A radial oil pickup ring for under-the-hub oil supply of an aeroengine

Abstract

The application provides a radial oil collecting ring for under-the-ring oil supply of an aero-engine, which comprises a vane wheel, an oil dam, an oil collecting inner wall with a slope, and an oil delivery cavity between the oil dam and the oil collecting inner wall, wherein the rear side of the oil dam is provided with an axial groove perpendicular to the circumference, and the side edge of the oil delivery cavity leading to an oil collecting cavity is provided with a side wall with a taper, the side wall extending from the oil collecting inner wall to the oil dam in the circumferential direction; after the collected lubricating oil enters the oil delivery cavity, the lubricating oil flows along the oil delivery cavity to the oil collecting inner wall and enters the oil collecting cavity along the oil collecting inner wall; when the backflow lubricating oil flows to the oil dam, the lubricating oil is guided into the oil collecting cavity through the axial groove, so that the multi-way lubricating oil dispersion and collection function of the radial oil collecting ring is realized.

Description

Technical Field

[0001] This application belongs to the field of aero-engine technology, and specifically relates to a radial oil receiving ring for aero-engine under-ring oil supply. Background Technology

[0002] Aero-engine main bearings operate at high speeds and generate significant heat. To ensure their long-term reliable operation, a stable flow of lubricating oil is required for lubrication and cooling. To achieve effective lubrication and cooling, some main bearings employ an under-ring oil supply structure. An oil collection ring (axial or radial) collects the lubricating oil sprayed from the nozzle and flows through an oil delivery groove to an annular oil collection groove under the inner ring of the bearing. The lubricating oil lubricates the bearing under centrifugal force.

[0003] like Figure 1 The diagram shows a conventional radial oil collection ring 10, which includes an impeller 11, an oil dam 12, an oil delivery chamber 13, and an oil collection inner wall 14. Lubricating oil enters through the impeller 11, passes through the oil dam 12, and enters the oil delivery chamber 13. To prevent backflow, the lubricating oil flows towards the oil collection inner wall 14 after encountering the oil dam 12. Upon encountering the oil collection inner wall 14, the lubricating oil begins to flow axially into the annular oil collection chamber.

[0004] Due to space constraints in engine design, radial oil retainer rings are primarily used at the front support bearing of the high-pressure compressor and the rear support bearing of the high-pressure turbine. The bearings in these locations operate under extremely harsh conditions and require large quantities of lubricating oil. The flow characteristics of the lubricating oil in the oil supply channel beneath the ring affect the bearing lubrication efficiency. After being injected into the impeller through the nozzle, the flow velocity of the lubricating oil decreases due to airflow resistance and internal wall resistance, easily causing oil accumulation in the oil delivery chamber, which is detrimental to the lubrication and cooling of the engine's main bearings. Summary of the Invention

[0005] The purpose of this application is to provide a radial oil receiving ring for under-ring oil supply in an aircraft engine, in order to solve or mitigate at least one of the problems in the prior art.

[0006] The technical solution of this application is: a radial oil receiving ring for oil supply under the ring of an aero-engine. The radial oil receiving ring includes: an impeller, an oil dam, an inner oil receiving wall with a slope, and an oil delivery chamber located between the oil dam and the inner oil receiving wall. The rear side of the oil dam is provided with an axial groove perpendicular to the circumferential direction. The side edge of the oil delivery chamber leading to the oil collection chamber is provided with a tapered sidewall. The sidewall extends circumferentially from the inner oil receiving wall to the oil dam. After the lubricating oil collected by the impeller enters the oil delivery chamber, it flows along the oil delivery chamber to the inner oil receiving wall and then enters the oil collection chamber. When the returning lubricating oil flows to the oil dam, it is guided into the oil collection chamber through the axial groove, thereby realizing the multi-path lubricating oil dispersion and collection function of the radial oil receiving ring.

[0007] In a preferred embodiment of this application, the slope of the inner wall of the oil collection device is at an obtuse angle to the circumferential direction.

[0008] In a preferred embodiment of this application, the depth of the axial groove is 0.05 mm to 0.2 mm.

[0009] In a preferred embodiment of this application, the cross-sectional shape of the axial groove is semi-circular.

[0010] In a preferred embodiment of this application, the cross-sectional edge line of the axial groove is tangent to the oil dam.

[0011] The radial oil collection ring provided in this application has a structure optimized inside the compact radial oil collection ring, which can realize the dispersed collection of lubricating oil from multiple channels, accelerate the flow of lubricating oil in the oil delivery chamber, and improve the oil supply, lubrication and cooling effect under the main bearing ring of the aero-engine. Attached Figure Description

[0012] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0013] Figure 1 This is a schematic diagram of a typical radial oil collection ring structure in the prior art.

[0014] Figure 2 This is a schematic diagram of the radial oil collection ring structure of this application. Detailed Implementation

[0015] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0016] To overcome the problem of oil accumulation caused by radial oil collection rings in the prior art, this application provides a radial oil collection ring for oil supply under the ring of an aero-engine, which improves its rapid oil collection capability and enhances bearing lubrication efficiency based on the original structure, thereby meeting the higher functional requirements of the engine main bearing.

[0017] like Figure 2 As shown, the radial oil receiving ring 20 for oil supply under the ring of an aircraft engine provided in this application includes: an impeller 21, an oil dam 22, an oil delivery chamber 24, and an oil receiving inner wall 25.

[0018] The oil dam 22 and the oil receiving inner wall 25 form an oil delivery chamber 24.

[0019] The inner wall 25 of the oil-collecting section has a slope that forms an obtuse angle with the circumference.

[0020] An axial groove 23 perpendicular to the circumferential direction is provided on the rear side of the oil dam 22. The axial groove 23 has a slight depth, for example, it can be 0.05mm to 0.2mm deep. The cross-section of the axial groove 23 can be machined into a semi-circle using a circular milling cutter. The distance between the axial groove 23 and the oil dam 22 should not be too short. In the preferred embodiment of this application, the edge line of the cross-section of the axial groove 23 is tangent to the oil dam 22.

[0021] Furthermore, a tapered sidewall 26 is provided on one edge of the oil delivery chamber 24 leading to the oil collection chamber (not shown). The sidewall 26 extends circumferentially from the inner oil receiving wall 25 to the oil dam 22. For example, in some embodiments of this application, the sidewall 26 is implemented in the form of a chamfer, and the angle can be 45 degrees.

[0022] The radial oil collection ring 20 for under-ring oil supply in an aero-engine provided in this application operates as follows: Lubricating oil is collected by the impeller 21, enters the oil delivery chamber 24 after passing through the oil dam 22, and continues to flow forward. When it encounters the sloped inner wall 25, due to the circumferential path difference, the lubricating oil is sequentially diverted and flows along the inner wall. The lubricating oil passes through the tapered side wall 26 to the oil collection chamber, and is accelerated to the annular oil collection groove by the action of centrifugal force. At the same time, backflow of lubricating oil is prevented. When the lubricating oil flows towards the oil dam 22, it is directly introduced into the annular oil collection chamber through the slightly deep axial groove 23, thereby realizing the multi-path lubricating oil dispersion and collection function of the radial oil collection ring.

[0023] The radial oil collection ring provided in this application has a structure optimized inside the compact radial oil collection ring, which can realize the dispersed collection of lubricating oil from multiple channels, accelerate the flow of lubricating oil in the oil delivery chamber, and improve the oil supply, lubrication and cooling effect under the main bearing ring of the aero-engine.

[0024] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A radial oil receiving ring for under-ring oil supply in an aircraft engine, characterized in that, The radial oil collection ring includes: an impeller, an oil dam, a sloped oil collection inner wall, and an oil delivery chamber located between the oil dam and the oil collection inner wall. The rear side of the oil dam is provided with an axial groove perpendicular to the circumferential direction, and the oil delivery chamber has a tapered sidewall on one side edge leading to the oil collection chamber. The sidewall extends circumferentially from the oil collection inner wall to the oil dam. After the lubricating oil collected by the impeller enters the oil delivery chamber, it flows along the oil delivery chamber to the inner wall of the oil receiving chamber and then enters the oil collection chamber along the inner wall of the oil receiving chamber. When the lubricating oil flows back to the oil dam, it is guided into the oil collection chamber through the axial groove, thereby realizing the multi-path lubricating oil dispersion and collection function of the radial oil receiving ring.

2. The radial oil receiving ring for under-ring oil supply in an aircraft engine as described in claim 1, characterized in that, The slope of the inner wall of the oil collection system is obtuse at the circumferential direction.

3. The radial oil receiving ring for under-ring oil supply in an aircraft engine as described in claim 1, characterized in that, The depth of the axial groove is 0.05mm~0.2mm.

4. The radial oil receiving ring for under-ring oil supply in an aircraft engine as described in claim 3, characterized in that, The cross-sectional shape of the axial groove is semi-circular.

5. The radial oil receiving ring for under-ring oil supply in an aircraft engine as described in claim 4, characterized in that, The edge line of the axial groove is tangent to the oil dam.

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