first compression section 110 of the main circuit compressor 100, and the second gas source flow path 520 is connected to the second gas source compression chamber (e.g., the second gas source compression chamber 16 of the compressor in the aforementioned embodiment) of the second compression section 120 of the main circuit compressor 100. The pressure of the refrigerant in the second compression section 120 is greater than the pressure of the refrigerant in the first compression section 110.

[0452] In some embodiments, the first gas source flow path 510 is in communication with the exhaust port of the first gas source compression chamber, and the second gas source flow path 520 is in communication with the exhaust port of the second gas source compression chamber.

[0453] In some embodiments, the inlet of the first gas source flow path 510 is connected to the intake port of the main circuit compressor 100. The refrigerant introduced into the intake port of the main circuit compressor 100 is the refrigerant that has evaporated and cooled in the evaporator. This refrigerant has a lower temperature and is beneficial for cooling the gas bearing. The inlet of the second gas source flow path 520 is connected to the exhaust port of the main circuit compressor 100. The second gas source flow path 520 is used to direct the higher-pressure refrigerant to the storage container 600.

[0454] In this embodiment, the refrigerant circulation system further includes a temperature detection element 610 for detecting the temperature of the refrigerant in the storage container 600 .

[0455] The regulating valves include a first gas source regulating valve 511 provided in the first gas source flow path 510 and a second gas source regulating valve 521 provided in the second gas source flow path 520. When the pressure within the storage container 600 is less than a first predetermined pressure, the opening of the first gas source regulating valve 511 is reduced and / or the opening of the second gas source regulating valve 521 is increased to reduce the flow ratio between the first gas source flow path 510 and the second gas source flow path 520, thereby increasing the refrigerant pressure within the storage container 600. When the pressure within the storage container 600 is greater than a second predetermined pressure, the opening of the first gas source regulating valve 511 is increased and / or the opening of the second gas source regulating valve 521 is decreased to increase the flow ratio between the first gas source flow path 510 and the second gas source flow path 520, thereby reducing the refrigerant pressure within the storage container 600. The first predetermined pressure is equal to or less than the second predetermined pressure.

[0456] like ​ As shown, the refrigerant circulation system also includes a first gas source one-way valve 512 arranged in the first gas source flow path 510, the inlet of the first gas source one-way valve 512 is connected to the main refrigerant circuit, and the outlet of the first gas source one-way valve 512 is connected to the storage container 600.

[0457] The refrigerant circulation system also includes a second gas source one-way valve 522 arranged in the second gas source flow path 520 , the inlet of the second gas source one-way valve 522 is connected to the main refrigerant circuit, and the outlet of the second gas source one-way valve 522 is connected to the storage container 600 .

[0458] The main circuit compressor 100 also includes a shell air supply duct inlet (for example, the shell air supply duct inlet of the compressor of the aforementioned embodiment) connected to the motor accommodating cavity of the main circuit compressor 100 (for example, the motor accommodating cavity 14 of the compressor of the aforementioned embodiment), and an air supply duct 530 for connecting the storage container 600 and the shell air supply duct inlet, and an air supply regulating valve 531 is provided in the air supply duct 530.

[0459] The refrigerant circulation system also includes a pressure detection element 620 and a controller for detecting the pressure of the refrigerant in the storage container 600. The controller is communicatively connected to the regulating valve and the pressure detection element 620. The controller is used to reduce the flow ratio of the first gas source flow path 510 and the second gas source flow path 520 by adjusting the opening of the regulating valve when the pressure in the storage container 600 is less than the first predetermined pressure, or to increase the flow ratio of the first gas source flow path 510 and the second gas source flow path 520 by adjusting the opening of the regulating valve when the pressure in the storage container 600 is greater than the second predetermined pressure.

[0460] like ​ As shown, the refrigerant circulation system further includes an auxiliary gas source flow path 540, which includes an inlet end communicating with the condenser 200 and an outlet end communicating with the storage container 600. A second gas source compressor 541 is provided in the auxiliary gas source flow path 540, and the second gas source compressor 541 is used to compress the refrigerant flowing from the condenser 200 to the storage container 600.

[0461] The controller is in communication with the second gas source compressor 541 and is configured to deliver refrigerant to the storage container 600 during the start-up or stop phase of the main loop compressor 100 .

[0462] An air supply check valve 542 is provided in the auxiliary air source flow path 540 . The inlet of the air supply check valve 542 is connected to the condenser, and the outlet of the air supply check valve 542 is connected to the storage container 600 .

[0463] According to another aspect of the present disclosure, a control method for a refrigerant circulation system is provided, the control method comprising:

[0464] Obtaining pressure information of condensation in the storage container 600; and

[0465] The flow ratio of the first gas source flow path 510 and the second gas source flow path 520 is reduced when the pressure is less than the first predetermined pressure, and the flow ratio of the first gas source flow path 510 and the second gas source flow path 520 is increased when the pressure is greater than the second predetermined pressure. The first predetermined pressure is equal to or less than the second predetermined pressure.

[0466] The control method further includes, during the start-up phase or the stop phase of the main circuit compressor 100, delivering refrigerant from the condenser 200 to the storage container 600 by the second gas source compressor 541.

[0467] The refrigerant circulation system includes two working states: a start-stop state and a normal working state.

[0468] When the first compressor 100 is in the start-stop phase, the refrigerant circulation system is in the start-stop state, the first gas source regulating valve 511, the second gas source regulating valve 521, and the gas supply regulating valve 531 are closed, and the second gas source compressor 541 is used to compress the gas from the upper part of the condenser 200 and then supply the gas to the storage part.

[0469] The states of the first gas source regulating valve 511, the second gas source regulating valve 521, and the gas supply regulating valve 531 are adjusted according to the pressure displayed by the pressure detection element on the storage container 600. When the pressure in the storage container 600 reaches the working pressure of the static pressure gas bearing, the gas supply regulating valve 531 is opened, the external gas enters the main circuit compressor 100 from the casing gas supply flow path inlet of the main circuit compressor 100, and then reaches the static pressure gas bearing through the flow path inside the main circuit compressor 100 to provide the pressure gas.

[0470] When the compressor is in normal working, the refrigerant circulation system is in the normal working state, at this time, the second gas source compressor 541 is closed, and the first gas source regulating valve 511 and the second gas source regulating valve 521 are opened, at this time, the gas is taken from the high-pressure stage and the low-pressure stage of the main circuit compressor 100 and then supplied to the storage container 600. According to the pressure detected by the pressure detection element 620, it is determined whether the pressure in the storage container 600 meets the working pressure of the static pressure gas bearing. If the pressure detected by the pressure detection element 620 is less than the working pressure of the static pressure gas bearing, the second gas source regulating valve 521 can be adjusted to take more gas from the high-pressure stage; if the pressure detected by the pressure detection element 620 is greater than the working pressure of the static pressure gas bearing, the first gas source regulating valve 511 can be adjusted to take more gas from the low-pressure stage. By using this gas supply mode, the gas supply pressure can be easily adjusted, so that the static pressure gas bearing with various working pressures can be met, and the pressure adjustment is convenient and reliable, which improves the working stability of the static pressure gas bearing.

[0471] ​ A refrigerant circulation system of another embodiment of the present disclosure is shown.

[0472] As shown in ​ , the refrigerant circulation system includes a main refrigerant circuit, a main gas source flow path, and a gas source cooling flow path 550.

[0473] As shown in ​ , the main refrigerant circuit includes a main circuit compressor 100, a condenser 200, a throttling device 300, and an evaporator 400 connected by a main refrigerant pipeline 900.

[0474] The refrigerant compressed by the main circuit compressor 100 enters the condenser 200, and the refrigerant condensed in the condenser 200 enters the evaporator 400 after being throttled and decompressed by the throttling device 300. The refrigerant evaporated in the evaporator 400 returns to the suction port of the main circuit compressor 100.

[0475] The main circuit compressor 100 can be the compressor of the foregoing embodiments, including a gas bearing and at least two compression chambers. As shown in ​ , in some embodiments, the flow inlet of the main gas source flow path is in communication with the compression chamber. In embodiments not shown, the flow inlet of the main gas source flow path can be in communication with other suitable positions of the main refrigerant circuit to introduce the refrigerant in the main refrigerant circuit into the main gas source flow path. The refrigerant in the main gas source flow path supplies working gas for the gas bearing. The gas source cooling flow path 550 exchanges heat with the main gas source flow path to cool the refrigerant in the main gas source flow path.

[0476] The optional structure of the refrigerant circulation system is described in detail below in three cases, with the main circuit compressor 100 including two compression chambers, a first compression chamber (which can be the first compression chamber 15 of the foregoing embodiments) and a second compression chamber (which can be the second compression chamber 16 of the foregoing embodiments). The main circuit compressor 100 includes a first compression part 110 and a second compression part 120, the exhaust port of the first compression part 110 is in communication with the gas inlet of the second compression part 120, and the second compression part 120 is used to compress the refrigerant compressed by the first compression part 110.

[0477] The three cases are: the main gas source flow path takes refrigerant from the first compression chamber of the first compression part 110 alone (see ​ ); the main gas source flow path takes refrigerant from the second compression chamber of the second compression part 120 alone (see ​ ); and the main gas source flow path takes refrigerant from both the first compression chamber and the second compression chamber (see ​ ).

[0478] The embodiments of the present disclosure provide a refrigerant circulation system, which includes a main refrigerant circuit, a first gas source flow path 510, and a gas source cooling flow path 550. The main refrigerant circuit is as described above. The main circuit compressor 100 of the main refrigerant circuit includes a gas bearing and at least two compression chambers.

[0479] ​ In the embodiment shown, the flow inlet of the first gas source flow path 510 is in communication with the compression chamber, and the refrigerant in the first gas source flow path 510 is used to supply working gas for the gas bearing. The gas source cooling flow path 550 is in heat exchange with the first gas source flow path 510, and is used to cool the refrigerant in the first gas source flow path 510.

[0480] In some embodiments, the main circuit compressor 100 includes two compression chambers, i.e., a first compression chamber and a second compression chamber. In the working state, the gas pressure in the second compression chamber is higher than the gas pressure in the first compression chamber.

[0481] Referring to ​ In some embodiments, the first gas source flow path 510 includes a first gas source flow path 510. The first gas source flow path 510 draws refrigerant from the first compression chamber, i.e., the inlet of the first gas source flow path 510 is in communication with the first compression chamber of the main circuit compressor 100. The refrigerant in the first gas source flow path 510 is subsequently used to supply gas for the gas bearing in the main circuit compressor 100.

[0482] In some embodiments, the refrigerant circulation system further includes a heat exchanger 700, which includes a first branch and a second branch. The first branch is connected in series to the first gas source flow path 510, and the second branch is connected in series to the gas source cooling flow path 550. The main gas source flow path is provided with a main gas source flow path one-way valve 561 at a position downstream of the first branch of the heat exchanger 700.

[0483] The temperature of the refrigerant in the gas source cooling flow path 550 is lower than the temperature of the refrigerant in the first gas source flow path 510. The refrigerant in the gas source cooling flow path 550 is drawn from the outlet of the condenser 200, or is drawn after being throttled by the throttling device 300.

[0484] The heat exchanger 700 is, for example, a plate heat exchanger.

[0485] Referring to ​ In some embodiments, the gas source cooling flow path 550 is parallel to the main refrigerant pipeline 900 between the condenser 200 and the evaporator 400. The gas source cooling flow path 550 is provided with a gas source cooling flow path regulating valve 551 to control the on-off state of the gas source cooling flow path 550.

[0486] Referring to ​ The refrigerant from the condenser 200 is throttled by the throttling device 300, and part of it flows to the evaporator 400, and the other part enters the gas source cooling flow path 550, and then flows to the second branch of the heat exchanger 700, and then flows to the evaporator 400.

[0487] In some embodiments, the first gas source flow path 510 is provided with a first gas source regulating valve 511 to regulate the flow rate, pressure and other parameters of the refrigerant in the first gas source flow path 510.

[0488] To prevent the backflow of the refrigerant, the first gas source flow path 510 is further provided with a first gas source one-way valve 512, which is located upstream of the first gas source regulating valve 511 for example.

[0489] In some embodiments, the refrigerant circulation system further comprises a storage container 600, which is located downstream of the first gas source flow path 510 and communicates with the first gas source flow path 510. The refrigerant cooled down is stored in the storage container 600 to supply the working gas for the gas bearing when needed. Downstream of the storage container 600 is provided with a gas supply flow path 530, the outlet of which is connected to the shell gas supply flow path inlet 101 of the main circuit compressor 100 and comprises a gas supply regulating valve 531. When the gas supply regulating valve 531 is opened, the refrigerant in the storage container 600 enters the bearing chamber where the gas bearing is located to supply the working gas for the gas bearing. When the gas supply regulating valve 531 is closed, the refrigerant in the storage container 600 does not flow out.

[0490] Referring to ​ In some embodiments, the refrigerant circulation system further comprises a temperature detecting element 610, which is located in the storage container 600 and is used to detect the temperature of the gas in the storage container 600. The temperature detecting element 610 comprises a temperature sensor and the like.

[0491] In some embodiments, the refrigerant circulation system further comprises a pressure detecting element 620, which is located in the storage container 600 and is used to detect the pressure of the gas in the storage container 600. The pressure detecting element 620 comprises a pressure sensor and the like.

[0492] The refrigerant circulation system comprises two working states: start-stop state and normal working state. When the refrigerant circulation system is in the normal working state, the working gas for the gas bearing is supplied through the above-mentioned first gas source flow path 510. When the refrigerant circulation system is in the start-stop state, the working gas for the gas bearing is supplied through the below-mentioned auxiliary gas source flow path 540.

[0493] In some embodiments, the refrigerant circulation system further comprises an auxiliary gas source flow path 540, one end of which communicates with the condenser 200 and the other end of which communicates with the bearing chamber where the gas bearing is located. Alternatively, the refrigerant circulation system further comprises an auxiliary gas source flow path 540, one end of which communicates with the condenser 200 and the other end of which communicates with the storage container 600, as shown in ​

[0494] ​The auxiliary gas source flow path 540 is provided with an auxiliary compressor 541 for drawing gaseous refrigerant from the condenser 200, which is compressed by the auxiliary compressor 541 and then flows to the storage container 600.

[0495] The auxiliary gas source flow path 540 is further provided with an auxiliary gas path one-way valve 542 to prevent refrigerant backflow and facilitate control of whether the auxiliary gas source flow path 540 is in an operating state. When the main circuit compressor 100 is in the start-stop phase, the auxiliary gas source flow path 540 is in the on state. In this state, the first gas source flow path 510 is not in operation and is in the off state. When the main circuit compressor 100 is in normal operation, the first gas source flow path 510 is in the on state. At this time, the auxiliary gas source flow path 540 is not in operation and is in the off state.

[0496] Referring to ​ , another flow path mode of the main gas source flow path is described below.

[0497] Referring to ​ , in some embodiments, the main circuit compressor 100 includes two compression chambers, i.e., a first compression chamber and a second compression chamber. In the working state, the gas pressure in the first compression chamber is lower than the gas pressure in the second compression chamber.

[0498] Referring to ​ , in some embodiments, the main gas source flow path includes a second gas source flow path 520, which draws refrigerant from the second compression chamber, i.e., the inlet of the second gas source flow path 520 is in communication with the second compression chamber of the main circuit compressor 100. The refrigerant in the second gas source flow path 520 is subsequently used to supply gas to the gas bearing in the main circuit compressor 100.

[0499] Referring to Figure 33 , in some embodiments, the refrigerant circulation system further includes a heat exchanger 700, which includes a first branch and a second branch. In Figure 33 the illustrated embodiment, the first branch is connected in series with the second gas source flow path 520, and the second branch is connected in series with the gas source cooling flow path 550. In this embodiment, the second gas source flow path 520 is provided with a main gas source flow path one-way valve 561 at a position downstream of the first branch of the heat exchanger 700.

[0500] The temperature of the refrigerant in the gas source cooling flow path 550 is lower than the temperature of the refrigerant in the second gas source flow path 520. The gas source cooling flow path 550 draws refrigerant from the outlet of the condenser 200, for example, or draws refrigerant from the condenser 200 after the refrigerant is throttled by the throttling device 300.

[0501] The heat exchanger 700 is, for example, a plate heat exchanger.

[0502] Referring to Figure 33In some embodiments, the gas source cooling flow path 550 is in parallel with the main refrigerant pipeline 900 between the condenser 200 and the evaporator 400. The gas source cooling flow path 550 is provided with a gas source cooling flow path regulating valve 551 to control the on-off state of the gas source cooling flow path 550.

[0503] Referring to Figure 33 The refrigerant from the condenser 200 passes through the throttling device 300 to be throttled, and part of the refrigerant flows to the evaporator 400, and the other part enters the gas source cooling flow path 550, and then flows to the second branch of the heat exchanger 700, and then flows to the evaporator 400.

[0504] Referring to Figure 33 In some embodiments, the second gas source flow path 520 is provided with a second gas source regulating valve 521 to adjust the flow, pressure and other parameters of the refrigerant in the second gas source flow path 520.

[0505] In order to prevent the refrigerant from flowing back, the second gas source flow path 520 is also provided with a second gas source one-way valve 522, which is located upstream of the second gas source regulating valve 521, for example.

[0506] Referring to Figure 33 In some embodiments, the refrigerant circulation system further comprises a storage container 600. The storage container 600 is located downstream of the second gas source flow path 520 and communicates with the second gas source flow path 520. The cooled refrigerant is stored in the storage container 600 to supply working gas to the gas bearing when needed. A gas supply flow path 530 is located downstream of the storage container 600 and is connected to the shell gas supply flow path inlet 101 of the compressor. The gas supply flow path 530 comprises a gas supply regulating valve 531. When the gas supply regulating valve 531 is opened, the refrigerant in the storage container 600 enters the bearing chamber where the gas bearing is located to supply working gas to the gas bearing. When the gas supply regulating valve 531 is closed, the refrigerant in the storage container 600 does not flow out.

[0507] Referring to Figure 33 In some embodiments, the refrigerant circulation system further comprises a temperature detection element 610 located in the storage container 600 for detecting the temperature of the gas in the storage container 600. The temperature detection element 610 comprises a temperature sensor and the like.

[0508] In some embodiments, the refrigerant circulation system further comprises a pressure detection element 620 located in the storage container 600 for detecting the pressure of the gas in the storage container 600. The pressure detection element 620 comprises a pressure sensor and the like.

[0509] The refrigerant circulation system comprises two working states: start-stop state and normal working state.

[0510] When the refrigerant circulation system is in normal working state, the second gas source flow path 520 supplies working gas for the gas bearing of the main loop compressor 100. When the refrigerant circulation system is in start-stop stage, the auxiliary gas source flow path 540 supplies working gas for the gas bearing of the main loop compressor 100.

[0511] Referring to Figure 33 In some embodiments, the refrigerant circulation system further comprises an auxiliary gas source flow path 540, one end of the auxiliary gas source flow path 540 being in communication with the condenser 200, and the other end of the auxiliary gas source flow path 540 being in communication with the bearing chamber where the gas bearing is located. Alternatively, the refrigerant circulation system further comprises an auxiliary gas source flow path 540, one end of the auxiliary gas source flow path 540 being in communication with the condenser 200, and the other end of the auxiliary gas source flow path 540 being in communication with the storage container 600, as shown in Figure 33

[0512] Referring to Figure 33 The auxiliary gas source flow path 540 is provided with an auxiliary compressor 541, and gaseous refrigerant is drawn from the condenser 200, and the gaseous refrigerant flows to the storage container 600 after being compressed by the auxiliary compressor 541.

[0513] Referring to Figure 33 The auxiliary gas source flow path 540 is further provided with an auxiliary gas path one-way valve 542, so as to prevent refrigerant backflow and facilitate control of whether the auxiliary gas source flow path 540 is in working state. When the main loop compressor 100 is in start-stop stage, the refrigerant circulation loop is in start-stop state, and the auxiliary gas source flow path 540 is in conducting state. In this state, the second gas source flow path 520 is not working and is in disconnected state. When the main loop compressor 100 is in normal working state, the refrigerant circulation loop is in normal working state, and the second gas source flow path 520 is in conducting state. In this state, the auxiliary gas source flow path 540 is not working and is in disconnected state.

[0514] Referring to Figure 34 Another kind of flow path of the main gas source flow path will be introduced below.

[0515] The refrigerant circulation system provided by the embodiments of the present disclosure comprises a main refrigerant loop, a main gas source flow path and a gas source cooling flow path 550. The main loop compressor 100 of the main refrigerant loop comprises a gas bearing and at least two compression cavities. The flow inlet of the main gas source flow path is in communication with the compression cavities, and the refrigerant in the main gas source flow path is used to supply working gas for the gas bearing. The gas source cooling flow path 550 is in heat exchange with the main gas source flow path, and is used to cool the refrigerant in the main gas source flow path.

[0516] In some embodiments, the main loop compressor 100 comprises two compression cavities, i.e. a first compression cavity and a second compression cavity. In working state, the gas pressure in the second compression cavity is higher than the gas pressure in the first compression cavity. ​

[0517] Referring to Figure 34 In some embodiments, the main gas source flow path includes two, a first gas source flow path 510 and a second gas source flow path 520.

[0518] The first gas source flow path 510 draws refrigerant from the first compression chamber, i.e., the inlet of the first gas source flow path 510 is in communication with the first compression chamber of the main circuit compressor 100. The second gas source flow path 520 draws refrigerant from the second compression chamber, i.e., the inlet of the second gas source flow path 520 is in communication with the second compression chamber of the main circuit compressor 100. The flow outlets of the second gas source flow path 520 and the first gas source flow path 510 converge into a gas source flow path trunk.

[0519] In some embodiments, the refrigerant circulation system further includes a heat exchanger 700, which includes a first branch and a second branch. The first branch is in series with the gas source flow path trunk, and the second branch is in series with the gas source cooling flow path 550. The main gas source flow path one-way valve 561 is arranged at a position downstream of the first branch of the heat exchanger 700.

[0520] The heat exchanger 700 is, for example, a plate heat exchanger.

[0521] In some embodiments, the gas source cooling flow path 550 is in parallel with the main refrigerant pipeline 900 between the condenser 200 and the evaporator 400. The gas source cooling flow path 550 is provided with a gas source cooling flow path regulating valve 551 to control the on-off state of the gas source cooling flow path 550.

[0522] Referring to Figure 34 The refrigerant from the condenser 200 passes through the throttling device 300 to be throttled, part of which flows to the evaporator 400, and the other part enters the gas source cooling flow path 550, and then flows to the second branch of the heat exchanger 700, and then flows to the evaporator 400.

[0523] In some embodiments, the first gas source flow path 510 is provided with a first gas source regulating valve 511 to regulate the flow, pressure, temperature and other parameters of the refrigerant in the first gas source flow path 510. The second gas source flow path 520 is provided with a second gas source regulating valve 521 to regulate the flow, pressure, temperature and other parameters of the refrigerant in the second gas source flow path 520.

[0524] In order to prevent the refrigerant in the first gas source flow path 510 from flowing back, the first gas source flow path 510 is further provided with a first gas source one-way valve 512, which is, for example, located upstream of the first gas source regulating valve 511. In order to prevent the refrigerant in the second gas source flow path 520 from flowing back, the second gas source flow path 520 is further provided with a second gas source one-way valve 522, which is, for example, located upstream of the second gas source regulating valve 521.

[0525] In some embodiments, the refrigerant circulation system further includes a storage container 600, which is provided downstream of the first gas source flow path 510 and the second gas source flow path 520 and communicates with both the first gas source flow path 510 and the second gas source flow path 520. The cooled refrigerant is stored in the storage container 600 to supply working gas to the gas bearing when needed.

[0526] Referring to Figure 34 In some embodiments, the refrigerant circulation system further includes a temperature detecting element 610, which is provided in the storage container 600 and detects the temperature of the gas in the storage container 600. The temperature detecting element 610 includes a temperature sensor or the like.

[0527] In some embodiments, the refrigerant circulation system further includes a pressure detecting element 620, which is provided in the storage container 600 and detects the pressure of the gas in the storage container 600. The pressure detecting element 620 includes a pressure sensor or the like.

[0528] In some embodiments, the refrigerant circulation system further includes an auxiliary gas source flow path 540, one end of which communicates with the condenser 200 and the other end of which communicates with the bearing chamber where the gas bearing is provided.

[0529] Alternatively, the refrigerant circulation system further includes an auxiliary gas source flow path 540, one end of which communicates with the condenser 200 and the other end of which communicates with the storage container 600, as shown in Figure 34

[0530] The auxiliary gas source flow path 540 described above is provided with an auxiliary compressor 541, which draws gaseous refrigerant from the condenser 200. The gaseous refrigerant is compressed by the auxiliary compressor 541 and then flows to the storage container 600.

[0531] The auxiliary gas source flow path 540 described above is further provided with an auxiliary gas path one-way valve 542, which prevents backflow of the refrigerant and facilitates control of whether the auxiliary gas source flow path 540 is in an operating state or not. When the main circuit compressor 100 is in the start-stop phase, the auxiliary gas source flow path 540 is in an on state. At this time, neither the second gas source flow path 520 nor the first gas source flow path 510 is in an on state. When the main circuit compressor 100 is in normal operation, at least one of the second gas source flow path 520 and the first gas source flow path 510 is in an on state. In this state, the auxiliary gas source flow path 540 is in an off state.

[0532] The foregoing description of how to adjust the pressure in the storage container 600 in the embodiment shown in Figure 31 applies to the present embodiment and will not be repeated here.

[0533] ​The embodiments of the present disclosure further provide a refrigeration device, which comprises the compressor or the refrigerant circulation system.

[0534] In some embodiments, the refrigeration device is an air conditioner.

[0535] Finally, it should be noted that the above embodiments are only used to illustrate but not limit the technical solutions of the present disclosure; although the present disclosure has been described in detail with reference to the preferred embodiments, it should be understood by those of ordinary skill in the art that the specific implementation of the present disclosure can be modified or some technical features can be replaced by equivalent replacements, which should be covered in the technical solution range of the present disclosure.

Claims

1. A compressor, characterized in that: include: The housing (10) has a receiving space and includes a cylinder (11), wherein a first end of the cylinder (11) includes an end wall (112), and the end wall (112) includes an end wall bearing chamber; A compressor rotor (20) rotatably disposed in the accommodation space, comprising a thrust plate (24); and A gas bearing assembly is used to support the compressor rotor (20) on the housing (10), the gas bearing assembly includes a thrust bearing assembly (41) and a first radial bearing (42), the thrust bearing assembly (41) cooperates with the thrust plate (24), the first end of the compressor rotor (20) is carried on the first radial bearing (42), the thrust bearing assembly (41) is affixed to the outer end surface of the end wall (112), the first radial bearing (42) is located in the end wall bearing chamber and the end surface of the first end of the first radial bearing (42) is affixed to the outer end surface of the thrust bearing assembly (41); wherein, The thrust bearing assembly includes a first thrust bearing (411), a second thrust bearing (412) and a positioning ring (413), wherein the first thrust bearing (411) is matched with the first end of the thrust disc (24), and the second thrust bearing (412) is matched with the second end of the thrust disc (24), and the positioning ring (413) is located on the radial outer side of the thrust disc (24), and the end faces of the positioning ring (413) are respectively fitted with the first thrust bearing (411) and the second thrust bearing (412), and the positioning ring (413) is provided with a positioning ring fluid channel connecting the radial inner side and the radial outer side of the positioning ring (413), so that the exhaust gas between the thrust disc (24) and the thrust surfaces of the first thrust bearing (411) and the second thrust bearing (412) is discharged from the positioning ring fluid channel to the radial outer side of the positioning ring (413).

2. The compressor according to claim 1, characterized in that The compressor further includes an end wall snap ring (82); The end wall (112) further includes an end wall annular groove, the end wall snap ring (82) cooperates with the end wall annular groove, and the first radial bearing (42) is axially limited between the thrust bearing assembly (41) and the end wall snap ring (82).

3. The compressor according to claim 1, characterized in that A radial bearing air supply channel (171) for supplying working gas to the first radial bearing (42) and a thrust bearing air supply channel (172) for supplying working gas to the thrust bearing assembly (41) are provided in the end wall (112).

4. The compressor according to claim 3, characterized in that The radial bearing air supply passage (171) is connected to or isolated from the thrust bearing air supply passage (172).

5. The compressor according to claim 1, characterized in that The end wall (112) includes a diffuser mounting opening; The compressor includes a diffuser (50), the diffuser (50) includes a diffuser positioning stop that cooperates with the diffuser mounting port, the diffuser (50) is fixedly connected to the end wall (112), and the outer end surface of the thrust bearing assembly (41) away from the end wall (112) is in contact with the end surface of the diffuser (50).

6. The compressor according to claim 5, characterized in that The inner hole of the diffuser (50) cooperates with the first end of the compressor rotor (20), and a first shaft sealing structure (56) is provided on the hole wall of the inner hole of the diffuser (50).

7. The compressor according to claim 1, characterized in that The gas bearing assembly further comprises a second radial bearing (43), and the second end of the compressor rotor (20) is supported on the second radial bearing (43); The compressor further includes a bearing bearing component (60), the bearing bearing component (60) including an integrally arranged diffuser portion and a bearing seat portion, the diffuser portion being fixedly connected to the second end of the cylinder (11), the bearing seat portion including a bearing component bearing chamber (62), and the second radial bearing (43) being located in the bearing component bearing chamber (62).

8. The compressor according to claim 7, characterized in that The end wall bearing chamber and the bearing component bearing chamber (62) are formed by fixedly connecting the cylinder (11) and the bearing bearing component (60) and then boring them together.

9. The compressor according to claim 7, characterized in that The diffuser portion includes a shaft seal mounting hole (67); The compressor further includes a shaft sealing component (70), the shaft sealing component (70) being fixed in the shaft sealing mounting hole (67) and being sleeved on the second end of the compressor rotor, the shaft sealing component (70) including a second shaft sealing structure (711) cooperating with the second end of the compressor rotor (20), and the first end of the shaft sealing component (70) cooperating with the end face of the second radial bearing (43).

10. The compressor according to claim 9, characterized in that The bearing bearing component (60) includes a bearing component annular groove (66), the compressor includes a bearing component snap ring (81), the bearing component snap ring (81) cooperates with the bearing component annular groove (66), and the second radial bearing (43) is axially limited between the shaft sealing component (70) and the bearing component snap ring (81).

11. The compressor according to claim 9, characterized in that The bearing bearing component (60) includes a fluid inlet channel (63) communicating with the bearing component bearing chamber (62) and a fluid outlet channel (64) communicating with the shaft seal mounting hole (67); The shaft sealing component (70) includes a shaft sealing fluid passage communicating with a gap between the bearing chamber (62) of the bearing component and the compressor rotor (20) and the fluid outflow passage (64).

12. The compressor according to claim 1, characterized in that The compressor rotor (20) comprises a rotating shaft (21), and the rotating shaft (21) comprises a permanent magnet (211) and a first shaft segment (212) and a second shaft segment (213) coaxially arranged at two axial ends of the permanent magnet (211).

13. The compressor according to any one of claims 1 to 12, characterized in that The thrust bearing assembly (41) includes a first thrust bearing (411) matched with the first end of the thrust disc (24) and a second thrust bearing (412) matched with the second end of the thrust disc (24); the gas bearing assembly also includes a second radial bearing (43), and the second end of the compressor rotor (20) is supported on the second radial bearing (43); wherein the first radial bearing, the second radial bearing, the first thrust bearing and the second thrust bearing are static pressure gas bearings.

14. A refrigerant circulation system, characterized in that: A compressor comprising the compressor according to any one of claims 1 to 13.

15. A refrigeration device, characterized in that: A compressor comprising the compressor according to any one of claims 1 to 13.

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