Multifunctional aero-engine bearing sleeve assembly and aero-engine

Abstract

The invention relates to the technical field of aero-engines, in particular to a multifunctional aero-engine bearing sleeve assembly and an aero-engine, the multifunctional aero-engine bearing sleeve assembly comprises a sleeve main body, one end of the sleeve main body is provided with an oil inlet hole, an oil outlet hole and a plurality of air inlet holes, and the other end of the sleeve main body is provided with a plurality of air outlet holes; at least one annular groove is formed in the end, where the air outlet hole is located, of the sleeve body, an oil inlet pipeline, an oil outlet pipeline and a gas pipeline which extend in the axial direction are arranged in the sleeve wall of the sleeve body, and the oil inlet hole, the oil inlet pipeline, the annular groove, the oil outlet pipeline and the oil outlet hole are sequentially communicated; the air inlet, the gas pipeline and the air outlet are sequentially communicated; at least one lubricating oil hole is formed in the end, where the annular groove is located, of the sleeve body, communicates with the annular groove and is used for lubricating a bearing installed at the end, where the annular groove is located, of the sleeve body. Integrated design of the sleeve body, the oil way and the gas way is achieved, and function integration and effective weight reduction are achieved while sufficient structural rigidity and reliability are guaranteed.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, specifically to a multifunctional aero-engine bearing sleeve assembly and an aero-engine. Background Technology

[0002] In existing aero-engines, bearing sleeves are critical components, and their structural design has a significant impact on the overall performance of the engine. Currently, widely used aero-engine bearing sleeves are typically made of a single solid structure and manufactured through machining. However, this traditional solid bearing sleeve structure has significant shortcomings in practical applications.

[0003] First, due to structural limitations, traditional solid bearing sleeves typically lack integrated oil or air supply channels. Therefore, when an engine requires lubrication or cooling air passages in the bearing area, an additional welding or assembly of a separate piping system is often necessary outside the bearing sleeve. This external piping not only increases structural complexity and the number of parts, but also, due to limitations in welding or connection processes, is prone to potential leakage risks at the connection interfaces. This could affect the sealing reliability and long-term stability of the entire engine's oil or air passages, posing a threat to the engine's safe operation.

[0004] Secondly, traditional solid bearing sleeves, in order to meet the stringent requirements for support stiffness under high-speed, heavy-load engine conditions, often require large cross-sectional dimensions and wall thicknesses, resulting in a significant weight. In the field of aero-engines, reducing structural weight is one of the key ways to improve the engine's thrust-to-weight ratio and enhance the aircraft's fuel economy and maneuverability. The substantial weight of solid bearing sleeves undoubtedly becomes a disadvantage, hindering further optimization of the overall engine performance. Summary of the Invention

[0005] To address the shortcomings of existing aero-engine bearing sleeves, this invention provides a multifunctional aero-engine bearing sleeve assembly and aero-engine, integrating the oil inlet pipe, oil outlet pipe, and gas pipe into the sleeve body's cylinder wall. This achieves an integrated design of the sleeve body, oil passage, and gas passage, ensuring sufficient structural rigidity and reliability while achieving functional integration and effective weight reduction.

[0006] The technical solution provided by this invention is as follows: a multifunctional aero-engine bearing sleeve assembly, comprising a hollow sleeve body, one end of which is provided with an oil inlet, an oil outlet, and a plurality of air inlets, and the inner wall of the other end of the sleeve body is provided with a plurality of air outlets; at least one annular groove is provided in the sleeve wall at the end where the air outlets are located, and an axially extending oil inlet pipe, oil outlet pipe, and gas pipe are provided in the sleeve wall, wherein the oil inlet, oil inlet pipe, annular groove, oil outlet pipe, and oil outlet are sequentially connected; the air inlets, gas pipes, and air outlets are sequentially connected; at least one lubricating hole is provided at the end of the sleeve body where the annular groove is located, and the lubricating hole is connected to the annular groove, the lubricating hole being used to lubricate the bearing installed at the end of the sleeve body where the annular groove is located.

[0007] Optionally, it also includes a squirrel-cage elastic support, which includes a support ring, a bearing mounting ring, and a connecting folding plate. The support ring and the bearing mounting ring are fixedly connected by the connecting folding plate, so that the squirrel-cage elastic support forms a folded structure and there is a first gap between the support ring and the bearing mounting ring. The inner side of the bearing mounting ring is used for assembly with the outer ring of the bearing. A limiting part is fixedly provided on the sleeve body. The limiting part is located at one end of the sleeve body where the air inlet is located. The limiting part is inserted into the first gap. There is a second gap between the limiting part and the inner wall of the opening of the sleeve body. The support ring is inserted into the second gap.

[0008] Optionally, the sleeve body is provided with a first branch oil hole, which is located at the end of the sleeve body where the oil inlet is located; the sleeve body has a first branch oil passage extending axially in its cylinder wall; the sleeve body has a second branch oil hole at the end opposite to the first branch oil hole, which penetrates the interior and exterior of the sleeve body; the first branch oil hole, the first branch oil passage, and the second branch oil hole are sequentially connected; the limiting part has a second branch oil passage connected to the first branch oil passage, and the limiting part has an oil film hole on the side facing the bearing mounting ring; there is an annular gap between the limiting part and the bearing mounting ring; the annular gap, the oil film hole, and the second branch oil passage are connected to the first branch oil passage so that an oil film is formed in the annular gap.

[0009] Optionally, the width of the annular gap is 0.1 to 0.2 mm.

[0010] Optionally, the second branch oil hole is inclined so that the opening of the second branch oil hole inside the sleeve body faces the bearing installed at the end of the annular groove of the sleeve body.

[0011] Optionally, the support ring is provided with cavities evenly distributed along its circumference, and the cavities form ribs.

[0012] Optionally, the dimensions of the oil inlet and oil outlet are larger than the dimensions of the air inlet, and the dimensions of the oil inlet pipe and oil outlet pipe are larger than the dimensions of the gas pipe.

[0013] Optionally, reinforcing ribs are provided in the communication path between the oil inlet hole and the oil inlet pipeline, and / or in the communication path between the oil outlet hole and the oil outlet pipeline.

[0014] Optionally, 15 to 20 gas pipelines are provided, and the gas pipelines are evenly distributed circumferentially in the cylinder wall of the sleeve body.

[0015] An aircraft engine, comprising the aforementioned multi-functional aircraft engine bearing sleeve assembly.

[0016] Compared with the prior art, the technical solution provided by this invention has the following advantages: In view of the shortcomings of existing aero-engine bearing sleeves, this invention integrates the oil inlet pipe, oil outlet pipe and gas pipe into the cylinder wall of the sleeve body, realizing the integrated design of the sleeve body, oil circuit and gas circuit, while ensuring sufficient structural rigidity and reliability, achieving functional integration and effective weight reduction. Attached Figure Description

[0017] Figure 1 This is one of the structural schematic diagrams of the multifunctional aero-engine bearing sleeve assembly proposed in the embodiments of the present invention.

[0018] Figure 2 This is the second structural schematic diagram of the multifunctional aero-engine bearing sleeve assembly proposed in an embodiment of the present invention.

[0019] Figure 3 This is a front view of the multifunctional aero-engine bearing sleeve assembly proposed in an embodiment of the present invention.

[0020] Figure 4 for Figure 3 A cross-sectional view along the AA direction.

[0021] Figure 5 for Figure 3 A cross-sectional view along the BB direction.

[0022] Figure 6 for Figure 5 Enlarged diagram of point C in the middle.

[0023] Figure 7 This is a schematic diagram of the structure of the squirrel cage elastic support proposed in an embodiment of the present invention. Detailed Implementation

[0024] To further understand the content of this invention, a detailed description of the invention will be provided in conjunction with the accompanying drawings and embodiments.

[0025] The present application will now be described in further detail with reference to the accompanying drawings and embodiments. It is understood that the specific embodiments described herein are merely illustrative of the invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, only the parts relevant to the invention are shown in the accompanying drawings. The terms "first," "second," etc., used in this invention are for the convenience of describing the technical solutions of the invention and have no specific limiting effect; they are all general terms and do not constitute a limitation on the technical solutions of the invention. It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of this application can be combined with each other. In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the invention and simplifying the description, not to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. In addition, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances. Multiple technical solutions in the same embodiment, as well as multiple technical solutions in different embodiments, can be arranged and combined to form new technical solutions that do not contradict or conflict, all of which are within the scope of protection claimed by this invention.

[0026] Example 1 Combined with appendix Figure 1 To be continued Figure 7 This embodiment proposes a multifunctional aero-engine bearing sleeve assembly, including a hollow sleeve body 1. One end of the sleeve body 1 is provided with an oil inlet 101, an oil outlet 102 and several air inlets 103, and the inner wall of the other end of the sleeve body 1 is provided with several air outlets 104.

[0027] At least one annular groove 110 is provided in the cylinder wall at one end where the air outlet 104 is located. An oil inlet pipe 111, an oil outlet pipe 112, and a gas pipe 113 extending along the axial direction are provided in the cylinder wall of the sleeve body 1. The oil inlet 101, the oil inlet pipe 111, the annular groove 110, the oil outlet pipe 112, and the oil outlet 102 are connected in sequence. The air inlet 103, the gas pipe 113, and the air outlet 104 are connected in sequence.

[0028] At least one lubricating hole 105 is provided at one end of the annular groove 110 of the sleeve body 1. The lubricating hole 105 communicates with the annular groove 110 and is used to lubricate the bearing installed at one end of the annular groove 110 of the sleeve body 1.

[0029] The multifunctional aero-engine bearing sleeve assembly of this embodiment is used to assemble bearings. Generally, bearings are embedded in both ends of the sleeve body 1, as shown in the attached figure. Figure 4 As shown, the oil inlet 101 is defined as the front or end portion of the sleeve body 1, where a front bearing is installed. Correspondingly, a rear bearing is installed at the other end of the sleeve body 1. In this embodiment, the lubricating oil hole 105 is used to lubricate the rear bearing.

[0030] Clearly, this embodiment integrates the oil passage formed by the sequential connection of the oil inlet 101, oil inlet pipe 111, annular groove 110, oil outlet pipe 112, and oil outlet 102, and the air passage formed by the sequential connection of the air inlet 103, air pipe 113, and air outlet 104 onto the sleeve body 1. This achieves an integrated design of the sleeve body 1, the oil passage, and the air passage, allowing the sleeve body 1 to function as both an oil passage and an air passage in addition to assembling bearings, thus forming a multifunctional sleeve body 1. Furthermore, since no external additional welding pipes are required, the impact of pipe welding processes on the sealing performance of the engine's oil and air passages is avoided.

[0031] Meanwhile, the oil inlet 101, oil inlet pipe 111, annular groove 110, oil outlet pipe 112, oil outlet 102, air inlet 103, gas pipe 113, and air outlet 104 significantly reduce the weight of the sleeve body 1. Thus, the multi-functional aero-engine bearing sleeve assembly achieves functional integration and effective weight reduction while ensuring sufficient structural rigidity and reliability. In this embodiment, the sleeve body 1 is preferably manufactured using additive manufacturing (3D printing).

[0032] For multi-functional aero-engine bearing sleeve assemblies, with attachment Figures 1 to 4Taking the illustrated embodiment as an example, the sleeve body 1 is respectively provided with an oil inlet pipe 111 and an oil outlet pipe 112, and is equipped with a corresponding number of oil inlet holes 101 and oil outlet holes 102. At least one annular groove 110 is provided; in this embodiment, four annular grooves 110 are provided. There are generally 15 to 20 gas pipes 113, which are evenly distributed circumferentially within the sleeve body 1. In this embodiment, 17 gas pipes are provided, each with a corresponding number of air inlet holes 103 and air outlet holes 104. In both embodiments, the dimensions of the oil inlet holes 101 and oil outlet holes 102 are larger than the dimensions of the air inlet holes 103, and the dimensions of the oil inlet pipes 111 and oil outlet pipes 112 are larger than the dimensions of the gas pipes 113. That is, the dimensions of the oil inlet pipes 111 and oil outlet pipes 112 (with cross-sectional area as a reference) are relatively larger than the dimensions of the gas pipes 113 to meet the flow requirements of gas and fuel.

[0033] The multi-functional aero-engine bearing sleeve assembly of this embodiment is mainly used in aero-engines such as micro turbojet engines. Taking a micro turbojet engine as an example, it generally uses pure fuel lubrication. (See attached...) Figure 4 In the illustrated embodiment, the opening direction of the oil inlet 101 faces the annular groove 110, while the opening direction of the oil outlet 102 faces away from the annular groove 110. The opening of the air inlet 103 also faces the annular groove 110, while the opening direction of the oil outlet 102 faces away from the oil inlet 101 and towards the bearing installed at one end of the sleeve body 1 where the annular groove 110 is located, thereby adapting to the layout of a micro turbojet engine.

[0034] In this embodiment, the multi-functional aero-engine bearing sleeve assembly operates as follows: fuel first enters through the oil inlet 101 at the front of the sleeve body 1, flows through the oil inlet pipe 111, and reaches the annular groove 110 located at the rear of the sleeve body 1. The position of the annular groove 110 corresponds to the position of the rear bearing. Fuel fills the annular groove 110 and flows within it to reduce the temperature of the rear bearing before flowing to the oil outlet pipe 112. Thus, most of the fuel returns to the front of the sleeve body 1 through the oil outlet pipe 112 and continues to enter the combustion chamber for combustion through the oil outlet 102. Simultaneously, since the rear end of the sleeve body 1 is provided with an oil lubrication hole 105 communicating with the annular groove 110, some fuel can also be sprayed out from the oil lubrication hole 105 to lubricate the rear bearing.

[0035] In the above process, since the annular groove 110 is arranged near the rear bearing, it has a certain cooling effect on the rear bearing, which can improve the bearing life. Furthermore, since the fuel will carry away the heat of the rear bearing, the fuel will be further heated. The relatively high fuel temperature will help improve the combustion efficiency of the fuel entering the combustion chamber.

[0036] In a preferred embodiment, the phase difference between the oil inlet hole 101 and the oil outlet hole 102 is 180°. Correspondingly, the phase difference between the oil inlet pipe 111 and the oil outlet pipe 112 is also set to 180°. This allows the fuel to pass fully through the annular groove 110, carrying away the heat from the rear bearing and ensuring that the fuel is fully heated for subsequent combustion.

[0037] Furthermore, in this embodiment, the gas flow process of the multi-functional aero-engine bearing sleeve assembly is as follows: since the bearing is located outside the combustion chamber, the radiant heat from the combustion in the combustion chamber will also cause the rear bearing temperature to be significantly higher. In this embodiment, the high-pressure air introduced from the compressor outlet through the air inlet 103 flows out through the gas pipeline 113 and the air outlet 104 to cool the rear bearing.

[0038] As can be seen from the actual situation, the lubricating oil for the rear bearing cannot achieve effective splash lubrication without air mixing. However, in this embodiment, high-pressure gas released by the compressor is introduced through the air inlet 103, gas pipeline 113 and air outlet 104, which can be mixed with the lubricating oil of the rear bearing, thereby improving the lubrication efficiency of the rear bearing.

[0039] In addition, the high-pressure air ejected through the exhaust port has another function: a portion of the air continues to pass through the gaps in the sprockets of the subsequent aero-engine, blowing cool air onto the turbine disk, reducing the temperature and stress level of the turbine disk, thereby increasing the service life of the turbine disk and thus increasing the reliability of the aero-engine.

[0040] In aero-engine design, the critical rotor speed is calculated to determine whether a flexible support is needed at the front bearing position. When a flexible support is required, the multi-functional aero-engine bearing sleeve assembly is an integral assembly that includes the flexible support. In one embodiment, a squirrel-cage flexible support 2 is provided inside the multi-functional aero-engine bearing sleeve assembly. The squirrel-cage flexible support 2 includes a support ring 20, a bearing mounting ring 21, and a connecting folding plate 22. The support ring 20 and the bearing mounting ring 21 are fixedly connected by the connecting folding plate 22, so that the squirrel-cage flexible support 2 forms a folded structure, and a first gap 231 exists between the support ring 20 and the bearing mounting ring 21. The inner side of the bearing mounting ring 21 is used for assembly with the outer ring of the bearing. A limiting part 12 is fixedly provided on the sleeve body 1. The limiting part 12 is located at one end where the air inlet 103 of the sleeve body 1 is located. The limiting part 12 is inserted into the first gap 231. A second gap 232 exists between the limiting part 12 and the inner wall of the opening of the sleeve body 1. The support ring 20 is inserted into the second gap 232.

[0041] In this implementation, the squirrel-cage elastic support 2 adopts a folded-back structure and is assembled with the limiter for assembling the bearing. This ensures the support stiffness without increasing the length of the support position, making the multi-functional aero-engine bearing sleeve assembly a compact assembly structure.

[0042] A multi-functional aero-engine bearing sleeve assembly is used in aero-engines. The sleeve body 1 is equipped with a rotor via bearings at the front and rear ends, and the rotor will vibrate during operation. To address this vibration problem, in a further embodiment, the sleeve body 1 is provided with a first branch oil hole 130, which is located at the end of the sleeve body 1 where the oil inlet 101 is located; a first branch oil passage 131 extending axially is provided in the sleeve body 1; a second branch oil hole 132 is provided at the end of the sleeve body 1 opposite to the first branch oil hole 130, and the second branch oil hole 132 penetrates the interior and exterior of the sleeve body 1; the first branch oil hole 130, the first branch oil passage 131, and the second branch oil hole 132 are sequentially connected. The limiting section 12 is provided with a second branch oil passage 121 that communicates with the first branch oil passage 131. An oil film hole 122 is provided on the side of the limiting section 12 facing the bearing mounting ring 21. An annular gap 123 exists between the limiting section 12 and the bearing mounting ring 21. The annular gap 123, the oil film hole 122, and the second branch oil passage 121 communicate with the first branch oil passage 131, so that an oil film is formed within the annular gap 123. Based on this embodiment, a damping effect can be generated by the oil film to reduce rotor vibration during operation.

[0043] The working principle of this implementation is as follows: When the aircraft engine is operating, a portion of the fuel flows through the first branch oil hole 130, the first branch oil passage 131, and the second branch oil passage 121 to the oil film hole 122 and enters the annular gap 123, thereby filling the annular gap 123 and forming an oil film. The width of the annular gap 123 is typically 0.1–0.2 mm, and the corresponding oil film thickness is also 0.1–0.2 mm. When the bearing whirls with the rotor, the outer ring of the bearing periodically squeezes the oil film in the annular gap 123, and the oil film produces a damping effect, thereby reducing rotor vibration during operation. Furthermore, in this embodiment, the second branch oil hole 132 penetrates both the interior and exterior of the sleeve body 1, and is used to guide fuel to the outside for subsequent combustion or lubrication of other components.

[0044] In a further embodiment, the second branch oil hole 132 is inclined so that the opening of the second branch oil hole 132 inside the sleeve body 1 faces the bearing (i.e., the rear bearing) installed at the end where the annular groove 110 of the sleeve body 1 is located. Therefore, the temperature of the rear bearing can be further reduced by the fuel injected through the second branch oil hole 132, and the fuel injected through the second branch oil hole 132 can also achieve oil lubrication of the rear bearing.

[0045] In a preferred embodiment, the support ring 20 of the squirrel-cage elastic support 2 has cavities 201 evenly distributed circumferentially, and ribs 202 are formed between the cavities 201. Therefore, the stiffness of the squirrel-cage elastic support 2 can be adjusted during the design phase by changing the width of the ribs 202 to alter the size of the cavities 201. Preferably, the roots of the ribs 202 are rounded to ensure a smooth transition at the corners of the cavities 201.

[0046] As described above, the dimensions (with reference to cross-sectional area) of the oil inlet pipe 111 and the oil outlet pipe 112 are relatively larger than those of the gas pipe 113. To ensure the strength of the sleeve body 1, in a preferred embodiment, reinforcing ribs 140 are provided in the communication path between the oil inlet hole 101 and the oil inlet pipe 111, and / or in the communication path between the oil outlet hole 102 and the oil outlet pipe 112. Similarly, reinforcing ribs 140 can also be provided in the communication path between the aforementioned first branch oil hole 130 and the first branch oil passage 131 to ensure the structural strength around the fuel flow path.

[0047] Example 2 Combined with appendix Figure 1 To be continued Figure 7 This embodiment proposes an aero-engine that includes the multifunctional aero-engine bearing sleeve assembly described in the technical solution of Embodiment 1.

[0048] The present invention and its embodiments have been described above illustratively. This description is not restrictive, and the figures shown are only one embodiment of the present invention; the actual structure is not limited thereto. Therefore, if those skilled in the art are inspired by this description and design similar structures and embodiments without departing from the spirit of the present invention, such designs should fall within the protection scope of the present invention.

Claims

1. A multifunctional aircraft engine bearing sleeve assembly, characterized in that, It includes a hollow sleeve body (1), one end of which is provided with an oil inlet (101), an oil outlet (102) and several air inlets (103), and the inner wall of the other end of the sleeve body (1) is provided with several air outlets (104). At least one annular groove (110) is provided in the cylinder wall at one end of the sleeve body (1) where the air outlet (104) is located. An oil inlet pipe (111), an oil outlet pipe (112), and a gas pipe (113) extending along the axial direction are provided in the cylinder wall of the sleeve body (1). The oil inlet (101), oil inlet pipe (111), annular groove (110), oil outlet pipe (112), and oil outlet (102) are connected in sequence. The air inlet (103), gas pipe (113), and air outlet (104) are connected in sequence. At least one lubricating hole (105) is provided at one end of the sleeve body (1) where the annular groove (110) is located. The lubricating hole (105) communicates with the annular groove (110) and is used to lubricate the bearing installed at one end of the sleeve body (1) where the annular groove (110) is located.

2. The multifunctional aero-engine bearing sleeve assembly according to claim 1, characterized in that, It also includes a squirrel cage elastic support (2), which includes a support ring (20), a bearing mounting ring (21) and a connecting fold plate (22). The support ring (20) and the bearing mounting ring (21) are fixedly connected by the connecting fold plate (22) so that the squirrel cage elastic support (2) forms a folded structure and a first gap (231) exists between the support ring (20) and the bearing mounting ring (21). The inner side of the bearing mounting ring (21) is used for assembly with the outer ring of the bearing. A limiting part (12) is fixedly provided on the sleeve body (1). The limiting part (12) is located at one end of the sleeve body (1) where the air inlet (103) is located. The limiting part (12) is inserted into the first gap (231). There is a second gap (232) between the limiting part (12) and the inner wall of the opening of the sleeve body (1). The support ring (20) is inserted into the second gap (232).

3. A multifunctional aero-engine bearing sleeve assembly according to claim 2, characterized in that, The sleeve body (1) is provided with a first branch oil hole (130), which is located at the end of the sleeve body (1) where the oil inlet (101) is located; the sleeve body (1) is provided with a first branch oil passage (131) extending axially in the sleeve wall; the sleeve body (1) is provided with a second branch oil hole (132) at the end opposite to the first branch oil hole (130), which penetrates the interior and exterior of the sleeve body (1); the first branch oil hole (130), the first branch oil passage (131), and the second branch oil hole (132) are connected in sequence; The limiting part (12) is provided with a second branch oil passage (121) that communicates with the first branch oil passage (131). The limiting part (12) is provided with an oil film hole (122) on the side facing the bearing mounting ring (21). There is an annular gap (123) between the limiting part (12) and the bearing mounting ring (21). The annular gap (123), the oil film hole (122), and the second branch oil passage (121) are connected to the first branch oil passage (131) so that an oil film is formed in the annular gap (123).

4. A multifunctional aero-engine bearing sleeve assembly according to claim 3, characterized in that, The width of the annular gap (123) is 0.1 to 0.2 mm.

5. A multifunctional aero-engine bearing sleeve assembly according to claim 3, characterized in that, The second branch oil hole (132) is inclined so that the second branch oil hole (132) is located inside the sleeve body (1) and faces the bearing installed at the end of the sleeve body (1) where the annular groove (110) is located.

6. A multifunctional aero-engine bearing sleeve assembly according to claim 2, characterized in that, The support ring (20) has cavities (201) evenly arranged along the circumference, and the cavities (201) form ribs (202).

7. A multifunctional aero-engine bearing sleeve assembly according to claim 1, characterized in that, The dimensions of the oil inlet (101) and oil outlet (102) are larger than the dimensions of the air inlet (103), and the dimensions of the oil inlet pipe (111) and oil outlet pipe (112) are larger than the dimensions of the gas pipe (113).

8. A multifunctional aero-engine bearing sleeve assembly according to claim 1 or 7, characterized in that, A reinforcing rib (140) is provided in the communication path between the oil inlet hole (101) and the oil inlet pipeline (111), and / or in the communication path between the oil outlet hole (102) and the oil outlet pipeline (112).

9. A multifunctional aero-engine bearing sleeve assembly according to claim 1, characterized in that, There are 15 to 20 gas pipelines (113), which are evenly distributed circumferentially in the cylinder wall of the sleeve body (1).

10. An aircraft engine, characterized in that, Includes a multi-functional aircraft engine bearing sleeve assembly as described in any one of claims 1-9.

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