Aircraft engine cylinder machining device and method

Abstract

The invention belongs to the technical field of engine cylinder machining, and particularly relates to an aircraft engine cylinder machining device and method. The device is reasonable in design, all the components cooperate with one another, and the outer cylinder component is clamped through the outer cylinder clamping and conveying assembly and driven to move to the first butt joint station, the second butt joint station and the welding station; an inner cylinder clamping and positioning assembly arranged at the first butt joint station is used for clamping the inner cylinder component, and the inner cylinder component and the outer cylinder component are located at the butt joint position; a cover plate clamping and positioning assembly arranged at the second butt joint station is used for clamping the cover plate component, and the cover plate component and the outer cylinder component are located at the butt joint position; the welding assembly arranged above the welding station is used for fixing the outer cylinder component and the inner cylinder component in a spot welding mode and then fixing the outer cylinder component and the cover plate component in a full-seam welding mode, in this way, the welding assembly requirement of the combined type air inlet cover cylinder is met, and the combined type air inlet cover cylinder obtained through machining has the advantage of being high in structural strength.

Description

Technical Field

[0001] The present invention belongs to the technical field of engine cylinder machining, and particularly relates to a machining device and method for an aircraft engine cylinder. Background Art

[0002] The advantages of using a combined intake hood cylinder for an aircraft engine are mainly reflected in aspects such as design flexibility, performance optimization, maintenance convenience, reliability improvement, and adaptation to various flight conditions. The following is a detailed analysis: 1) Design flexibility: The combined intake hood cylinder design allows for the flexible selection and combination of different types of engine components according to the specific requirements of the aircraft, such as turbojet engines, ramjet engines, rocket engines, etc. This flexibility enables the aircraft to be optimized for specific missions or flight phases to achieve optimal performance. 2) Performance optimization: By combining different types of engine components, the advantages of each can be fully utilized, such as the high efficiency of turbojet engines at low speeds and high altitudes, and the high thrust of rocket engines at high altitudes, high speeds, and in vacuum environments. This combination can significantly improve the overall performance of the aircraft, including thrust, fuel efficiency, flight speed, etc. 3) Maintenance convenience: The combined intake hood cylinder design usually means that each engine component can be maintained and replaced relatively independently. This not only reduces maintenance costs but also improves maintenance efficiency because a faulty component can be repaired individually without disassembling the entire engine. 4) Reliability improvement: The combined intake hood cylinder improves the reliability of the entire engine system by spreading risks. If a component fails, other components can still continue to operate to ensure the safety of the aircraft. In addition, through redundant design, the reliability of the system can be further enhanced. 5) Adaptation to various flight conditions: The combined intake hood cylinder design enables the aircraft to adapt to various flight conditions, including different altitudes, speeds, temperatures, etc. For example, during takeoff and climb phases, a turbojet engine can be used to provide sufficient thrust; during high-speed cruise, a ramjet engine can be switched to improve fuel efficiency; when rapid acceleration or orbit change is required, a rocket engine can be started. 6) Technology integration and innovation: The combined intake hood cylinder design promotes the integration and innovation between different engine technologies. By integrating the advantages of different technologies, a new type of engine system with superior performance and lower cost can be developed. This technology integration also provides more possibilities for future aircraft design.

[0003] Using a combined intake hood cylinder for an aircraft engine has significant advantages such as design flexibility, performance optimization, maintenance convenience, reliability improvement, and adaptation to various flight conditions. These advantages make the combined intake hood cylinder an important direction for future aircraft engine design, contributing to the continuous progress and development of aircraft technology.

[0004] The existing aircraft engine cylinder processing device has deficiencies in use. Firstly, it cannot meet the rapid welding and assembly requirements of the combined air intake shroud cylinder. Secondly, the combined air intake shroud cylinder processed by it has the problem of unsatisfactory structural strength. Therefore, it is necessary to optimize and improve the existing aircraft engine cylinder processing device. Summary of the Invention

[0005] The purpose of the present invention is to overcome the above problems existing in the traditional technology and provide an aircraft engine cylinder processing device and method.

[0006] To achieve the above technical purposes and reach the above technical effects, the present invention is realized through the following technical solutions:

[0007] The present invention provides an aircraft engine cylinder processing device, including:

[0008] An outer cylinder clamping and conveying assembly, which is used to clamp the outer cylinder component and drive it to move to the first docking station, the second docking station, and the welding station;

[0009] An inner cylinder clamping and positioning assembly, which is arranged at the first docking station and is used to clamp the inner cylinder component and make it in the docking position with the outer cylinder component;

[0010] A cover plate clamping and positioning assembly, which is arranged at the second docking station and is used to clamp the cover plate component and make it in the docking position with the outer cylinder component;

[0011] A welding assembly, which is arranged above the welding station and is used to perform welding and assembly processing on the outer cylinder component, the inner cylinder component, and the cover plate component to obtain a combined air intake shroud cylinder.

[0012] Further, in the above aircraft engine cylinder processing device, an annular cavity is provided inside the outer cylinder component, one end of the annular cavity is an opening, and the cross-section of the annular cavity is semi-elliptical.

[0013] Further, in the above aircraft engine cylinder processing device, the inner cylinder component is composed of an inner cylinder and inner support plates evenly distributed on its outer side in the circumferential direction. A plurality of air guide holes are provided on the inner support plates, and the outer edge shape of the inner support plate matches the shape of the annular cavity of the outer cylinder component.

[0014] Further, in the above aircraft engine cylinder processing device, the cover plate component is composed of an annular cover plate and arc-shaped positioning blocks evenly distributed on one side of it in the circumferential direction. An installation hole is provided in the annular cover plate between adjacent two arc-shaped positioning blocks; the specification of the annular cover plate enables it to fill the tail area after the inner cylinder component is installed in the annular cavity, and the shape of the arc-shaped positioning block matches the shape of the cavity of the inner cylinder.

[0015] Furthermore, in the above-mentioned aircraft engine cylinder body processing device, the outer cylinder clamping and conveying assembly includes a horizontal longitudinal linear guide pair, a vertical seat, an outer cylinder adsorption ring, a driven anti-detachment gear ring, a driving motor, and a driving gear. A vertical seat is installed on the upper side of the slider of the horizontal longitudinal linear guide pair. An outer cylinder adsorption ring with a driven anti-detachment gear ring is movably restricted in the vertical seat. The inner cavity surface of the outer cylinder adsorption ring is evenly distributed with negative pressure adsorption holes. An annular adsorption cavity and a negative pressure pump for providing negative pressure to the annular adsorption cavity are arranged inside the outer cylinder adsorption ring. A driving motor is fixed on the vertical seat, and a driving gear meshing with the driven anti-detachment gear ring is installed at the output end of the driving motor.

[0016] Furthermore, in the above-mentioned aircraft engine cylinder body processing device, the inner cylinder clamping and positioning assembly includes a first horizontal transverse linear guide pair, a first mounting plate, and a first annular suction cup. The slider of the first horizontal transverse linear guide pair is installed with a first annular suction cup for adsorbing the inner cylinder component through the first mounting plate. The central axis of the first annular suction cup coincides with the central axis of the outer cylinder adsorption ring.

[0017] Furthermore, in the above-mentioned aircraft engine cylinder body processing device, the cover plate clamping and positioning assembly includes a second horizontal transverse linear guide pair, a second mounting plate, and a second annular suction cup. The slider of the second horizontal transverse linear guide pair is installed with a second annular suction cup for adsorbing the cover plate component through the second mounting plate. The central axis of the second annular suction cup coincides with the central axis of the outer cylinder adsorption ring.

[0018] Furthermore, in the above-mentioned aircraft engine cylinder body processing device, the welding assembly includes a substrate, a lifting push rod, a mounting seat, and a laser welding head. A lifting push rod is installed on the lower side of the substrate. The movable end of the lifting push rod is fixed with a mounting seat, and a laser welding head with an adjustable inclination angle to the horizontal plane is installed in the mounting seat.

[0019] Furthermore, in the above-mentioned aircraft engine cylinder body processing device, positioning shafts penetrating through the mounting seat are symmetrically arranged on both sides of the laser welding head. An installation cavity facilitating the up-and-down swing of the laser welding head is arranged inside the mounting seat. An inclination adjustment push rod is installed at the rear end of the mounting seat, and the movable end of the inclination adjustment push rod is hinged to the tail end of the laser welding head through a connecting plate.

[0020] The present invention also provides a method for processing an aircraft engine cylinder body, which is realized based on the above-mentioned aircraft engine cylinder body processing device, and includes the following steps:

[0021] S1. Use the inner cylinder clamping and positioning component to clamp the inner cylinder component and convey it to the first docking station. Use the outer cylinder clamping and conveying component to clamp the outer cylinder component. The outer cylinder clamping and conveying component drives the outer cylinder component to move to the first docking station, so that the inner cylinder component is inserted into the inside of the outer cylinder component. The inner cylinder clamping and positioning component releases the locking of the inner cylinder component. Then, the outer cylinder clamping and conveying component drives the outer cylinder component to move to the welding station, and use the welding component to spot-weld and fix the inner support plate of the inner cylinder component and the inner wall of the annular cavity of the outer cylinder component.

[0022] S2. Use the cover plate clamping and positioning component to clamp the cover plate component and convey it to the second docking station. The outer cylinder clamping and conveying component drives the outer cylinder component to move to the second docking station, so that the cover plate component is inserted into the inside of the outer cylinder component. The cover plate clamping and positioning component releases the locking of the cover plate component. Then, the outer cylinder clamping and conveying component drives the outer cylinder component to move to the welding station, and use the welding component to perform full-seam welding and fix the annular cover plate of the cover plate component and the inner wall of the annular cavity of the outer cylinder component.

[0023] The beneficial effects of the present invention are:

[0024] The structure of the present invention is reasonably designed. It mainly consists of an outer cylinder clamping and conveying component, an inner cylinder clamping and positioning component, a cover plate clamping and positioning component, and a welding component. Each component cooperates with each other. Use the outer cylinder clamping and conveying component to clamp the outer cylinder component and drive it to move to the first docking station, the second docking station, and the welding station; use the inner cylinder clamping and positioning component arranged at the first docking station to clamp the inner cylinder component and make it in the docking position with the outer cylinder component; use the cover plate clamping and positioning component arranged at the second docking station to clamp the cover plate component and make it in the docking position with the outer cylinder component; use the welding component arranged above the welding station to first spot-weld and fix the outer cylinder component and the inner cylinder component, and then perform full-seam welding and fix the outer cylinder component and the cover plate component. In this way, the welding and assembly requirements of the combined air intake hood cylinder are met, and the processed combined air intake hood cylinder has the advantage of high structural strength.

[0025] Of course, it is not necessary for any product implementing the present invention to achieve all the above advantages simultaneously. Description of the Drawings

[0026] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0027] Figure 1 It is a structural schematic diagram of the processing device for the aircraft engine cylinder of the present invention;

[0028] Figure 2 Structural schematic diagram of the combined air intake hood cylinder in the present invention;

[0029] Figure 3 Front view schematic diagram of the outer cylinder member in the present invention;

[0030] Figure 4 Left view schematic diagram of the outer cylinder member in the present invention;

[0031] Figure 5 Right view schematic diagram of the outer cylinder member in the present invention;

[0032] Figure 6 Front view schematic diagram of the inner cylinder member in the present invention;

[0033] Figure 7 Left view schematic diagram of the inner cylinder member in the present invention;

[0034] Figure 8 Right view schematic diagram of the inner cylinder member in the present invention;

[0035] Figure 9 Front view schematic diagram of the cover plate member in the present invention;

[0036] Figure 10 Left view schematic diagram of the cover plate member in the present invention;

[0037] Figure 11 Structural schematic diagram of the outer cylinder clamping and conveying assembly in the present invention;

[0038] Figure 12 Structural schematic diagram of the inner cylinder clamping and positioning assembly in the present invention;

[0039] Figure 13 Structural schematic diagram of the cover plate clamping and positioning assembly in the present invention;

[0040] Figure 14 Structural schematic diagram of the welding assembly in the present invention;

[0041] In the drawings, the reference numerals of each component are as follows:

[0042] 1 - Outer cylinder clamping and conveying assembly, 101 - Horizontal longitudinal linear guide pair, 102 - Standing seat, 103 - Outer cylinder adsorption ring, 104 - Driven anti - detachment gear ring, 105 - Driving motor, 106 - Driving gear;

[0043] 2 - Inner cylinder clamping and positioning assembly, 201 - First horizontal transverse linear guide pair, 202 - First mounting plate, 203 - First annular suction cup;

[0044] 3 - Cover plate clamping and positioning assembly, 301 - Second horizontal transverse linear guide pair, 302 - Second mounting plate, 303 - Second annular suction cup;

[0045] 4 - Welding assembly, 401 - Substrate, 402 - Lifting push rod, 403 - Mounting seat, 404 - Laser welding head, 405 - Positioning shaft, 406 - Tilting adjustment push rod, 407 - Connecting plate;

[0046] 5 - Outer cylinder member;

[0047] 6 - Inner cylinder member, 601 - Inner cylinder, 602 - Inner support plate, 603 - Air guide hole;

[0048] 7 - Cover plate member, 701 - Ring - shaped cover plate, 702 - Arc - shaped positioning block, 703 - Mounting hole. Detailed implementation mode

[0049] 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. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without making creative efforts belong to the scope of protection of the present invention.

[0050] Embodiment 1

[0051] As Figure 1 shown, this embodiment provides a processing device for an aircraft engine cylinder body, including an outer cylinder clamping and conveying assembly 1, an inner cylinder clamping and positioning assembly 2, a cover plate clamping and positioning assembly 3, and a welding assembly 4. The outer cylinder clamping and conveying assembly 1 is used to clamp the outer cylinder member 5 and drive it to move to the first docking station, the second docking station, and the welding station. The inner cylinder clamping and positioning assembly 2 is arranged at the first docking station and is used to clamp the inner cylinder member 6 and make it in a docking position with the outer cylinder member 5. The cover plate clamping and positioning assembly 3 is arranged at the second docking station and is used to clamp the cover plate member 7 and make it in a docking position with the outer cylinder member 5. The welding assembly 4 is arranged above the welding station and is used to perform welding and assembly processing on the outer cylinder member 5, the inner cylinder member 6, and the cover plate member 7 to obtain a combined intake hood cylinder body as Figure 2 shown.

[0052] As Figures 3 - 5 shown, an annular cavity is provided inside the outer cylinder member 5, one end of the annular cavity is an opening, and the cross - section of the annular cavity is semi - elliptical.

[0053] As Figures 6 - 8 shown, the inner cylinder member 6 is composed of an inner cylinder 601 and inner support plates 602 evenly distributed on its outer side along the circumferential direction. A plurality of air guide holes 603 are opened on the inner support plates 602, and the outer edge shape of the inner support plates 602 matches the shape of the annular cavity of the outer cylinder member 5.

[0054] As Figures 9 - 10As shown in the figure, the cover plate component 7 is composed of an annular cover plate 701 and arc-shaped positioning blocks 702 evenly distributed circumferentially on one side thereof. An installation hole 703 is provided in the annular cover plate 701 between two adjacent arc-shaped positioning blocks 702. The specification of the annular cover plate 701 enables it to fill the tail area after the inner cylinder component 6 is installed in the annular cavity, and the shape of the arc-shaped positioning block 702 matches the cavity shape of the inner cylinder 601.

[0055] As Figure 11 shown in the figure, the outer cylinder clamping and conveying assembly 1 includes a horizontal and longitudinal linear guide pair 101, a vertical seat 102, an outer cylinder adsorption ring 103, a driven anti-disengagement gear ring 104, a driving motor 105, and a driving gear 106. A vertical seat 102 is installed on the upper side of the slider of the horizontal and longitudinal linear guide pair 101, and an outer cylinder adsorption ring 103 with a driven anti-disengagement gear ring 104 is movably restricted in the vertical seat 102. Negative pressure adsorption holes are evenly distributed on the inner cavity surface of the outer cylinder adsorption ring 103. An annular adsorption cavity and a negative pressure pump for providing negative pressure to the annular adsorption cavity are provided inside the outer cylinder adsorption ring 103, and the negative pressure adsorption holes are communicated with the annular adsorption cavity. A driving motor 105 is fixed on the vertical seat 102, and a driving gear 106 meshing with the driven anti-disengagement gear ring 104 is installed at the output end of the driving motor 105.

[0056] In the outer cylinder clamping and conveying assembly 1, the function of the horizontal and longitudinal linear guide pair 101 is to drive the vertical seat 102 and the outer cylinder adsorption ring 103 to perform horizontal and longitudinal reciprocating linear displacements. The function of the outer cylinder adsorption ring 103 is to be able to adsorb and clamp the outer cylinder component 5. The driving motor 105 drives the driven anti-disengagement gear ring 104 to rotate through the driving gear 106, and then drives the outer cylinder adsorption ring 103 and the outer cylinder component 5 adsorbed thereon to rotate.

[0057] As Figure 12 shown in the figure, the inner cylinder clamping and positioning assembly 2 includes a first horizontal and transverse linear guide pair 201, a first mounting plate 202, and a first annular suction cup 203. A first annular suction cup 203 for adsorbing the inner cylinder component 6 is installed on the slider of the first horizontal and transverse linear guide pair 201 through the first mounting plate 202, and the central axis of the first annular suction cup 203 coincides with the central axis of the outer cylinder adsorption ring 103.

[0058] In the inner cylinder clamping and positioning assembly 2, the first horizontal and transverse linear guide pair 201 is used to drive the inner cylinder component 6 adsorbed by the first mounting plate 202 and the first annular suction cup 203 to perform horizontal and transverse linear displacements. After the feeding operation of the inner cylinder component 6 is completed, the first mounting plate 202 can be timely removed from the first docking position to avoid affecting the horizontal and longitudinal linear displacement of the vertical seat 102.

[0059] As Figure 13As shown in the figure, the cover plate clamping and positioning assembly 3 includes a second horizontal transverse linear guide pair 301, a second mounting plate 302, and a second annular suction cup 303. The slider of the second horizontal transverse linear guide pair 301 is equipped with a second annular suction cup 303 for adsorbing the cover plate member 7 through the second mounting plate 302. The central axis of the second annular suction cup 303 coincides with the central axis of the outer cylinder suction ring 103.

[0060] In the cover plate clamping and positioning assembly 3, the second horizontal transverse linear guide pair 301 is used to drive the cover plate member 7 adsorbed by the second mounting plate 302 and the second annular suction cup 303 to perform horizontal transverse linear displacement. After the feeding operation of the cover plate member 7 is completed, the second mounting plate 302 can be removed from the second docking position in time to avoid affecting the horizontal longitudinal linear displacement of the upright seat 102.

[0061] As Figure 14 shown in the figure, the welding assembly 4 includes a substrate 401, a lifting push rod 402, a mounting seat 403, and a laser welding head 404. The lower side of the substrate 401 is equipped with a lifting push rod 402. The movable end of the lifting push rod 402 is fixed with a mounting seat 403. A laser welding head 404 with an adjustable inclination angle to the horizontal plane is installed in the mounting seat 403. Positioning shafts 405 penetrating the mounting seat 403 are symmetrically arranged on both sides of the laser welding head 404. An installation cavity for the laser welding head 404 to swing up and down is provided inside the mounting seat 403. A tilting push rod 406 is installed at the rear end of the mounting seat 403. The movable end of the tilting push rod 406 is hinged to the tail end of the laser welding head 404 through a connecting plate 407.

[0062] In the welding assembly 4, the lifting push rod 402 is used to adjust the height of the laser welding head 404. The outer cylinder clamping and conveying assembly 1 is used to drive the welding object to displace relative to the laser welding head 404 to adjust the welding distance. The tilting push rod 406 is used to adjust the inclination angle of the laser welding head 404, so as to meet the welding requirements in this way.

[0063] This embodiment also provides a method for machining an aircraft engine cylinder body, including the following steps:

[0064] S1. Use the inner cylinder clamping and positioning component 2 to clamp the inner cylinder member 6 and convey it to the first docking station. Use the outer cylinder clamping and conveying component 1 to clamp the outer cylinder member 5. The outer cylinder clamping and conveying component 1 drives the outer cylinder member 5 to move to the first docking station, so that the inner cylinder member 6 is inserted into the inside of the outer cylinder member 5. The inner cylinder clamping and positioning component 2 releases the locking of the inner cylinder member 6. Then, the outer cylinder clamping and conveying component 1 drives the outer cylinder member 5 to move to the welding station. Use the welding component 4 to spot-weld and fix the inner support plate 602 of the inner cylinder member 6 and the inner wall of the annular cavity of the outer cylinder member 5. During spot welding, after each spot welding operation of an inner support plate 602 is completed, use the outer cylinder clamping and conveying component 1 to drive the outer cylinder member 5 to rotate a certain angle, and this angle is equal to the central angle between two adjacent inner support plates 602. At this time, the spot welding operation of the next inner support plate 602 can be carried out until all the spot welding operations of the inner support plates 602 are completed.

[0065] S2. Use the cover plate clamping and positioning component 3 to clamp the cover plate member 7 and convey it to the second docking station. The outer cylinder clamping and conveying component 1 drives the outer cylinder member 5 to move to the second docking station, so that the cover plate member 7 is inserted into the inside of the outer cylinder member 5. The cover plate clamping and positioning component 3 releases the locking of the cover plate member 7. Then, the outer cylinder clamping and conveying component 1 drives the outer cylinder member 5 to move to the welding station. Use the welding component 4 to perform full-seam welding and fix the annular cover plate 701 of the cover plate member 7 and the inner wall of the annular cavity of the outer cylinder member 5.

[0066] A specific application of this embodiment is as follows: This device mainly consists of an outer cylinder clamping and conveying component 1, an inner cylinder clamping and positioning component 2, a cover plate clamping and positioning component 3, and a welding component 4. Each component cooperates with each other. Use the outer cylinder clamping and conveying component 1 to clamp the outer cylinder member 5 and drive it to move to the first docking station, the second docking station, and the welding station. Use the inner cylinder clamping and positioning component 2 arranged at the first docking station to clamp the inner cylinder member 6 and make it in the docking position with the outer cylinder member 5. Use the cover plate clamping and positioning component 3 arranged at the second docking station to clamp the cover plate member 7 and make it in the docking position with the outer cylinder member 5. Use the welding component 4 arranged above the welding station to first perform spot welding and fix the outer cylinder member 5 and the inner cylinder member 6, and then perform full-seam welding and fix the outer cylinder member 5 and the cover plate member 7. In this way, the welding and assembly requirements of the combined air intake hood cylinder are met, and the processed combined air intake hood cylinder has the advantage of high structural strength.

[0067] The preferred embodiments of the present invention disclosed above are only used to help illustrate the present invention. The preferred embodiments do not describe all the details in detail, nor do they limit the invention to only specific embodiments. Obviously, many modifications and variations can be made according to the content of this specification. These embodiments are selected and specifically described in this specification in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can well understand and utilize the present invention. The present invention is only limited by the claims and their full scope and equivalents.

Claims

1. An aircraft engine cylinder body processing device, characterized in that Comprising: An outer cylinder clamping and conveying assembly for clamping an outer cylinder member and driving it to move to a first docking station, a second docking station, and a welding station; An inner cylinder clamping and positioning assembly disposed at the first docking station for clamping an inner cylinder member and bringing it into a docking position with the outer cylinder member; A cover plate clamping and positioning assembly disposed at the second docking station for clamping a cover plate member and bringing it into a docking position with the outer cylinder member; A welding assembly disposed above the welding station for welding and assembling the outer cylinder member, the inner cylinder member, and the cover plate member to obtain a combined intake hood cylinder body.

2. The aircraft engine cylinder body processing device according to claim 1, wherein, An annular cavity is provided inside the outer cylinder member, one end of the annular cavity is open, and the cross-section of the annular cavity is semi-elliptical.

3. The aircraft engine cylinder machining device according to claim 2, characterized in that, The inner cylinder member is composed of an inner cylinder and inner support plates evenly distributed circumferentially on its outer side. A plurality of air guide holes are provided on the inner support plates, and the shape of the outer edge of the inner support plates matches the shape of the annular cavity of the outer cylinder member.

4. The aircraft engine cylinder body processing device according to claim 3, characterized in that, The cover plate member is composed of an annular cover plate and arc-shaped positioning blocks evenly distributed circumferentially on one side thereof. An installation hole is provided in the annular cover plate between adjacent arc-shaped positioning blocks; the specification of the annular cover plate enables it to fill the tail area after the inner cylinder member is installed in the annular cavity, and the shape of the arc-shaped positioning blocks matches the shape of the cavity of the inner cylinder.

5. The aircraft engine cylinder machining device according to claim 4, characterized in that, The outer cylinder clamping and conveying assembly includes a horizontal longitudinal linear guide pair, a vertical seat, an outer cylinder adsorption ring, a driven anti-detachment gear ring, a driving motor, and a driving gear. A vertical seat is installed on the upper side of the slider of the horizontal longitudinal linear guide pair. An outer cylinder adsorption ring with a driven anti-detachment gear ring is movably restricted in the vertical seat. Negative pressure adsorption holes are evenly distributed on the inner cavity surface of the outer cylinder adsorption ring. An annular adsorption cavity and a negative pressure pump for providing negative pressure to the annular adsorption cavity are provided inside the outer cylinder adsorption ring. A driving motor is fixed on the vertical seat, and a driving gear meshing with the driven anti-detachment gear ring is installed at the output end of the driving motor.

6. The aircraft engine cylinder machining device according to claim 5, wherein The inner cylinder clamping and positioning assembly includes a first horizontal transverse linear guide pair, a first mounting plate, and a first annular suction cup. A first annular suction cup for adsorbing the inner cylinder member is installed on the slider of the first horizontal transverse linear guide pair through the first mounting plate. The central axis of the first annular suction cup coincides with the central axis of the outer cylinder adsorption ring.

7. The aircraft engine cylinder machining device according to claim 6, characterized in that, The cover plate clamping and positioning assembly includes a second horizontal transverse linear guide pair, a second mounting plate, and a second annular suction cup. A second annular suction cup for adsorbing the cover plate member is installed on the slider of the second horizontal transverse linear guide pair through the second mounting plate. The central axis of the second annular suction cup coincides with the central axis of the outer cylinder adsorption ring.

8. The aircraft engine cylinder machining device according to claim 7, characterized in that, The welding assembly includes a substrate, a lifting push rod, a mounting seat, and a laser welding head. A lifting push rod is installed on the lower side of the substrate, and a mounting seat is fixed at the movable end of the lifting push rod. A laser welding head with an adjustable inclination angle with respect to the horizontal plane is installed in the mounting seat.

9. The aircraft engine cylinder processing device according to claim 8, wherein, On both sides of the laser welding head, positioning shafts penetrating through the mounting seat are symmetrically provided. An installation cavity facilitating the up-and-down swing of the laser welding head is provided inside the mounting seat. A tilting push rod is installed at the rear end of the mounting seat, and the movable end of the tilting push rod is hinged to the tail end of the laser welding head through a connecting plate.

10. A method for machining an aircraft engine cylinder body, implemented based on the aircraft engine cylinder body machining device described in claim 9, characterized in that, It includes the following steps: S1. Use the inner cylinder clamping and positioning component to clamp the inner cylinder component and convey it to the first docking station. Use the outer cylinder clamping and conveying component to clamp the outer cylinder component. The outer cylinder clamping and conveying component drives the outer cylinder component to move to the first docking station, so that the inner cylinder component is inserted into the inner part of the outer cylinder component. The inner cylinder clamping and positioning component releases the locking of the inner cylinder component. Then, the outer cylinder clamping and conveying component drives the outer cylinder component to move to the welding station, and use the welding component to spot-weld and fix the inner support plate of the inner cylinder component and the inner wall of the annular cavity of the outer cylinder component. S2. Use the cover plate clamping and positioning component to clamp the cover plate component and convey it to the second docking station. The outer cylinder clamping and conveying component drives the outer cylinder component to move to the second docking station, so that the cover plate component is inserted into the inner part of the outer cylinder component. The cover plate clamping and positioning component releases the locking of the cover plate component. Then, the outer cylinder clamping and conveying component drives the outer cylinder component to move to the welding station, and use the welding component to fully weld and fix the annular cover plate of the cover plate component and the inner wall of the annular cavity of the outer cylinder component.

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