A turbo-compressor and vehicle

Abstract

This application discloses a turbo compressor and a vehicle. The turbo compressor includes a motor assembly, a bearing housing, and a scroll assembly arranged sequentially in an axial direction. The motor assembly includes an open motor housing and a motor housed within the motor housing, with the open end of the motor housing facing the bearing housing. The bearing housing has an air passage communicating with the interior of the motor housing. The scroll assembly includes a moving scroll and a stationary scroll that mesh with each other. The moving scroll is disposed between the bearing housing and the stationary scroll. A mounting hole is provided on the side of the moving scroll facing the bearing housing, and an anti-swirl ring is installed in the mounting hole. A protruding structure is provided between the motor assembly and the anti-swirl ring along the axial direction. The orthogonal projection of the protruding structure on the bearing housing partially overlaps with the air passage to prevent the anti-swirl ring from entering the motor housing through the air passage. Through these methods, this application can improve the reliability of the turbo compressor.

Description

Technical Field

[0001] This application relates to the field of turbo compressor technology, and in particular to a turbo compressor and a vehicle. Background Technology

[0002] As a core device for high-efficiency energy conversion, turbo compressors are widely used in aero engines, gas turbines, industrial drives, and other fields. Their operational stability and reliability directly affect the performance and safety of the entire system. Precise installation and positioning are crucial during the integration and assembly of turbo compressors. The applicant of this application discovered that anti-rotation rings can accidentally fall off during assembly. Fallen parts can generate noise and damage precision components inside the motor, potentially leading to motor failure in severe cases. Utility Model Content

[0003] The main technical problem addressed by this application is to provide a turbo compressor and a vehicle that can improve the reliability of the turbo compressor.

[0004] To solve the above-mentioned technical problems, one technical solution adopted in this application is: providing a turbo compressor, including a motor assembly, a bearing housing, and a scroll assembly arranged sequentially in an axial direction; the motor assembly includes an open motor housing and a motor housed in the motor housing, with the open end of the motor housing facing the bearing housing; the bearing housing is provided with an air passage communicating with the interior of the motor housing; the scroll assembly includes a moving scroll and a stationary scroll that mesh with each other, the moving scroll being disposed between the bearing housing and the stationary scroll, and the moving scroll having a mounting hole on its side surface facing the bearing housing, in which an anti-swirl ring is installed; wherein, along the axial direction, a protruding structure is provided between the motor assembly and the anti-swirl ring, the orthogonal projection of the protruding structure on the bearing housing partially overlapping the air passage, to prevent the anti-swirl ring from entering the motor housing from the air passage.

[0005] The air passage includes a first sidewall and a second sidewall disposed opposite to each other in the radial direction of the turbine compressor. In the radial direction, the protruding structure protrudes from the first sidewall and is spaced apart from the second sidewall. The distance between the protruding structure and the second sidewall is less than the height of the anti-spin ring.

[0006] The number of air passages and protruding structures are both multiple, and the multiple air passages and multiple protruding structures are arranged in a one-to-one correspondence. In the radial direction, each protruding structure protrudes from the first sidewall of the corresponding air passage and is spaced apart from the second sidewall of the corresponding air passage.

[0007] The protruding structure is formed on the first sidewall of the airway.

[0008] The turbo compressor further includes: a wear-resistant plate disposed between the bearing housing and the moving scroll, and the protruding structure protruding from the outer peripheral surface of the wear-resistant plate.

[0009] In the radial direction, the distance between the protruding structure and the side of the airway away from the protruding structure ranges from 1 cm to 4 cm.

[0010] Wherein, the area of ​​the cross-section of the protruding structure perpendicular to the axial direction is less than 12 square centimeters.

[0011] The cross-section of the protruding structure perpendicular to the axial direction is hemispherical, triangular, or rectangular.

[0012] The length of the air passage is less than the diameter of the anti-spin ring.

[0013] To solve the above-mentioned technical problems, another technical solution adopted in this application is to provide a vehicle that includes the turbo compressor described in any of the above technical solutions.

[0014] The beneficial effects of this application are as follows: Unlike the prior art, the air passage of the bearing housing in this application is connected to the interior of the motor housing, an anti-rotation ring is provided in the mounting hole of the moving scroll, and a protruding structure is provided between the moving scroll and the motor assembly. The protruding structure overlaps with the orthogonal projection of the air passage in the bearing housing, and the protruding structure covers part of the air passage. The protruding structure prevents the anti-rotation ring from falling into the air passage, thereby improving the protection of the motor assembly and enhancing the reliability of the turbo compressor. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. Wherein:

[0016] Figure 1 This is a schematic diagram of one embodiment of the turbo compressor of this application;

[0017] Figure 2 yes Figure 1 Schematic diagram of the structure of the bearing housing;

[0018] Figure 3 yes Figure 2 A schematic diagram of the airway structure in the middle;

[0019] Figure 4 yes Figure 1 Schematic diagram of the structure of the anti-spin ring;

[0020] Figure 5 yes Figure 1 Schematic diagram of the wear-resistant plate and bearing housing. Detailed Implementation

[0021] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0022] See Figure 1 and Figure 2 The turbo compressor 1 includes a motor assembly 10, a bearing housing 20, and a scroll assembly 30 arranged sequentially along the axial direction 11.

[0023] The motor assembly 10 includes an open motor housing 110 and a motor 120 housed within the motor housing 110. The open end of the motor housing 110 faces the bearing seat 20. The bearing seat 20 is provided with an air passage 210 communicating with the interior of the motor housing 110. The vortex assembly 30 includes a moving vortex 310 and a stationary vortex 320 that mesh with each other. The moving vortex 310 is disposed between the bearing seat 20 and the stationary vortex 320. Meanwhile, the side surface of the moving vortex 310 facing the bearing seat 20 is provided with a mounting hole (not shown). An anti-rotation ring 311 is installed in the mounting hole. Along the axial direction 11, a protruding structure 40 is provided between the motor assembly 10 and the anti-rotation ring 311. The orthogonal projection of the protruding structure 40 on the bearing seat 20 partially overlaps with the air passage 210 to prevent the anti-rotation ring 311 from entering the motor housing 110 from the air passage 210.

[0024] Specifically, the motor 120 is located in the cavity between the motor housing 110 and the bearing seat 20. The motor 120 drives the moving scroll 310 to translate, and the scroll lines of the moving scroll 310 and the stationary scroll 320 always remain tangentially meshed. The air passage 210 on the bearing seat 20 transmits the gas inside the motor housing 110 to the cavity between the moving scroll 310 and the stationary scroll 320. The motor 120 rotates the moving scroll 310 to compress the gas. To prevent the moving scroll 310 from rotating, an anti-rotation ring 311 is provided in the mounting hole on the side of the moving scroll 310 facing the bearing seat 20. The anti-rotation ring 311 forces the moving scroll 310 to maintain a fixed angular direction through a mechanical structure, allowing only the center of the moving scroll 310 to revolve around the center of the stationary scroll 320. During the installation or disassembly of the turbo compressor 1, the anti-rotation ring 311 is easily dislodged from the mounting hole due to the clearance fit between the anti-rotation ring 311 and the mounting hole. It then enters the cavity of the motor housing 110 through the air passage 210, causing abnormal noise and vibration in the turbo compressor 1. In this application, a protruding structure 40 is provided between the motor assembly 10 and the anti-rotation ring 311. The protruding structure 40 is located on one side of the air passage 210, and the orthogonal projection of the protruding structure 40 on the bearing seat 20 coincides with the orthogonal projection of the air passage 210. The protruding structure 40 partially blocks the air passage 210, preventing the anti-rotation ring 311 from falling from the air passage 210 into the cavity of the motor housing 110, thereby improving the reliability of the turbo compressor 1.

[0025] See Figure 3 and Figure 4 The air passage 210 includes a first sidewall 211 and a second sidewall 212 disposed opposite to each other in the radial direction of the turbine compressor 1. In the radial direction, a protruding structure 40 protrudes from the first sidewall 211 and the protruding structure 40 and the second sidewall 212 are spaced apart. The distance a between the protruding structure 40 and the second sidewall 212 is less than the height h of the anti-rotation ring 311.

[0026] Specifically, the protruding structure 40 protrudes from the first sidewall 211 of the air passage 210, that is, the protruding structure 40 extends radially from the first sidewall 211 into the air passage 210. The distance a between the protruding structure 40 and the second sidewall 212 is less than the height h of the anti-rotation ring 311. When the anti-rotation ring 311 falls out of the mounting hole, the radial clearance of the air passage 210 is reduced due to the protruding structure 40, thus preventing the anti-rotation ring 311 from entering the air passage 210.

[0027] In another embodiment, the protruding structure 40 protrudes from the second sidewall 212, and the protruding structure 40 is spaced apart from the first sidewall 211. The distance between the protruding structure 40 and the first sidewall 211 is less than the height h of the anti-rotation ring 311, so as to prevent the anti-rotation ring 311 from falling out of the mounting hole and entering the air passage 210.

[0028] See Figure 2In one embodiment, there are multiple air passages 210 and multiple protrusions 40. The multiple air passages 210 are arranged in a one-to-one correspondence with the multiple protrusions 40. In the radial direction, the protrusions 40 protrude from the first sidewall 211 of the corresponding air passage 210 and are spaced apart from the second sidewall 212 of the corresponding air passage 210.

[0029] Specifically, multiple air passages 210 are arranged circumferentially around the bearing housing 20, with each air passage 210 corresponding to a protruding structure 40. In the radial direction, each protruding structure 40 protrudes from the first sidewall 211 of the corresponding air passage 210 and is spaced apart from the second sidewall 212 of the corresponding air passage 210. The multiple air passages 210 increase the gas flow through the air passages 210 while preventing the anti-rotation ring 311 from falling into the motor housing 110. Alternatively, in other embodiments, each protruding structure 40 may protrude from the second sidewall 212 of the corresponding air passage 210 and be spaced apart from the first sidewall 211 of the corresponding air passage 210.

[0030] In another embodiment, a portion of the multiple air passages 210 are provided with protruding structures 40, each protruding from the first sidewall 211 of the corresponding air passage 210 and spaced apart from the second sidewall 212 of the corresponding air passage 210, while the other portion of the air passages 210 are not provided with protruding structures 40, in order to increase the gas flow rate through the air passages 210.

[0031] See Figure 3 In one embodiment, a protrusion 40 is formed on the first sidewall 211 of the airway 210. The protrusion 40 is located on the first sidewall 211. Compared to installing the protrusion 40 as a separate part into the airway 210, the protrusion 40 being formed on the first sidewall 211 of the airway 210 reduces additional connection points or fixing structures.

[0032] In one embodiment, the height of the protrusion 40 along the axial direction 11 may be less than the depth of the air passage 210 along the axial direction 11. In another embodiment, the height of the protrusion 40 along the axial direction 11 may also be equal to the depth of the air passage 210 along the axial direction 11, which facilitates the fabrication of the protrusion 40 when machining the air passage 210. In yet another embodiment, the height of the protrusion 40 along the axial direction 11 may be greater than the depth of the air passage 210 along the axial direction 11. The height of the protrusion 40 can be adjusted as needed to meet diverse application scenarios.

[0033] See Figure 1 and Figure 5 In one embodiment, the turbo compressor 1 further includes a wear-resistant plate 50, which is disposed between the bearing housing 20 and the moving scroll 310, and the protruding structure 40 protrudes from the outer peripheral surface of the wear-resistant plate 50.

[0034] Specifically, the wear-resistant plate 50 is disposed between the bearing housing 20 and the moving scroll 310. The wear-resistant plate 50 bears the main abrasive load and can effectively reduce excessive wear and material loss of the core components of the turbo compressor 1, extending the service life of the components and the overall operating time of the turbo compressor 1. The protruding structure 40 protrudes from the outer peripheral surface of the wear-resistant plate 50 and covers part of the air passage 210 to prevent the anti-rotation ring 311 from falling into the air passage 210. By providing the protruding structure 40 on the outer peripheral surface of the wear-resistant plate 50, when the protruding structure 40 needs to be replaced, the wear-resistant plate 50 can be replaced directly, which is easier to replace and reduces costs, compared to having the protruding structure 40 on the bearing housing 20.

[0035] Continue reading Figure 5 In one embodiment, the outer peripheral surface of the wear-resistant sheet 50 is provided with a plurality of protrusions 40, each protrusion 40 corresponding to a corresponding air passage 210, thereby further reducing the probability of the anti-rotation ring 311 falling into the air passage 210.

[0036] See Figure 3 In one embodiment, the distance between the protrusion 40 and the side of the airway 210 away from the protrusion 40 in the radial direction ranges from 1 cm to 4 cm.

[0037] Specifically, such as Figure 5 As shown, the protrusion structure 40 can be provided on the outer peripheral surface of the wear-resistant sheet 50, or, as... Figure 3 As shown, the protrusion 40 can also be formed on the first sidewall 211 of the air passage 210 of the bearing housing 20. The distance between the protrusion 40 and the side of the air passage 210 away from the protrusion 40 is 1 cm, 1.5 cm, 2 cm, 2.5 cm, 3 cm, 3.5 cm or 4 cm. The height h of the anti-rotation ring 311 is usually 5 cm. The distance between the protrusion 40 and the side of the air passage 210 away from the protrusion 40 is in the range of 1 cm to 4 cm, which can effectively prevent the anti-rotation ring 311 from falling into the air passage 210, and at the same time prevent the gas flow in the air passage 210 from being too small.

[0038] In one embodiment, the distance between the protruding structure 40 and the side of the airway 210 away from the protruding structure 40 may also be less than 1 cm, for example, the distance is 0.5 cm.

[0039] Combination Figure 2 and Figure 3 In one embodiment, when the protrusion 40 is formed on the first sidewall 211 of the air passage 210 of the bearing housing 20, the distance between the protrusion 40 and the side of the air passage 210 away from the protrusion 40 is the interval distance a between the protrusion 40 and the second sidewall 212, and the interval distance a between the protrusion 40 and the second sidewall 212 ranges from 1 cm to 4 cm.

[0040] In another embodiment, when the protrusion 40 is formed on the second sidewall 212 of the air passage 210 of the bearing housing 20, the distance between the protrusion 40 and the side of the air passage 210 away from the protrusion 40 is the interval distance between the protrusion 40 and the first sidewall 211, and the interval distance between the protrusion 40 and the first sidewall 211 ranges from 1 cm to 4 cm.

[0041] In one embodiment, the protrusion structure 40 is disposed on the outer peripheral surface of the wear-resistant sheet 50, and the distance between the protrusion structure 40 and the side of the air passage 210 away from the protrusion structure 40 is the interval distance a between the protrusion structure 40 and the second sidewall 212. The interval distance a between the protrusion structure 40 and the second sidewall 212 ranges from 1 cm to 4 cm.

[0042] See Figure 3 In one embodiment, the area of ​​the cross-section of the protrusion 40 perpendicular to the axial direction 11 is less than 12 square centimeters.

[0043] Specifically, the area of ​​the cross-section of the protruding structure 40 perpendicular to the axial direction 11 can be 7 square centimeters, 8 square centimeters, 9 square centimeters, 10 square centimeters, or 11 square centimeters. The area of ​​the cross-section of the protruding structure 40 perpendicular to the axial direction 11 is less than 12 square centimeters to avoid the cross-section of the protruding structure 40 being too large, thereby effectively preventing the protruding structure 40 from excessively reducing the gas flow rate in the airway 210. In another embodiment, the area of ​​the cross-section of the protruding structure 40 perpendicular to the axial direction 11 can also be 12 square centimeters.

[0044] In one embodiment, the area of ​​the cross-section of the protruding structure 40 perpendicular to the axial direction 11 does not exceed one-tenth of the area of ​​the cross-section of the airway 210 perpendicular to the axial direction 11, thereby reducing the influence of the excessively large cross-section of the protruding structure 40 on the airflow in the airway 210.

[0045] See Figure 3 In one embodiment, the cross-section of the protrusion 40 perpendicular to the axial direction 11 is hemispherical, triangular or rectangular.

[0046] Specifically, the cross-section of the protruding structure 40 perpendicular to the axis 11 can be hemispherical, triangular, or rectangular. Alternatively, some of the protruding structures 40 may have a hemispherical cross-section perpendicular to the axis 11, some may have a triangular cross-section, and the rest may have a rectangular cross-section. Figure 3 The cross-section of the protruding structure 40 perpendicular to the axis 11 is hemispherical, which is used for illustration.

[0047] In one embodiment, the protrusion structure 40 is a solid structure; in another embodiment, the protrusion structure 40 is a hollow structure, which can reduce the weight of the protrusion structure 40.

[0048] See Figure 3 In one embodiment, the length L of the air passage 210 is smaller than the diameter D of the anti-rotation ring 311. That is, by setting the length L of the air passage 210, the anti-rotation ring 311 is prevented from entering the air passage 210. The structure of the air passage 210 itself provides protection for the motor 120, which is convenient for processing and reduces costs.

[0049] In other embodiments, the length L of the airway 210 may also be greater than the diameter D of the anti-rotation ring 311, by providing a protruding structure 40 to prevent the anti-rotation ring 311 from falling into the airway 210.

[0050] This application also protects a vehicle that includes a turbo compressor 1 as described in any of the above claims. The vehicle includes gasoline-powered vehicles, electric vehicles, hybrid vehicles, and hydrogen fuel cell vehicles, and also includes sedans, SUVs, and commercial vehicles, etc. It should be noted that this application does not limit the type of vehicle. The specific structure of the turbo compressor 1 is as described above and will not be repeated here.

[0051] The above description is merely an embodiment of this application and does not limit the patent scope of this application. Any equivalent structural or procedural transformations made using the content of this application's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this application.

Claims

1. A turbo-compressor characterized in that, It includes a motor assembly, a bearing housing, and a scroll assembly arranged sequentially in the axial direction; The motor assembly includes an open motor housing and a motor housed within the motor housing, with the open end of the motor housing facing the bearing seat. The bearing housing is provided with an air passage that communicates with the interior of the motor housing; The vortex assembly includes a moving vortex and a stationary vortex that mesh with each other. The moving vortex is disposed between the bearing housing and the stationary vortex. Meanwhile, the moving vortex has a mounting hole on the side surface facing the bearing housing, and an anti-rotation ring is installed in the mounting hole. Along the axial direction, a protruding structure is provided between the motor assembly and the anti-rotation ring. The orthogonal projection of the protruding structure on the bearing seat overlaps with the air passage portion to prevent the anti-rotation ring from entering the motor housing through the air passage.

2. The turbo-compressor of claim 1, wherein, The air passage includes a first sidewall and a second sidewall disposed opposite to each other in the radial direction of the turbo compressor. In the radial direction, the protruding structure protrudes from the first sidewall and is spaced apart from the second sidewall. The distance between the protruding structure and the second sidewall is less than the height of the anti-rotation ring.

3. The turbo-compressor of claim 2, wherein, There are multiple air passages and multiple protruding structures, with each air passage corresponding to one of the multiple protruding structures. In the radial direction, each of the protruding structures protrudes from the first sidewall of the corresponding airway and is spaced apart from the second sidewall of the corresponding airway.

4. The turbo-compressor of claim 2, wherein, The protruding structure is formed on the first sidewall of the airway.

5. The turbo-compressor of claim 2, wherein, The turbo compressor also includes: A wear-resistant plate is disposed between the bearing housing and the moving vortex, and the protruding structure protrudes from the outer peripheral surface of the wear-resistant plate.

6. The turbo-compressor of claim 1, wherein, In the radial direction, the distance between the protruding structure and the side of the airway away from the protruding structure ranges from 1 cm to 4 cm.

7. The turbo-compressor of claim 1, wherein, The area of ​​the cross-section of the protruding structure perpendicular to the axial direction is less than 12 square centimeters.

8. The turbo-compressor of claim 1, wherein, The cross-section of the protrusion structure perpendicular to the axial direction is hemispherical, triangular, or rectangular.

9. The turbo-compressor of claim 1, wherein, The length of the air passage is less than the diameter of the anti-spin ring.

10. A vehicle characterized by comprising: Including the turbo compressor as described in any one of claims 1 to 9.

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