An aeroengine bearing with the function of oil-gas separation in the bearing cavity

Abstract

The present invention belongs to the technical field of aeroengines, and in particular, to an aeroengine bearing with an oil-gas separation function in a bearing cavity, which includes a bearing column. An oil-gas separation mechanism is sleeved on the outer surface of the bearing column. Shielding caps are fixedly connected to both sides of the oil-gas separation mechanism respectively. A perforation adapted to the surface of the bearing column is opened at the center of the shielding cap, and a sealing mechanism is fixedly connected to the inner wall of the perforation. The oil-gas separation mechanism includes a limiting ring, an oil inlet hole is opened on the side surface of the limiting ring, and a fixing ring is fixedly connected to the inner wall of the limiting ring. For this aeroengine bearing, by setting the oil-gas separation mechanism, the oil-gas mixture entering the bearing cavity can be effectively separated. During the oil-gas separation process, impurities and bubbles that may be mixed in can be separated from the lubricating oil, reducing the wear of the bearing caused by impurities and the adverse effects of bubbles on the lubricating performance, and further improving the working stability and durability of the bearing.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engines, and particularly relates to an aero-engine bearing with an oil-gas separation function in a bearing cavity. Background Art

[0002] A bearing is an important component in contemporary mechanical equipment. Its main function is to support a mechanical rotating body, reduce the friction coefficient during its movement, and ensure its rotational accuracy. As a major type of bearing, a sliding bearing operates under sliding friction. A sliding bearing features smooth operation, reliability, and noiselessness. In an aero-engine fuel gear pump, the sliding bearing is particularly important and widely used.

[0003] The traditional oil-gas separation device for aero-engine bearings cannot fully separate lubricating oil and gas, resulting in some gas mixing into the lubricating oil, which affects the lubrication effect. The presence of gas will reduce the viscosity and lubrication performance of the lubricating oil, increase the wear of the bearing, and shorten the service life of the bearing. Especially in a working environment of high temperature, high pressure, and high-speed rotation, the sealing structure of the bearing cavity is prone to leakage problems. Oil-gas leakage will not only cause waste of lubricating oil but also may contaminate other components of the engine, affecting the overall performance and reliability of the engine.

[0004] In view of the above problems, the present invention proposes an aero-engine bearing with an oil-gas separation function in a bearing cavity. Summary of the Invention

[0005] Based on the existing technical problems of oil-gas separation in aero-engine bearings, the present invention proposes an aero-engine bearing with an oil-gas separation function in a bearing cavity.

[0006] An aero-engine bearing with an oil-gas separation function in a bearing cavity proposed by the present invention includes a bearing column. An oil-gas separation mechanism is sleeved on the outer surface of the bearing column. Shielding caps are fixedly connected to both sides of the oil-gas separation mechanism. A perforation adapted to the surface of the bearing column is opened at the center of the shielding cap. A sealing mechanism is fixedly connected to the inner wall of the perforation. The oil-gas separation mechanism includes a limit ring. An oil inlet hole is opened on the side surface of the limit ring. A fixing ring is fixedly connected to the inner wall of the limit ring. Threaded holes are arrayed on the body of the fixing ring. A connecting ring adapted to it is arranged on the outer side surface of the fixing ring. The connecting ring is threadedly connected to the fixing ring by bolts. An oil inlet ring is fixedly connected to the inner wall of the fixing ring. The inner wall of the oil inlet hole extends to the side surface of the oil inlet ring. A bearing is fixedly connected to the inner wall of the connecting ring. The inner ring of the bearing is fixedly connected to the surface of the bearing column.

[0007] Preferably, the sealing mechanism includes a sealing ring. The outer side surface of the sealing ring is fixedly connected to the inner wall of the perforation of the shielding cap. An oil sealing ring is fixedly connected to the inner wall of the sealing ring. A spring is fixedly sleeved on the outer side surface of the oil sealing ring. A ferrule is fixedly connected to the surface of the bearing column. The ferrule is located inside the oil sealing ring. Slots are arrayed on the outer side surface of the ferrule. Blades are fixedly inserted into the inner walls of the slots.

[0008] Preferably, the oil inlet hole is in an "L" shape, and the lower end of the oil inlet hole faces the rotating part of the bearing.

[0009] Preferably, the end of the blade inclines towards the inside of the oil sealing ring, and the inclination angle of the blade is 30° to 60°.

[0010] Preferably, an oil outlet hole is formed in the inner wall of the shielding cap, and the contact part between the inner wall of the oil outlet hole and the inner wall of the shielding cap is concave.

[0011] The beneficial effects in the present invention are as follows:

[0012] 1. By providing an oil-gas separation mechanism, the oil-gas mixture entering the bearing cavity can be effectively separated. During the oil-gas separation process, bubbles and impurities can be removed, such as wear particles generated by the aero-engine itself during operation and various dust, sand, salt spray pollutants in the air. In addition, lubricating oil will gradually undergo an oxidation reaction under the action of high temperature, high pressure and oxygen, generating some impurities such as gums or asphaltenes, which are separated from the lubricating oil, reducing the wear of the impurities on the bearing and the adverse effects of the bubbles on the lubrication performance, and further improving the working stability and durability of the bearing.

[0013] 2. By providing a sealing mechanism, oil and gas can be effectively prevented from leaking from the connection between the bearing column and the shielding cap, ensuring that the oil and gas in the bearing cavity are in a relatively closed environment (the vent hole in the bearing cavity is provided to balance the pressure in the cavity. During the operation of the aero-engine, the high-speed rotation of the bearing will cause the temperature in the cavity to rise, and the oil and gas will expand due to heat. Without the vent hole, the pressure in the cavity will rise sharply, which may damage the bearing structure. However, the vent hole can only achieve limited pressure regulation, that is, gas discharge. Under the high-speed rotation of the blades, oil molecules adhere to the inner wall of the shielding cap through centrifugal force and finally flow down along the inner wall and converge at the oil outlet hole. Without a good sealing mechanism, a large amount of oil and gas will still leak from the connection between the bearing column and the shielding cap, making it difficult to maintain a stable pressure in the cavity), maintaining the stability of the oil and gas pressure, improving the utilization efficiency of the oil and gas, and at the same time avoiding the pollution of other engine components caused by the leakage of oil and gas. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic diagram of an aero-engine bearing with an oil-gas separation function in the bearing cavity proposed by the present invention;

[0015] Figure 2 Cross-sectional view of the shielding cap of an aero-engine bearing with oil-gas separation function in the bearing cavity proposed by the present invention;

[0016] Figure 3 Position diagram of the fixing ring of an aero-engine bearing with oil-gas separation function in the bearing cavity proposed by the present invention;

[0017] Figure 4 Position diagram of the oil inlet ring of an aero-engine bearing with oil-gas separation function in the bearing cavity proposed by the present invention;

[0018] Figure 5 Position diagram of the fan blade of an aero-engine bearing with oil-gas separation function in the bearing cavity proposed by the present invention;

[0019] Figure 6 Stereogram of the bearing of an aero-engine bearing with oil-gas separation function in the bearing cavity proposed by the present invention;

[0020] Figure 7 Cross-sectional view of the sealing ring of an aero-engine bearing with oil-gas separation function in the bearing cavity proposed by the present invention;

[0021] Figure 8 Cross-sectional view of the oil sealing ring of an aero-engine bearing with oil-gas separation function in the bearing cavity proposed by the present invention;

[0022] Figure 9 Cross-sectional view of the bearing of an aero-engine bearing with oil-gas separation function in the bearing cavity proposed by the present invention;

[0023] Figure 10 Enlarged view of the position A of an aero-engine bearing with oil-gas separation function in the bearing cavity proposed by the present invention Figure 9 in the figure.

[0024] In the figure: 1, bearing column; 2, oil-gas separation mechanism; 21, limit ring; 22, oil inlet hole; 23, fixing ring; 24, threaded hole; 25, oil inlet ring; 26, connecting ring; 27, bearing; 3, shielding cap; 30, oil outlet hole; 31, ventilation hole; 4, sealing mechanism; 41, sealing ring; 42, oil sealing ring; 43, spring; 44, ferrule; 45, fan blade. Specific embodiments

[0025] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments.

[0026] Refer to Figures 1 - 10, an aeroengine bearing with oil-gas separation function in the bearing cavity, includes a bearing column 1. An oil-gas separation mechanism 2 is sleeved on the outer surface of the bearing column 1. Shielding caps 3 are fixedly connected to both sides of the oil-gas separation mechanism 2. A perforation adapted to the surface of the bearing column 1 is opened at the center of the shielding cap 3. A sealing mechanism 4 is fixedly connected to the inner wall of the perforation. By setting the sealing mechanism 4 on the inner wall of the perforation at the center of the shielding cap 3, it can effectively prevent the leakage of oil and gas from the connection between the bearing column 1 and the shielding cap 3, ensure that the oil and gas in the bearing cavity are in a relatively closed environment, maintain the stability of the oil and gas pressure, improve the utilization efficiency of the oil and gas, and at the same time avoid the pollution of other engine components caused by the leakage of oil and gas; The oil-gas separation mechanism 2 includes a limiting ring 21. An oil inlet hole 22 is opened on the side surface of the limiting ring 21. A fixing ring 23 is fixedly connected to the inner wall of the limiting ring 21. Threaded holes 24 are arrayed on the body of the fixing ring 23. A connecting ring 26 adapted to it is arranged on the outer side surface of the fixing ring 23. The connecting ring 26 is threadedly connected to the fixing ring 23 by bolts. An oil inlet ring 25 is fixedly connected to the inner wall of the fixing ring 23. The inner wall of the oil inlet hole 22 extends to the side surface of the oil inlet ring 25. A bearing 27 is fixedly connected to the inner wall of the connecting ring 26. The inner ring of the bearing 27 is fixedly connected to the surface of the bearing column 1. Structures such as the oil inlet hole 22 opened on the limiting ring 21 and the oil inlet ring 25 communicated with it can accurately deliver the lubricating oil to parts such as the bearing 27 that need lubrication, avoid local poor lubrication caused by uneven mixing of oil and gas, thereby improving the lubrication efficiency of the bearing, ensuring its reliable operation, and extending the service life of the bearing.

[0027] In this embodiment, the sealing mechanism 4 includes a sealing ring 41. The outer side surface of the sealing ring 41 is fixedly connected to the inner wall of the perforation of the shielding cap 3. An oil sealing ring 42 is fixedly connected to the inner wall of the sealing ring 41. A spring 43 is fixedly sleeved on the outer side surface of the oil sealing ring 42. A collar 44 is fixedly connected to the surface of the bearing column 1. The collar 44 is located inside the oil sealing ring 42. Slots are arrayed on the outer side surface of the collar 44, and fan blades 45 are fixedly inserted into the inner walls of the slots. An oil outlet hole 30 is formed in the inner wall of the shielding cap 3. The contact part between the inner wall of the oil outlet hole 30 and the inner wall of the shielding cap 3 is concave. The inner wall of the oil outlet hole 30 is externally connected to a lubrication system. The basic structure and working mode of the lubrication system externally connected to this aero-engine bearing are the same as those of common general lubrication systems in the industry. That is, the lubrication system mainly consists of an oil pump, an oil filter, oil pipes, a radiator, and corresponding control valves, etc. Its working principle is that the oil pump pumps lubricating oil out of the fuel tank, and after filtering impurities through the oil filter, it is transported to the parts of the engine that need lubrication, including this bearing. The oil outlet hole 30 is connected to this lubrication system. After the lubricating oil completes the lubrication task, it will return to the fuel tank with heat and impurities, and after cooling and re-filtering, it will participate in the cycle again, enabling the lubricating oil separated from the bearing cavity to smoothly flow into the lubrication system and participate in subsequent recycling. Through this connection method, it not only ensures that the bearing is effectively lubricated but also realizes the reasonable recovery and reuse of the lubricating oil after oil-gas separation, which conforms to the conventional design concept and general practice of the aero-engine lubrication system.

[0028] Specifically, the sealing ring 41 made of ceramized silicone rubber is directly connected to the inner wall of the perforation of the shielding cap 3, which can initially prevent the leakage of oil and gas from the gap between the shielding cap 3 and the bearing column 1 and provide basic sealing. The oil sealing ring 42 cooperates with the sealing ring 41 to further block oil and gas, especially for the oil and gas that may leak along the axial direction of the bearing column 1, forming a second layer of sealing defense line, significantly improving the sealing performance, effectively preventing the leakage of oil and gas, and ensuring the stability of the lubrication and pressure environment in the bearing cavity. The oil sealing ring 42 made of polyimide rubber, and the spring 43 made of molybdenum-rhenium alloy sleeved on its outer side surface can keep a certain pressure on the cylindrical surface of the bearing column 1. During the operation of the engine, even if there is a certain degree of vibration or displacement of the bearing column 1, the elastic effect of the spring 43 can prompt the oil sealing ring 42 to adaptively adjust and always closely fit the bearing column 1, maintaining a good sealing state and reducing the risk of sealing failure caused by vibration.

[0029] The fan blades 45 provided on the raceway 44 on the surface of the bearing column 1 have a heat dissipation function. When the engine is running, the bearing 27 rotates at a high speed and generates heat. The fan blades 45 rotate with the bearing column 1, accelerating the flow of the surrounding air and taking away the heat through air convection, which helps to reduce the working temperature of the bearing 27 and avoid problems such as performance degradation and lubrication failure of the bearing 27 caused by high temperature, and extends the service life of the bearing 27; during the rotation of the fan blades 45, it has a certain guiding effect on the flow of oil and gas in the bearing cavity. The high-speed rotating bearing 27 will generate high temperature, which causes the lubricating oil in the bearing 27 to evaporate. The lubricating oil molecules are then carried out of the interior of the bearing 27 by the exhaust of the high-speed rotating fan blades 45, and a large part of them adheres to the surface of the fan blades 45. Finally, they are thrown out of the fan blades 45 by centrifugal force and adhere to the inner wall of the shielding cap 3. The lubricating oil molecules accumulate, and under the high-temperature and high-pressure environment generated by the rotation of the lubricating oil bearing 27, they flow out through the oil outlet holes 30 opened on the inner wall of the shielding cap 3 to an external lubrication system.

[0030] In this embodiment, the oil inlet hole 22 is in an "L" shape, and the lower end of the oil inlet hole 22 faces the rotating part of the bearing 27.

[0031] Specifically, the lower end of the "L"-shaped oil inlet hole 22 is accurately aligned with the rotating part of the bearing 27, and the lubricating oil can be directly delivered to the position where the bearing 27 most needs lubrication, that is, the contact area between the rolling elements and the raceway. Compared with other oil supply methods, this accurate positioning can ensure that the key friction parts are fully lubricated, effectively reduce the friction coefficient, reduce wear, improve the working efficiency and service life of the bearing 27, avoid unnecessary splashing and diffusion of the lubricating oil in the bearing cavity, enable the lubricating oil to play the lubricating role to the greatest extent, reduce the waste of lubricating oil caused by unreasonable lubrication paths, improve the utilization rate of the lubricating oil, and reduce the operating cost of the engine to a certain extent.

[0032] In this embodiment, the end of the fan blade 45 inclines towards the inner side of the oil sealing ring 42, and the inclination angle of the fan blade 45 is 30° to 60°.

[0033] Specifically, by throwing the oil molecules onto the inner wall of the shielding cap 3, the distribution state of the oil and gas in the bearing cavity is changed. The thrown-out oil flows down along the inner wall of the shielding cap 3 and can participate in the lubrication cycle again, while the separated gas can be discharged more smoothly, optimizing the distribution of the oil and gas in the bearing cavity and improving the overall performance of the lubrication system.

[0034] The edge array of the shielding cap 3 is provided with ventilation holes 31, and a filter screen is installed in each ventilation hole 31. The material of the filter screen is silicon carbide ceramic; by setting the silicon carbide ceramic filter screen, it has an accurate and stable pore structure. During the long-term working process, its pore size will not change significantly due to factors such as high temperature and high pressure, and can always maintain the same filtration accuracy, ensuring the stability of the oil-gas separation effect and avoiding the problem of incomplete separation caused by fluctuations in the filter screen performance.

[0035] Refer to Figures 1 - 10 , a separation method for an aeroengine bearing with an oil-gas separation function in a bearing cavity:

[0036] Step 1: The bearing column 1 rotates at a high speed, simultaneously driving the fan blades 45 fixedly inserted into the inner wall of the raceway 44 and the inner ring of the bearing 27 to rotate at a high speed. The oil inlet hole 22 is opened for oil inlet, and the lubricating oil flows through the oil inlet hole 22 and is sprayed onto the rotating part of the bearing 27 through the body of the oil inlet ring 25.

[0037] Step 2: The lubricating oil entering the bearing 27 evaporates into a gas under the high-temperature and high-pressure environment generated by the high-speed rotation of the bearing 27. The gaseous lubricating oil molecules adhere to the surface of the high-speed rotating fan blades 45, and then are thrown off the surface of the fan blades 45 by centrifugal force until they adhere to the inner wall of the shielding cap 3. The lubricating oil that accumulates in small amounts flows down from the inner wall of the shielding cap 3 and flows out through the oil outlet hole 30 opened on the inner wall of the shielding cap 3 to the externally connected lubrication system.

[0038] The above is only a preferred specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention, according to the technical solution and inventive concept of the present invention, makes equivalent substitutions or changes, and should be covered by the protection scope of the present invention.

Claims

1. An aircraft engine bearing with an oil-gas separation function in a bearing cavity, comprising a bearing column (1), characterized in that: The outer surface of the bearing column (1) is sleeved with an oil-gas separation mechanism (2), and shielding caps (3) are fixedly connected to both sides of the oil-gas separation mechanism (2), and a through hole matching the surface of the bearing column (1) is provided at the center of the shielding cap (3), and a sealing mechanism (4) is fixedly connected to the inner wall of the through hole. The oil-gas separation mechanism (2) comprises a limit ring (21), and an oil inlet hole (22) is provided on the side of the limit ring (21), and a fixing ring (23) is fixedly connected to the inner wall of the limit ring (21), and the fixing ring (23) is fixedly connected to the inner wall of the fixing ring (21). The main body array of the fixing ring (23) is provided with threaded holes (24), the outer side surface of the fixing ring (23) is provided with a matching connecting ring (26), the connecting ring (26) is threadedly connected to the fixing ring (23) by bolts, the inner wall of the fixing ring (23) is fixedly connected with an oil inlet ring (25), the inner wall of the oil inlet hole (22) extends to the side of the oil inlet ring (25), the inner wall of the connecting ring (26) is fixedly connected with a bearing (27), and the inner ring of the bearing (27) is fixedly connected to the surface of the bearing column (1); The sealing mechanism (4) comprises a sealing ring (41), the outer side surface of the sealing ring (41) being fixedly connected to the inner wall of the hole of the shielding cap (3), the inner wall of the sealing ring (41) being fixedly connected to an oil sealing ring (42), the outer side surface of the oil sealing ring (42) being fixedly sleeved with a spring (43), the surface of the bearing column (1) being fixedly connected to a ferrule (44), the ferrule (44) being located on the inner side of the oil sealing ring (42), the outer side surface of the ferrule (44) being provided with slots in an array, and the inner wall of the slot being fixedly plugged with a fan blade (45); The edge array of the shielding cap (3) is provided with ventilation holes (31), and a filter screen is installed in each of the ventilation holes (31), and the material of the filter screen is silicon carbide ceramic.

2. The aircraft engine bearing with oil-gas separation function in the bearing cavity according to claim 1, characterized in that: The oil inlet hole (22) is in an "L" shape, and the lower end of the oil inlet hole (22) faces the rotating part of the bearing (27).

3. The aircraft engine bearing with oil-gas separation function in the bearing cavity according to claim 2, characterized in that: The end of the fan blade (45) is inclined toward the inner side of the oil sealing ring (42), and the inclination angle of the fan blade (45) is 30° to 60°.

4. The aircraft engine bearing with oil-gas separation function in the bearing cavity according to claim 3, characterized in that: The inner wall of the shielding cap (3) is provided with an oil outlet hole (30), the contact point between the inner wall of the oil outlet hole (30) and the inner wall of the shielding cap (3) is arranged to be concave, and the inner wall of the oil outlet hole (30) is externally connected to a lubrication system.

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