阅读说明：本技术 一种基于蜂鸟翅膀结构的气体动压止推轴承 (Gaseous dynamic pressure footstep bearing based on hummingbird wing structure ) 是由 殷玉枫 龚霖 付良 柴晓峰 韩原臻 王嘉誉 于 2021-01-14 设计创作，主要内容包括：本发明公开了一种基于蜂鸟翅膀结构的气体动压止推轴承,属于滑动轴承领域。该轴承包括主轴、转子止推板和止推轴承,转子止推板和主轴固定连接,与转子止推板同轴心的下方设有止推轴承,转子止推板与止推轴承之间为气膜；止推轴承上表面均匀开有模拟蜂鸟翅膀结构的凹槽。空气从凹槽的前边缘进入,通过凹槽的节流作用在台区与凹槽交界处改变气体速度和密度,形成一个高压气体区,使得气体动压止推轴承具有更高的承载能力；同时由于凹槽圆周阵列于止推轴承的上表面,高压气体因此可以均匀分布于气膜中,提高了气体动压止推轴承的稳定性,使得该轴承的整体性能得以提升。(The invention discloses a gas dynamic pressure thrust bearing based on a hummingbird wing structure, and belongs to the field of sliding bearings. The bearing comprises a main shaft, a rotor thrust plate and a thrust bearing, wherein the rotor thrust plate is fixedly connected with the main shaft, the thrust bearing is arranged below the rotor thrust plate in the same axial center, and an air film is arranged between the rotor thrust plate and the thrust bearing; the upper surface of the thrust bearing is uniformly provided with grooves simulating the wing structure of the hummingbird. Air enters from the front edge of the groove, the speed and the density of the air are changed at the junction of the platform area and the groove through the throttling action of the groove, and a high-pressure gas area is formed, so that the gas dynamic pressure thrust bearing has higher bearing capacity; meanwhile, the grooves are circumferentially arrayed on the upper surface of the thrust bearing, so that high-pressure gas can be uniformly distributed in the gas film, the stability of the gas dynamic pressure thrust bearing is improved, and the overall performance of the bearing is improved.)

1. The utility model provides a gaseous dynamic pressure footstep bearing based on hummingbird wing structure which characterized in that: comprises a main shaft (1), a rotor thrust plate (2) and a thrust bearing (3); the rotor thrust plate (2) and the main shaft (1) are coaxially arranged and fixedly connected; a thrust bearing (3) is arranged on a main shaft (1) below a rotor thrust plate (2), grooves (5) are formed in the upper surface of the thrust bearing (3), and a platform area (6) is formed between the grooves (5); the thrust bearing (3) is in clearance fit with the main shaft (1), and an air film (4) is arranged between the rotor thrust plate (2) and the thrust bearing (3).

2. The winged-structure-based aerodynamic thrust bearing of claim 1, wherein: the single groove (5) is obliquely arranged relative to the straight line where the radius of the upper surface of the thrust bearing (3) is located; the grooves (5) are distributed on the upper surface of the thrust bearing (3) in a circumferential array.

3. The winged-structure-based aerodynamic thrust bearing of claim 2, wherein: the outer contour of each groove (5) is in a streamline shape of a hummingbird wing structure; the groove (5) comprises a front edge (7), a lower edge (8), an upper edge (9) and a rear edge (10).

4. The winged-structure-based aerodynamic thrust bearing of claim 3, wherein: the front edge (7) of the groove (5) is a gas pumping end, the front edge (7) is overlapped with the circumferential surface of the thrust bearing (3), and the rear edge (10), the lower edge (8) and the upper edge (9) are connected with the platform area (6).

5. The winged-structure-based aerodynamic thrust bearing of claim 3, wherein: the included angle between the tangent line at the intersection point of the upper edge (9) of the groove (5) and the excircle of the thrust bearing (3) and the tangent line at the outer side end point of the upper edge (9) is 18-25 degrees.

Technical Field

The invention relates to the field of sliding bearings, in particular to a gas dynamic pressure thrust bearing based on a hummingbird wing structure.

Background

Thrust bearings, also known as thrust bearings, are commonly used to bear the axial force of a rotating shaft and axially position the rotating shaft. The gas lubrication bearing has the advantages of high precision, long service life and good thermal performance, and has wide application prospect in the high-precision field such as precision machine tools, hydrogen fuel cells, photoetching machines, electronic precision instruments, medical instruments and the like.

Gas bearings can be classified into static pressure gas bearings and dynamic pressure gas bearings according to the gas lubrication mechanism. The static pressure gas bearing is to make the external high pressure gas pass through the restrictor and enter the bearing gap to form a high pressure gas film to support the load. The aerostatic bearing must be equipped with a corresponding gas supply device and a gas pressurization device, so that the aerostatic bearing is complex in structure and high in manufacturing cost and running cost. The gas dynamic pressure bearing is formed with a load capacity by means of a dynamic pressure effect generated when a rotor thrust plate rotates.

The bearing capacity of the prior known gas dynamic thrust bearing is low, and the gas dynamic thrust bearing is easy to destabilize under the condition of overhigh rotating speed, so that the use of the gas dynamic thrust bearing in actual production and life is limited within a certain range, and the majority of actual working conditions cannot be met.

In nature, the hummingbird is the only bird which can realize real hovering, forward flying and backward flying. The flying characteristics of the hummingbird are unique mainly because of the particularity of the wing structure, and the lifting force in flying is 75% from the upper fan of the wing and 25% from the lower fan of the wing. The special wing structure provides enough lift force for the flying of the hummingbird, so that the hummingbird can fly at high speed, and meanwhile, the hummingbird can hover in the air and fly forwards, backwards and turn at high speed. The performance of the thrust bearing is improved by applying the similar structure to the aerodynamic thrust bearing at present.

Disclosure of Invention

The invention provides a gas dynamic pressure thrust bearing based on a hummingbird wing structure, which solves the problems that the existing thrust bearing is easy to be unstable and has low bearing capacity under the condition of high-speed operation.

In order to solve the technical problems, the technical scheme provided by the invention is as follows: a gas dynamic pressure thrust bearing based on a hummingbird wing structure comprises a main shaft, a rotor thrust plate and a thrust bearing; the rotor thrust plate and the main shaft are coaxially arranged and fixedly connected; a thrust bearing is arranged on a main shaft below a rotor thrust plate, grooves are formed in the upper surface of the thrust bearing, and a platform area is formed between the grooves; the thrust bearing is in clearance fit with the main shaft, and an air film is arranged between the rotor thrust plate and the thrust bearing. The design of the recess corresponds to a viscous compressor. When the bearing works, the thrust bearing and the rotor thrust plate move relatively, and correspondingly, gas between the thrust bearing and the rotor thrust plate also moves relatively; the gas flow blocked in the relative movement process is throttled and blocked by the groove, and the speed and the density of the gas at the junction of the groove and the platform area are changed, so that the gas pressure of a gas film between the thrust bearing and the rotor thrust plate is increased, and the load bearing capacity is formed.

The single groove is obliquely arranged relative to the straight line of the radius of the upper surface of the thrust bearing, so that external air can be better pumped into the groove close to the inner part of the bearing from the front edge when the bearing works; the grooves are distributed on the upper surface of the thrust bearing in a circumferential array, and the grooves are arranged at equal intervals, so that a high-pressure gas film is uniformly distributed between the thrust bearing and the rotor thrust plate, and the stability of the thrust bearing in the operation process is improved.

The outer contour of each groove is in a streamline shape of a hummingbird wing structure; the groove includes a front edge, a lower edge, an upper edge, and a rear edge. The length of the front edge is smaller than that of the rear edge, the length of the upper edge is smaller than that of the lower edge, the outline edge of the groove simulates the shape of a hummingbird wing, and the linearity of the structure of the hummingbird wing is good, so that the speed of air entering the thrust bearing can be increased, the speed and the density of gap air between the thrust bearing and a rotor thrust plate are changed, and the dynamic pressure of an air film corresponding to a platform area part is increased. Due to the special physiological structure of the hummingbird wing, the hummingbird generates larger lifting force in the flying process, and the groove simulating the hummingbird wing structure on the thrust bearing can also enable the bearing to have larger bearing capacity.

Furthermore, the front edge of the groove is the gas pumping end, the front edge is overlapped with the circumferential surface of the thrust bearing, and the rear edge, the lower edge and the upper edge are connected with the platform area. Specifically, the radian of the front edge is consistent with the radian of the circumferential surface of the outer side of the corresponding thrust bearing. Furthermore, the outer contour of the groove simulates the shape of a hummingbird wing, and the function of guiding and pumping gas is achieved, namely, external gas is pumped into a position between the thrust bearing and the rotor thrust plate from the front edge of the outer circumferential surface of the thrust bearing, the flow rate and the density of the gas at the junction of the groove and the platform area are changed through the throttling resistance of the groove, further, the pressure of part of the gas corresponding to the platform area in the thrust bearing is increased, the pressure difference is formed between the groove and the platform area, and the dynamic pressure gas film rigidity of the gas film area and the bearing capacity of the whole thrust bearing are improved.

Preferably, the included angle between the tangent line of the intersection point of the upper edge of the groove and the excircle of the thrust bearing and the tangent line of the outer side end point of the upper edge is 18-25 degrees, the included angle is an angle between the hummingbird and the hummingbird body during flying, and the included angle is a result of natural evolution for tens of thousands of years, so that the included angle is beneficial to gas which can be pumped into the bearing from the front edge better to form the load capacity.

Compared with the prior art, the invention has the substantial characteristics that: the flying characteristic of the hummingbird is utilized, and the hummingbird wing structure is applied to design a pneumatic thrust bearing so as to improve the performance of the bearing. The method is characterized in that:

1. the special physiological structure of the hummingbird wing is simulated, and a groove which simulates the shape of the hummingbird wing is opened on the upper surface of the thrust bearing. The gas in the gas film is more rapidly changed in flow rate and density at the junction of the groove and the platform area compared with the traditional spiral groove and herringbone groove thrust bearings due to the throttling and blocking effect of the groove, so that the gas film pressure of the platform area on the upper surface of the thrust bearing is increased, and the rigidity of a dynamic pressure gas film between the thrust bearing and a rotor thrust plate and the integral bearing capacity of the bearing are improved;

2. the grooves are uniformly arranged on the upper surface of the thrust bearing, so that a dynamic pressure air film formed when the main shaft runs at a high speed is uniformly distributed between the thrust bearing and the rotor thrust plate; meanwhile, because of the stability of the hummingbird in the flying process, the grooves simulating the wing structures of the hummingbird improve the stability of the aerodynamic thrust bearing in high-speed operation.

3. The invention uses gas as lubricating medium, and the gas plays roles of lubricating and radiating. Compared with the traditional oil lubrication thrust bearing, the oil supply device is not needed, the quality of the thrust bearing is reduced, and the running reliability of the bearing is improved; simultaneously because open the recess that has simulation hummingbird wing structure on footstep bearing, compare in traditional gaseous dynamic pressure footstep bearing and have faster gas pumping function for the inside gas pressure of footstep bearing is higher, and gaseous dynamic pressure footstep bearing's bearing capacity is stronger.

Drawings

The invention is further described with reference to the following figures and detailed description.

FIG. 1 is a schematic structural diagram of a dynamic gas pressure thrust bearing based on a wing structure of a hummingbird according to the present invention.

FIG. 2 is a schematic view of a thrust plate of a rotor of the aerodynamic thrust bearing based on a wing structure of a hummingbird according to the present invention.

FIG. 3 is a schematic view of a thrust bearing of the aerodynamic thrust bearing based on a wing structure of a hummingbird according to the present invention.

FIG. 4 is a schematic diagram showing the space details of the grooves of the aerodynamic thrust bearing based on the wing structure of the hummingbird according to the present invention.

Reference numbers in the figures: 1. the novel motor comprises a main shaft, 2 rotor thrust plates, 3 thrust bearings, 4 air films, 5 grooves, 6 lands, 7 front edges, 8 lower edges, 9 upper edges and 10 rear edges.

Detailed Description

The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it should be noted that, as the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. appear, their indicated orientations or positional relationships are based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" as appearing herein are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

Examples

As shown in fig. 1-4, a dynamic gas pressure thrust bearing based on a hummingbird wing structure comprises a main shaft 1, a rotor thrust plate 2 and a thrust bearing 3, wherein a gas film 4 is arranged between the lower surface of the rotor thrust plate 2 and the upper surface of the thrust bearing 3. The main shaft 1 and the rotor thrust plate 2 are coaxially arranged and cast into a whole; a thrust bearing 3 is arranged on the main shaft 1 below the rotor thrust plate 2 in a matching way.

As shown in fig. 3, eight grooves 5 are formed in the upper surface of the thrust bearing 3, the grooves 5 are arranged on the upper surface of the thrust bearing 3 at equal intervals, and the direction of each groove 5 is inclined relative to the straight line where the radius of the upper surface of the thrust bearing 3 is located, so that gas can enter and exit the grooves 5 conveniently; the area between the grooves 5 is a land 6.

As shown in fig. 4, the outer contour of the groove 5 simulates the structure of a hummingbird wing, including a front edge 7, a rear edge 10, an upper edge 9 and a lower edge 8. Wherein the front edge 7 coincides with the outer circumferential surface of the thrust bearing 3, and the upper edge 9, the lower edge 8 and the rear edge 10 are connected with the platform area 6.

When the device is used, the thrust bearing 3 is fixed, the main shaft 1 rotates to drive the rotor thrust plate 2 to rotate, and a certain relative motion exists between the thrust bearing 3 and the rotor thrust plate 2; the gap between the thrust bearing 3 and the rotor thrust plate 2 is filled with a gas having a certain viscosity as a lubricating medium. At the same time, the gas is also filled in the grooves 5 whose outer contour simulates the wing structure of a hummingbird.

Specifically, the spindle 1 rotates to drive the rotor thrust plate 2 to rotate, gas in the gas film 4 is driven to enter the groove 5 from the front edge 7, the speed and the density of the gas at the rear edge 10, the upper edge 9 and the lower edge 8 of the groove 5 are changed due to the throttling blocking effect of the groove 5, the pressure of the platform area 6 on the upper surface of the thrust bearing 3 is increased, and the rigidity and the load capacity of the gas film 4 between the thrust bearing 3 and the rotor thrust plate 2 are improved.

The gas film 4 for supporting the axial force is composed of a dynamic pressure gas film formed by the high pressure gas of the land 6 when the main shaft 1 rotates. Because the groove 5 simulating the wing structure of the hummingbird is in a streamline profile, the pumping speed of gas from the front edge 7 into the groove 5 is increased, the speed and the density of the gas in the gap between the thrust bearing 3 and the rotor thrust plate 2 are changed, the pressure of the gas in the groove is increased, and the rigidity and the bearing capacity of the gas film 4 are improved. Meanwhile, the grooves 5 are circumferentially arrayed on the upper surface of the thrust bearing 3, so that a formed high-pressure gas film is uniformly distributed in a gap between the thrust bearing 3 and the rotor thrust plate 2, and the stability of the gas dynamic pressure thrust bearing is improved.

Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.