An aero-engine casing deformation automatic correction device and a correction method

Abstract

The application discloses an automatic correction device for aero-engine casing deformation, which comprises a ring-shaped base, a plurality of bottom fixing assemblies which are equally distributed along the circumferential direction of the ring-shaped base, a vertical rod which is arranged at the center position of the ring-shaped base, and an automatic correction assembly which is rotatably arranged on the vertical rod through a sliding seat and is slidably arranged on the vertical rod in the height direction. The device has a simple overall structure, the sliding seat which moves up and down can correct the casing at multiple positions, the automatic correction device has high automation degree in the whole process, and the working efficiency is greatly improved. The application further provides an automatic correction method for aero-engine casing deformation, which is realized by using the above device, is simple to operate, is automatically operated, and improves the working efficiency.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aero-engine casing detection and processing, and particularly relates to an aero-engine casing deformation automatic correction device and a correction method. BACKGROUND

[0002] An aero-engine is a power core component of an airplane, and an aero-engine casing, as a main force receiving component of the engine, has a significant influence on the aero-engine. The aero-engine casing can be divided into two categories according to the design structure, namely, a ring-shaped casing and a box casing. The material of the aero-engine casing is mainly titanium alloy and nickel-based alloy. When the aero-engine casing cylinder and the mounting edge are welded, the aero-engine casing is prone to deformation due to the thin wall of the aero-engine casing. The deformation of the aero-engine casing is usually corrected by workers knocking the deformed part of the casing. However, this correction method is relatively low in efficiency.

[0003] A Chinese patent with the authorized (announced) number CN103551425B discloses a correction method for a thin-walled titanium alloy welded casing ring-shaped weld seam deformation part. The correction method is performed by using a hot rolling correction device including an upper rolling disc, a lower rolling disc, a pressing mechanism, a power supply and a circuit, and includes the following steps: pressing, power-on heating and rolling. Although the correction method can correct the local bulging deformation of the ring-shaped weld seam of the casing, the position of the upper rolling disc and the lower rolling disc cannot be adjusted, and it is inconvenient to correct multiple positions of the casing. SUMMARY

[0004] To solve the above problems, the application aims to provide an aero-engine casing deformation automatic correction device and a correction method. The device has a simple overall structure, can correct multiple positions of the casing by using a sliding seat moving up and down, has a high degree of automation throughout the process, and greatly improves the work efficiency. The correction method is implemented by using the above device, is simple to operate, and is automatically operated, thereby improving the work efficiency.

[0005] To achieve the above purpose, the application adopts the following technical solutions:

[0006] An aero-engine casing deformation automatic correction device includes a ring-shaped base.

[0007] A plurality of bottom fixing assemblies are evenly distributed along the circumferential direction of the ring-shaped base.

[0008] A vertical rod is arranged at the center position of the ring-shaped base.

[0009] An automatic correction assembly is arranged on the vertical rod through a sliding seat, and the automatic correction assembly is arranged to slide up and down along the height direction of the vertical rod.

[0010] The bottom fixing assembly comprises a fixing rod connected to the annular base at one end, a sliding groove arranged along the length direction of the fixing rod, a sliding frame body slidingly arranged in the sliding groove, and a fixing clamp plate arranged on the sliding frame body; the fixing clamp plate extends upwards above the top of the fixing rod; the bottom of the fixing rod is provided with an anti-static universal wheel.

[0011] A connecting plate for mounting the fixing clamp plate is slidingly arranged in the sliding frame body, the connecting plate penetrates through the opposite two sides of the sliding frame body and extends to be connected with the square plate; a spring is arranged between the square plate and the sliding frame body.

[0012] The other opposite two sides of the sliding frame body extend outwards to the side wall of the fixing rod, and a driving shaft is arranged at the extending end of each side and arranged perpendicularly thereto; a rotating drum is arranged on the driving shaft and in contact with the outer wall of the fixing rod; a first motor for driving the rotating drum to rotate is further arranged on the sliding frame body.

[0013] A groove is arranged in the height direction of the vertical rod, and a guide rod and a lead screw connected with the sliding seat are arranged in the groove respectively; a driving member for driving the sliding seat to slide up and down is arranged at the bottom of the vertical rod.

[0014] The sliding seat is connected with the guide rod and the lead screw through a connecting block; a T-shaped groove and an annular rotating groove are arranged in the sliding seat, and the annular rotating groove is arranged on the two sides of the T-shaped groove.

[0015] The automatic correction assembly comprises a rotating base rod arranged in the T-shaped groove, a driving combination rod connected with the rotating base rod, a connecting shaft connected with the driving combination rod, a correction cylinder connected with the connecting shaft through a support, and an electric wheel arranged in the annular rotating groove; a third motor is arranged on the correction cylinder.

[0016] The automatic correction assembly further comprises a support rod arranged on the rotating base rod; an oil cylinder is arranged at the top of the support rod, a connecting rod and a suction cup are sequentially arranged at the output end of the oil cylinder; an infrared sensor module and a pressure sensor module are arranged on the suction cup.

[0017] A plurality of support frames connected with the vertical rod are arranged in the annular base.

[0018] An automatic correction method for deformation of an aero-engine casing, comprising the following steps:

[0019] S1. Fixing the casing, adjusting the bottom fixing assembly according to the diameter size of one end of the aero-engine casing, and then inserting one end of the casing into the bottom fixing assembly for fixation;

[0020] S2. Driving the sliding seat to move to the uppermost end of the casing to start the work, and driving the automatic correction assembly to move downwards along the vertical rod while rotating circumferentially along the vertical rod;

[0021] S3. When there is a protruding part on the inner wall of the casing, the protruding part is returned to a smooth state by the cooperation of the correcting cylinder and the components connected thereto; when there is a recessed part on the inner wall of the casing, the recessed part is adsorbed to a smooth state by the cooperation of the suction cup and the components connected thereto;

[0022] S4. When the above two states are returned to a smooth state, the automatic correcting assembly continues to work, and in the process of constantly moving downward, simultaneously rotates along the inner wall of the casing to find new recessed or protruding parts, repeats S3, and continues until the entire casing correction is completed.

[0023] Compared with the prior art, the present application has the following advantages:

[0024] 1. The device has a simple overall structure, utilizes a motor to drive the up and down movement of the sliding seat, thereby realizing the correction of multiple positions of the casing, and the correcting cylinder can move horizontally along the length direction of the rotating base rod under the driving of the air cylinder, thereby the position of the correcting cylinder can change according to the change of the inner diameter of the casing, and the degree of automation is high throughout the process, and the work efficiency is greatly improved.

[0025] 2. The module electronic element is used to realize the automatic rotation of the correcting cylinder, automatically corrects the protruding part of the casing, and can control the automatic movement of the suction cup to automatically correct the recessed part of the casing, can cover the entire operation of the inner wall of the casing, and improves the accuracy of correction.

[0026] 3. The movable control fixed clamping plate is provided, the casing is fixed by the fixed clamping plate, the operation is convenient, and the fixed clamping plate can be adjusted to be suitable for the correction of casings of different sizes.

[0027] 4. The anti-static universal wheel is provided to improve the movement performance of the overall device, facilitate movement to different positions in the workshop for correction work, and facilitate use.

[0028] 5. The overall structure is simple, and the operation method is simple. BRIEF DESCRIPTION OF DRAWINGS

[0029] In order to more clearly illustrate the technical solutions in the specific embodiments of the present application, the following will briefly introduce the drawings needed to be used in the embodiment description. Obviously, the drawings described below are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creating any creative labor.

[0030] Figure 1 It is an overall structure schematic diagram of an aviation engine casing deformation automatic correction device in the present application.

[0031] Figure 2 It is a top view structure schematic diagram of an aviation engine casing deformation automatic correction device in the present application

[0032] Figure 3 is Figure 1 enlarged view of B in FIG. 1;

[0033] Figure 4 is Figure 2 enlarged view of C in FIG. 1;

[0034] Figure 5 is a partial perspective view of the bottom fixing assembly;

[0035] Figure 6 is a sectional view of the vertical rod center;

[0036] Figure 7 is Figure 6 enlarged view of D in FIG. 1;

[0037] Figure 8 is Figure 7 enlarged view of E in FIG. 1;

[0038] Figure 9 is Figure 7 enlarged view of F in FIG. 1;

[0039] Figure 10 is Figure 7 enlarged view of F in FIG. 1.

[0040] The drawings show: 1 - annular base, 2 - vertical rod, 3 - automatic correction assembly, 4 - bottom fixing assembly, 5 - sliding seat, 6 - fixed rod, 7 - sliding groove, 8 - sliding frame, 9 - connecting plate, 10 - fixed clamping plate, 11 - square plate, 12 - spring, 13 - drive shaft, 14 - rotating drum, 15, first motor - 16 - anti-static universal wheel, 17 - support frame, 18 - groove, 19 - guide rod, 20 - lead screw, 21 - connecting block, 22 - T-shaped groove, 23 - annular rotating groove, 24 - second motor, 25 - rotating base rod, 26 - electric wheel, 27 - drive combination rod, 28 - air cylinder, 29 - connecting shaft, 30 - support, 31 - correction drum, 32 - third motor, 33 - travel switch, 34 - support rod, 35 - oil cylinder, 36 - connecting rod, 37 - suction cup, 38 - infrared sensor module, 39 - pressure sensor module. DETAILED DESCRIPTION

[0041] The present application will be further described below in conjunction with the drawings and specific embodiments, but should not be understood as limiting the scope of the subject matter described herein to the following embodiments, and any modifications, replacements and changes made according to ordinary technical knowledge and conventional means in the art without departing from the above technical idea of the present application are included in the scope of the present application.

[0042] By way of example Figures 1 to 10An automatic deformation correction device for an aero-engine casing, as described in this invention, Figure 1 As shown, the automatic correction device for deformation of the aero-engine casing includes an annular base 1, and a vertical rod 2 is provided at the center of the annular base 1. The vertical rod 2 is fixed inside the annular base 1 by multiple support frames 17.

[0043] Specifically, for ease of distinction, the support frame 17 is referred to as the first support frame and the second support frame. In this embodiment, three first support frames and three second support frames are provided. The first support frame is located inside the annular base 1, with one end connected to the side wall of the vertical rod 2 and the other end connected to the side wall of the annular base 1. The three first support frames divide the annular base 1 equally.

[0044] Each first support frame is connected to a corresponding second support frame. One end of the second support frame is connected to the first support frame, and the other end is connected to the side wall of the vertical rod 2, forming a triangle with the side wall of the vertical rod 2, the first support frame, and the second support frame. The first and second support frames are provided to ensure the support effect of the vertical rod 2 and prevent it from breaking.

[0045] The bottom fixing component 4 is located on the circumference of the annular base 1. In a preferred embodiment of the present invention, the bottom fixing component 4 is provided in three sets, which are evenly distributed along the circumference of the annular base 1.

[0046] Specifically, the bottom fixing component 4 includes a fixing rod 6 with one end welded to the annular base 1, and an anti-static caster wheel 16 provided at the other end of the fixing rod 6. The anti-static caster wheel 16 is installed at the bottom of the fixing rod 6 by screws.

[0047] The fixed rod 6 is designed as a hollow structure; a sliding groove 7 is provided along the length of the fixed rod 6. Specifically, the sliding groove 7 is provided on the opposite side walls of the fixed rod 6, and a sliding frame 8 is provided in the sliding groove 7, which can move within the sliding groove.

[0048] The sliding frame 8 is a rectangular frame, with one set of opposite sides extending outwards from the opposite side walls of the fixing rod 6. The extended ends of the sliding frame 8 are rotatably connected to a drive shaft 13, which is perpendicular to the sliding frame 8. One end of the drive shaft 13 is fixed with a rotating cylinder 14. Specifically, the rotating cylinder 14 is rotatably connected to the bottom of the sliding frame 8, and two rotating cylinders 14 are provided on each side of the extended ends of the sliding frame 8. That is, in this embodiment, four rotating cylinders are provided at the four corners of the sliding frame 8 and are in contact with the outer walls of the fixing rod 6.

[0049] A motor is also provided at the extended end of one side of the sliding frame 8. Specifically, in this embodiment, two first motors 15 are provided, fixed on the top of the sliding frame 8, and connected to the two rotating drums 14 on that side via drive shafts 13. When the first motor 15 is working, it can drive the drive shaft 13 to rotate. As the drive shaft 13 and the rotating drums 14 rotate, the sliding frame 8 is driven to move along the slide groove 7, adjusted to the required position, and the casing is fixed.

[0050] A connecting plate 9 is slidably connected inside the sliding frame 8, extending through opposite sides of the sliding frame 8. A fixing clamp 10 is provided on the connecting plate 9 at the middle position of the sliding frame 8. Two fixing clamps 10 are symmetrically arranged and used to fix the housing. The fixing clamp 10 extends from the connecting plate 9 towards the top of the fixing rod 6, and its height can be set according to the height of the housing.

[0051] The connecting plate 9 extends through both opposite sides of the sliding frame 8, meaning that the opposite sides of the connecting plate 9 extend outward from the sliding frame 8. A square plate 11 is provided at each extended end of the connecting plate, and a spring 12 is fixedly connected between the square plate 11 and the outer wall of the sliding frame 8. Specifically, the connecting plate 9 and the square plate 11 are arranged on the same straight line and parallel to the center line of the length direction of the fixing rod 6. The springs 12 are symmetrically arranged about the middle of the connecting plate 9.

[0052] The automatic correction component 3 is mounted on the side wall of the vertical rod 2 via a sliding seat 5. The sliding seat 5 can drive the automatic correction component 3 to slide up and down along the height direction of the vertical rod 2, and can also rotate along the circumference of the vertical rod 2.

[0053] The bottom of the vertical rod 2 is also provided with a driving component for driving the sliding seat 5 to slide up and down. Specifically, the driving component includes a second motor 24 connected to the lead screw 20. The second motor 24 is located at the bottom of the vertical rod 2. Driven by the second motor 24, since the lead screw 20 is threadedly connected to the second connecting block, when the lead screw 20 rotates, the second connecting block moves along the lead screw 20, thereby driving the sliding seat 5 to move. In this embodiment, the second motor 24 is a servo motor, which can be controlled to rotate in both directions, thus enabling the sliding seat 5 to move up and down.

[0054] To ensure that the sliding seat 5 can be driven to move along the vertical rod 2, grooves 18 are provided on opposite sides of the side wall of the vertical rod 2. A guide rod 19 is fixed inside one groove 18, and a lead screw 20 is rotatably connected inside the other groove 18. Both the guide rod 19 and the lead screw 20 are arranged along the height direction of the vertical rod 2.

[0055] The sliding seat 5 is provided with connecting blocks 21 that are respectively connected to the guide rod 19 and the lead screw 20. For easy distinction, they are referred to as the first connecting block and the second connecting block. The first connecting block is slidably connected to the guide rod 19, and the second connecting block is threadedly connected to the lead screw 20.

[0056] Inside the sliding seat 5, there is also a T-shaped groove 22, and on both sides of the T-shaped groove 22, there are annular rotating grooves 23.

[0057] Specifically, the automatic correction component 3 includes a rotating base rod 25 connected inside the T-slot 22, with electric wheels 26 rotatably connected to both sides of the rotating base rod 25, and the electric wheels 26 rotating inside the annular rotating groove 23.

[0058] The end of the rotating base rod 25 away from the sliding seat 5 is connected to the drive combination rod 27; specifically, a cylinder 28 is provided inside the rotating base rod 25, and the output end of the cylinder 28 is fixed to the drive combination rod 27; a limit switch 33 is fixed inside the drive combination rod 27, and the limit switch 33 is connected in series with the third motor 32, the second motor 24, and the electric wheel 26.

[0059] The end of the drive combination rod 27 away from the rotating base rod 25 is elastically slidably connected to a connecting shaft 29, and a top contact rod for triggering the limit switch 33 is provided at the connecting shaft 29.

[0060] A bracket 30 is fixed at the end of the coupling 2 away from the drive assembly rod 27. A straightening cylinder 31 is rotatably connected inside the bracket 30. A third motor 32 is connected to the upper end of the straightening cylinder 31.

[0061] The automatic correction assembly 3 also includes a support rod 34 mounted on the rotating base rod 25. A hydraulic cylinder 35 is mounted on the top of the support rod 34. A connecting rod 36 is fixed to the output end of the hydraulic cylinder 35. The hydraulic cylinder 35 and the connecting rod 36 are positioned toward the direction of the correction cylinder 31.

[0062] A suction cup 37 is fixed at the end of the connecting rod 36 away from the oil cylinder 35. An infrared sensor module 38 is embedded in the middle of the suction cup 37. A pressure sensor module 39 is also fixed inside the suction cup 37. Both the infrared sensor module 38 and the pressure sensor module 39 are electrically connected to the oil cylinder 35. The pressure sensor module 39 is also electrically connected to the electric wheel 26.

[0063] The principle of the automatic correction component 3 is as follows: as the correction cylinder 31 rotates, the protruding part is gradually pressed down to a smooth state by the resistance effect of the correction cylinder 31 against the protruding part. The correction cylinder 31 is a roller-shaped structure made of alloy material. As for the correction of the concave part, the infrared sensor module 38 and the pressure sensor work together and are controlled by a microcontroller. The microcontroller control principle in this invention is existing technology and will not be described in detail. The concave part is corrected to a smooth state by coordinating the suction cup 37 to adsorb and then pull it out.

[0064] The present invention discloses an automatic correction method for deformation of an aero-engine casing, wherein the correction is performed by a specific device and includes the following steps:

[0065] S1. Casing fixing: Adjust the bottom fixing component according to the diameter of one end of the aircraft engine casing, and then insert one end of the casing into the bottom fixing component for fixing;

[0066] S2. Drive the sliding block to move to the top of the housing and start the operation. The sliding block drives the automatic correction component to move down the vertical bar while rotating around the vertical bar.

[0067] S3. When there is a protrusion on the inner wall of the casing, the protrusion is returned to a smooth state by the cooperation of the straightening cylinder and the components connected to it; when there is a depression on the inner wall of the casing, the depression is adsorbed to a smooth state by the cooperation of the suction cup and the components connected to it.

[0068] S4. When the above two states return to the smooth state, the automatic correction component continues to work, moving downwards while rotating along the inner wall of the casing to find new depressions or protrusions. Repeat S3 until the entire casing correction is completed.

[0069] Specifically: Based on the diameter of one end of the aircraft engine casing, adjust the position of the sliding frame 8 on each fixing rod 6. The distance between the middle position of the sliding frame 8 and the center of the annular base 1 is 1 / 2 of the diameter of one end of the casing. Insert one end of the casing into the three sets of fixing plates 10 to complete the casing fixing.

[0070] Turn on the second motor 24 to drive the sliding seat 5 to move to the top of the casing and start the operation; at the same time, turn on the electric wheel 26 and the second motor 24, and the sliding seat 5 will move down along the vertical rod 2. The electric wheel 26 drives the rotating base rod 25 to rotate along the sliding seat 5.

[0071] When there is a protrusion on the inner wall of the casing, as the base rod 25 rotates, the protrusion can abut against the straightening cylinder 31. The straightening cylinder 31 then drives the connecting shaft 29 to move, abutting against the limit switch 33 inside the drive combination rod 27. The limit switch 33 controls the second motor 24 to turn off, the sliding seat 5 to stop moving, controls the electric wheel 26 to turn off, the base rod 25 to stop rotating, controls the third motor 32 to turn on, and the third motor 32 drives the straightening cylinder 31 to rotate. As the straightening combination rod and the connecting shaft 29 elastically abut against each other, the protrusion returns to a smooth state.

[0072] When there is a depression on the inner wall of the casing, the infrared sensor module 38 senses a distance exceeding a preset value, triggering an electrical signal. The microcontroller controls the electric wheel 26 to stop rotating, and controls the hydraulic cylinder 35 to extend, bringing the suction cup 37 to the depression. Then, the pressure sensor module 39 on the inner wall of the suction cup 37 triggers an electrical signal, and the microcontroller controls the hydraulic cylinder 35 to retract, allowing the suction cup 37 to suck up the depression until it is smooth.

[0073] When the two states return to a smooth state in the above steps, either the resistance of the limit switch 33 is released, or the infrared sensor module 38 is within the preset value range, the second motor 24 continues to work, the electric wheel 26 continues to work, and during the continuous downward movement, it rotates along the inner wall of the casing to find new depressions or protrusions; until the entire casing is corrected.

[0074] When the diameter of the inner wall of the casing changes, the cylinder 28 can be opened, and the cylinder 28 drives the connecting shaft 29 to move along the rotating base rod 25, thereby adjusting the position of the cover plate straightening cylinder 31 and the suction cup 37 to ensure that they fit against the inner wall of the casing.

[0075] Unless otherwise specified, all structures in this embodiment are made of alloy and can be welded and assembled. The infrared sensor module is model SL621, the pressure sensor module is model FSS1500NS, and the anti-static casters are made of polyurethane with brakes and have anti-static properties. The motor, cylinder, and hydraulic cylinder are all existing technologies.

[0076] The above provides a detailed description of the automatic correction device and method for deformation of an aero-engine casing provided by the present invention. Specific examples have been used to illustrate the structure and working principle of the invention. The descriptions of the embodiments above are only for the purpose of helping to understand the method and core ideas of the present invention. It should be noted that those skilled in the art can make various improvements and modifications to the present invention without departing from its principles, and these improvements and modifications also fall within the scope of protection of the claims of the present invention.

Claims

1. An automatic correction device for deformation of an aircraft engine casing, characterized in that: Includes a ring-shaped base (1); Multiple sets of bottom fixing components (4) are evenly distributed along the circumference of the annular base (1); The vertical rod (2) is located at the center of the annular base (1); The automatic correction component (3) is rotatably mounted on the vertical rod (2) via the sliding seat (5), and the automatic correction component (3) is slidably mounted up and down along the height direction of the vertical rod (2); The bottom fixing assembly (4) includes a fixing rod (6) connected to the annular base (1) at one end, a slide groove (7) provided along the length of the fixing rod (6), a sliding frame (8) slidably provided in the slide groove (7), and a fixing clamp (10) provided on the sliding frame (8); the fixing clamp (10) extends above the top of the fixing rod (6); The sliding seat (5) is provided with a T-shaped groove (22) and an annular rotating groove (23), with the annular rotating groove (23) located on both sides of the T-shaped groove (22); The automatic correction assembly (3) includes a rotating base rod (25) disposed in a T-slot (22), a drive assembly rod (27) connected to the rotating base rod (25), a connecting shaft (29) connected to the drive assembly rod (27), a correction cylinder (31) connected to the connecting shaft (29) via a bracket (30), and an electric wheel (26) disposed in an annular rotating groove (23); a third motor (32) is disposed on the correction cylinder (31); The automatic correction assembly (3) also includes a support rod (34) mounted on the rotating base rod (25); a hydraulic cylinder (35) is mounted on the top of the support rod (34), and a connecting rod (36) and a suction cup (37) are mounted sequentially on the output end of the hydraulic cylinder (35).

2. The automatic deformation correction device for an aero-engine casing according to claim 1, characterized in that: The bottom of the fixing rod (6) is equipped with anti-static casters (16).

3. The automatic deformation correction device for an aero-engine casing according to claim 2, characterized in that: A mounting and fixing clamp (10) and a connecting plate (9) are slidably arranged inside the sliding frame (8). The connecting plate (9) passes through a set of opposite sides of the sliding frame (8) and extends to connect with the square plate (11). A spring (12) is provided between the square plate (11) and the sliding frame (8).

4. The automatic deformation correction device for an aero-engine casing according to claim 3, characterized in that: The other two sides of the sliding frame (8) extend outward from the side wall of the fixed rod (6), and a drive shaft (13) is provided at the extended end of each side, which is perpendicular to the drive shaft (13). A rotating drum (14) is provided on the drive shaft (13) and is in contact with the outer wall of the fixed rod. A first motor (15) for driving the rotating drum (14) to rotate is also provided on the sliding frame (8).

5. The automatic deformation correction device for an aero-engine casing according to claim 1, characterized in that: A groove (18) is provided in the height direction of the vertical rod (2), and a guide rod (19) and a lead screw (20) connected to the sliding seat (5) are respectively provided in the groove (18); a driving component for driving the sliding seat (5) to slide up and down is provided at the bottom of the vertical rod (2).

6. The automatic deformation correction device for an aero-engine casing according to claim 5, characterized in that: The sliding seat (5) is connected to the guide rod (19) and the lead screw (20) respectively via the connecting block (21).

7. The automatic deformation correction device for an aero-engine casing according to claim 1, characterized in that: An infrared sensor module (38) and a pressure sensor module (39) are provided on the suction cup (37).

8. The automatic deformation correction device for an aero-engine casing according to claim 1, characterized in that: Multiple support frames (17) connected to the vertical rod (2) are provided inside the annular base (1).

9. A method using the automatic deformation correction device for an aero-engine casing as described in any one of claims 1-8, characterized in that: Includes the following steps: S1. Casing fixing: Adjust the bottom fixing component (4) according to the diameter of one end of the aircraft engine casing, and then insert one end of the casing into the bottom fixing component (4) for fixing; S2. Drive the sliding block (5) to move to the top of the casing and start the operation. The sliding block (5) drives the automatic correction component (3) to move down along the vertical rod (2) while rotating around the vertical rod (2). S3. When there is a protrusion on the inner wall of the casing, the protrusion is returned to a smooth state by the cooperation of the straightening cylinder (31) and the components connected thereto; when there is a depression on the inner wall of the casing, the depression is attracted to a smooth state by the cooperation of the suction cup (37) and the components connected thereto. S4. When the above two states return to the smooth state, the automatic correction component (3) continues to work. During the continuous downward movement, it rotates along the inner wall of the casing to find new depressions or protrusions. S3 is repeated until the entire casing correction is completed.

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