Aerospace engine blade end intelligent milling device

Abstract

The invention discloses an airspace engine blade end intelligent milling device, and relates to the technical field of intelligent machinery manufacturing, the airspace engine blade end intelligent milling device comprises a base, the top of the base is provided with a machine tool, one side of the machine tool is provided with a rotating shaft, and one side of the rotating shaft is provided with a vacuum adsorption mechanism. Therefore, it is guaranteed that the adsorption position of the aero-engine blade on the adsorption piece is the centermost 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 strips and clamp and lock the adsorption piece, and the clamping blocks can be clamped and locked when the connecting disc, the adsorption piece and the aero-engine blade are driven by the subsequent rotating shaft to rotate together for milling. Therefore, the problem that a certain position of the blade sinks and deforms due to larger pressure caused by non-uniform weight distribution on the left and right due to the problem of center-of-gravity shift of the blade of the aero-engine is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of intelligent mechanical manufacturing, and in particular to an intelligent milling device for the end of an aerospace engine blade. Background Art

[0002] There is a very important part in the aircraft engine, which is the engine blades. These blades are equivalent to the cylinders in the car engine. It can be said that the safety and reliability of the engine are mainly reflected in these blades. An intelligent milling device for the ends of fan blades described in the patent application with announcement number CN113290389A is intended to solve the problem that after the fan blades are formed, their ends are relatively rough and cannot be completely fitted and installed, and their ends need to be post-processed and milled. It includes a vehicle body that can move autonomously after driving, a frame is vertically installed on the upper end of the vehicle body, and a vertically arranged circular chassis is installed on the side of the frame facing away from the cab, and the side wall edge of the circular chassis facing away from the frame is fixedly installed with nested outer circular rails and inner circular rails, and an annular milling base is rotatably installed in the annular track formed between the outer circular rail and the inner circular rail, and a plurality of milling cutters extending from the annular track are installed on the side wall of the annular milling base. The present invention is particularly suitable for post-processing of the ends of fan blades to ensure the stable installation of fan blades, and has high social use value and application prospects; When clamping and rotating aircraft blades, there are a series of problems that may cause the blades to deform. Due to the large size and thin thickness of aircraft blades, this structural characteristic makes them relatively fragile in terms of force stability. Even more problematic is that during the clamping process, the blades are likely to have an uneven weight distribution on the left and right, that is, the left side is heavier and the right side is lighter. This unbalanced weight distribution, over a long period of time, will cause the left side of the blade to sink and deform due to the greater pressure. The precision requirements of aircraft engine blades are very high, so any deformation will lead to a decrease in the efficiency of the aircraft engine. Summary of the Invention

[0003] In view of the deficiencies in the prior art, the present invention provides an intelligent milling device for the end of an aerospace engine blade, which achieves the purpose of solving the above-mentioned problems.

[0004] To achieve the above objectives, the present invention is implemented through the following technical solutions: an intelligent milling device for the end of an aerospace engine blade, comprising a base, a machine tool is arranged on the top of the base, a rotating shaft is arranged on one side of the machine tool, and a vacuum adsorption mechanism is arranged on one side of the rotating shaft; The vacuum adsorption mechanism comprises: A vacuum pump having a circular block structure, wherein one side of the vacuum pump is fixedly connected to one end of the rotating shaft, the other side of the vacuum pump is fixedly connected to a connecting disk, and the right side of the connecting disk is fixedly connected to an adsorption member; 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, and the first bearing ring is used to make the adsorption component and the connecting disk rotate relative to each other.

[0005] Preferably, the inner wall of the adsorption member is provided with air holes, and the air holes are distributed in equal proportion and evenly inside the adsorption member.

[0006] Preferably, a connecting hole is opened inside the connecting disk, the inside of the connecting hole is connected with the inside of the air hole, and the inside of the connecting hole is connected with the inside of the vacuum pump.

[0007] Preferably, a sliding bar is fixedly connected to the right side of the connecting plate, an electric sliding machine 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 machine.

[0008] Preferably, one side of the clamping block is an arc-shaped surface, and the curvature of the arc-shaped surface on one side of the clamping block is the same as the curvature of the outer wall of the adsorption component.

[0009] Preferably, the arc surface on one side of the clamping block is made of rubber and serves to increase the clamping friction force on the adsorption component.

[0010] Preferably, an air jet mechanism is provided on the outer wall of the connecting disk, and the air jet mechanism includes a connecting ring, and second bearing rings are fixedly connected to both sides of the connecting ring, and the inner wall of the second bearing ring is fixedly connected to the outer wall of the connecting disk.

[0011] Preferably, an air jet ring is fixedly connected to one side of the connecting disk, an air jet groove is provided on the inner wall of the air jet ring, a second bearing ring is fixedly connected to the outer wall of the connecting disk, and a connecting ring is fixedly connected to one side of the second bearing ring.

[0012] Preferably, the top of the connecting ring is fixedly connected to a connecting air pipe, the bottom of the connecting ring is fixedly connected to a counterweight block, the inner wall of the connecting ring is provided with a first annular air groove, and the outer wall of the connecting disk is provided with a second annular air groove.

[0013] Preferably, the interior of the connecting air pipe is communicated with the first annular air groove inside the connecting ring, and the first annular air groove is communicated with the air jet groove inside the air jet ring through the second annular air groove.

[0014] The present invention provides an intelligent milling device for the end of aerospace engine blades, which relates to intelligent manufacturing equipment industry technology and has the following beneficial effects: 1. The present invention provides a vacuum adsorption mechanism to ensure that the adsorption position of the aircraft engine blade on the adsorption member is at the center of its center of gravity. Then, three electric slides are started to drive the clamping blocks to slide on the sliding bar and clamp and lock the adsorption member. When the rotating shaft subsequently drives the connecting disk, the adsorption member and the aircraft engine blade to rotate and mill together, the aircraft engine blade will not have the problem of uneven weight distribution on the left and right due to the problem of gravity center offset, which will cause a certain part of the blade to sink and deform due to greater pressure.

[0015] 2. The present invention provides a vacuum adsorption mechanism to avoid the problem that when entering the rotary milling stage, the center of gravity of the aircraft engine blades constantly changes as the rotation process proceeds. This dynamic center of gravity offset further aggravates the uneven force on the aircraft engine blades, making the blades extremely prone to deformation during the rotary milling process, thereby seriously affecting the processing accuracy and quality of the aircraft engine blades, thereby improving the processing accuracy of the aircraft engine blades.

[0016] 3. The present invention provides a vacuum adsorption mechanism and the automatic rotation of the adsorption part, so that the heavier side of the aircraft engine blade that is vacuum adsorbed can be automatically rotated to the bottom. The staff only needs to reduce the adsorption force of the vacuum pump on the aircraft engine blade through the air hole to push the aircraft engine blade vertically upward, and can quickly and accurately adjust the uneven clamping and adsorption position of the aircraft engine blade, thereby realizing automatic self-inspection, and making it easier to correct its position and ensure the accuracy of the correction.

[0017] 4. The present invention provides an air jet mechanism, which enters the connecting disk through the second annular air groove and is ejected through the air jet groove in the air jet ring on one side of the connecting disk, thereby continuously blowing and cleaning the outer surface of the aircraft engine blade during the milling process, quickly pushing away the metal wire generated during milling, and preventing the milling head from affecting the milling accuracy of the aircraft engine blade due to the presence of the metal wire. At the same time, the opening direction of the air jet ring and the internal air jet groove is an inward inclination, so that the air can flow evenly along the surface of the aircraft engine blade, ensuring the efficiency of blowing and removing the metal wire.

[0018] 5. The present invention provides a toggle mechanism. The greater the force with which the toggle plate is to be toggled to drive the adsorption member and the aircraft engine blade to rotate, the greater the degree of displacement of the aircraft engine blade, and vice versa. Thus, the staff can quickly identify the position distance that needs to be corrected for the aircraft engine blade, and there will be no overcorrection after correction. It also avoids the problem that the staff has difficulty in grasping the correction distance, resulting in time delay and reduced efficiency. Similarly, the toggle of the toggle plate also makes it easier for the staff to manually adjust the joint rotation of the adsorption member and the aircraft engine blade, so as to make it easier to observe the entire outer surface of the aircraft engine blade and facilitate the subsequent related work.

[0019] 6. The present invention provides a toggle mechanism, and by observing the swinging speed of the toggle plate, it can immediately determine the degree of center of gravity offset of the aircraft engine blade. If the aircraft engine blade swings down quickly with gravity when it is just adsorbed on the adsorption part, it means that the aircraft engine blade has a large offset when it is clamped, which can greatly overcome the friction force exerted on the rotation of the adsorption part, and vice versa. Combined with the opening of the scale groove, it can further assist the staff's judgment, improve the staff's accurate judgment of the clamping stability and center position of the aircraft engine blade, and at the same time improve the accuracy of the aircraft engine blade during the rotation milling process, reducing the problem of deformation caused by uneven weight distribution.

[0020] 7. The present invention provides a toggle mechanism. When the toggle plate and the adsorption member rotate on one side of the connecting plate through the first bearing ring, the bristles on one side of the toggle plate can assist in cleaning the jet groove inside the jet ring, thereby ensuring uniform ventilation in the jet groove, avoiding blockage, and ensuring stability during the milling process of the aircraft engine blade. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the structure of the present invention; Figure 2 It is a structural schematic diagram of the rotating shaft of the present invention; Figure 3 The structure of the vacuum adsorption mechanism of the present invention is shown in FIG. Figure 1 ; Figure 4 The structure of the vacuum adsorption mechanism of the present invention is shown in FIG. Figure 2 ; Figure 5 The structure of the vacuum adsorption mechanism of the present invention is shown in FIG. Figure 3 ; Figure 6 The structure of the vacuum adsorption mechanism of the present invention is shown in FIG. Figure 4 ; Figure 7 For the present invention Figure 4 A magnified view of point A; Figure 8 Schematic diagram of the disassembled structure of the jet mechanism of the present invention Figure 1 ; Figure 9 Schematic diagram of the disassembled structure of the jet mechanism of the present invention Figure 2 ; Figure 10 It is a structural schematic diagram of the toggle mechanism of the present invention; Figure 11 The structure of the jet mechanism of the present invention is shown in FIG. Figure 1 ; Figure 12 The structure of the jet mechanism of the present invention is shown in FIG. Figure 2 .

[0022] In the figure: 1. Base; 2. Machine tool; 3. Vacuum adsorption mechanism; 301. Vacuum pump; 302. Connecting plate; 303. Adsorption part; 304. Air hole; 305. Connecting hole; 306. Electric slide; 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; 5. Toggle mechanism; 501. Toggle plate; 502. Weight reduction groove; 503. Brush; 504. Scale groove; 6. Rotating axis; 7. Aircraft engine blade. DETAILED DESCRIPTION

[0023] 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, comprising a base 1, a machine tool 2 is arranged on the top of the base 1, a rotating shaft 6 is arranged on one side of the machine tool 2, and a vacuum adsorption mechanism 3 is arranged on one side of the rotating shaft 6; The vacuum adsorption mechanism 3 includes: 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 disk 302. The right side of the connecting disk 302 is fixedly connected to an adsorption member 303. 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 enable the adsorption member 303 and the connecting disk 302 to rotate relative to each other. During use, the aircraft engine blade 7 to be milled is placed on the side of the adsorption member 303, and then the vacuum pump 301 is started to form a vacuum negative pressure inside the adsorption member 303 on the side of the connecting disk 302, so that the rectangular seat at one end of the aircraft engine blade 7 is vacuum-adsorbed on the adsorption member 303. This clamping method is used to avoid the problem of deformation of the thin aircraft engine blade 7 caused by clamping with traditional clamping members. Then, the milling head is controlled by a designated intelligent robotic arm, and the vacuum pump 301 and the aircraft engine blade 7 are controlled to rotate along with the rotating shaft 6 to complete the milling manufacturing work of the aircraft engine blade 7. Example 2: Please refer to Figure 1-7, based on the first embodiment, the present invention provides a technical solution: currently when entering the rotary milling stage, the situation becomes more complicated. As the rotation process proceeds, the center of gravity of the blade will continue to change. This dynamic center of gravity offset further aggravates the uneven force on the blade, making the blade extremely prone to deformation during the rotary milling process, thereby seriously affecting the processing accuracy and quality of the blade. Therefore, the inner wall of the adsorption part 303 is provided with air holes 304, and the air holes 304 are evenly distributed in proportion inside the adsorption part 303.

[0024] A communication hole 305 is defined inside the connection disk 302 . The interior of the communication hole 305 is communicated with the interior of the air hole 304 , and the interior of the communication hole 305 is communicated with the interior of the vacuum pump 301 .

[0025] A sliding bar 307 is fixedly connected to the right side of the connecting plate 302 , an electric slider 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 slider 306 .

[0026] One side of the clamping block 308 is an arc-shaped surface, and the curvature of the arc-shaped surface on one side of the clamping block 308 is the same as the curvature of the outer wall of the adsorption component 303.

[0027] The arc surface on one side of the clamping block 308 is made of rubber and serves to increase the friction force of clamping the adsorption member 303; When the aircraft engine blade 7 is adsorbed on the adsorption member 303, the adsorption member 303 is rotatably connected to the connecting plate 302 through the first bearing ring 309. Therefore, after the aircraft engine blade 7 is vacuum adsorbed, the aircraft engine blade 7 and the adsorption member 303 will start to rotate together with the center of gravity position of the aircraft engine blade 7. The rotation of the aircraft engine blade 7 adsorbed on the adsorption member 303 is used to judge whether the aircraft engine blade 7 has a center of gravity deviation problem when clamped under the action of vacuum adsorption, so that the staff can adjust the adsorption position of the aircraft engine blade 7 on the adsorption member 303, and finally achieve the aircraft engine blade 7 is vacuum-adsorbed on the adsorption member 303 without causing any part to sink due to the center of gravity, thereby ensuring that the adsorption position of the aircraft engine blade 7 on the adsorption member 303 is at the center of its center of gravity. Then, the three electric slides 306 are activated to drive the clamping blocks 308 to slide on the sliding bars 307 and clamp and lock the adsorption member 303. When the rotating shaft 6 subsequently drives the connecting disk 302, the adsorption member 303 and the aircraft engine blade 7 to rotate and mill together, the aircraft engine blade 7 will not suffer from uneven weight distribution on the left and right due to the problem of gravity center offset, which would cause a part of the blade to sink and deform due to greater pressure. The invention also avoids the problem that the center of gravity of the aero-engine blade 7 constantly changes as the rotation process progresses during the rotary milling stage. This dynamic center of gravity shift further aggravates the uneven force on the aero-engine blade 7, making the blade extremely prone to deformation during the rotary milling process, thereby seriously affecting the processing accuracy and quality of the aero-engine blade 7. The processing accuracy of the aero-engine blade 7 is thereby improved. The automatic rotation of the suction member 303 can automatically rotate the heavier side of the vacuum-adsorbed aircraft engine blade 7 to the lowest position. The operator only needs to reduce the suction force of the vacuum pump 301 on the aircraft engine blade 7 through the air hole 304 to push the aircraft engine blade 7 vertically upward, thereby quickly and accurately adjusting the uneven clamping and adsorption position of the aircraft engine blade 7, thereby achieving automatic self-checking, making it easier to correct its position and ensure the accuracy of the correction. Example 3: Please refer to Figure 1-8 Based on the first and second embodiments, the present invention provides a technical solution: Currently, during the milling process, the metal wire generated is easy to adhere to the surface of the aircraft engine blade. If it is not cleaned in time, it will seriously affect the processing accuracy of the milling head on the blade, resulting in the blade processing quality not meeting the standards.

[0028] Difficulties in judging and correcting blade center of gravity offset: When aircraft engine blades are clamped in vacuum negative pressure, it is difficult to quickly and accurately judge the degree of their center of gravity offset. When adjusting and correcting, staff are prone to overcorrection or inaccurate correction distance, which not only affects the correction efficiency, but may also reduce the blade processing efficiency due to repeated adjustments.

[0029] Difficulty in fully observing the blades: During the milling process, due to the limitations of blade position and angle, it is difficult for workers to fully observe the outer surface of the blades, which is not conducive to timely discovery of potential problems and affects the subsequent development of related work. Therefore, a jet mechanism 4 is provided on the outer wall of the connecting disk 302. The jet mechanism 4 includes a connecting ring 401. The second bearing ring 403 is fixedly connected on 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 disk 302.

[0030] An air jet ring 406 is fixedly connected to one side of the connecting disc 302 , and an air jet groove 407 is provided on the inner wall of the air jet ring 406 . A second bearing ring 403 is fixedly connected to the outer wall of the connecting disc 302 , and a connecting ring 401 is fixedly connected to one side of the second bearing ring 403 .

[0031] 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 disk 302 is provided with a second annular air groove 405 .

[0032] 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 injection groove 407 inside the air injection ring 406 through the second annular air groove 405; The connecting air pipe 402 is connected to the ventilation duct, and the wind passes through the connecting air pipe 402 and the first annular air groove 404 in the connecting ring 401 into the second annular air groove 405 in the second bearing ring 403, and enters the connecting disk 302 through the second annular air groove 405, and is ejected through the jet groove 407 in the jet ring 406 on one side of the connecting disk 302, so that the outer surface of the aircraft engine blade 7 is continuously blown and cleaned during the milling process, and the metal wire generated during milling is quickly pushed away, so as to prevent the milling head from affecting the milling accuracy of the aircraft engine blade 7 due to the presence of the metal wire. At the same time, the opening direction of the jet ring 406 and the internal jet groove 407 is an inward inclination angle, so that the air can flow evenly along the surface of the aircraft engine blade 7, thereby ensuring the efficiency of blowing and removing the metal wire; Example 4: Please refer to Figure 1-12 Based on the first and second embodiments, the present invention provides a technical solution: Currently, there are challenges in determining blade clamping stability and centering: Aeroengine blades are large and thin, making them prone to center-of-gravity shift during clamping. This can cause blade deformation during rotary milling due to uneven weight distribution, impacting machining accuracy. Traditional methods make it difficult to accurately determine the degree of blade center-of-gravity shift, making it difficult to adjust the clamping state in a timely manner to ensure blade clamping stability and centering.

[0033] Problems with jet slot cleaning and ventilation assurance: During the blade milling process, the jet slot inside the jet ring is easily clogged by impurities, affecting the uniformity of ventilation, thereby destroying the stability of the milling process and reducing the blade processing quality.

[0034] Airflow conduction stability issue: During the blade milling process, it is necessary to ensure the stability of the airflow conduction between the connecting ring and the connecting air pipe to ensure the smooth progress of the milling process. Therefore, a toggle mechanism 5 is provided on the outer wall of the adsorption member 303. The toggle mechanism 5 includes a weight-reducing groove 502. One end of the weight-reducing groove 502 is fixedly connected to the outer wall of the adsorption member 303. A toggle plate 501 is provided on the inner wall of the weight-reducing groove 502. A scale groove 504 is provided on the inner wall of the jet ring 406. When the suction member 303 clamps the aircraft engine blade 7 under vacuum negative pressure, the suction member 303 and the aircraft engine blade 7 can be driven to swing by toggling the toggle plate 501. The force of toggling the toggle plate 501 can be used to judge whether the center of gravity offset of the aircraft engine blade 7 being adsorbed is large. The greater the force of toggling the toggle plate 501 to drive the suction member 303 and the aircraft engine blade 7 to rotate, the greater the offset of the aircraft engine blade 7, and vice versa. In this way, the staff can quickly identify the position distance that needs to be corrected for the aircraft engine blade 7, and will not overcorrect after correction. It also avoids the problem that the staff has difficulty in grasping the correction distance, resulting in time delay and reduced efficiency. Similarly, the toggling of the toggle plate 501 also makes it easier for the staff to manually adjust the joint rotation of the suction member 303 and the aircraft engine blade 7, so as to make it easier to observe the entire outer surface of the aircraft engine blade 7 and facilitate the subsequent related work. When the aircraft engine blade 7 is adsorbed on the adsorption part 303, the aircraft engine blade 7 begins to swing downward with its heavier side, driving the adsorption part 303 and the toggle plate 501 to swing together. By observing the swinging speed of the toggle plate 501, the degree of the center of gravity offset of the aircraft engine blade 7 can be judged immediately. If the aircraft engine blade 7 swings down quickly due to gravity when it is just adsorbed on the adsorption part 303, it means that the aircraft engine blade 7 has a large offset when it is clamped, which can greatly overcome the friction force exerted by the rotation of the adsorption part 303. Otherwise, the opposite is true. Combined with the provision of the scale groove 504, it can further assist the judgment of the staff, improve the staff's accurate judgment of the clamping stability and center position of the aircraft engine blade 7, and at the same time improve the accuracy of the aircraft engine blade 7 during the rotation milling process, reducing the problem of deformation caused by uneven weight distribution. At the same time, when the toggle plate 501 and the adsorption member 303 rotate on one side of the connecting plate 302 via the first bearing ring 309, the bristles 503 on one side of the toggle plate 501 can assist in cleaning the air injection groove 407 inside the air injection ring 406, thereby ensuring uniform ventilation in the air injection groove 407 and avoiding blockage, thereby ensuring stability during the milling process of the aircraft engine blade 7; The counterweight 408 at the bottom of the connecting ring 401 ensures that the position of the connecting ring 401 and the connecting air pipe 402 remains stable. The second bearing ring 403 is used to rotate relative to the connecting disk 302 on the outer wall of the connecting disk 302, and air flow is achieved through the first annular air groove 404 and the second annular air groove 405 provided between the connecting ring 401 and the connecting disk 302. After the milling is completed, the negative pressure in the air hole 304 in the adsorption member 303 is released by controlling the vacuum pump 301, and the aircraft engine blade 7 is removed, completing the milling work.

[0035] The above are only preferred specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with this technical field, within the technical scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solutions and inventive concepts of the present invention, should be covered by the scope of protection of the present invention.

Claims

1. An intelligent milling device for the end of an aerospace engine blade, comprising a base (1), a machine tool (2) disposed on the top of the base (1), a rotating shaft (6) disposed on one side of the machine tool (2), and characterized in that: A vacuum adsorption mechanism (3) is provided on one side of the rotating shaft (6); The vacuum adsorption mechanism (3) comprises: A vacuum pump (301), wherein 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 disk (302), and the right side of the connecting disk (302) is fixedly connected to an adsorption member (303); A first bearing ring (309), 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), and the first bearing ring (309) is used to enable the adsorption member (303) and the connecting disk (302) to rotate relative to each other.

2. The intelligent milling device for aerospace engine blade ends according to claim 1, characterized in that: The inner wall of the adsorption member (303) is provided with air holes (304), and the air holes (304) are evenly distributed in equal proportions inside the adsorption member (303).

3. The intelligent milling device for aerospace engine blade ends according to claim 2, characterized in that: A communication hole (305) is provided inside the connection disk (302), the interior of the communication hole (305) is communicated with the interior of the air hole (304), and the interior of the communication hole (305) is communicated with the interior of the vacuum pump (301).

4. The intelligent milling device for aerospace engine blade ends according to claim 3, characterized in that: The right side of the connecting disk (302) is fixedly connected to a sliding bar (307), the outer wall of the sliding bar (307) is slidably connected to an electric slide (306), and one side of the electric slide (306) is fixedly connected to a clamping block (308).

5. The intelligent milling device for aerospace engine blade ends according to claim 4, characterized in that: One side of the clamping block (308) is an arc-shaped surface, and the curvature of the arc-shaped surface on one side of the clamping block (308) is the same as the curvature of the outer wall of the adsorption member (303).

6. The intelligent milling device for aerospace engine blade ends according to claim 5, characterized in that: The arc surface on one side of the clamping block (308) is made of rubber and serves to increase the clamping friction force on the adsorption member (303).

7. The intelligent milling device for aerospace engine blade ends according to claim 6, characterized in that: An air jet mechanism (4) is provided on the outer wall of the connecting disk (302), and the air jet mechanism (4) comprises a connecting ring (401). Second bearing rings (403) are fixedly connected to both sides of the connecting ring (401), and the inner wall of the second bearing ring (403) is fixedly connected to the outer wall of the connecting disk (302).

8. The intelligent milling device for aerospace engine blade ends according to claim 7, characterized in that: An air jet ring (406) is fixedly connected to one side of the connecting disk (302), and an air jet groove (407) is provided on the inner wall of the air jet ring (406). A second bearing ring (403) is fixedly connected to the outer wall of the connecting disk (302), and a connecting ring (401) is fixedly connected to one side of the second bearing ring (403).

9. The intelligent milling device for aerospace engine blade ends according to claim 8, characterized in that: 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 disk (302) is provided with a second annular air groove (405).

10. The intelligent milling device for the end of an aerospace engine blade according to claim 9, characterized in that: The interior of the connecting air pipe (402) is communicated with the first annular air groove (404) inside the connecting ring (401), and the first annular air groove (404) is communicated with the jet groove (407) inside the jet ring (406) through the second annular air groove (405).

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