Intelligent milling device for end of aerospace engine blade

Abstract

The application discloses an intelligent milling device for an aero-engine blade end, and relates to the technical field of intelligent mechanical manufacturing. The vacuum adsorption mechanism is arranged, so that the adsorption position of the aero-engine blade on the adsorption accessory is the most central position of the gravity center of the aero-engine blade, then the three electric sliding machines are started to drive the clamping blocks to slide on the sliding bars and clamp and lock the adsorption accessory, and when the connecting disc, the adsorption accessory and the aero-engine blade are jointly rotated and milled by the rotating shaft, the aero-engine blade cannot be deformed due to the problem of the gravity center deviation, and the problem that the aero-engine blade is sunk and deformed due to the uneven distribution of the left and right weights.

Description

Technical Field

[0001] This invention relates to the field of intelligent mechanical manufacturing technology, specifically to an intelligent milling device for the tip of aerospace engine blades. Background Technology

[0002] One very important part of an aircraft engine is the engine blades. These blades are equivalent to the cylinders in a car engine. It can be said that the safety and reliability of the engine are mainly reflected in these blades.

[0003] A smart milling device for the ends of wind turbine blades, as described in patent application CN113290389A, aims to solve the problem that the ends of wind turbine blades are relatively rough after forming, making complete fitting and installation impossible, and requiring post-processing milling. The device includes a self-propelled vehicle body. A frame is vertically mounted on the upper part of the vehicle body, and a vertically arranged circular chassis is mounted on the side of the frame facing away from the driver's cab. Nested outer and inner circular rails are fixedly mounted on the sidewall edge of the circular chassis facing away from the frame. A ring milling base is rotatably mounted within the annular track formed between the outer and inner circular rails. Multiple milling cutters extending from the annular track are mounted on the sidewall of the ring milling base. This invention is particularly suitable for the post-processing of wind turbine blade ends to ensure stable installation of wind turbine blades, and has high social value and application prospects.

[0004] When clamping and rotating aircraft blades, a series of problems arise that can lead to blade deformation. Due to their large size and thinness, aircraft blades are inherently vulnerable to stress and instability. Even more challenging is the potential for uneven weight distribution during clamping, with the left side heavier than the right. Over time, this imbalance can cause the left side of the blade to sag and deform under greater pressure. Since aircraft engine blades require extremely high precision, any deformation can lead to a decrease in engine efficiency. Summary of the Invention

[0005] To address the shortcomings of existing technologies, this invention provides an intelligent milling device for the ends of aerospace engine blades, thereby solving the aforementioned problems.

[0006] To achieve the above objectives, the present invention is implemented through the following technical solution: an intelligent milling device for the end of an aerospace engine blade, comprising a base, a machine tool disposed on the top of the base, a rotating shaft disposed on one side of the machine tool, and a vacuum adsorption mechanism disposed on one side of the rotating shaft;

[0007] The vacuum adsorption mechanism includes:

[0008] A vacuum pump, which has a circular block structure, is fixedly connected to one end of a rotating shaft on one side, and a connecting plate is fixedly connected to the other side of the vacuum pump. An adsorption element is fixedly connected to the right side of the connecting plate.

[0009] The first bearing ring is a circular ring structure. The left side of the first bearing ring is fixedly connected to the right side of the connecting disk. The inner wall of the first bearing ring is fixedly connected to the outer wall of the adsorption component. The first bearing ring is used to make the adsorption component and the connecting disk rotate relative to each other.

[0010] Preferably, the inner wall of the adsorption element is provided with air holes, and the air holes are distributed proportionally and evenly inside the adsorption element.

[0011] Preferably, the connecting plate has a connecting hole inside, which communicates with the inside of the air hole and the inside of the vacuum pump.

[0012] Preferably, a sliding bar is fixedly connected to the right side of the connecting plate, an electric sliding mechanism is slidably connected to the outer wall of the sliding bar, and a clamping block is fixedly connected to one side of the electric sliding mechanism.

[0013] Preferably, one side of the clamping block is an arc-shaped surface, and the curvature of the arc surface on one side of the clamping block is the same as the curvature of the outer wall of the adsorption component.

[0014] Preferably, the arc surface on one side of the clamping block is made of rubber and serves to increase the frictional force for clamping the adsorption component.

[0015] Preferably, the outer wall of the connecting plate is provided with an air jet mechanism, the air jet mechanism includes a connecting ring, and second bearing rings are fixedly connected to both sides of the connecting ring, the inner wall of the second bearing rings being fixedly connected to the outer wall of the connecting plate.

[0016] Preferably, a jet ring is fixedly connected to one side of the connecting plate, and a jet groove is formed on the inner wall of the jet ring. A second bearing ring is fixedly connected to the outer wall of the connecting plate, and a connecting ring is fixedly connected to one side of the second bearing ring.

[0017] Preferably, a connecting air pipe is fixedly connected to the top of the connecting ring, a counterweight is fixedly connected to the bottom of the connecting ring, a first annular air groove is formed on the inner wall of the connecting ring, and a second annular air groove is formed on the outer wall of the connecting plate.

[0018] Preferably, the inside of the connecting air pipe is connected to the first annular air groove inside the connecting ring, and the first annular air groove is connected to the air groove inside the air jet ring through the second annular air groove.

[0019] This invention provides an intelligent milling device for the tip of aerospace engine blades, relating to intelligent manufacturing equipment industry technology, and has the following beneficial effects:

[0020] 1. This invention uses a vacuum adsorption mechanism to ensure that the adsorption position of the aero-engine blade on the adsorption component is at the center of its center of gravity. Then, three electric sliding mechanisms are activated to drive the clamping block to slide on the sliding bar and clamp and lock the adsorption component. This ensures that when the rotating shaft drives the connecting disk, the adsorption component and the aero-engine blade to rotate and mill together, the aero-engine blade will not have uneven weight distribution due to the center of gravity shift, which would cause the blade to sink and deform due to greater pressure in a certain part.

[0021] 2. By setting up a vacuum adsorption mechanism, this invention avoids the problem that when entering the rotary milling stage, the center of gravity of the aero-engine blades changes continuously as the rotation process proceeds. This dynamic shift in the center of gravity further exacerbates the uneven stress on the aero-engine blades, making the blades prone to deformation during rotary milling, which seriously affects the machining accuracy and quality of the aero-engine blades, thereby improving the machining accuracy of the aero-engine blades.

[0022] 3. By setting up a vacuum adsorption mechanism, the automatic rotation of the adsorption component allows the heavier side of the vacuum-adsorbed aero-engine blade to automatically rotate to the bottom. Operators only need to reduce the adsorption force of the vacuum pump on the aero-engine blade through the air hole to push the aero-engine blade vertically upward, which can quickly and accurately adjust the uneven clamping and adsorption position of the aero-engine blade, thereby realizing automatic self-checking, making it easier to correct its position and ensuring the accuracy of correction.

[0023] 4. This invention, by setting up a jet mechanism, allows air to enter the connecting plate through the second annular air groove and be ejected through the jet groove in the jet ring on one side of the connecting plate. This achieves continuous air blowing and cleaning of the outer surface of the aero-engine blade during the milling process, quickly pushing away the metal wires generated during milling. This prevents the milling head from affecting the milling accuracy of the aero-engine blade due to the presence of metal wires. At the same time, the opening direction of the jet ring and the inner jet groove is at an inward angle, allowing air to flow evenly along the surface of the aero-engine blade, ensuring the efficiency of blowing away metal wires.

[0024] 5. This invention, by setting up a toggle mechanism, allows the adsorption component and the aero-engine blade to rotate with greater force when the toggle plate is moved. The greater the rotation force, the greater the deviation of the aero-engine blade, and vice versa. This enables the staff to quickly identify the position and distance that needs to be corrected for the aero-engine blade, preventing overcorrection after correction. It also avoids the problem of time delays and reduced efficiency caused by the staff's inability to grasp the correction distance. Similarly, the toggle plate also makes it easier for the staff to manually adjust the joint rotation of the adsorption component and the aero-engine blade, making it easier to observe the entire outer surface of the aero-engine blade and facilitate subsequent related work.

[0025] 6. This invention, by setting up a toggle mechanism, allows for immediate assessment of the degree of center-of-gravity shift in aero-engine blades by observing the swing speed of the toggle plate. If the aero-engine blade swings down rapidly under gravity immediately after being attached to the adsorption component, it indicates a significant shift when the blade is clamped, which greatly overcomes the frictional force experienced by the rotating adsorption component. Conversely, the opposite is true. Combined with the opening of the scale groove, this further assists the operator's judgment, improving the operator's accurate judgment of the clamping stability and centering position of the aero-engine blade. It also improves the accuracy of the aero-engine blade during rotary milling, reducing deformation caused by uneven weight distribution.

[0026] 7. By setting up a toggle mechanism, when the toggle plate and the adsorption component rotate on one side of the connecting plate through the first bearing ring, the brush bristles on one side of the toggle plate can assist in cleaning the jet groove inside the jet ring, ensuring uniform airflow in the jet groove, avoiding blockage, and ensuring stability during the milling process of aero-engine blades. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the structure of the present invention;

[0028] Figure 2 This is a schematic diagram of the structure of the rotating shaft of the present invention;

[0029] Figure 3 This is a schematic diagram of the vacuum adsorption mechanism of the present invention. Figure 1 ;

[0030] Figure 4 This is a schematic diagram of the vacuum adsorption mechanism of the present invention. Figure 2 ;

[0031] Figure 5 This is a schematic diagram of the vacuum adsorption mechanism of the present invention. Figure 3 ;

[0032] Figure 6 This is a schematic diagram of the vacuum adsorption mechanism of the present invention. Figure 4 ;

[0033] Figure 7 For the present invention Figure 4 Enlarged view of point A;

[0034] Figure 8 This is a schematic diagram of the disassembly structure of the jet mechanism of the present invention. Figure 1 ;

[0035] Figure 9 This is a schematic diagram of the disassembly structure of the jet mechanism of the present invention. Figure 2 ;

[0036] Figure 10This is a schematic diagram of the actuation mechanism of the present invention;

[0037] Figure 11 This is a schematic diagram of the jet mechanism of the present invention. Figure 1 ;

[0038] Figure 12 This is a schematic diagram of the jet mechanism of the present invention. Figure 2 .

[0039] In the diagram: 1. Base; 2. Machine tool; 3. Vacuum adsorption mechanism; 301. Vacuum pump; 302. Connecting plate; 303. Adsorption component; 304. Air hole; 305. Connecting hole; 306. Electric sliding mechanism; 307. Sliding bar; 308. Clamping block; 309. First bearing ring; 4. Jet mechanism; 401. Connecting ring; 402. Connecting air pipe; 403. Second bearing ring; 404. First annular air groove; 405. Second annular air groove; 406. Jet ring; 407. Jet groove; 408. Counterweight block; 5. Actuating mechanism; 501. Actuating plate; 502. Weight reduction groove; 503. Brush bristles; 504. Scale groove; 6. Rotating shaft; 7. Aircraft engine blade. Detailed Implementation

[0040] Example 1: Please refer to Figure 1-3 The present invention provides a technical solution: an intelligent milling device for the end of an aerospace engine blade, including a base 1, a machine tool 2 on the top of the base 1, a rotating shaft 6 on one side of the machine tool 2, and a vacuum adsorption mechanism 3 on one side of the rotating shaft 6;

[0041] Vacuum adsorption mechanism 3 includes:

[0042] Vacuum pump 301 has a circular block structure. One side of vacuum pump 301 is fixedly connected to one end of rotating shaft 6, and a connecting plate 302 is fixedly connected to the other side of vacuum pump 301. An adsorption component 303 is fixedly connected to the right side of connecting plate 302.

[0043] The first bearing ring 309 is a circular ring structure. The left side of the first bearing ring 309 is fixedly connected to the right side of the connecting disk 302. The inner wall of the first bearing ring 309 is fixedly connected to the outer wall of the adsorption member 303. The first bearing ring 309 is used to make the adsorption member 303 and the connecting disk 302 rotate relative to each other.

[0044] In use, the aero-engine blade 7 to be milled is placed on the side of the adsorption component 303. Then, the vacuum pump 301 is started to create a vacuum negative pressure inside the adsorption component 303 on one side of the connecting plate 302, and the rectangular seat at one end of the aero-engine blade 7 is vacuum adsorbed onto the adsorption component 303. This clamping method is used to avoid the problem of deformation of the thin aero-engine blade 7 caused by traditional clamping. Then, the milling head is controlled by the designated intelligent robotic arm, and the rotation of the vacuum pump 301 and the aero-engine blade 7 is controlled by the rotating shaft 6 to complete the milling manufacturing work of the aero-engine blade 7.

[0045] Example 2: Please refer to Figure 1-7 Based on Embodiment 1, the present invention provides a technical solution: Currently, the situation becomes more complex when entering the rotary milling stage. As the rotation process proceeds, the center of gravity of the blade continuously changes. This dynamic shift in the center of gravity further exacerbates the uneven stress on the blade, making the blade extremely prone to deformation during rotary milling, thus severely affecting the machining accuracy and quality of the blade. Therefore, the inner wall of the adsorption component 303 is provided with air holes 304, which are distributed proportionally and evenly inside the adsorption component 303.

[0046] The connecting plate 302 has a connecting hole 305 inside, which is connected to the air hole 304 and the vacuum pump 301.

[0047] A sliding bar 307 is fixedly connected to the right side of the connecting plate 302. An electric sliding mechanism 306 is slidably connected to the outer wall of the sliding bar 307. A clamping block 308 is fixedly connected to one side of the electric sliding mechanism 306.

[0048] One side of the clamping block 308 is an arc-shaped surface, and the curvature of the arc surface on one side of the clamping block 308 is the same as the curvature of the outer wall of the adsorption component 303.

[0049] The curved surface on one side of the clamping block 308 is made of rubber and serves to increase the clamping friction of the adsorption component 303.

[0050] When the aero-engine blade 7 is adsorbed onto the adsorption member 303, the adsorption member 303 is rotatably connected to the connecting disk 302 via the first bearing ring 309. Therefore, after the aero-engine blade 7 is vacuum adsorbed, the aero-engine blade 7 and the adsorption member 303 will rotate together with the center of gravity of the aero-engine blade 7. By using the rotation of the aero-engine blade 7 adsorbed onto the adsorption member 303, it is possible to determine whether there is a problem of center of gravity shift during the vacuum adsorption of the aero-engine blade 7. Thus, the operator can adjust the adsorption position of the aero-engine blade 7 on the adsorption member 303, ultimately achieving the desired position of the aero-engine blade. 7. Vacuum adsorption on the adsorption component 303 will not cause any part of the aero-engine blade 7 to drop due to the center of gravity, thus ensuring that the adsorption position of the aero-engine blade 7 on the adsorption component 303 is at the center of its center of gravity. Then, the three electric sliding mechanisms 306 are activated to drive the clamping block 308 to slide on the sliding bar 307 and clamp and lock the adsorption component 303. This ensures that when the rotating shaft 6 drives the connecting plate 302, the adsorption component 303 and the aero-engine blade 7 to rotate and mill together, the aero-engine blade 7 will not have uneven weight distribution due to the center of gravity shift, which would cause a part of the blade to sink and deform due to greater pressure.

[0051] This avoids the problem that when entering the rotary milling stage, the center of gravity of the aero-engine blade 7 changes continuously as the rotation process proceeds. This dynamic shift in the center of gravity further exacerbates the uneven stress on the aero-engine blade 7, making the blade extremely prone to deformation during rotary milling, which seriously affects the machining accuracy and quality of the aero-engine blade 7, thereby improving the machining accuracy of the aero-engine blade 7.

[0052] The automatic rotation of the adsorption component 303 allows the heavier side of the vacuum-adsorbed aero-engine blade 7 to automatically rotate to the bottom. The operator only needs to reduce the adsorption force of the vacuum pump 301 on the aero-engine blade 7 through the air hole 304 to push the aero-engine blade 7 vertically upward, which can quickly and accurately adjust the uneven clamping and adsorption position of the aero-engine blade 7, thereby realizing automatic self-checking, making it easier to correct its position and ensure the accuracy of correction.

[0053] Example 3: Please refer to Figure 1-8 Based on Embodiment 1 and Embodiment 2, the present invention provides a technical solution: Currently, during the milling process, the generated metal wires are prone to adhere to the surface of aero-engine blades. If they are not cleaned in time, they will seriously affect the milling head's machining accuracy on the blades, resulting in substandard blade machining quality.

[0054] Challenges in judging and correcting blade center of gravity offset: When aero-engine blades are clamped under vacuum, it is difficult to quickly and accurately judge the degree of their center of gravity offset. When adjusting and correcting, workers are prone to overcorrection or inaccurate judgment of the correction distance, which not only affects the correction efficiency, but may also reduce the blade processing efficiency due to repeated adjustments.

[0055] Challenges in comprehensive blade observation: During the milling process, due to the limitations of the blade position and angle, it is difficult for workers to fully observe the outer surface of the blade, which is not conducive to timely detection of potential problems and affects the subsequent related work. Therefore, an air jet mechanism 4 is provided on the outer wall of the connecting plate 302. The air jet mechanism 4 includes a connecting ring 401, and a second bearing ring 403 is fixedly connected to both sides of the connecting ring 401. The inner wall of the second bearing ring 403 is fixedly connected to the outer wall of the connecting plate 302.

[0056] A jet ring 406 is fixedly connected to one side of the connecting plate 302. A jet groove 407 is provided on the inner wall of the jet ring 406. A second bearing ring 403 is fixedly connected to the outer wall of the connecting plate 302. A connecting ring 401 is fixedly connected to one side of the second bearing ring 403.

[0057] A connecting air pipe 402 is fixedly connected to the top of the connecting ring 401, and a counterweight 408 is fixedly connected to the bottom of the connecting ring 401. A first annular air groove 404 is opened on the inner wall of the connecting ring 401, and a second annular air groove 405 is opened on the outer wall of the connecting plate 302.

[0058] The first annular air groove 404 inside the connecting tube 402 is connected to the first annular air groove 404 inside the connecting ring 401, and the first annular air groove 404 is connected to the jet groove 407 inside the jet ring 406 through the second annular air groove 405.

[0059] The connecting air pipe 402 is connected to the ventilation duct. The air force enters the second annular air groove 405 in the second bearing ring 403 through the connecting air pipe 402 and the first annular air groove 404 in the connecting ring 401. It then enters the connecting plate 302 through the second annular air groove 405 and is ejected through the air groove 407 in the air jet ring 406 on one side of the connecting plate 302. This achieves continuous air blowing and cleaning of the outer surface of the aero-engine blade 7 during the milling process, quickly pushing away the metal wires generated during milling. This prevents the milling head from affecting the milling accuracy of the aero-engine blade 7 due to the presence of metal wires. At the same time, the opening direction of the air jet ring 406 and the inner air groove 407 is inclined inward, so that the air can flow evenly along the surface of the aero-engine blade 7, ensuring the efficiency of air blowing and removing metal wires.

[0060] Example 4: Please refer to Figure 1-12 Based on Embodiment 1 and Embodiment 2, the present invention provides a technical solution:

[0061] Currently, there are challenges in determining the stability and centering position of blade clamping: Aero-engine blades are large and thin, making them prone to center-of-gravity shift during clamping. This causes deformation of the blade during rotary milling due to uneven weight distribution, affecting machining accuracy. Traditional methods struggle to accurately determine the degree of blade center-of-gravity shift in a timely manner, thus failing to adjust the clamping state promptly to ensure blade clamping stability and centering position.

[0062] Issues related to cleaning the jet grooves and ensuring ventilation: During blade milling, the jet grooves inside the jet ring are easily blocked by impurities, affecting the uniformity of ventilation, which in turn disrupts the stability of the milling process and reduces the quality of blade machining.

[0063] Airflow conduction stability issue: During blade milling, it is necessary to ensure the stability of airflow conduction between the connecting ring and the connecting air pipe to ensure the smooth progress of the milling process. Therefore, the outer wall of the adsorption component 303 is provided with a toggle mechanism 5. The toggle mechanism 5 includes a weight reduction groove 502. One end of the weight reduction groove 502 is fixedly connected to the outer wall of the adsorption component 303. The inner wall of the weight reduction groove 502 is provided with a toggle plate 501. The inner wall of the jet ring 406 is provided with a scale groove 504.

[0064] When the adsorption component 303 clamps the aero-engine blade 7 under vacuum negative pressure, the adsorption component 303 and the aero-engine blade 7 can be swayed by moving the actuating plate 501. The force of moving the actuating plate 501 can be used to judge whether the center of gravity of the adsorbed aero-engine blade 7 has shifted significantly. The greater the force of moving the actuating plate 501 to rotate the adsorption component 303 and the aero-engine blade 7, the greater the shift of the aero-engine blade 7, and vice versa. This allows the staff to quickly identify the position and distance that the aero-engine blade 7 needs to be corrected, avoiding overcorrection after correction. It also avoids the problem of time delay and reduced efficiency caused by the staff's inability to grasp the correction distance. Similarly, the movement of the actuating plate 501 also makes it easier for the staff to manually adjust the joint rotation of the adsorption component 303 and the aero-engine blade 7, making it easier to observe the entire outer surface of the aero-engine blade 7 and facilitating subsequent related work.

[0065] When the aero-engine blade 7 is adsorbed onto the adsorption component 303, the aero-engine blade 7 begins to swing downwards with its heavier side, causing the adsorption component 303 and the actuating plate 501 to swing together. By observing the swing speed of the actuating plate 501, the degree of center of gravity shift of the aero-engine blade 7 can be judged immediately. If the aero-engine blade 7 swings downwards quickly with gravity when it is first adsorbed onto the adsorption component 303, it indicates that the aero-engine blade 7 is offset more when clamped, which can greatly overcome the frictional force of the rotation of the adsorption component 303. Conversely, the opposite is true. In combination with the opening of the scale groove 504, it can further assist the operator's judgment, improve the operator's accurate judgment of the clamping stability and centering position of the aero-engine blade 7, and also improve the accuracy of the aero-engine blade 7 during the rotary milling process, reducing the problem of deformation caused by uneven weight distribution.

[0066] At the same time, when the actuating plate 501 and the adsorption component 303 rotate on one side of the connecting plate 302 via the first bearing ring 309, the brush bristles 503 on one side of the actuating plate 501 can assist in cleaning the jet groove 407 inside the jet ring 406, ensuring uniform airflow in the jet groove 407, avoiding blockage, and ensuring stability during the milling process of the aero-engine blade 7.

[0067] The bottom of the connecting ring 401 is stabilized by the counterweight block 408 to ensure that the position of the connecting ring 401 and the connecting air pipe 402 remains unchanged. The second bearing ring 403 rotates relative to the connecting plate 302 on the outer wall of the connecting plate 302. The airflow is conducted through the first annular air groove 404 and the second annular air groove 405 opened between the connecting ring 401 and the connecting plate 302.

[0068] After milling is completed, the negative pressure in the air hole 304 of the adsorption component 303 is released by controlling the vacuum pump 301, and the aero-engine blade 7 is removed, thus completing the milling work.

[0069] The above are merely preferred embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. An intelligent milling device for the tip of an aerospace engine blade, comprising a base (1), a machine tool (2) disposed on the top of the base (1), and a rotating shaft (6) disposed on one side of the machine tool (2), characterized in that: A vacuum adsorption mechanism (3) is provided on one side of the rotating shaft (6); The vacuum adsorption mechanism (3) includes: Vacuum pump (301), the vacuum pump (301) is a circular block structure, one side of the vacuum pump (301) is fixedly connected to one end of the rotating shaft (6), the other side of the vacuum pump (301) is fixedly connected to a connecting plate (302), and an adsorption element (303) is fixedly connected to the right side of the connecting plate (302). The first bearing ring (309) is a circular ring structure. The left side of the first bearing ring (309) is fixedly connected to the right side of the connecting disk (302). The inner wall of the first bearing ring (309) is fixedly connected to the outer wall of the adsorption member (303). The first bearing ring (309) is used to make the adsorption member (303) and the connecting disk (302) rotate relative to each other. The inner wall of the adsorption element (303) is provided with air holes (304), and the air holes (304) are distributed proportionally and evenly inside the adsorption element (303). The connecting plate (302) has a connecting hole (305) inside, which is connected to the air hole (304) and the vacuum pump (301). A sliding bar (307) is fixedly connected to the right side of the connecting plate (302), an electric sliding mechanism (306) is slidably connected to the outer wall of the sliding bar (307), and a clamping block (308) is fixedly connected to one side of the electric sliding mechanism (306). One side of the clamping block (308) is an arc-shaped surface, and the curvature of the arc surface on one side of the clamping block (308) is the same as the curvature of the outer wall of the adsorption component (303). The arc surface on one side of the clamping block (308) is made of rubber and serves to increase the clamping friction on the adsorption component (303); The outer wall of the connecting plate (302) is provided with an air jet mechanism (4), the air jet mechanism (4) includes a connecting ring (401), and a second bearing ring (403) is fixedly connected to both sides of the connecting ring (401). The inner wall of the second bearing ring (403) is fixedly connected to the outer wall of the connecting plate (302). A jet ring (406) is fixedly connected to one side of the connecting plate (302), and a jet groove (407) is provided on the inner wall of the jet ring (406). A second bearing ring (403) is fixedly connected to the outer wall of the connecting plate (302), and a connecting ring (401) is fixedly connected to one side of the second bearing ring (403). The top of the connecting ring (401) is fixedly connected to a connecting air pipe (402), the bottom of the connecting ring (401) is fixedly connected to a counterweight (408), the inner wall of the connecting ring (401) is provided with a first annular air groove (404), and the outer wall of the connecting plate (302) is provided with a second annular air groove (405).

2. The intelligent milling device for the tip of an aerospace engine blade according to claim 1, characterized in that: The interior of the connecting air pipe (402) is connected to the first annular air groove (404) inside the connecting ring (401), and the first annular air groove (404) is connected to the air groove (407) inside the air jet ring (406) through the second annular air groove (405).

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