Foil bearing assembly and motor

Abstract

The invention provides a foil bearing assembly and a motor, the foil bearing assembly comprises a first axial bearing, a thrust plate, a second axial bearing and a rotor, the thrust plate is arranged on the rotor and integrally rotates along with the rotor, the first axial bearing is arranged on the periphery of the rotor and is located on one axial side of the thrust plate, and the second axial bearing is located on the other axial side of the thrust plate. The second axial bearing is arranged on the periphery of the rotor and located on the other axial side of the thrust plate, first rotor comb teeth are arranged on the periphery of the rotor and located at the position opposite to the first axial bearing in the radial direction, and second rotor comb teeth are arranged on the periphery of the rotor and located at the position opposite to the second axial bearing in the radial direction. And airflow blocking can be carried out on the inner circle of the first axial bearing and the inner circle of the second axial bearing. According to the thrust bearing, high-pressure gas end leakage in the circumferential direction of the inner circle of the axial bearing can be reduced, the bearing capacity of the thrust bearing is effectively improved, and the problems that a foil gas thrust bearing is low in bearing capacity, and the service life is short due to the fact that the gas foil thrust bearing is prone to abrasion are solved.

Description

Technical Field

[0001] The present invention relates to the technical field of air bearings, and in particular to a foil bearing assembly and a motor. Background Art

[0002] Gas dynamic pressure bearings utilize the viscosity and compressibility of gas to form a high-pressure gas film under the action of fluid dynamic pressure effect to support loads and reduce friction. They have the advantages of high precision, pollution-free, high speed and simple structure. They have very broad application prospects in the fields of high-speed turbines, machine tool manufacturing and space technology. Gas dynamic pressure bearings have been widely used in high-speed rotating machinery such as oil-free turbines of aircraft engines, micro gas turbines and aircraft air cycle machines at home and abroad.

[0003] CN204783801 U proposes an axial thrust bearing structure for a centrifugal compressor with a high-speed motor. The axial thrust bearing is fixed to the back of the impeller to simplify and shorten the rotor structure. However, the temperature and pressure of the ambient gas fluctuate significantly when the impeller and axial thrust bearing are in operation, resulting in poor performance and reliability of the thrust bearing. CN214424901U proposes a thrust bearing and air conditioning unit. The thrust bearing is mounted on a bearing seat with a dynamic pressure air hole. Air is supplied through the dynamic pressure air hole to improve bearing support stiffness, thereby reducing bearing deformation that can lead to increased wear of the top foil and reduced bearing reliability.

[0004] When a foil-type gas dynamic pressure bearing is in operation, the high-speed rotation of the rotor creates a dynamic pressure gas film within the rotor-bearing air gap, supporting the rotor's suspension. To accommodate high-speed motors of varying power, the load-bearing performance of foil-type gas dynamic pressure bearings needs to be improved. Therefore, how to improve bearing load-bearing performance without changing bearing size and stiffness is a pressing challenge for those skilled in the field.

[0005] Since the foil thrust bearing in the prior art has technical problems such as high-pressure gas leakage in the circumferential direction of the inner circle of the bearing, resulting in low bearing capacity of the thrust bearing, the present invention studies and designs a foil bearing assembly and a motor. Summary of the Invention

[0006] Therefore, the technical problem to be solved by the present invention is to overcome the defect of the foil thrust bearing in the prior art that high-pressure gas leaks out in the circumferential direction of the inner circle of the bearing, resulting in low bearing capacity of the thrust bearing, thereby providing a foil bearing assembly and a motor.

[0007] In order to solve the above problems, the present invention provides a foil bearing assembly, which includes:

[0008] A first axial bearing, a thrust plate, a second axial bearing and a rotor, wherein the thrust plate is arranged on the rotor and rotates integrally with the rotor, the first axial bearing is arranged on the outer periphery of the rotor and is located on one axial side of the thrust plate, the second axial bearing is arranged on the outer periphery of the rotor and is located on the other axial side of the thrust plate, and a first rotor comb tooth is arranged on the outer periphery of the rotor and at a position radially opposite to the first axial bearing, and a second rotor comb tooth is arranged on the outer periphery of the rotor and at a position radially opposite to the second axial bearing, which can block the airflow at the inner circle of the first axial bearing and the inner circle of the second axial bearing.

[0009] In some embodiments,

[0010] A first gap is formed between the first axial bearing and the thrust plate in the axial direction;

[0011] A second gap is formed between the second axial bearing and the thrust plate in the axial direction;

[0012] The first comb teeth of the rotor are opposite to the first gap in the radial direction, and one axial end of the first comb teeth of the rotor extends to connect with the thrust plate. The second comb teeth of the rotor are opposite to the second gap in the radial direction, and one axial end of the second comb teeth of the rotor extends to connect with the thrust plate.

[0013] In some embodiments,

[0014] In a projection plane along the radial direction of the rotor, the first comb teeth of the rotor completely cover the first axial bearing and the first gap, and the second comb teeth of the rotor completely cover the second axial bearing and the second gap.

[0015] In some embodiments,

[0016] The first axial bearing includes a first axial bearing top foil and a first axial bearing wave foil, wherein the first axial bearing top foil is connected to the first axial bearing wave foil in the axial direction and faces the thrust plate, so that the first axial bearing top foil is located between the first axial bearing wave foil and the thrust plate, and the first gap is formed between the first axial bearing top foil and the thrust plate;

[0017] The second axial bearing comprises a second axial bearing top foil and a second axial bearing wave foil, the second axial bearing top foil is connected to the second axial bearing wave foil in the axial direction, and the second axial bearing top foil faces the thrust plate, so that the second axial bearing top foil is located between the second axial bearing wave foil and the thrust plate, and the second gap is formed between the second axial bearing top foil and the thrust plate;

[0018] The axial length of the first comb tooth of the rotor is greater than the sum of the axial length of the first axial bearing top foil, the axial length of the first axial bearing wave foil and the axial length of the first gap; the axial length of the second comb tooth of the rotor is greater than the sum of the axial length of the second axial bearing top foil, the axial length of the second axial bearing wave foil and the axial length of the second gap.

[0019] In some embodiments,

[0020] The first comb teeth of the rotor are located radially inward of the inner circle of the first axial bearing, and a third gap is defined between the outer periphery of the first comb teeth of the rotor and the radial inner circle of the first axial bearing; the second comb teeth of the rotor are located radially inward of the inner circle of the second axial bearing, and a fourth gap is defined between the outer periphery of the second comb teeth of the rotor and the radial inner circle of the second axial bearing;

[0021] The thrust plate is provided with a thrust plate vent hole, one end of the thrust plate vent hole is opposite to the third gap between the first axial bearing and the first comb tooth of the rotor, and the other end of the thrust plate vent hole is opposite to the fourth gap between the second axial bearing and the second comb tooth of the rotor; the third gap between the first axial bearing and the first comb tooth of the rotor and the fourth gap between the second axial bearing and the second comb tooth of the rotor can be connected through the thrust plate vent hole.

[0022] In some embodiments,

[0023] A first thrust plate groove is provided on a first axial end surface of the thrust plate facing the third gap, the first thrust plate groove is a blind groove structure, and the first thrust plate groove extends from the first axial end surface toward the interior of the thrust plate; a second thrust plate groove is provided on a second axial end surface of the thrust plate facing the fourth gap, the second thrust plate groove is a blind groove structure, and the second thrust plate groove extends from the second axial end surface toward the interior of the thrust plate;

[0024] The thrust plate vent hole is located inside the thrust plate, and one end of the thrust plate vent hole is communicated with the first groove of the thrust plate, and the other end of the thrust plate vent hole is communicated with the second groove of the thrust plate.

[0025] In some embodiments,

[0026] The first groove of the thrust plate extends along the axial direction of the thrust plate, the thrust plate vent hole extends along the axial direction of the thrust plate, and the second groove of the thrust plate extends along the axial direction of the thrust plate. The flow cross-sectional area of the first groove of the thrust plate is larger than the flow cross-sectional area of the thrust plate vent hole, and the flow cross-sectional area of the second groove of the thrust plate is larger than the flow cross-sectional area of the thrust plate vent hole.

[0027] In some embodiments,

[0028] It also includes a radial bearing and a rotating shaft, at least part of the structure of the rotating shaft is located on the inner circumference of the rotor, the rotating shaft is a hollow shaft structure, one end of its hollow channel can be connected to the first groove of the thrust plate or the second groove of the thrust plate, and the other end of the hollow channel can be connected to the position between the radial bearing and the rotor so as to conduct the gas to the radial bearing.

[0029] In some embodiments,

[0030] The first groove of the thrust plate is located on the axial end face of the thrust plate away from the radial bearing, the radial inner side of the first groove of the thrust plate extends to connect with the outer peripheral surface of the rotating shaft, one end of the hollow channel extends to the outer peripheral surface of the rotating shaft to communicate with the first groove of the thrust plate, and a rotor radial air hole is also provided on the rotor at a position radially opposite to the radial bearing, and the other end of the hollow channel can extend to the outer peripheral surface of the rotating shaft to communicate with the rotor radial air hole.

[0031] The present invention also provides a motor, which includes the above-mentioned foil bearing assembly.

[0032] The foil bearing assembly and motor provided by the present invention have the following beneficial effects:

[0033] 1. The present invention provides first rotor comb teeth on the outer periphery of the rotor and at a position radially opposite to the first axial bearing, and provides second rotor comb teeth on the outer periphery of the rotor and at a position radially opposite to the second axial bearing, thereby blocking airflow at the inner circumference of the first axial bearing and the inner circumference of the second axial bearing, and reducing the end leakage of high-pressure gas in the circumferential direction of the inner circumference of the axial bearing. That is, by designing a sealing comb tooth structure on the rotor at the radial mounting position of the foil thrust bearing, the end leakage of high-pressure gas at the inner circumference of the axial bearing is suppressed, the bearing capacity of the thrust bearing is effectively improved, and the problems of low bearing capacity of the foil gas thrust bearing and easy wear of the gas foil thrust bearing, which leads to a short service life, are solved.

[0034] 2. The present invention also opens a thrust plate vent hole on the thrust plate, which can connect the space on both sides of the thrust plate, effectively coordinate the environmental pressure of the front and rear axial bearings, accelerate the gas flow, and improve the heat dissipation efficiency of the bearing; especially through the first groove and the second groove of the thrust plate, combined with the structure of the thrust plate vent hole, it can further ensure the connection of the space on both sides of the thrust plate, further coordinate the front and rear bearing pressures, and accelerate the gas flow and cooling efficiency.

[0035] 3. The present invention also adopts the structure of a hollow shaft, which has a hollow channel inside, and can introduce gas from the first groove of the thrust plate or the second groove of the thrust plate, and conduct it to the radial bearing, which can avoid the blockage of the inlet gas of the radial bearing, ensure the smoothness of the supporting gas of the radial bearing, and effectively improve the bearing performance of the radial bearing; in particular, it extends from the radial inner side of the first groove of the thrust plate to the outer peripheral surface of the rotating shaft, and a rotor radial air hole is also provided on the rotor at a position radially opposite to the radial bearing, which can make the hollow channel inside the hollow shaft connected with the first groove of the thrust plate and the radial air hole of the rotor respectively, thereby ensuring the gas supply to the radial bearing, further avoiding the blockage of the inlet gas of the radial bearing, further ensuring the smoothness of the supporting gas of the radial bearing, and improving the bearing performance of the radial bearing. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 is a schematic diagram of a thrust bearing portion of a gas dynamic pressure bearing of the present invention;

[0037] Figure 2 Schematic diagram of the gas flow path of the thrust bearing portion of the gas dynamic pressure bearing of the present invention;

[0038] Figure 3 Schematic diagram of the thrust bearing portion of the gas dynamic pressure bearing of the present invention when the thrust plate vent is provided;

[0039] Figure 4 It is a schematic diagram of a gas dynamic pressure bearing according to the present invention having a thrust bearing portion on a hollow shaft.

[0040] The reference numerals indicate:

[0041] 1. Casing; 2. Stator; 3. Rotor; 3-1. First end face of rotor; 3-2. Second end face of rotor; 3-3. First comb teeth of rotor; 3-4. Second comb teeth of rotor; 3-5. Radial air holes of rotor; 4. Radial bearing seat; 5. Radial bearing; 6. Thrust plate; 6-1. First end face of thrust plate; 6-2. Second end face of thrust plate; 6-3. First groove of thrust plate; 6-4. Second groove of thrust plate; 6-5. Air holes of thrust plate; 7. First axial bearing; 7-1. Top foil of first axial bearing; 7-2. Corrugated foil of first axial bearing; 8. Second axial bearing; 8-1. Top foil of second axial bearing; 8-2. Corrugated foil of second axial bearing; 9. First axial bearing housing; 10. Impeller; 11. First gap; 12. Second gap; 13. Third gap; 14. Fourth gap; 15. Rotating shaft. DETAILED DESCRIPTION

[0042] The following will be combined with the accompanying drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, rather than all the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is in no way intended to limit the present invention and its application or use. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0043] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, they indicate the presence of features, steps, operations, devices, components and / or combinations thereof.

[0044] Unless otherwise specifically stated, the relative arrangement of the parts and steps, the numerical expressions and the numerical values set forth in these embodiments do not limit the scope of the present invention. At the same time, it should be understood that, for ease of description, the sizes of the various parts shown in the drawings are not drawn according to the actual proportional relationship. The techniques, methods and equipment known to those of ordinary skill in the relevant art may not be discussed in detail, but where appropriate, the techniques, methods and equipment should be considered as part of the authorization specification. In all examples shown and discussed here, any specific values should be interpreted as being merely exemplary and not as limiting. Therefore, other examples of the exemplary embodiments may have different values. It should be noted that similar numbers and letters represent similar items in the following figures, and therefore, once an item is defined in one figure, it does not need to be further discussed in subsequent figures.

[0045] In the description of the present invention, it should be understood that the directions or positional relationships indicated by directional words such as "front, back, up, down, left, right", "horizontal, vertical, perpendicular, horizontal" and "top, bottom" are usually based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description. Unless otherwise specified, these directional words do not indicate or imply that the device or element referred to must have a specific direction or be constructed and operated in a specific direction. Therefore, they cannot be understood as limiting the scope of protection of the present invention; the directional words "inside and outside" refer to the inside and outside relative to the outline of each component itself.

[0046] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used herein to describe the spatial positional relationship of a device or feature to other devices or features as shown in the figures. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figures. For example, if the device in the drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0047] In addition, it should be noted that the use of terms such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore cannot be understood as limiting the scope of protection of the present invention.

[0048] like Figure 1-4 As shown, the present invention provides a foil bearing assembly, which includes:

[0049] A first axial bearing 7, a thrust plate 6, a second axial bearing 8 and a rotor 3, wherein the thrust plate 6 is arranged on the rotor 3 and rotates integrally with the rotor 3, the first axial bearing 7 is arranged on the outer periphery of the rotor 3 and is located on one axial side of the thrust plate 6, the second axial bearing 8 is arranged on the outer periphery of the rotor 3 and is located on the other axial side of the thrust plate 6, and a rotor first comb tooth 3-3 is arranged on the outer periphery of the rotor 3 and at a position radially opposite to the first axial bearing 7, and a rotor second comb tooth 3-4 is arranged on the outer periphery of the rotor 3 and at a position radially opposite to the second axial bearing 8, which can block the airflow at the inner circle of the first axial bearing 7 and the inner circle of the second axial bearing 8.

[0050] The present invention provides first rotor comb teeth on the outer periphery of the rotor and at a position radially opposite to the first axial bearing, and provides second rotor comb teeth on the outer periphery of the rotor and at a position radially opposite to the second axial bearing, thereby blocking the airflow at the inner circle of the first axial bearing and the inner circle of the second axial bearing, and reducing the end leakage of high-pressure gas in the circumferential direction of the inner circle of the axial bearing. That is, by designing a sealing comb tooth structure on the rotor at the radial mounting position of the foil thrust bearing, the end leakage of high-pressure gas at the inner circle of the axial bearing is suppressed, the bearing capacity of the thrust bearing is effectively improved, and the problems of low bearing capacity of the foil gas thrust bearing and easy wear of the gas foil thrust bearing, resulting in a short service life, are solved.

[0051] The sealing structure of the present invention is a comb-tooth groove, which is arranged on the rotor end face at the corresponding position of the axial bearing. It can seal the air gap between the axial bearing and the rotor, inhibit the gas from flowing away from the bearing end face and the gap between the corrugated foil, and increase the environmental pressure inside the axial bearing. The present invention does not have an airflow toward the radial inner periphery at the axial bearing, and effectively inhibits the leakage of high-pressure gas at the inner circle of the axial bearing.

[0052] Conventional seals are used to seal the connection between the axial bearing system and other structures to prevent the high-pressure gas in the axial system from flowing out;

[0053] The comb tooth structure of the present invention is used to seal the inner side of the axial bearing, and is aimed at the inner end leakage of the foil gas thrust bearing.

[0054] In some embodiments,

[0055] A first gap 11 is formed between the first axial bearing 7 and the thrust plate 6 in the axial direction;

[0056] A second gap 12 is formed between the second axial bearing 8 and the thrust plate 6 in the axial direction;

[0057] The first comb teeth 3-3 of the rotor are radially opposite to the first gap 11, and one axial end of the first comb teeth 3-3 of the rotor extends to connect with the thrust plate 6. The second comb teeth 3-4 of the rotor are radially opposite to the second gap 12, and one axial end of the second comb teeth 3-4 of the rotor extends to connect with the thrust plate 6.

[0058] This is the preferred structural form of the first comb teeth and the second comb teeth of the rotor of the present invention. By setting the first comb teeth of the rotor to be opposite to the first gap in the radial direction, the first comb teeth of the rotor can effectively block the airflow coming from the first gap, prevent the gas therefrom from leaking to the corrugated foil of the axial bearing, and prevent the corrugated foil of the axial bearing from leaking into the first gap, thereby effectively improving the effect of preventing the end leakage of the axial bearing; by using the second comb teeth of the rotor to effectively block the airflow coming from the second gap, prevent the gas therefrom from leaking to the corrugated foil of the axial bearing, and prevent the corrugated foil of the axial bearing from leaking into the second gap, thereby effectively improving the effect of preventing the end leakage of the axial bearing; and extending the first comb teeth of the rotor to connect with the thrust plate can further improve the effect of preventing the end leakage between the first gap and the axial bearing, and extending the second comb teeth of the rotor to connect with the thrust plate can further improve the effect of preventing the end leakage between the second gap and the axial bearing.

[0059] In some embodiments,

[0060] In the projection plane along the radial direction of the rotor 3 , the first comb teeth 3 - 3 of the rotor completely cover the positions of the first axial bearing 7 and the first gap 11 , and the second comb teeth 3 - 4 of the rotor completely cover the positions of the second axial bearing 8 and the second gap 12 .

[0061] The present invention completely covers the position of the first axial bearing and the first gap in the radial projection plane with the first comb teeth of the rotor, thereby blocking the gas leakage of the first axial bearing toward the radial inside or radial outside through the first comb teeth of the rotor, and improving the anti-end leakage effect between the first gap and the first axial bearing, thereby further improving the anti-end leakage effect of the first bearing; the present invention completely covers the position of the second axial bearing and the second gap in the radial projection plane with the second comb teeth of the rotor, thereby blocking the gas leakage of the second axial bearing toward the radial inside or radial outside through the second comb teeth of the rotor, and improving the anti-end leakage effect between the second gap and the second axial bearing, thereby further improving the anti-end leakage effect of the second bearing.

[0062] In some embodiments,

[0063] The first axial bearing 7 includes a first axial bearing top foil 7-1 and a first axial bearing bump foil 7-2. The first axial bearing top foil 7-1 is connected to the first axial bearing bump foil 7-2 in the axial direction, and the first axial bearing top foil 7-1 faces the thrust plate 6, so that the first axial bearing top foil 7-1 is located between the first axial bearing bump foil 7-2 and the thrust plate 6. The first gap 11 is defined between the first axial bearing top foil 7-1 and the thrust plate 6.

[0064] The second axial bearing 8 includes a second axial bearing top foil 8-1 and a second axial bearing bump foil 8-2. The second axial bearing top foil 8-1 is connected to the second axial bearing bump foil 8-2 in the axial direction, and the second axial bearing top foil 8-1 faces the thrust plate 6, so that the second axial bearing top foil 8-1 is located between the second axial bearing bump foil 8-2 and the thrust plate 6. A second gap 12 is defined between the second axial bearing top foil 8-1 and the thrust plate 6.

[0065] The axial length of the first comb tooth 3-3 of the rotor is greater than the sum of the axial length of the first axial bearing top foil 7-1, the axial length of the first axial bearing wave foil 7-2 and the axial length of the first gap 11; the axial length of the second comb tooth 3-4 of the rotor is greater than the sum of the axial length of the second axial bearing top foil 8-1, the axial length of the second axial bearing wave foil 8-2 and the axial length of the second gap 12.

[0066] This is a further preferred structural form between the first comb teeth of the rotor and the top foil of the first axial bearing, the wave foil of the first axial bearing and the first gap of the present invention. It can block the gas leakage of the wave foil and the top foil of the first axial bearing toward the radial inside or radial outside through the first comb teeth of the rotor, and improve the anti-end leakage effect between the first gap and the first axial bearing, thereby further improving the anti-end leakage effect of the first bearing; it is a further preferred structural form between the second comb teeth of the rotor and the top foil of the second axial bearing, the wave foil of the second axial bearing and the second gap. It can block the gas leakage of the wave foil and the top foil of the second axial bearing toward the radial inside or radial outside through the second comb teeth of the rotor, and improve the anti-end leakage effect between the second gap and the second axial bearing, thereby further improving the anti-end leakage effect of the second bearing.

[0067] Under the action of viscosity, the gas in the axial bearing area of the present invention flows from the outer edge annular surface of the second axial bearing 8 in the radial direction into the surface of the second axial bearing top foil 8-1 and the second axial bearing wave foil 8-2 respectively. A part of the gas is compressed in the working gap between the second axial bearing top foil 8-1 and the second end face 6-2 of the thrust plate to obtain high-pressure gas, providing axial support force for the axial rotation system; the other part of the gas flows into the gap area between the second axial bearing 8 and the rotor 3 through the cooling channel of the second axial bearing wave foil 8-2, which can reduce the temperature rise of the second axial bearing and inhibit the deformation of the foil. When the rotor rotates at high speed, the higher the pressure of the high-pressure gas in the working area of the axial bearing is, the closer it is to the inner circle of the bearing top foil, the lower the gas pressure is, and the higher the pressure is, the closer it is to the outer circle of the bearing top foil (the outer ring has a high linear speed, so the pressure generated is greater, so the gas gathers outside the high-pressure area). Therefore, the deformation of the inner circle of the bearing top foil is small and the deformation of the outer circle is large, that is, the gap between the inner circle area of the bearing top foil and the thrust plate 6 is small under heavy load (the smaller the pressure, the smaller the gap), and the wear is more serious. Therefore, increasing the deformation of the inner circle of the top foil can significantly improve the bearing capacity of the axial bearing.

[0068] The present invention designs a first comb tooth on the outer circle of the rotor and a second comb tooth on the outer circle of the rotor, which correspond to the positions of the first axial bearing and the second axial bearing. The comb tooth structure seals the circumferential air gap outlet of the inner circle of the top foil of the axial bearing, inhibits the outflow of high-pressure gas in the inner circle area of the top foil of the bearing, and draws in the external fluid circulation through the gap between adjacent foils. The circumferential flow of the axial bearing wave foil is dominated by the end suction effect, which draws the gas outside the axial bearing into the bearing area for mass replenishment. The rotor-axial bearing combination structure of the axial rotating system can reduce the outflow of high-pressure gas in the inner circle area of the top foil of the bearing, increase the pressure in the inner circle area of the top foil of the bearing, inhibit the end leakage of high-pressure gas, increase the deformation of the inner circle area of the top foil of the bearing, and thus improve the bearing capacity of the axial bearing. (Because the comb teeth are set, the environmental pressure increases, thereby increasing the deformation of the inner circle area and improving the bearing capacity).

[0069] In some embodiments,

[0070] The first rotor comb teeth 3-3 are located radially inward of the inner circle of the first axial bearing 7, and a third gap 13 is defined between the outer periphery of the first rotor comb teeth 3-3 and the radial inner circle of the first axial bearing 7; the second rotor comb teeth 3-4 are located radially inward of the inner circle of the second axial bearing 8, and a fourth gap 14 is defined between the outer periphery of the second rotor comb teeth 3-4 and the radial inner circle of the second axial bearing 8;

[0071] The thrust plate 6 is provided with a thrust plate vent hole 6-5, one end of the thrust plate vent hole 6-5 is opposite to the third gap 13 between the first axial bearing 7 and the first comb tooth 3-3 of the rotor, and the other end of the thrust plate vent hole 6-5 is opposite to the fourth gap 14 between the second axial bearing 8 and the second comb tooth 3-4 of the rotor; the third gap 13 between the first axial bearing 7 and the first comb tooth 3-3 of the rotor and the fourth gap 14 between the second axial bearing 8 and the second comb tooth 3-4 of the rotor can be connected through the thrust plate vent hole 6-5.

[0072] The present invention also opens a thrust plate vent hole on the thrust plate, cooperates with the third gap between the first comb tooth of the rotor and the first axial bearing, and the fourth gap between the second comb tooth of the rotor and the second circumferential bearing, so as to connect the space on both sides of the thrust plate, effectively coordinate the environmental pressure of the front and rear axial bearings, accelerate gas flow, and improve the heat dissipation efficiency of the bearing.

[0073] In some embodiments,

[0074] A thrust plate first groove 6-3 is provided on a first axial end surface of the thrust plate 6 facing the third gap 13, and the thrust plate first groove 6-3 is a blind groove structure. The thrust plate first groove 6-3 extends from the first axial end surface toward the interior of the thrust plate 6; a thrust plate second groove 6-4 is provided on a second axial end surface of the thrust plate 6 facing the fourth gap 14, and the thrust plate second groove 6-4 is a blind groove structure. The thrust plate second groove 6-4 extends from the second axial end surface toward the interior of the thrust plate 6;

[0075] The thrust plate vent hole 6 - 5 is located inside the thrust plate 6 , and one end of the thrust plate vent hole 6 - 5 is communicated with the first thrust plate groove 6 - 3 , and the other end is communicated with the second thrust plate groove 6 - 4 .

[0076] The present invention can further ensure the connectivity of the spaces on both sides of the thrust plate, further coordinate the front and rear bearing pressures, and accelerate gas flow and cooling efficiency through the first and second grooves of the thrust plate and the structure of the thrust plate vents.

[0077] The high-speed rotor and air bearing system of the present invention has a thrust plate first groove 6-3 and a thrust plate second groove 6-4 on both sides of the inner circle of the thrust plate, and a plurality of axial thrust plate vents 6-5 are opened along the circumferential direction of the thrust plate to connect the first axial bearing and the second axial bearing. Figure 3 As shown in the figure, high-pressure gas flows from the air gap between the inner diameter of the second axial bearing and the second comb tooth of the rotor, through the second groove of the thrust plate, through the thrust plate vent, and into the first groove of the thrust plate. Then, it enters the air gap between the first axial bearing and the first end face of the thrust plate. Part of the gas flows from the first axial bearing corrugated foil to circulate within the axial rotating system, cooling the axial system. The remaining gas flows through the air gap between the radial bearing and the rotor into the motor cavity, cooling the radial bearing. This structural feature primarily reduces the accumulation of high-pressure gas between the second axial bearing and the second comb tooth of the rotor, accelerating gas flow, increasing heat exchange efficiency, reducing the temperature rise of the axial system, and improving the stability of the axial system.

[0078] In some embodiments,

[0079] The first groove 6-3 of the thrust plate extends along the axial direction of the thrust plate 6, the thrust plate vent 6-5 extends along the axial direction of the thrust plate 6, and the second groove 6-4 of the thrust plate extends along the axial direction of the thrust plate 6. The flow cross-sectional area of the first groove 6-3 of the thrust plate is larger than the flow cross-sectional area of the thrust plate vent 6-5, and the flow cross-sectional area of the second groove 6-4 of the thrust plate is larger than the flow cross-sectional area of the thrust plate vent 6-5.

[0080] The present invention has a first groove and a second groove of the thrust plate at both axial ends of the thrust plate, and the flow cross-sectional area is larger than the flow cross-sectional area of the thrust plate vent hole, which can produce a buffering effect of increasing pressure and reducing speed when the gas reaches the first or second groove of the thrust plate after passing through the thrust plate vent hole. When the gas first passes through the first or second groove of the thrust plate, it can form a pressurization, thereby providing conditions for the speed-increasing effect when entering the thrust plate vent hole, thereby ensuring the smooth flow of air.

[0081] In some embodiments,

[0082] It also includes a radial bearing 5 and a rotating shaft 15. At least part of the structure of the rotating shaft 15 is located on the inner periphery of the rotor 3. The rotating shaft 15 is a hollow shaft structure. One end of its hollow channel can be connected to the first groove 6-3 of the thrust plate or the second groove 6-4 of the thrust plate, and the other end of the hollow channel can be connected to the position between the radial bearing 5 and the rotor 3 so as to conduct the gas to the radial bearing 5.

[0083] The present invention also adopts the structure of a hollow shaft, which has a hollow channel inside, and can introduce gas from the first groove of the thrust plate or the second groove of the thrust plate and conduct it to the radial bearing, thereby avoiding the blockage of the inlet gas of the radial bearing, ensuring the smoothness of the supporting gas of the radial bearing, and effectively improving the load-bearing performance of the radial bearing.

[0084] like Figure 4 As shown, based on the first groove or the second groove of the thrust plate, a hollow shaft structure is adopted inside the rotor 3. The first groove of the thrust plate penetrates into the hollow part of the rotor 3. The circumferential high-pressure gas of the inner edge of the rotor-axial bearing flows into the hollow shaft through the first groove of the thrust plate, and then flows into the air gap between the outer circle of the rotor and the radial bearing 5 through the radial holes 3-5 of the rotor, thereby replenishing the air source for the radial bearing, preventing the radial bearing gas from being blocked during axial suction, balancing the gas pressure of the axial system and the radial system, accelerating the gas flow rate of the rotor-bearing system, and improving the gas cooling efficiency.

[0085] In some embodiments,

[0086] The first groove 6-3 of the thrust plate is located on the axial end face of the thrust plate 6 away from the radial bearing 5, and the radial inner side of the first groove 6-3 of the thrust plate extends to connect with the outer peripheral surface of the rotating shaft 15. One end of the hollow channel extends to the outer peripheral surface of the rotating shaft 15 to communicate with the first groove 6-3 of the thrust plate. A rotor radial air hole 3-5 is also provided on the rotor 3 at a position radially opposite to the radial bearing 5. The other end of the hollow channel can extend to the outer peripheral surface of the rotating shaft 15 to communicate with the rotor radial air hole 3-5.

[0087] The present invention is particularly characterized in that the radial inner side of the first groove of the thrust plate extends to connect with the outer peripheral surface of the rotating shaft, and a rotor radial air hole is provided on the rotor at a position radially opposite to the radial bearing, so that the hollow channel inside the hollow shaft can be connected with the first groove of the thrust plate and the rotor radial air hole respectively, thereby ensuring the gas supply to the radial bearing, further avoiding the inlet gas blockage of the radial bearing, further ensuring the smoothness of the supporting gas of the radial bearing, and improving the load-bearing performance of the radial bearing.

[0088] The present invention aims to design a sealing comb structure on the rotor of the radial mounting position of the foil thrust bearing to reduce the leakage of high-pressure gas in the circumferential direction of the inner circle of the axial bearing, improve the bearing capacity of the thrust bearing, open shallow grooves and vents on the thrust plate, coordinate the pressure of the front and rear bearings, accelerate gas flow and cooling efficiency, and use a hollow shaft to guide the high-pressure gas in the axial bearing area into the inlet of the radial bearing to suppress gas blockage.

[0089] The present invention also provides a motor, which includes the above-mentioned foil bearing assembly.

[0090] The invention of the present invention is:

[0091] 1. A sealing comb structure is designed on the rotor of the radial installation position of the foil thrust bearing to suppress the leakage of high-pressure gas from the inner circle of the axial bearing;

[0092] 2. Shallow grooves and vents are designed on the rotor thrust plate to coordinate the environmental pressure of the front and rear axial bearings, accelerate gas flow, and improve bearing heat dissipation efficiency;

[0093] 3. The hollow shaft structure is adopted to introduce the high-pressure gas between the rotor and the axial bearing into the cavity through the hollow shaft, thereby improving the load-bearing performance of the radial bearing;

[0094] The present invention proposes a high-speed rotor and air bearing system, such as Figure 1 and Figure 2 As shown, it includes a housing 1, a stator 2, and a high-speed rotor 3; a radial bearing seat 4 supporting the rotor 3 is arranged on one end face of the housing 1, a radial bearing 5 is arranged in the inner hole of the radial bearing seat 4, a thrust plate 6 is arranged on one side of the rotor 3, and the rotor 3 is respectively arranged with the first rotor comb teeth 3-3 and the second rotor comb teeth 3-4 on both axial sides of the thrust plate 6. The first axial bearing 7 and the second axial bearing 8 are arranged on both sides of the axial end face of the thrust plate 6, corresponding one-to-one with the first rotor comb teeth 3-3 and the second rotor comb teeth 3-4. Among them, the first axial bearing 7 is composed of a first axial bearing top foil 7-1 and a first axial bearing wave foil 7-2, which are fixed to the end face of the radial bearing seat 4; the second axial bearing 8 is composed of a second axial bearing top foil 8-1 and a second axial bearing wave foil 8-2, which are placed on the inner end face of the first axial bearing housing 9 and fixed to the housing 1 or the end face of the radial bearing seat 4. An impeller 10 is arranged near the end of the rotor 3 in the axial direction. The first axial bearing 7 and the second axial bearing 8 are preferably foil-type gas dynamic pressure bearings, which are more suitable for the field of high-speed turbine machinery due to their good adaptability, low vibration and noise.

[0095] When rotor 3 operates at high speed, impeller 10 rotates at high speed, performing work on the gas and generating high-pressure gas. Most of the high-pressure gas is discharged through the flow channel, while a small amount of high-pressure gas flows from the back of impeller 10 through the rotor and first axial bearing housing 9 into the gap between second axial bearing 8 and rotor 3, increasing the ambient pressure on the inner annular surface of second axial bearing 8. When the axial force is directed toward impeller 10, first axial bearing 7 acts as an auxiliary bearing, while second axial bearing 8 acts as the main bearing, supporting the axial load.

[0096] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention. The above description is merely a preferred embodiment of the present invention. It should be noted that those skilled in the art can make various improvements and variations without departing from the technical principles of the present invention, and such improvements and variations shall also be considered within the scope of protection of the present invention.

Claims

1. A foil bearing assembly, characterized in that: include: A first axial bearing (7), a thrust plate (6), a second axial bearing (8) and a rotor (3); the thrust plate (6) is arranged on the rotor (3) and rotates integrally with the rotor (3); the first axial bearing (7) is arranged on the outer periphery of the rotor (3) and is located on one axial side of the thrust plate (6); the second axial bearing (8) is arranged on the outer periphery of the rotor (3) and is located on the other axial side of the thrust plate (6); a first rotor comb tooth (3-3) is arranged on the outer periphery of the rotor (3) and is radially opposite to the first axial bearing (7); and a second rotor comb tooth (3-4) is arranged on the outer periphery of the rotor (3) and is radially opposite to the second axial bearing (8), so as to block airflow at the inner circumference of the first axial bearing (7) and the inner circumference of the second axial bearing (8).

2. The foil bearing assembly according to claim 1, wherein: A first gap (11) is formed between the first axial bearing (7) and the thrust plate (6) in the axial direction; A second gap (12) is formed between the second axial bearing (8) and the thrust plate (6) in the axial direction; The first comb teeth (3-3) of the rotor are opposite to the first gap (11) in the radial direction, and one axial end of the first comb teeth (3-3) of the rotor extends to connect with the thrust plate (6); the second comb teeth (3-4) of the rotor are opposite to the second gap (12) in the radial direction, and one axial end of the second comb teeth (3-4) of the rotor extends to connect with the thrust plate (6).

3. The foil bearing assembly according to claim 2, wherein: In a projection plane along the radial direction of the rotor (3), the first comb teeth (3-3) of the rotor completely cover the position of the first axial bearing (7) and the first gap (11), and the second comb teeth (3-4) of the rotor completely cover the position of the second axial bearing (8) and the second gap (12).

4. The foil bearing assembly according to claim 2 or 3, characterized in that: The first axial bearing (7) comprises a first axial bearing top foil (7-1) and a first axial bearing wave foil (7-2); the first axial bearing top foil (7-1) and the first axial bearing wave foil (7-2) are connected in the axial direction, and the first axial bearing top foil (7-1) faces the thrust plate (6), so that the first axial bearing top foil (7-1) is located between the first axial bearing wave foil (7-2) and the thrust plate (6); and the first gap (11) is provided between the first axial bearing top foil (7-1) and the thrust plate (6); The second axial bearing (8) comprises a second axial bearing top foil (8-1) and a second axial bearing wave foil (8-2), the second axial bearing top foil (8-1) and the second axial bearing wave foil (8-2) are connected in the axial direction, and the second axial bearing top foil (8-1) faces the thrust plate (6), so that the second axial bearing top foil (8-1) is located between the second axial bearing wave foil (8-2) and the thrust plate (6), and a second gap (12) is provided between the second axial bearing top foil (8-1) and the thrust plate (6); The axial length of the first comb tooth (3-3) of the rotor is greater than the sum of the axial length of the first axial bearing top foil (7-1), the axial length of the first axial bearing wave foil (7-2), and the axial length of the first gap (11); the axial length of the second comb tooth (3-4) of the rotor is greater than the sum of the axial length of the second axial bearing top foil (8-1), the axial length of the second axial bearing wave foil (8-2), and the axial length of the second gap (12).

5. The foil bearing assembly according to any one of claims 1 to 4, characterized in that: The first comb teeth (3-3) of the rotor are located radially inside the inner circle of the first axial bearing (7), and a third gap (13) is provided between the outer periphery of the first comb teeth (3-3) of the rotor and the radial inner circle of the first axial bearing (7); the second comb teeth (3-4) of the rotor are located radially inside the inner circle of the second axial bearing (8), and a fourth gap (14) is provided between the outer periphery of the second comb teeth (3-4) of the rotor and the radial inner circle of the second axial bearing (8); The thrust plate (6) is provided with a thrust plate vent hole (6-5), one end of the thrust plate vent hole (6-5) is opposite to the third gap (13) between the first axial bearing (7) and the first comb tooth (3-3) of the rotor, and the other end of the thrust plate vent hole (6-5) is opposite to the fourth gap (14) between the second axial bearing (8) and the second comb tooth (3-4) of the rotor; the third gap (13) between the first axial bearing (7) and the first comb tooth (3-3) of the rotor and the fourth gap (14) between the second axial bearing (8) and the second comb tooth (3-4) of the rotor can be communicated through the thrust plate vent hole (6-5).

6. The foil bearing assembly according to claim 5, wherein: A thrust plate first groove (6-3) is provided on a first axial end surface of the thrust plate (6) facing the third gap (13), the thrust plate first groove (6-3) being a blind groove structure, and the thrust plate first groove (6-3) extending from the first axial end surface toward the interior of the thrust plate (6); a thrust plate second groove (6-4) is provided on a second axial end surface of the thrust plate (6) facing the fourth gap (14), the thrust plate second groove (6-4) being a blind groove structure, and the thrust plate second groove (6-4) extending from the second axial end surface toward the interior of the thrust plate (6); The thrust plate vent hole (6-5) is located inside the thrust plate (6), and one end of the thrust plate vent hole (6-5) is communicated with the first thrust plate groove (6-3), and the other end is communicated with the second thrust plate groove (6-4).

7. The foil bearing assembly according to claim 6, wherein: The first groove (6-3) of the thrust plate extends along the axial direction of the thrust plate (6), the thrust plate vent hole (6-5) extends along the axial direction of the thrust plate (6), and the second groove (6-4) of the thrust plate extends along the axial direction of the thrust plate (6). The flow cross-sectional area of the first groove (6-3) of the thrust plate is larger than the flow cross-sectional area of the thrust plate vent hole (6-5), and the flow cross-sectional area of the second groove (6-4) of the thrust plate is larger than the flow cross-sectional area of the thrust plate vent hole (6-5).

8. The foil bearing assembly according to claim 6, wherein: The invention also includes a radial bearing (5) and a rotating shaft (15), wherein at least part of the structure of the rotating shaft (15) is located on the inner periphery of the rotor (3), and the rotating shaft (15) is a hollow shaft structure, one end of the hollow channel of which can be communicated with the first groove (6-3) of the thrust plate or the second groove (6-4) of the thrust plate, and the other end of the hollow channel can be communicated with the position between the radial bearing (5) and the rotor (3) so as to conduct gas to the radial bearing (5).

9. The foil bearing assembly according to claim 8, wherein: The first groove (6-3) of the thrust plate is located on the axial end face of the thrust plate (6) away from the radial bearing (5), the radial inner side of the first groove (6-3) of the thrust plate extends to connect with the outer peripheral surface of the rotating shaft (15), one end of the hollow channel extends to the outer peripheral surface of the rotating shaft (15) to communicate with the first groove (6-3) of the thrust plate, and a rotor radial air hole (3-5) is also provided on the rotor (3) at a position radially opposite to the radial bearing (5), and the other end of the hollow channel can extend to the outer peripheral surface of the rotating shaft (15) to communicate with the rotor radial air hole (3-5).

10. A motor, characterized in that: A foil bearing assembly comprising the foil bearing assembly according to any one of claims 1 to 9.

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