Aero-engine bearing with function of separating oil and gas in bearing cavity

Abstract

The invention belongs to the technical field of aero-engines, and particularly relates to an aero-engine bearing with a function of separating oil and gas in a bearing cavity, the aero-engine bearing comprises a bearing column, the outer surface of the bearing column is sleeved with an oil-gas separation mechanism, and the two sides of the oil-gas separation mechanism are fixedly connected with shielding caps respectively; a through hole matched with the surface of the bearing column is formed in the circle center of the shielding cap, a sealing mechanism is fixedly connected to the inner wall of the through hole, the oil-gas separation mechanism comprises a limiting ring, an oil inlet hole is formed in the side face of the limiting ring, and a fixing ring is fixedly connected to the inner wall of the limiting ring. According to the aero-engine bearing, by arranging the oil-gas separation mechanism, an oil-gas mixture entering the bearing cavity can be effectively separated, in the oil-gas separation process, impurities, bubbles and the like which are possibly mixed can be separated from lubricating oil, abrasion of the impurities to the bearing and adverse effects of the bubbles to the lubricating performance are reduced, and the service life of the bearing is prolonged. And the working stability and durability of the bearing are further improved.

Description

Technical Field

[0001] The invention relates to the technical field of aeroengines, and in particular to an aeroengine bearing with an oil-gas separation function in a bearing cavity. Background Art

[0002] Bearings are an important component in modern mechanical equipment. Their main function is to support the mechanical rotating body, reduce the friction coefficient during its movement, and ensure its rotation accuracy. Sliding bearings are a large category of bearings, and they are bearings that work under sliding friction. Sliding bearings have the characteristics of stable, reliable and noiseless operation. In aircraft engine fuel gear pumps, sliding bearings are particularly important and widely used.

[0003] Traditional aircraft engine bearing oil-gas separation devices cannot fully separate the lubricating oil and gas, resulting in some gas mixing into the lubricating oil, affecting the lubrication effect. The presence of gas will reduce the viscosity and lubricating performance of the lubricating oil, increase bearing wear, and shorten the service life of the bearing. Especially in high temperature, high pressure, and high-speed rotation working environments, the sealing structure of the bearing cavity is prone to leakage problems. Oil and gas leakage will not only cause waste of lubricating oil, but may also 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 aircraft engine bearing with oil-gas separation function in the bearing cavity. Summary of the invention

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

[0006] The present invention proposes an aircraft engine bearing with oil-gas separation function in a bearing cavity, comprising a bearing column, an outer surface of the bearing column is sleeved with an oil-gas separation mechanism, two sides of the oil-gas separation mechanism are respectively fixedly connected with shielding caps, a through hole matched with 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 through hole, the oil-gas separation mechanism comprises a limit ring, a side surface of the limit ring is opened with an oil inlet hole, the inner wall of the limit ring is fixedly connected with a fixing ring, the body array of the fixing ring is opened with threaded holes, the outer side surface of the fixing ring is provided with a connecting ring matched with it, the connecting ring is threadedly connected to the fixing ring by bolts, the inner wall of the fixing ring is fixedly connected with an oil inlet ring, the inner wall of the oil inlet hole extends to the side of the oil inlet ring, the inner wall of the connecting ring is fixedly connected with a bearing, and 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, the inner wall of the sealing ring is fixedly connected to an oil sealing ring, the outer side surface of the oil sealing ring is fixedly sleeved with a spring, the surface of the bearing column is fixedly connected with a ferrule, the ferrule is located on the inner side of the oil sealing ring, the outer side surface of the ferrule is provided with an array of slots, and the inner wall of the slot is fixedly inserted with a fan blade.

[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 fan blade is inclined toward the inner side of the oil sealing ring, and the inclination angle of the fan blade is 30° to 60°.

[0010] Preferably, an oil outlet hole is formed on the inner wall of the shielding cap, and a contact point between the inner wall of the oil outlet hole and the inner wall of the shielding cap is configured to be concave.

[0011] The beneficial effects of the present invention are: 1. By setting up 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, such as wear particles generated by the aircraft engine itself when it is working and various dust, sand, salt spray pollutants in the air, and lubricating oil will gradually undergo oxidation reactions under the action of high temperature, high pressure and oxygen to generate some impurities such as colloids or asphalt, which are separated from the lubricating oil, reducing the wear of impurities on the bearing and the adverse effects of bubbles on the lubrication performance, and further improving the working stability and durability of the bearing.

[0012] 2. By setting up a sealing mechanism, it is possible to effectively prevent oil and gas from leaking from the connection between the bearing column and the baffle cap, ensuring that the oil and gas in the bearing cavity are in a relatively closed environment (the vent in the bearing cavity is set to balance the pressure in the cavity. During the operation of the aircraft engine, the high-speed operation of the bearing will increase the temperature in the cavity, and the oil and gas will expand due to the heat. If there is no vent, the pressure in the cavity will rise sharply, which may damage the bearing structure. However, the vent can only achieve limited pressure regulation, i.e. gas discharge. Under the high-speed operation of the fan blades, the oil molecules adhere to the inner wall of the baffle cap through centrifugal force, and finally flow down along its inner wall and converge to the oil outlet. If there is no good sealing mechanism, oil and gas will still leak in large quantities from the connection between the bearing column and the baffle cap, making it difficult to maintain stable pressure in the cavity), maintain the stability of the oil and gas pressure, improve the utilization efficiency of oil and gas, and at the same time avoid pollution to other engine components caused by oil and gas leakage. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 A schematic diagram of an aircraft engine bearing with oil-gas separation function in the bearing cavity proposed by the present invention; Figure 2A cross-sectional view of a shielding cap of an aircraft engine bearing with an oil-gas separation function in a bearing cavity proposed by the present invention; Figure 3 This is a position diagram of a fixing ring of an aircraft engine bearing with oil-gas separation function in the bearing cavity proposed by the present invention; Figure 4 This is a position diagram of an oil inlet ring of an aircraft engine bearing with an oil-gas separation function in a bearing cavity proposed by the present invention; Figure 5 This is a fan blade position diagram of an aircraft engine bearing with oil-gas separation function in the bearing cavity proposed by the present invention; Figure 6 A three-dimensional view of an aircraft engine bearing with oil-gas separation function in the bearing cavity proposed by the present invention; Figure 7 A cross-sectional view of a sealing ring of an aircraft engine bearing with an oil-gas separation function in a bearing cavity proposed by the present invention; Figure 8 A cross-sectional view of an oil seal ring of an aircraft engine bearing with an oil-gas separation function in a bearing cavity proposed by the present invention; Fig. 9 A cross-sectional view of an aircraft engine bearing with an oil-gas separation function in a bearing cavity proposed by the present invention; Fig.10 The invention proposes an aircraft engine bearing with oil-gas separation function in the bearing cavity. Fig. 9 Enlarged view of point A in the middle.

[0014] 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. vent hole; 4. sealing mechanism; 41. sealing ring; 42. oil sealing ring; 43. spring; 44. ring; 45. fan blade. DETAILED DESCRIPTION

[0015] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0016] Reference Figure 1-Figure 10, an aircraft engine bearing with oil-gas separation function in a bearing cavity, comprising 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 through hole matching the surface of the bearing column 1 is opened at the center of the shielding cap 3, and a sealing mechanism 4 is fixedly connected to the inner wall of the through hole. By setting the sealing mechanism 4 on the inner wall of the through hole at the center of the shielding cap 3, oil and gas can be effectively prevented from leaking from the connection between the bearing column 1 and the shielding cap 3, ensuring that the oil and gas in the bearing cavity are in a relatively closed environment, maintaining the stability of the oil and gas pressure, improving the oil and gas utilization efficiency, and preventing oil and gas leakage from causing pollution to other engine components; the oil and gas separation mechanism 2 comprises a limiting ring 21, an oil inlet hole 22 is opened on the side of the limiting ring 21, and the limiting ring 21 has a sealing mechanism 4. A fixing ring 23 is fixedly connected to the inner wall, and a threaded hole 24 is provided in the body array of the fixing ring 23. A matching connecting ring 26 is provided on the outer side of the fixing ring 23, and 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, and the inner wall of the oil inlet hole 22 extends to the side of the oil inlet ring 25. A bearing 27 is fixedly connected to the inner wall of the connecting ring 26, and the inner ring of the bearing 27 is fixedly connected to the surface of the bearing column 1. The oil inlet hole 22 provided on the limit ring 21 and the oil inlet ring 25 connected thereto can more accurately deliver the lubricating oil to the bearing 27 and other parts that need lubrication, avoiding local poor lubrication caused by uneven oil and gas mixing, thereby improving the lubrication efficiency of the bearing, ensuring its reliable operation, and extending the service life of the bearing.

[0017] In this embodiment, the sealing mechanism 4 includes a sealing ring 41, the outer side of the sealing ring 41 is fixedly connected to the inner wall of the perforation of the shielding cap 3, the inner wall of the sealing ring 41 is fixedly connected to an oil sealing ring 42, the outer side of the oil sealing ring 42 is fixedly sleeved with a spring 43, the surface of the bearing column 1 is fixedly connected to a ferrule 44, the ferrule 44 is located on the inner side of the oil sealing ring 42, the outer side of the ferrule 44 is arrayed with a slot, and the inner wall of the slot is fixedly plugged with a fan 45; the inner wall of the shielding cap 3 is provided with an oil outlet hole 30, and the inner wall of the oil outlet hole 30 is connected to the shielding cap 3. The inner wall contact of the cap 3 is set to be concave, and the inner wall of the oil outlet hole 30 is connected to a lubrication system. The lubrication system connected to the aircraft engine bearing has the same basic structure and working mode as the common general lubrication system in the industry, that is, the lubrication system is mainly composed of an oil pump, an oil filter, an oil pipe, a radiator and corresponding control valves, etc. Its working principle is to pump the lubricating oil from the oil tank through the oil pump, filter the impurities through the oil filter, and then transport it to the parts of the engine that need lubrication, including the bearing, and the oil outlet hole 30 is connected to the lubrication system. After completing the lubrication task, the lubricating oil will flow back to the oil tank with heat and impurities, and after cooling and re-filtration, it will re-participate in the circulation, so that the lubricating oil separated from the bearing cavity can smoothly flow into the lubrication system and participate in the subsequent recycling. Through this connection method, it is not only ensured that the bearing is effectively lubricated, but also the reasonable recovery and reuse of the lubricating oil after oil and gas separation is realized, which is in line with the conventional design ideas and common practices of the aircraft engine lubrication system.

[0018] Specifically, the sealing ring 41 made of ceramic silicone rubber is directly connected to the inner wall of the perforation of the shielding cap 3, which can initially prevent oil and gas from leaking from the gap between the shielding cap 3 and the bearing column 1, providing basic sealing. The oil sealing ring 42 cooperates with the sealing ring 41 to further block oil and gas, especially for 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 oil and gas leakage, and ensuring the stability of the lubrication and pressure environment in the bearing cavity; the oil sealing ring 42 made of polyimide rubber has a spring 43 made of molybdenum-rhenium alloy sleeved on its outer side, which can enable the oil sealing ring 42 to always maintain a certain pressure on the cylindrical surface of the bearing column 1. During the operation of the engine, even if the bearing column 1 has a certain degree of vibration or displacement, the elastic effect of the spring 43 can prompt the oil sealing ring 42 to adjust itself adaptively, always fit closely to the bearing column 1, maintain a good sealing state, and reduce the risk of sealing failure caused by vibration; The fan blades 45 arranged on the ring 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 to generate heat. The fan blades 45 rotate with the bearing column 1 to accelerate the flow of surrounding air and take away the heat through air convection, which helps to reduce the working temperature of the bearing 27, avoid the problems of bearing 27 performance degradation and lubrication failure caused by high temperature, and extend the service life of the bearing 27; during the rotation process, the fan blades 45 have a certain guiding effect on the oil and gas flow in the bearing cavity. The high-speed rotating bearing 27 will generate high temperature, and the high temperature will cause the lubricating oil in the bearing 27 to evaporate. The lubricating oil molecules are then taken out of the interior of the bearing 27 by the high-speed rotating fan blades 45 when exhausting, and a large part of them adhere to the surface of the fan blades 45, and finally are thrown out from the fan blades 45 by centrifugal force and adhere to the inner wall of the shielding cap 3. The lubricating oil molecules gather together, and the lubricating oil flows out to the external lubrication system through the oil outlet 30 opened on the inner wall of the shielding cap 3 under the high temperature and high pressure environment generated by the rotation of the bearing 27.

[0019] 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 .

[0020] Specifically, the lower end of the "L"-shaped oil inlet hole 22 is precisely aligned with the rotating part of the bearing 27, and the lubricating oil can be directly delivered to the position of the bearing 27 that needs lubrication the most, that is, the contact area between the rolling element and the raceway. Compared with other oil supply methods, this precise 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, so that the lubricating oil can play a lubricating role to the greatest extent, reduce the waste of lubricating oil caused by unreasonable lubrication paths, improve the utilization rate of lubricating oil, and reduce the operating cost of the engine to a certain extent.

[0021] In this embodiment, 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°.

[0022] Specifically, by throwing the oil molecules to the inner wall of the shielding cap 3, the distribution state of oil and gas in the bearing cavity is changed. The thrown 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, thereby optimizing the distribution of oil and gas in the bearing cavity and improving the overall performance of the lubrication system.

[0023] 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, and the material of the filter screen is silicon carbide ceramic. By setting the silicon carbide ceramic filter screen, it has a precise and stable aperture structure. During the long-term working process, its aperture will not change significantly due to factors such as high temperature and high pressure, and can always maintain consistent filtering accuracy, thereby ensuring the stability of the oil and gas separation effect and avoiding the problem of incomplete separation due to fluctuations in the filter screen performance.

[0024] Reference Figure 1-Figure 10 , a separation method for an aircraft engine bearing with oil-gas separation function in a bearing cavity: Step 1: The bearing column 1 rotates at high speed, and at the same time drives the fan blade 45 fixedly connected to the inner wall of the ferrule 44 and the inner ring of the bearing 27 to rotate at high speed, and the oil inlet hole 22 is opened to inlet oil, and the lubricating oil flows through the oil inlet hole 22 and the body of the oil inlet ring 25 to spray to the rotating part of the bearing 27; 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 blade 45, and are then thrown away from the surface of the fan blade 45 by centrifugal force until they adhere to the inner wall of the shielding cap 3. The lubricating oil that gathers little by little is left on the inner wall of the shielding cap 3, and flows out through the oil outlet 30 opened on the inner wall of the shielding cap 3 to the external lubrication system.

[0025] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which 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 to 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 to a bearing (27), and the inner ring of the bearing (27) is fixedly connected to the surface of the bearing column (1).

2. The aircraft engine bearing with oil-gas separation function in the bearing cavity according to claim 1, characterized in that: 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).

3. The aircraft engine bearing with oil-gas separation function in the bearing cavity according to claim 2, 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).

4. The aircraft engine bearing with oil-gas separation function in the bearing cavity according to claim 3, 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°.

5. The aircraft engine bearing with oil-gas separation function in the bearing cavity according to claim 4, 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.

6. The aircraft engine bearing with oil-gas separation function in the bearing cavity according to claim 5, characterized in that: 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.

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