Gas dynamic thrust bearing assembly and motor having the same

Abstract

The application provides a gas dynamic pressure thrust bearing assembly and a motor with the same. The gas dynamic pressure thrust bearing assembly comprises a rotating shaft and a thrust plate on the rotating shaft. The thrust plate has two end faces along the axial direction of the rotating shaft. At least one of the end faces is provided with a plurality of first grooves. The first grooves are distributed on the thrust plate at intervals and surround the rotating shaft. The first grooves comprise a communicating inner side section and an outer side section. The outer side section is located outside the inner side section along the radial direction of the thrust plate. The outer side section is arranged to be inclined relative to the inner side section to form a horn mouth structure. According to the application, the first grooves are arranged on the thrust plate opposite to the thrust bearing, thereby solving the problem that it is not suitable to arrange grooves on the thrust bearing with a small thickness to improve the overall performance of the bearing. The arrangement of the grooves on the thrust plate can increase the gas film thickness, facilitate the rapid formation of the gas film, thereby improving the vibration resistance and stability of the bearing and improving the bearing carrying capacity.

Description

Technical Field

[0001] This invention belongs to the field of motor technology, specifically relating to a gas dynamic thrust bearing assembly and a motor having the same. Background Technology

[0002] Currently, a pneumatic thrust bearing assembly with a hummingbird wing structure is disclosed in the prior art. It mainly includes a main shaft 1, a thrust plate 2, and a thrust bearing 3. The thrust plate 2 and the main shaft 1 are coaxially arranged and fixedly connected. The thrust bearing 3 is installed on the main shaft 1 below the thrust plate 2. The upper surface of the thrust bearing 3 has grooves, and the area between the grooves is a platform. The thrust bearing 3 has a clearance fit with the main shaft 1, and an air film exists between the thrust plate 2 and the thrust bearing 3. Figure 4 and Figure 5 As shown, the upper surface of the thrust bearing 3 has uniformly distributed grooves simulating the structure of a hummingbird wing. Air enters from the leading edge of the grooves, and the throttling effect of the grooves changes the gas velocity and density at the junction of the platform and the grooves, forming a high-pressure gas zone. This gives the gas dynamic thrust bearing a higher load-bearing capacity. Simultaneously, because the grooves are arranged circumferentially on the upper surface of the thrust bearing 3, the high-pressure gas can be evenly distributed in the gas film, improving the stability of the gas dynamic thrust bearing and thus enhancing its overall performance. However, this groove structure simulating a honeycomb wing is not suitable for thinner thrust bearings, mainly because thinner thrust bearings limit the depth of the grooves, and the groove construction also reduces the structural strength of the thrust bearing, affecting its load-bearing performance. Summary of the Invention

[0003] Therefore, the present invention provides a gas dynamic thrust bearing assembly and a motor having the same, which can solve the problem that it is not suitable to construct grooves on the surface of a thin thrust bearing to improve the overall performance of the bearing.

[0004] To address the aforementioned problems, the present invention provides a gas dynamic thrust bearing assembly and a motor having the same, comprising: a rotating shaft and a thrust plate on the rotating shaft; the thrust plate having two end faces along the axial direction of the rotating shaft, and at least one of the end faces having a plurality of first grooves; each of the first grooves being spaced apart on the thrust plate and surrounding the rotating shaft; each first groove including a communicating inner section and an outer section; along the radial direction of the thrust plate, the outer section being located outside the inner section, and the outer section being inclined relative to the inner section to form a flared structure.

[0005] In some embodiments, the direction of the large opening of the flared structure is the same as the direction of rotation of the rotating shaft.

[0006] In some embodiments, the inner segment (41) has a first sidewall and the outer segment (42) has a second sidewall, the first sidewall and the second sidewall intersect and form an angle θ between them, 30°≤θ≤120°.

[0007] In some embodiments, the width of the first groove gradually increases along the direction from the radially inner side to the radially outer side of the thrust plate.

[0008] In some embodiments, the groove depth of the first groove is 0.01mm-0.05mm.

[0009] In some embodiments, at least one of the end faces is provided with a second groove that surrounds the pivot, and the first groove is provided on the bottom wall of the second groove.

[0010] In some embodiments, the second groove is annular, extending radially from the inner side to the outer side of the thrust plate, with the intersection of the inner and outer sections located at 40%-70% of the width of the second groove.

[0011] In some embodiments, the thrust plate further has a first inner annular region and a first outer annular region. Along the radial direction of the thrust plate, the first inner annular region is located inside the first outer annular region. The second groove is located between the first inner annular region and the first outer annular region. A plurality of third grooves are constructed on the first inner annular region. Each of the third grooves is circumferentially spaced along the first inner annular region and surrounds the pivot.

[0012] In some embodiments, the number of the third grooves is the same as the number of the first grooves and their positions correspond one-to-one, and each of the third grooves is connected to each of the first grooves.

[0013] In some embodiments, the width of the third groove gradually increases along the direction from the radially inner side to the radially outer side of the first inner annular region.

[0014] In some embodiments, the third groove is inclined, and the inclination direction of the third groove is the same as the rotation direction of the rotating shaft.

[0015] In some embodiments, the rotating shaft is further fitted with two thrust bearings, and the two thrust bearings are respectively located on both sides of the thrust plate. The end face of the thrust bearing facing the thrust plate has a raised area, and the raised area corresponds to the second groove.

[0016] The present invention also provides an electric motor, including the above-described gas dynamic thrust bearing assembly.

[0017] This invention provides a gas dynamic thrust bearing assembly and a motor having the same. By constructing a first groove on the thrust plate opposite to the thrust bearing, it solves the problem that it is not suitable to construct grooves on thin thrust bearings to improve the overall performance of the bearing. Constructing grooves on the thrust plate can increase the gas film thickness, facilitate the rapid formation of the gas film, thereby improving the bearing's vibration resistance and stability, and increasing the bearing's load-bearing capacity. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the structure of the gas dynamic thrust bearing assembly according to an embodiment of the present invention;

[0019] Figure 2 This is a schematic diagram of the structure of the gas dynamic thrust bearing assembly according to an embodiment of the present invention, in which the thrust plate is mounted on the rotating shaft.

[0020] Figure 3 This is a schematic diagram of the thrust plate of the gas dynamic thrust bearing assembly according to an embodiment of the present invention;

[0021] Figure 4 This is a schematic diagram of a prior art gas dynamic thrust bearing assembly;

[0022] Figure 5 A schematic diagram of the thrust bearing in a prior art gas dynamic thrust bearing assembly.

[0023] The reference numerals in the attached figures are as follows:

[0024] 1. Shaft; 2. Thrust plate; 3. Thrust bearing; 4. First groove; 41. Inner section; 42. Outer section; 5. Second groove; 6. Third groove; 7. First inner annular area; 8. Protruding area; 9. Second inner annular area. Detailed Implementation

[0025] See also Figures 1 to 5As shown, according to an embodiment of the present invention, a gas dynamic thrust bearing assembly and a motor having the same are provided, comprising: a rotating shaft 1 and a thrust plate 2 mounted on the rotating shaft 1. Along the axial direction of the rotating shaft 1, the thrust plate 2 has two end faces, and at least one end face has a plurality of first grooves 4. Each first groove 4 is spaced apart on the thrust plate 2 and surrounds the rotating shaft 1. Each first groove 4 includes a communicating inner section 41 and an outer section 42. Along the radial direction of the thrust plate 2, the outer section 42 is located outside the inner section 41, and the outer section 42 is inclined relative to the inner section 41 to form a flared structure. Two thrust bearings 3 are also mounted on the rotating shaft 1, and the two thrust bearings 3 are respectively located on the left and right sides of the thrust plate 2. In this technical solution, by constructing the first grooves on the thrust plate 2 opposite to the thrust bearings 3, the problem of not being suitable for constructing grooves on thin-thick thrust bearings 3 to improve the overall performance of the bearing is solved. A first groove 4 is constructed on the thrust plate 2. The outer section 42 of the first groove 4 is inclined relative to the inner section 41. This allows the airflow to enter from one end of the inner section 41 and the other end of the outer section 42, facilitating the impact of the two airflows to form high pressure. This increases the thickness of the gas film, promotes rapid gas film formation, and improves the bearing's vibration resistance, stability, and load-bearing capacity. The shaft 1 and the thrust plate 2 can be integrally formed, or the thrust plate 2 can be fitted onto the shaft 1 with an interference fit. The thrust bearing 3 can be a thin-film bearing, such as a foil thrust bearing, thus achieving a good film-forming effect without the need to construct corresponding grooves on the bearing foil.

[0026] See Figure 1 As shown, a first groove 4 is constructed on both end faces of the thrust plate 2, and the thrust bearings 3 respectively provided on the two end faces can both be foil thrust bearings.

[0027] See also Figures 1 to 3 As shown, the opening direction of the large opening of the flared structure is the same as the rotation direction of the rotating shaft 1. When the rotating shaft 1 rotates, it will drive the air around it to move together. When the opening direction of the large opening of the flared structure is the same as the rotation direction of the rotating shaft 1, it will facilitate the airflow into the first groove 4.

[0028] See also Figure 3 As shown, the inner section 41 has a first sidewall, and the outer section 42 has a second sidewall. The first sidewall and the second sidewall intersect, forming an angle θ between them, where 30° ≤ θ ≤ 120°. This results in a better high-pressure effect when the airflow enters from one end of the inner section 41 and the outer section 42, respectively, after the two airflows collide. Preferably, 40° ≤ θ ≤ 70°, which provides the optimal high-pressure effect. The inner section 41 and the outer section 42 have two sets of connected sidewalls, and the intersecting first and second sidewalls can be either of these two sets.

[0029] Preferably, the width of the first groove 4 gradually increases from the radial inner side to the radial outer side of the thrust plate 2. This facilitates the entry of gas into the high-pressure zone and the accumulation of high-pressure gas in the bearing zone. If the first groove 4 is too deep, the gas at its bottom will not play a significant role in increasing the gas pressure, which would instead affect the structural strength of the thrust plate 2. Preferably, the groove depth of the first groove 4 is 0.01mm-0.05mm.

[0030] See also Figures 1 to 3 As shown, a second groove 5 is constructed on the end face of the thrust plate 2, surrounding the rotating shaft 1. The groove depth of the second groove 5 is 0.01mm-0.1mm. Each first groove 4 is constructed on the bottom wall of the second groove 5, extending from the inner circumferential sidewall to the outer inner circumferential sidewall. The thrust bearing 3 has a raised area 8 on its end face facing the thrust plate 2, corresponding to the second groove 5. The area containing the raised area 8 and the second groove 5 is the main load-bearing area. The raised area 8 can change the gas velocity and density, forming a high-pressure gas zone, thus giving the gas dynamic thrust bearing a higher load-bearing capacity. The design of the second groove 5 results in a gas film with a small thickness at both ends and a large thickness in the middle between the thrust plate 2 and the thrust bearing 3, which can improve the leakage of high-pressure gas. At the same time, each first groove 4 is evenly distributed along the circumference of the thrust plate 2, so that the axial thrust bearing can bear the load evenly in all directions, thereby further improving the vibration resistance and stability of the bearing.

[0031] Preferably, the second groove 5 is annular, extending radially from the inner side to the outer side of the thrust plate 2, with the intersection of the inner section 41 and the outer section 42 located at 40%-70% of the width of the second groove 5. When the first groove 4 is not constructed on the thrust plate 2, the high-pressure zone of the gas film formed between the thrust plate 2 and the thrust bearing 3 is slightly biased towards the radial outer side of the thrust plate 2. However, when the first groove 4 is constructed on the thrust plate 2, and the intersection of the inner section 41 and the outer section 42 of the first groove 4 is located at 40%-70% of the width of the second groove 5, the high-pressure gas formed at the intersection will overlap with the high-pressure zone of the gas film itself, thereby further improving the bearing capacity.

[0032] See also Figures 1 to 3As shown, the thrust plate 2 also has a first inner annular region 7 and a first outer annular region. Along the radial direction of the thrust plate 2, the first inner annular region 7 is located inside the first outer annular region. The second groove 5 is located between the first inner annular region 7 and the first outer annular region. Multiple third grooves 6 are constructed on the first inner annular region 7. Each third groove 6 is distributed circumferentially around the shaft 1. Since high-pressure gas accumulation in the bearing area can easily lead to end leakage, when multiple third grooves 6 are constructed in the region of the thrust plate 2 near the shaft 1, that is, in the first inner annular region 7, the third grooves 6 can store high-pressure gas, and their position is higher than the first groove 4. Therefore, the third grooves 6 can be used for gas sealing, improving the high-pressure gas end leakage phenomenon, increasing the gas film stiffness, and thus improving the bearing load-bearing performance. The thrust bearing 3 also has a second inner annular region 9 and a second outer annular region on the end face facing the thrust plate 2. Along the radial direction of the thrust bearing 3, the second inner annular region 9 is located inside the second outer annular region, and the protruding region 8 is located between the second inner annular region 9 and the second outer annular region. The second inner annular region 9 corresponds to the first inner annular region 7, which facilitates the alignment and installation of the thrust bearing 3.

[0033] Specifically, the number of third grooves 6 is the same as the number of first grooves 4, and their positions correspond one-to-one. Each third groove 6 is connected to each first groove 4. Since the opening of the first groove 4 facing the rotating shaft 1 is radially inward, it is difficult for airflow to enter the first groove 4 from this point. When each third groove 6 is connected to the first groove 4, airflow can easily enter the first groove 4 through the third groove 6.

[0034] See also Figure 3 As shown, the width of the third groove 6 gradually increases along the radially inner side to the radially outer side of the first inner annular region 7. When the airflow enters the first groove 4 from the third groove 6, the airflow will diffuse within the third groove 6 due to the gradually increasing width of the third groove 6, resulting in a higher pressure of the gas entering the first groove 4.

[0035] Specifically, the third groove 6 is inclined, and the inclination direction of the third groove 6 is the same as the rotation direction of the rotating shaft 1. When the rotating shaft 1 rotates, the rotating shaft 1 will drive the air around it to move together. The inclination direction of the third groove 6 is the same as the rotation direction of the rotating shaft 1, which makes it easier for the airflow to enter the third groove 6, and thus facilitates the airflow to enter the first groove 4 from the radial inner side of the thrust plate 2.

[0036] According to an embodiment of the present invention, an electric motor is also provided, including the above-described pneumatic thrust bearing assembly.

[0037] It will be readily understood by those skilled in the art that the aforementioned advantageous methods can be freely combined and superimposed without conflict.

[0038] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention. The above are merely preferred embodiments of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present invention, and these improvements and modifications should also be considered within the protection scope of the present invention.

Claims

1. A gas dynamic thrust bearing assembly, comprising a rotating shaft (1) and a thrust plate (2) located on the rotating shaft (1), the thrust plate (2) having two end faces along the axial direction of the rotating shaft (1), characterized in that, At least one of the end faces is provided with a plurality of first grooves (4), each of the first grooves (4) being spaced apart on the thrust plate (2) and surrounding the pivot (1). Each first groove (4) includes a communicating inner section (41) and an outer section (42). Along the radial direction of the thrust plate (2), the outer section (42) is located outside the inner section (41), and the outer section (42) is inclined relative to the inner section (41) to form a flared structure. A second groove (5) is formed on the end face, surrounding the rotating shaft (1) for one circumference, and the first groove (4) is formed on the bottom wall of the second groove (5); The thrust plate (2) also has a first inner annular region (7) and a first outer annular region. Along the radial direction of the thrust plate (2), the first inner annular region (7) is located inside the first outer annular region. The second groove (5) is located between the first inner annular region (7) and the first outer annular region. A plurality of third grooves (6) are constructed on the first inner annular region (7). Each of the third grooves (6) is distributed circumferentially around the first inner annular region (7) and surrounds the rotating shaft (1).

2. The gas dynamic thrust bearing assembly according to claim 1, characterized in that, The direction of the large opening of the flared structure is the same as the rotation direction of the rotating shaft (1).

3. The gas dynamic thrust bearing assembly according to claim 1, characterized in that, The inner segment (41) has a first sidewall, and the outer segment (42) has a second sidewall. The first sidewall and the second sidewall intersect and form an angle θ between them, where 30°≤θ≤120°.

4. The gas dynamic thrust bearing assembly according to claim 1, characterized in that, Along the radial inner side to the radial outer side of the thrust plate (2), the width of the first groove (4) gradually increases.

5. The gas dynamic thrust bearing assembly according to claim 1, characterized in that, The groove depth of the first groove (4) is 0.01mm-0.05mm.

6. The gas dynamic thrust bearing assembly according to claim 1, characterized in that, The second groove (5) is annular, extending from the radial inner side to the radial outer side of the thrust plate (2). The intersection of the inner section (41) and the outer section (42) is located at 40%-70% of the width of the second groove (5).

7. The gas dynamic thrust bearing assembly according to claim 1, characterized in that, The number of the third grooves (6) is the same as the number of the first grooves (4) and their positions correspond one-to-one. Each of the third grooves (6) is connected to each of the first grooves (4).

8. The gas dynamic thrust bearing assembly according to claim 1 or 7, characterized in that, The width of the third groove (6) gradually increases along the radial inner side to the radial outer side of the first inner annular region (7).

9. The gas dynamic thrust bearing assembly according to claim 1 or 7, characterized in that, The third groove (6) is inclined, and the inclination direction of the third groove (6) is the same as the rotation direction of the rotating shaft (1).

10. The gas dynamic thrust bearing assembly according to claim 1, characterized in that, Two thrust bearings (3) are also fitted on the shaft (1), and the two thrust bearings (3) are respectively located on the axial sides of the thrust plate (2). The end face of the thrust bearing (3) facing the thrust plate (2) has a raised area (8), which corresponds to the second groove (5).

11. An electric motor, characterized in that, Includes the gas dynamic thrust bearing assembly as described in any one of claims 1 to 10.

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