Aero-engine bearing and outer ring structure thereof

Abstract

The application provides an aero-engine bearing and an outer ring structure thereof, and belongs to the technical field of aero-engine bearings. A plurality of heat dissipation holes are arranged in a circle on the end faces of the outer ring. The circumferential surface of the center line of the heat dissipation hole is close to or coincides with the outer ring raceway surface of the bearing. The application improves the heat dissipation and pollution removal capacity of the aero-engine bearing outer ring structure by designing the circumferentially arranged heat dissipation holes, thereby reducing the working temperature of the bearing, reducing foreign matters in the bearing, and ultimately achieving the purpose of improving the service life and reliability of the bearing.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine bearing technology, and specifically relates to an aero-engine bearing and its outer ring structure. Background Technology

[0002] Aircraft engine bearings 10 generally include an inner ring 12, an outer ring 11, rolling elements 13, and a cage 14, with a structure as follows: Figure 1 As shown, the function of the cage 14 is to evenly distribute the rolling elements 13 at equal intervals within the bearing and to allow the rolling elements 13 to move in a direction. There are three guiding methods for the cage 14: inner ring guiding, outer ring guiding, and rolling element guiding. Outer ring guiding is generally used for high-speed, stable load applications. Its advantages include facilitating the entry of lubricating oil into the guiding surface and raceway, and aiding in the correction of the cage 14's position. When the cage 14 is guided by the outer ring, the gap between the outer ring and the cage is very small. During operation, due to centrifugal force, contaminants entering the bearing are not easily discharged. When they enter between the rolling elements 13 and the raceway, they will damage the surface of the raceway or rolling elements 13, increasing the probability of bearing damage and thus reducing the bearing's operational reliability. Simultaneously, in bearings with outer ring guiding, the small gap between the cage 14 and the outer ring 11 means that, due to centrifugal force, the lubricating oil takes longer to discharge compared to bearings with inner ring guiding. If the outer ring 11 has a flange, the flange will act as an oil dam, intercepting the lubricating oil, resulting in relatively high internal turbulence heat within the bearing, which is detrimental to bearing operation. Summary of the Invention

[0003] The purpose of this invention is to provide an aero-engine bearing and its outer ring structure to solve or mitigate at least one of the problems in the prior art.

[0004] The technical solution of the present invention is: an outer ring structure for an aero-engine bearing, wherein a plurality of heat dissipation holes are arranged circumferentially on both end faces of the outer ring, and the circumferential surface where the center line of the heat dissipation holes is located is close to or coincides with the raceway surface of the outer ring of the bearing.

[0005] In a preferred embodiment of the present invention, the structural parameters of the heat dissipation hole include depth L and diameter D.

[0006] In a preferred embodiment of the invention, the diameter D of the heat dissipation hole is configured to be larger than the gap between the cage and the outer ring.

[0007] In a preferred embodiment of the present invention, the depth L of the heat dissipation hole satisfies L≈1 / 2, where W is the bearing width and H is the roller length.

[0008] In a preferred embodiment of the present invention, the number of heat dissipation holes is determined based on the bearing dynamic balance and the degree of weakening of the cage strength, and the number of heat dissipation holes is minimized while meeting the requirements for heat dissipation and sewage discharge capacity.

[0009] On the other hand, the present invention provides an aircraft engine bearing, comprising:

[0010] The outer ring as described in any of the above;

[0011] Inner circle;

[0012] The rolling element located between the inner and outer rings; and

[0013] A cage, on which the rolling elements are disposed, is positioned between the inner and outer rings by the cage, and the cage is guided by the outer ring.

[0014] Based on the outer ring structure of aero-engine bearings, this invention designs circumferentially arranged heat dissipation holes, which simultaneously improve heat dissipation and contaminant removal capabilities, thereby reducing the bearing's operating temperature, minimizing foreign matter in the bearing, and ultimately improving bearing life and reliability. Attached Figure Description

[0015] To more clearly illustrate the technical solution provided by the present invention, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of the present invention.

[0016] Figure 1 This is a cross-sectional view of an existing aero-engine bearing structure.

[0017] Figure 2 This is a cross-sectional view of the aero-engine bearing structure in this invention.

[0018] Figure 3 This is a schematic diagram of the overall structure of the aero-engine bearing in this invention.

[0019] Figure 4 This is a schematic diagram showing the dimensions of the heat dissipation holes on the outer ring of the bearing in this invention. Detailed Implementation

[0020] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions in the embodiments of this invention will be described in more detail below with reference to the accompanying drawings.

[0021] To address the issues of poor sewage discharge capacity, poor heat dissipation performance, and significant temperature differences in aero-engine bearings with outer ring guidance, this application provides a novel aero-engine bearing and its outer ring structure. By improving the outer ring structure, the aforementioned problems are solved.

[0022] like Figure 2 The figure shown is a cross-sectional view of the bearing structure with holes in this invention, and as shown in the figure. Figure 3 The schematic diagram of the bearing structure shown illustrates that the bearing 20 in this invention mainly consists of an outer ring 21, an inner ring 22, rolling elements 23, and a cage 24. The rolling elements 23 are disposed between the outer ring 21 and the inner ring 22 and are held in place by the cage 24. The cage 24 is guided by the outer ring 21; that is, the gap between the cage 24 and the outer ring 21 is significantly smaller than the gap between the cage 24 and the inner ring 22, and the gap between the cage 24 and the outer ring 21 is even smaller. For example, the gap between the cage 24 and the outer ring 21 can be controlled within the range of 0.1mm to 0.5mm, and the specific value can be determined according to the bearing type, size, speed, load, and other operating conditions.

[0023] The outer ring 21 has a ring of circumferentially arranged heat dissipation holes 211 on both end faces. These holes form a new heat dissipation channel for the outer ring 21, which is beneficial for heat dissipation. Simultaneously, the heat dissipation holes 211 can store more lubricating oil, which itself has a cooling effect, thus improving heat dissipation. For aero-engine bearings, especially outer ring-guided bearings, the clearance between the cage and the inner ring is large, while the clearance between the cage and the outer ring is small. Slightly larger contaminants can enter through the clearance between the cage and the inner ring and remain near the clearance between the cage and the outer ring. The heat dissipation holes 211, located near the circumferential surface of the bearing outer ring raceway, facilitate the discharge of contaminants with the lubricating oil.

[0024] In this invention, the heat dissipation effect of the heat dissipation holes 211 is improved by adjusting the structural dimensions of the heat dissipation holes 211. For example... Figure 4The diagram shows the structural dimensions of the heat dissipation hole 211 in this invention. The structural dimensions of the heat dissipation hole 211 include depth L and diameter D. The structural dimensions of the heat dissipation hole 211 are determined based on factors such as bearing heat generation, outer ring strength and stiffness, and the size of lubricating oil contaminant particles. For bearings with an outer ring guide, the gap between the cage 24 and the outer ring 21 is very small. Therefore, the diameter D of the heat dissipation hole 211 is configured to be larger than this gap to improve its drainage capacity. The circumferential surface containing the centerline of the heat dissipation hole 211 is close to or coincides with the raceway surface of the bearing outer ring to ensure that lubricating oil can easily flow out through the heat dissipation hole via the outer ring raceway, and that contaminants on the bearing outer ring raceway can also be easily discharged. Furthermore, the design of the diameter D of the heat dissipation hole 211 should also consider stress concentration. If necessary, finite element numerical simulation can be performed to ensure that the heat dissipation hole 211 does not affect or reduce the structural strength of the bearing outer ring 21. In this invention, the number of heat dissipation holes 211 can be minimized based on the bearing dynamic balance and the degree of weakening of the cage strength, while meeting the requirements for heat dissipation and drainage capacity, so as to ensure the strength of the cage. Furthermore, the depth L of the heat dissipation holes 211 is designed to be approximately equal to half the difference between the bearing width W and the roller length H, i.e., L≈1 / 2 (WH).

[0025] Based on the outer ring structure of aero-engine bearings, this invention designs circumferentially arranged heat dissipation holes, which simultaneously improve heat dissipation and contaminant removal capabilities, thereby reducing the bearing's operating temperature, minimizing foreign matter in the bearing, and ultimately improving bearing life and reliability.

[0026] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention 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 the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A structure for the outer ring of an aero-engine bearing, characterized in that, The outer ring (211) has a plurality of heat dissipation holes (211) arranged in a circumferential pattern on both sides of its end face. The circumferential surface where the center line of the heat dissipation hole (211) is located is close to or coincides with the raceway surface of the outer ring of the bearing.

2. The aero-engine bearing outer ring structure as described in claim 1, characterized in that, The structural parameters of the heat dissipation hole (211) include depth L and diameter D.

3. The aero-engine bearing outer ring structure as described in claim 2, characterized in that, The diameter D of the heat dissipation hole (211) is configured to be greater than the gap between the retainer (24) and the outer ring (21).

4. The aero-engine bearing outer ring structure as described in claim 2, characterized in that, The depth L of the heat dissipation hole (211) satisfies L≈1 / 2(WH), where W is the bearing width and H is the roller length.

5. The aero-engine bearing outer ring structure as described in claim 1, characterized in that, The number of heat dissipation holes (211) is determined based on the bearing dynamic balance and the degree of weakening of the cage strength. The number of heat dissipation holes should be minimized while meeting the requirements for heat dissipation and sewage discharge.

6. An aircraft engine bearing, characterized in that, include: The outer ring (21) as described in any one of claims 1 to 5; Inner circle (22); The rolling element (23) located between the inner ring (22) and the outer ring (21); and The cage (24) contains the rolling element (23) mounted on it and is positioned between the inner ring (22) and the outer ring (21) by the cage (24), and the cage (24) is guided by the outer ring (21).

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