Rotor assemblies, compressors, and air conditioners

Abstract

A rotor assembly 1100, a compressor 1000 and an air conditioner. The rotor assembly 1100 includes a first rotor 200 including a first working part 210 and a second working part 220 arranged coaxially, the first working part 210 and the second working part 220 being rotatable about a first axis, the first working part 210 including a plurality of first helical blades 211, a first blade groove 212 being formed between two adjacent ones of the plurality of first helical blades 211, and at least one first pneumatic groove 213 being provided on a first end surface 214 of the first working part 210 away from the second working part 220, the first pneumatic groove 213 being configured to form a force in a predetermined direction along the first axis when rotating. The rotor assembly can reduce the cost of the compressor, simplify the structure of the moving parts of the compressor, and improve the performance and reliability of the compressor.

Description

Technical Field

[0001] The present disclosure relates to the field of compressor technology, and more particularly, to a rotor assembly, a compressor, and an air conditioner.

Background Art

[0002] Compressors are widely used in aerodynamics, cooling air conditioners, and various technical processes due to their compact, efficient, reliable, and adaptable characteristics, and their market share continues to expand. As a new compressor structure, the four-rotor compressor is different from the conventional compressor in that two pairs of double-compressor rotors are symmetrically arranged on the end face of the suction orifice. Similar to two parallel compressors, one four-rotor compressor sucks air from the radial suction orifice in the middle of the four-rotor compressor and discharges air from the discharge orifices at its two ends. Due to the opposed, counter-rotating arrangement of the four rotors, the axial force of the four-rotor compressor can be fully counteracted under ideal conditions, and thus, in order to achieve further miniaturization of the compressor, the thrust bearing can be completely eliminated.

[0003] However, due to the differences existing in the actual machining and assembly processes of the four rotors, when the four rotors operate after being formed, the axial force cannot be fully counteracted, which can generate random gas axial forces along the two axial directions in the rotors of the compressor. Therefore, in order to ensure that the randomly appearing gas axial forces in the two directions are supported, it is necessary to arrange two sets of thrust bearings with opposite bearing directions. However, for one individual compressor, the direction of the random resultant force of the axial force is always constant. In this case, one set of the thrust bearings is used for restriction, and the other set of the thrust bearings is completely in an idle state, thus resulting in a lower price-performance ratio. Furthermore, redundant mechanical losses and the demand for lubricating oil occur, increasing the failure rate of the compressor.

Summary of the Invention

[0004] Embodiments of the present disclosure provide a rotor assembly, a compressor, and an air conditioner to reduce the cost of the compressor, simplify the structure of the moving parts of the compressor, and improve the performance and reliability of the compressor.

[0005] A first aspect of this disclosure is a rotor assembly, A rotor assembly is provided, comprising a first rotor including a first working part and a second working part arranged coaxially, wherein the first working part and the second working part are rotatable about a first axis, the first working part includes a plurality of first helical blades, a first blade groove is formed between two adjacent first helical blades, and at least one first pneumatic groove is provided on a first end face of the first working part away from the second working part, the first pneumatic groove is configured to form a force in a predetermined direction along the first axis when rotating.

[0006] In some embodiments, at least one first pneumatic groove communicates with at least one of a plurality of first blade grooves of the first operating part.

[0007] In some embodiments, the rotor assembly further includes a second rotor, the second rotor including a coaxially arranged third and fourth working part, the third working part engaging with the first working part, the fourth working part engaging with the second working part, and both the third and fourth working parts being rotatable about a second axis.

[0008] In some embodiments, the first end face is coated with an abrasion-resistant coating.

[0009] In some embodiments, the first working part includes a plurality of first helical blades, a plurality of first blade grooves each adjacent to a plurality of first helical blades, a plurality of at least one first pneumatic grooves, and each of the plurality of first helical blades is provided with at least one first pneumatic groove.

[0010] In some embodiments, the multiple first pneumatic grooves are distributed spirally across the first end face, with the center of the first end face as the central point.

[0011] In some embodiments, the number of first pneumatic grooves is equal to the number of first helical blades, each of the first pneumatic grooves is provided on the end face of the corresponding first helical blade, and each of the first pneumatic grooves communicates with the corresponding first blade groove.

[0012] A second aspect of this disclosure is a compressor, A housing including the first interior wall, The rotor assembly includes, and the rotor assembly is A compressor is provided, comprising a first rotor including a first working part and a second working part arranged coaxially, wherein the first working part and the second working part are rotatable about a first axis, the first working part includes a plurality of first helical blades, a first blade groove is formed between two adjacent first helical blades, and at least one first pneumatic groove is provided on a first end face of the first working part away from the second working part, the first pneumatic groove is configured to form a force in a predetermined direction along the first axis when rotating.

[0013] In some embodiments, at least one first pneumatic groove communicates with at least one of a plurality of first blade grooves of the first operating part.

[0014] In some embodiments, the rotor assembly further includes a second rotor comprising a third and a fourth coaxially arranged working part, the third working part being engaged with the first working part, the fourth working part being engaged with the second working part, and both the third and fourth working parts being rotatable about a second axis.

[0015] In some embodiments, the first end face is coated with an abrasion-resistant coating and / or the first inner wall is coated with an abrasion-resistant coating.

[0016] In some embodiments, the first working part includes a plurality of first helical blades, a plurality of first blade grooves each adjacent to a plurality of first helical blades, a plurality of at least one first pneumatic grooves, and each of the plurality of first helical blades is provided with at least one first pneumatic groove.

[0017] In some embodiments, a plurality of first pneumatic grooves are distributed spirally across the first end face, with the center of the first end face as the central point.

[0018] In some embodiments, the number of first pneumatic grooves is equal to the number of first helical blades, each of the first pneumatic grooves is provided on the end face of the corresponding first helical blade, and each of the first pneumatic grooves communicates with the corresponding first blade groove.

[0019] A third aspect of this disclosure provides a compressor, including the compressor of the second aspect of this disclosure.

[0020] Based on the technical solution provided by the present disclosure, a rotor assembly includes a first rotor including a first working part and a second working part arranged coaxially, wherein the first working part and the second working part are rotatable about a first axis, the first working part includes a plurality of first helical blades, a first blade groove formed between two adjacent first helical blades, and at least one first pneumatic groove provided on a first end face of the first working part away from the second working part, the first pneumatic groove configured to form a force in a predetermined direction along the first axis when rotating. The first working part of the compressor of this disclosure draws gas into the first blade groove through the first pneumatic groove and pressurizes it, thereby forming a fixed gas axial force directed toward the second working part, ensuring that the rotor shaft system is always subjected to an axial force only in a fixed direction, thereby requiring only one set of thrust bearings to support the gas axial force directed toward the second working part, and thus reducing the use of thrust bearings.

[0021] The compressor includes a housing and a rotor assembly, the housing including a first inner wall, and the rotor assembly including a first rotor including a first working part and a second working part coaxially arranged in the housing. The first and second working parts are rotatable about a first axis, and the first working part includes a plurality of first helical blades, with a first blade groove formed between two adjacent first helical blades. At least one first pneumatic groove is provided on a first end face of the first working part, away from the second working part, the first end face providing a clearance fit with the first inner wall, and the first pneumatic groove is configured to form a force in a predetermined direction along the first axis when rotating. The first working part of the compressor of this disclosure draws gas into the first blade groove through the first pneumatic groove and pressurizes it, thereby forming a fixed gas axial force directed toward the second working part, ensuring that the rotor shaft system is always subjected to axial force only in a fixed direction, thereby requiring only one set of thrust bearings to support the gas axial force directed toward the second working part, and thus reducing the use of thrust bearings. In this way, the cost of the compressor may be reduced, the volume of the compressor may be reduced, the structure of the moving parts of the compressor may be simplified, and the performance and reliability of the compressor may be improved. Furthermore, after the thrust bearings for supporting the gas axial force directed toward the second working part are eliminated, a layer of gas film formed between the first end face of the first working part and the first inner wall of the housing can prevent failures caused by collisions and friction between the first rotor and the housing, thus further improving the performance and reliability of the compressor.

[0022] To more clearly illustrate the technical solutions in the embodiments of this disclosure, the accompanying drawings necessary to illustrate the embodiments are briefly introduced below. Obviously, the accompanying drawings in the following description illustrate only a few embodiments of this disclosure, and those skilled in the art can derive other drawings from these accompanying drawings without creative effort.

[0023] To more fully understand the present disclosure and its advantageous effects, the following description is made in connection with the accompanying drawings, and the same reference numerals indicate the same members in the following description.

Brief Description of the Drawings

[0024] [Figure 1] It is a schematic partial structural diagram of a compressor provided by an embodiment of the present disclosure. [Figure 2] It is a schematic structural diagram of a rotor assembly provided by an embodiment of the present disclosure. [Figure 3] It is an end view showing the ends of the first rotor and the second rotor of the first type of rotor assembly provided by an embodiment of the present disclosure. [Figure 4] It is an end view showing the other ends of the first rotor and the second rotor of the second type of rotor assembly provided by an embodiment of the present disclosure. [[ID=​​​​​​​​​​​​​​​​In this specification, “Examples” or “Implementations” means that certain features, structures, or characteristics described in relation to an Example may be included in at least one Example of this Disclosure. Words appearing in different parts of the Specification do not necessarily refer to the same Example, nor do they refer to mutually exclusive, independent, or alternative Examples. It will be explicitly and implicitly understood by those skilled in the art that the Examples described herein may be combined with other Examples.

[0027] Referring to Figure 1, an embodiment of the present disclosure provides a schematic substructure diagram of a compressor. The compressor 1000 shown in Figure 1 may be a screw compressor. For example, the compressor 1000 may be a counter-screw compressor. Note that the compressor 1000 shown in Figure 1 is not limited to a screw compressor, and the compressor 1000 may be, for example, a scroll compressor. The compressor 1000 includes a rotor assembly 1100 which includes a first shaft body 100, a first rotor 200, a second shaft body 300 and a second rotor 400, and a housing 800 which is surrounded by a first bearing housing 500, a rotor housing 600 and a second bearing housing 700. The rotor housing 600 includes a hollow chamber 610, and at least a portion of the first shaft body 100, the first rotor 200, at least a portion of the second shaft body 300, and the second rotor 400 are housed in the hollow chamber 610 of the rotor housing 600. The first bearing housing 500 covers one end of the rotor housing 600 to form one end of the housing 800, and the second bearing housing 700 covers the other end of the rotor housing 600 to form the other end of the housing 800.

[0028] The first rotor 200 meshes with and transmits power to the second rotor 400. In some embodiments of the present disclosure, the first rotor 200 may be a male rotor and the second rotor 400 may be a female rotor. In other embodiments of the present disclosure, the first rotor 200 may be a female rotor and the second rotor 400 may be a male rotor. Embodiments of the present disclosure are described in detail below by using an example in which the first rotor 200 is a male rotor and the second rotor 400 is a female rotor.

[0029] A first rotor 200, functioning as a male rotor, may be understood as a driving rotor, and a second rotor 400, functioning as a female rotor, may be understood as a driven rotor. For example, the first rotor 200 may be drive-connected to a drive assembly such as a motor (including, but not limited to, a permanent magnet motor), and the first rotor 200 may be driven by the drive assembly to rotate, and the first rotor 200 may rotate while driving the second rotor 400, and rotate together by meshing transmission.

[0030] The first rotor 200 is supported by the first shaft body 100 and is fixedly connected to the first shaft body 100. One end of the first shaft body 100 is rotatably mounted in the first bearing housing 500, the other end of the first shaft body 100 is rotatably mounted in the second bearing housing 700, and one end of the first shaft body 100 is transmittedly connected to a drive assembly. The drive assembly can drive the first shaft body 100 to rotate, and the first shaft body 100 can rotate together with the first rotor 200, which is fixedly connected to the first shaft body 100, along the first axis 110 of the first shaft body 100 in the first bearing housing 500 and the second bearing housing 700. That is, the first rotor 200 is rotatably supported in the first bearing housing 500 and the second bearing housing 700. In some embodiments of the present disclosure, the first rotor 200 may be integrally formed with the first shaft body 100. In other embodiments of the present disclosure, the first rotor 200 may be partially integrally formed with the first shaft body 100 and partially sleeved to the first shaft body 100. In other embodiments of the present disclosure, the first rotor 200 may be directly sleeved to the first shaft body 100.

[0031] Referring to Figure 2, an embodiment of the present disclosure provides a schematic structural diagram of a rotor assembly. The first rotor 200 may have at least two parts. For example, the first rotor 200 has a coaxially arranged first working part 210 and a second working part 220, the first working part 210 of the first rotor 200 being integrally formed with the first shaft body 100, and the second working part 210 being sleeved on the first shaft body 100 and adjacent to the first working part 210. In some embodiments of the present disclosure, the end faces of the first working part 210 adjacent to the end face of the second working part 220 may be tightly fitted together. In other embodiments of the present disclosure, the end faces of the first working part 210 adjacent to the end face of the second working part 220 may not be tightly fitted together, and instead, a smaller gap, such as 0.1 mm, 0.2 mm, or 0.3 mm, may be provided between them.

[0032] In alternative embodiments, it should be understood that both the first actuation part 210 and the second actuation part 220 may be integrally formed with the first shaft body 100. Alternatively, both the first actuation part 210 and the second actuation part 220 are sleeved on the first shaft body 100.

[0033] Continuing to refer to Figures 1 and 2, the first rotor has helical blades, which may also be called male blades. In particular, the first working portion 210 has a plurality of first helical blades 211 and a plurality of first blade grooves 212 adjacent to each of the plurality of first helical blades 211, with one first blade groove 212 formed between two adjacent first helical blades 211. The second working portion 220 has a plurality of second helical blades 221 and a plurality of second blade grooves 222 adjacent to each of the plurality of second helical blades 221, with one second blade groove 222 formed between two adjacent second helical blades 221. The first helical blades 211 and the second helical blades 221 in the embodiments of the present disclosure are configured to have opposite helical directions. When the first rotor 200 and the second rotor 400 are engaged with each other in a rotational manner, opposite axial forces are generated between the first helical blade 211 and the second helical blade 221, which may be understood as generating opposite axial forces between the first helical blade 211 and the second helical blade 221. Due to the symmetry of the axial forces, the opposite axial forces generated between the first helical blade 211 and the second helical blade 221 may be almost reactive.

[0034] In this disclosure, unless otherwise explicitly stated, “multiple” means at least two.

[0035] Continuing to refer to Figures 1 and 2, the second rotor 400 is supported by the second shaft body 300 and is fixedly connected to the second shaft body 300, with one end of the second shaft body 300 rotatably mounted to the first bearing housing 500 and the other end of the second shaft body 300 rotatably mounted to the second bearing housing 700. In an alternative embodiment, the second rotor 400 is supported by the second shaft body 300 and is rotatably connected to the second shaft body 300, with one end of the second shaft body 300 fixedly mounted to the first bearing housing 500 and the other end of the second shaft body 300 fixedly mounted to the second bearing housing 700. The second rotor 400 meshes with and transmits power to the first rotor 400 and may be driven by the first rotor 200 to rotate in the first bearing housing 500 and the second bearing housing 700 along the second axis 310 of the second shaft body 300. That is, the second rotor 400 is rotatably supported in the first bearing housing 500 and the second bearing housing 700. In some embodiments of the present disclosure, the second rotor 400 may have at least two parts. For example, the second rotor 400 has a coaxially arranged third working part 410 and a fourth working part 420, both of which are sleeved on the second shaft body 300. Both the third working part 410 and the fourth working part 420 are rotatable in the housing 800 about the second axis 310.

[0036] The third operating part 410 engages with and transmits power to the first operating part 210, and the fourth operating part 420 engages with and transmits power to the second operating part 220. The rotation direction of the third operating part 410 is opposite to that of the first operating part 210, and the rotation direction of the fourth operating part 420 is opposite to that of the second operating part 220.

[0037] The second rotor 400 has helical blades, which may also be called female blades. In particular, the third working part 410 has a plurality of third helical blades 411 and a plurality of third blade grooves 412 adjacent to each of the plurality of third helical blades 411, with one third blade groove 412 formed between two adjacent third helical blades 411. The fourth working part 420 has a plurality of fourth helical blades 421 and a plurality of fourth blade grooves 422 adjacent to each of the plurality of fourth helical blades 421, with one fourth blade groove 422 formed between two adjacent fourth helical blades 421. The third helical blade 411 engages with the corresponding first blade groove 212, the first helical blade 211 engages with the corresponding third blade groove 412, the fourth helical blade 421 engages with the corresponding second blade groove 222, and the second helical blade 221 engages with the corresponding fourth blade groove 422. The third helical blade 411 and the fourth helical blade 421 in embodiments of the present disclosure are configured to have opposite helical directions. When the first rotor 200 and the fourth rotor 400 are engaged with each other to rotate, opposite axial forces are generated between the third helical blade 411 and the fourth helical blade 421, which may be understood as generating opposite axial forces between the third helical blade 411 and the fourth helical blade 421. Due to the symmetry of the axial forces, the opposing axial forces between the third helical blade 411 and the fourth helical blade 421 can be almost entirely reactive.

[0038] It should be noted that the terms “first,” “second,” “third,” and “fourth” in the description and claims of this disclosure are used to distinguish different subjects, not to indicate a specific order. Furthermore, the terms “includes” and “have,” and their variations, are intended to cover non-exclusive inclusion.

[0039] In the first rotor 200 and the second rotor 400, when the first rotor 200 and the second rotor 400 rotate together by meshing with each other, opposite axial forces may be generated due to the opposite rotation directions of the first operating part 210 and the second operating part 220, and opposite axial forces may be generated due to the opposite rotation directions of the third operating part 210 and the fourth operating part 420, and the axial force between the first operating part 210 and the second operating part 220 may be reacted to to some extent, and the axial force between the third operating part 410 and the fourth operating part 420 may be reacted to to some extent.

[0040] However, it should be noted that in the actual manufacturing process, in one embodiment, due to manufacturing deviation issues, differences exist in the configuration of different parts of the first rotor 200 and differences exist in the configuration of different parts of the second rotor 400. Also, differences exist between the first rotor 200 and the second rotor 400. In another embodiment, due to tolerance and deviation issues in assembly, differences exist in the mounting between the first rotor 200 and the second rotor 400. This leads to impossible complete reaction of axial forces between the first working part 210 and the second working part 220 and impossible complete reaction of axial forces between the third working part 410 and the fourth working part 420. That is, when the first rotor 200 and the second rotor 400 are engaged with each other so as to rotate together, it is impossible to form a resultant force of axial forces in random directions due to the impossible near-perfect reaction of axial forces. The resultant force of the axial forces may point in the first direction H1, and the resultant force of the axial forces may also point in the second direction H2.

[0041] In a further embodiment, in the quantification of compressor products, differences between rotors in each compressor lead to different directions of the resultant axial forces generated by the rotors in each compressor. For example, the direction of the resultant axial force of the rotors in some compressors points in a first direction H1, while the direction of the resultant axial force of the rotors in some other compressors points in a second direction H2. That is, a resultant force with random axial directions and random values ​​appears in the entire rotor-shaft system, causing the entire rotor-shaft system to be randomly pressed against one of the first bearing housing 500 and the second bearing housing 700, resulting in contact and friction between the rotor surface on that side and the housing, and ultimately leading to failure.

[0042] In the related technology, in order to ensure the stable operation of all molded compressors, two sets of thrust bearings (or axial thrust bearings) are sleeved on each shaft body of each compressor to limit the resultant force of the axial force on the rotor in all molded compressors. In this way, the stable operation of all molded compressors can be ensured.

[0043] Therefore, the use of thrust bearings to support limiting loads remains unavoidable. However, due to the randomness of the direction of the resultant force, the thrust bearings must be able to support limiting loads in two directions. That is, to ensure the limiting of the resultant force of axial forces on the rotor during the actual manufacturing and processing processes of the compressor, thrust bearings (axial thrust bearings) are still required to be installed on one rotating shaft to limit in two directions. For example, a compressor may be provided with two sets of thrust bearings having opposite bearing directions to ensure that the resultant force of axial forces appearing randomly in two directions is supported. However, for a single individual compressor, the direction of the random resultant force of axial forces is always constant. In this case, one set of thrust bearings is used for limiting, while the other set of thrust bearings is completely idle, resulting in a lower price-performance ratio. Furthermore, redundant mechanical losses and the demand for lubricating oil arise, increasing the failure rate of the compressor. Finally, the size and cost of the compressor assembly increase, the mechanical efficiency of the rotor-shaft system operation decreases to some extent, and the demand for lubricating oil increases.

[0044] Next, refer to Figure 3, an end view showing the ends of the first and second rotors of a first type rotor assembly provided by an embodiment of the present disclosure. Referring to Figure 2, at least one first pneumatic groove 213 is provided on the first end face 214 of the first working part 210, away from the second working part 220, and at least one first pneumatic groove 213 communicates with at least one of a plurality of first blade grooves 212 of the first working part 210, and the first pneumatic groove 213 is configured to form a force in a predetermined direction along the first axis 110 when rotating.

[0045] The first end face 214 provides a clearance fit with the first inner wall 510 of the first bearing housing 500. As the first and second working parts 210 and 220 rotate about the first axis 110, at least one first pneumatic groove 213 draws in and pressurizes gas from at least one of the plurality of first blade grooves 212, forming a layer of gas film between the first end face 214 and the first inner wall 510 to prevent the first working part 210 from coming into contact with the first inner wall 510.

[0046] In the embodiments of this disclosure, the first working part 210 of the compressor 1000 draws in and pressurizes gas from the first blade groove 212 through the first pneumatic groove 213, thereby forming a fixed gas axial force directed toward the second working part 220, ensuring that the rotor shaft system is always subjected to axial force only in a fixed direction, and only one set of thrust bearings 900 is required to support the gas axial force directed toward the second working part, thus reducing the use of thrust bearings 220. In this way, the cost of the compressor 1000 may be reduced, the volume of the compressor 1000 may be reduced, the structure of the moving parts of the compressor 1000 may be simplified, and the performance and reliability of the compressor 1000 may be improved. Furthermore, after the thrust bearing for supporting the axial gas force directed toward the second working part 220 is eliminated, the layer of gas film formed between the first end face 214 of the first working part 210 and the first inner wall 510 of the housing 800 can prevent failures caused by collisions and friction between the first rotor 200 and the housing 800, thus further improving the performance and reliability of the compressor 1000.

[0047] Based on the first type of rotor assembly described above, refer to Figure 4, an end view showing the first rotor and the other end of the second rotor of a second type of rotor assembly provided by an embodiment of the present disclosure. Referring to Figure 2, at least one second pneumatic groove 223 is provided on the second end face 224 of the second working part 220, away from the first working part 210, and at least one second pneumatic groove 223 communicates with at least one of a plurality of second blade grooves 222 of the second working part 220, and the second pneumatic groove 223 is configured to form a force in a predetermined direction along the first axis 110 when rotating.

[0048] The second end face 224 provides a clearance fit with the second inner wall 710 of the second bearing housing 700, the second inner wall 710 being spaced apart from the first inner wall 510 and positioned on the opposite side of the first inner wall 510. As the first and second working parts 210 and 220 rotate about the first axis 110, at least one second pneumatic groove 223 each draws in and pressurizes gas from at least one of the plurality of second blade grooves 222, forming a layer of gas film between the second end face 224 and the second inner wall 710 to prevent the second working part 220 from contacting the second inner wall 710.

[0049] In the embodiments of the present disclosure, the first working part 210 of the compressor 1000 draws in and pressurizes gas from the first blade groove 212 through the first pneumatic groove 213, thereby forming a fixed gas axial force directed toward the second working part 220. The second working part 220 of the compressor 1000 draws in and pressurizes gas from the second blade groove 222 through the second pneumatic groove 223, thereby forming a fixed gas axial force directed toward the first working part 210. The gas axial forces in the two directions can balance the axial force applied to the first rotor 200, thereby further eliminating the thrust bearing provided in the first shaft body 100. The embodiments of the present disclosure can further reduce the cost of the compressor 1000, reduce the volume of the compressor 1000, simplify the structure of the moving parts of the compressor 1000, and improve the performance and reliability of the compressor 1000. Furthermore, after the thrust bearings for supporting the axial gas forces directed toward the two ends of the first rotor 200 are eliminated, the gas films formed between the first end face 214 and the first bearing housing 500 and between the second end face 224 and the second bearing housing 700 can prevent failures caused by collisions and friction between the two ends of the first rotor 200 and the first and second bearing housings 500 and 700, thereby further improving the performance and reliability of the compressor 1000.

[0050] Based on the first type of rotor assembly described above, refer to Figure 5, an end view showing one end of the first and second rotors of a third type of rotor assembly provided by an embodiment of the present disclosure. Referring to Figure 2, at least one third pneumatic groove 413 is provided on the third end face 414 of the third working part 410, away from the fourth working part 420, and at least one third pneumatic groove 413 communicates with at least one of a plurality of third blade grooves 412 of the third working part 410, and the third pneumatic groove 413 is configured to form a force in a predetermined direction along the second axis 310 when rotating.

[0051] The third end face 414 provides a clearance fit with the first inner wall of the first bearing housing 500. As the third and fourth working parts 410 and 420 rotate about the second axis 310, at least one third pneumatic groove 413 draws in and pressurizes gas from at least one of the plurality of third blade grooves 412, forming a layer of gas film between the third section 414 and the first inner wall 510 to prevent the third working part from coming into contact with the first inner wall 510.

[0052] In the embodiments of the present disclosure, the first working part 210 of the compressor 1000 draws in and pressurizes gas from the first blade groove 212 through the first pneumatic groove 213, and the third working part 410 draws in and pressurizes gas from the third blade groove 412 through the third pneumatic groove 413, thereby forming a fixed gas axial force directed toward the second working part 220 and the fourth working part 420, ensuring that the rotor shaft system is always subjected to axial force only in a fixed direction, thereby requiring only one set of thrust bearings to be provided on the first shaft body 100 and the second shaft body 300, respectively, to support the gas axial force directed toward the second working part 220 and the fourth working part 420, thus reducing the use of thrust bearings. The embodiments of this disclosure can reduce the cost of the compressor 1000, decrease the volume of the compressor 1000, simplify the structure of the moving parts of the compressor 1000, and improve the performance and reliability of the compressor 1000. Furthermore, after the thrust bearings for supporting the axial gas forces directed toward the second working part 220 and the fourth working part 420 are eliminated, the gas films formed between the first end face 214 and the first bearing housing 500 and the gas films formed between the second end face 224 and the first bearing housing 500 can prevent failures caused by collisions and friction between the first rotor 200 or the second rotor 400 and the first bearing housing 500, thus further improving the performance and reliability of the compressor 1000.

[0053] Based on the second type of rotor assembly described above, further reference is made to Figure 6, an end view showing the first rotor and the other end of the second rotor of the second type of rotor assembly provided by an embodiment of the present disclosure. Referring to Figure 2, at least one third pneumatic groove 413 is provided on the third end face 414 of the third working part 410, away from the fourth working part 420, and at least one third pneumatic groove 413 communicates with at least one of a plurality of third blade grooves 412 of the third working part 410. At least one fourth pneumatic groove 423 is provided on the fourth end face 424 of the fourth working part 420, away from the third working part 410, and at least one fourth pneumatic groove 423 communicates with at least one of a plurality of fourth blade grooves 422 of the fourth working part 420, and the fourth pneumatic groove 423 is configured to form a force in a predetermined direction along the second axis 310 when rotating.

[0054] The third end face 414 provides a clearance fit with the first inner wall 510 of the first bearing housing 500, and the fourth end face 424 provides a clearance fit with the second inner wall 710 of the second bearing housing 700. As the third and fourth working parts 410 and 420 rotate around the second axis 310, at least one third pneumatic groove 413 draws in and pressurizes gas from at least one of the plurality of third blade grooves 412, forming a layer of gas film between the third end face 414 and the first inner wall 510 to prevent the third working part 410 from coming into contact with the first inner wall 510, and at least one fourth pneumatic groove 423 draws in and pressurizes gas from at least one of the plurality of fourth blade grooves 422, forming a layer of gas film between the fourth end face 424 and the second inner wall 710 to prevent the fourth working part 420 from coming into contact with the second inner wall 710.

[0055] In the embodiments of this disclosure, the first working part 210 of the compressor 1000 draws in and pressurizes gas from the first blade groove 212 through the first pneumatic groove 213, thereby forming a fixed gas axial force directed toward the second working part 220. The second working part 220 of the compressor 1000 draws in and pressurizes gas from the second blade groove 222 through the second pneumatic groove 223, thereby forming a fixed gas axial force directed toward the first working part 210. The gas axial forces in the two directions can balance the axial force applied to the first rotor 200, thereby further eliminating the thrust bearing provided in the first shaft body 100. Furthermore, the third working part 410 of the compressor 1000 draws in and pressurizes gas from the third blade groove 413 through the third pneumatic groove 413, thereby forming a fixed gas axial force directed toward the second working part 220. The fourth working part 420 of the compressor 1000 draws gas from the fourth blade groove 422 through the fourth pneumatic groove 423 and pressurizes it, thereby forming a fixed gas axial force directed toward the first working part 210. The gas axial forces in two directions can balance the axial force applied to the second rotor 400, thereby further eliminating the thrust bearing provided in the second shaft body 300. Embodiments of the present disclosure can further reduce the cost of the compressor 1000, reduce the volume of the compressor 1000, simplify the structure of the moving parts of the compressor 1000, and improve the performance and reliability of the compressor 1000. Furthermore, after the thrust bearings for supporting the axial gas forces directed toward the two ends of the first rotor 200 and the two ends of the second rotor 400 are eliminated, the gas films formed between the two ends of the first rotor 200 and the first bearing housing 500, and between the two ends of the second rotor 400 and the second bearing housing 700, can prevent failures caused by collisions and friction between the two ends of the first rotor 200 and the first bearing housing 500, and between the two ends of the second rotor 400 and the second bearing housing 700, thereby further improving the performance and reliability of the compressor 1000.

[0056] In some embodiments, the first end face 214, the second end face 224, the third end face 414, the fourth end face 424, and / or the first inner wall 510 and the second inner wall 710 are each coated with an abrasion-resistant coating. The abrasion-resistant coating may be formed by spraying ceramic, alloy, oxide, fluoroplastic, etc., onto the first end face 214, the second end face 224, the third end face 414, the fourth end face 424, and / or the first inner wall 510 and the second inner wall 710 by plasma spraying, arc spraying, or flame spraying. The wear-resistant coating may be formed by coating the first end face 214, the second end face 224, the third end face 414, the fourth end face 424 and / or the first inner wall 510 and the second inner wall 710 with a wear-resistant coating adhesive made of various resins, elastomers, etc., and then allowing the wear-resistant coating adhesive to cure naturally or by curing the wear-resistant coating adhesive by heating.

[0057] In embodiments of the present disclosure, by coating the first end face 214, the second end face 224, the third end face 414, the fourth end face 424 and / or the first inner wall 510 and the second inner wall 710 with an abrasion-resistant coating, it is possible to ensure that the gas film at the two ends of the first rotor 200 and the second rotor 400 has sufficient force applied to the first rotor 200 and the second rotor 400 during the initial start-up or shutdown phase of the compressor 1000, thereby preventing failures caused by collisions between the two ends of the first rotor 200 and the first bearing housing 500 and between the two ends of the second rotor 400 and the second bearing housing 700, and thus further improving the performance and reliability of the compressor 1000.

[0058] In some embodiments, the gap between the first end face 214 or the third end face 414 and the first inner wall 510 is in the range of 3 to 5 microns, and the gap between the second end face 224 or the fourth end face 424 and the second inner wall 710 is in the range of 3 to 5 microns. In embodiments of the present disclosure, by setting the gap between the first end face 214 or the third end face 414 and the first inner wall 510 to the range of 3 to 5 microns, and the gap between the second end face 224 or the fourth end face 424 and the second inner wall 710 to the range of 3 to 5 microns, it is possible to ensure that the gas film at the two ends of the first rotor 200 and the gas film at the two ends of the second rotor 400 have higher rigidity. Furthermore, the end faces at two ends of the first rotor 200 and the end faces at two ends of the second rotor 400 are completely isolated from the first bearing housing 500 and the second bearing housing 700, respectively, and therefore no collision or friction can occur.

[0059] In some embodiments, as shown in Figures 3 to 6, the number of at least one first pneumatic groove 213, the number of at least one second pneumatic groove 223, the number of at least one third pneumatic groove 413, and the number of at least one fourth pneumatic groove 423 are multiple. The number of multiple first pneumatic grooves 213 is equal to the number of multiple first helical blades 211, the number of multiple second pneumatic grooves 223 is equal to the number of multiple second helical blades 221, the number of multiple third pneumatic grooves 413 is equal to the number of multiple third helical blades 411, and the number of multiple fourth pneumatic grooves 423 is equal to the number of multiple fourth helical blades 421.

[0060] In some embodiments, as shown in Figures 3 to 6, a plurality of first pneumatic grooves 213 are distributed spirally on the first end face 214 with the center of the first end face 214 as the center; a plurality of second pneumatic grooves 223 are distributed spirally on the second end face 224 with the center of the second end face 224 as the center; a plurality of third pneumatic grooves 413 are distributed spirally on the third end face 414 with the center of the third end face 414 as the center; and a plurality of fourth pneumatic grooves 423 are distributed spirally on the fourth end face 424 with the center of the fourth end face 424 as the center.

[0061] In some embodiments, as shown in Figures 3 to 6, each of the plurality of first pneumatic grooves 213 is provided on the end face of the corresponding first helical blade 211, and each of the plurality of first pneumatic grooves 213 communicates with the corresponding first blade groove 212. Each of the plurality of second pneumatic grooves 223 is provided on the end face of the corresponding second helical blade 221, and each of the plurality of second pneumatic grooves 223 communicates with the corresponding second blade groove 222. Each of the plurality of third pneumatic grooves 413 is provided on the end face of the corresponding third helical blade 411, and each of the plurality of third pneumatic grooves 413 communicates with the corresponding third blade groove 412. Each of the multiple fourth pneumatic grooves 423 is provided on the end face of the corresponding fourth helical blade 421, and each of the multiple fourth pneumatic grooves 423 communicates with the corresponding fourth blade groove 422.

[0062] The compressor 1000 in one or more of the above embodiments may be applied to an air conditioner.

[0063] Embodiments of this disclosure also provide an air conditioner, which includes a compressor 1000 defined by a combination of one or more of the embodiments described above.

[0064] A detailed description of the rotor assembly, compressor, and air conditioner provided by the embodiments of this disclosure is given above, and the details of the principles and implementations of this disclosure are given by using the specific examples herein, and the description of the embodiments is intended solely to assist in understanding the methods and central concepts of this disclosure. Furthermore, those skilled in the art may modify the specific implementation and scope of the application in accordance with the central concepts of this disclosure. In conclusion, the contents of this specification are not to be construed as limiting this disclosure. [Explanation of Symbols]

[0065] 100 First shaft body 110 First axis 200 First Rotor 210 First operating part 211 First spiral blade 212 First blade groove 213 First pneumatic groove 214 First end face 220 Second operating part 221 Second spiral blade 222 Second blade groove 223 Second pneumatic groove 224 Second end face 300 Second shaft body 310 Second axis 400 Second rotor 410 Third operating part 411 Third spiral blade 412 Third blade groove 413 Third pneumatic groove 414 Third end face 420 Fourth operating part 421 Fourth spiral blade 422 Fourth blade groove 423 Fourth pneumatic groove 424 Fourth end face 500 First bearing housing 510 First inner wall 600 Rotor Housing 610 Hollow Chamber 610 700 Second bearing housing 710 Second inner wall 800 Housing 900 Thrust Bearing 1000 Compressor 1100 Rotor Assembly H1 First direction H2 Second direction

Claims

1. A compressor (1000), A housing (800) having a first inner wall (510), A rotor assembly (1100) and a rotor assembly (1100) are provided, The first rotor (200) comprises a first operating part (210) and a second operating part (220) coaxially arranged in the housing (800), wherein the first operating part (210) and the second operating part (220) are rotatable about a first axis, the first operating part (210) comprises a plurality of first helical blades (211), a first blade groove (212) is formed between two adjacent first helical blades (211), and at least one first pneumatic groove (213) is located on the first operating part (210) away from the second operating part (220) A compressor (1000) is provided on an end face (214), the first end face (214) providing a clearance fit with the first inner wall (510), the first pneumatic groove (213) being configured to form a force toward the second working part (220) along the first axis when rotating, and at least one second pneumatic groove (223) being provided on a second end face (224) of the second working part (220) away from the first working part (210), the at least one second pneumatic groove (223) being configured to form a force toward the first working part (210).

2. The compressor (1000) according to claim 1, wherein at least one first pneumatic groove (213) communicates with at least one of the plurality of first blade grooves (212) of the first operating part (210).

3. The compressor (1000) according to claim 1 or 2, wherein the rotor assembly (1100) further comprises a second rotor (400) having a coaxially arranged third operating part (410) and a fourth operating part (420), the third operating part (410) being engaged with the first operating part (210), the fourth operating part (420) being engaged with the second operating part (220), and both the third operating part (410) and the fourth operating part (420) being rotatable about a second axis.

4. The compressor (1000) according to any one of claims 1 to 3, wherein the first end face (214) is coated with an abrasion-resistant coating and / or the first inner wall (510) is coated with the abrasion-resistant coating.

5. A compressor (1000) according to any one of claims 1 to 3, wherein the first operating portion (210) comprises a plurality of first helical blades (211), the plurality of first blade grooves (212) are each adjacent to the plurality of first helical blades (211), the at least one first pneumatic groove (213) comprises a plurality of first pneumatic grooves (213), and each of the plurality of first helical blades (211) is provided with at least one first pneumatic groove (213).

6. The compressor (1000) according to claim 5, wherein a plurality of the first air pressure grooves (213) are distributed spirally on the first end face (214) with the center of the first end face (214) as the center.

7. The compressor (1000) according to claim 5, wherein the number of the plurality of first pneumatic grooves (213) is equal to the number of the plurality of first helical blades (211), each of the plurality of first pneumatic grooves (213) is provided on the end face of the corresponding first helical blade (211), and each of the plurality of first pneumatic grooves (213) is in communication with the corresponding first blade groove (212).

8. An air conditioner comprising a compressor (1000) according to any one of claims 1 to 7.