A multi-station clamping table for off-wing repair of an aeroengine blade

Abstract

A multi-station clamping table for aero-engine blade off-site repair, comprising a machine table, a lifting mechanism and a sliding mechanism; the machine table is provided with a plurality of stations, and the stations are provided with blade positioning mechanisms. The blade positioning mechanism comprises a rotating table rotatably arranged on the machine table, a pair of low-position clamp assemblies symmetrically arranged on the table surface of the rotating table, and a high-position clamp assembly arranged on the sliding mechanism; the rotating table is symmetrically provided with a pair of assembly through slots in the front-rear direction, and the assembly through slots penetrate the circumferential surface of the rotating table towards the front side; the low-position clamp assembly comprises a rotating table clamp seat, a low-position U-shaped clamp and a pair of cam locking pieces; the rotating table clamp seat is installed in the assembly through slot, the low-position U-shaped clamp is arranged on the rotating table clamp seat, and the cam locking pieces are arranged at both ends of the rotating table clamp seat; the cam locking piece comprises a cam shaft. The clamping table adjusts the turning direction and position of the rotating table clamp seat and adjusts the spacing of the U-shaped clamp to make the clamping position of the U-shaped clamp suitable for the curvature of the engine blade, thereby ensuring more stable clamping.

Description

Technical Field

[0001] This invention relates to the field of aircraft ground maintenance technology, and in particular to a multi-station clamping table for off-site repair of aero-engine blades. Background Technology

[0002] During scheduled aircraft maintenance, if corrosion or wear is found on the engine fan blades, the engine blades must be removed for off-site grinding. Previously, grinding of engine blades typically involved manually clamping or using specialized auxiliary fixtures to hold the blades in place. However, these methods had several drawbacks:

[0003] 1. If the fixing fixture is not compatible with the curvature or arc of the engine blade, forced clamping can easily cause scratches on the engine blade;

[0004] 2. Some auxiliary fixtures specially made based on experience are only suitable for a certain type of engine blade and are not suitable for blades of different types and sizes, resulting in poor versatility.

[0005] 3. Manual clamping can easily lead to fatigue, resulting in insufficient force and causing the blades to slip out and be damaged;

[0006] 4. The entire grinding process requires the cooperation of multiple people. Some people are dedicated to supporting the engine blades, while others are dedicated to grinding the blades. This results in high labor costs, is time-consuming and labor-intensive, and has low efficiency.

[0007] 5. Due to the high workload, it is basically a multi-person collaboration. After polishing one piece, the next piece is polished. It is impossible to work in parallel. When there are many repairs, the task takes a long time to complete and the efficiency is low. Summary of the Invention

[0008] To address the shortcomings of existing technologies, this invention provides a multi-station clamping table for off-site repair of aero-engine blades, thereby overcoming the deficiencies in existing technologies.

[0009] To achieve the above objectives, the present invention provides the following technical solution:

[0010] A multi-station clamping platform for off-site repair of aero-engine blades includes a platform, a lifting mechanism disposed on one side of the platform, and a carriage mechanism disposed above the platform and driven by the lifting mechanism; the platform is provided with several repair stations, each repair station being provided with a blade positioning mechanism, characterized in that:

[0011] The blade positioning mechanism includes a rotary table rotatably mounted on the machine base, a pair of low-position clamping assemblies symmetrically mounted on the rotary table surface, and a high-position clamping assembly mounted on the carriage mechanism.

[0012] The rotary table has a pair of symmetrically arranged assembly slots in the front and back directions, and the assembly slots penetrate the circumference of the rotary table from the front side.

[0013] The low-position clamping assembly includes a turntable clamp, a low-position U-shaped clamp, and a pair of cam locking components; the turntable clamp is installed in the assembly through slot, the low-position U-shaped clamp is located in the center of the top surface of the turntable clamp, and the cam locking components are respectively located at both ends of the turntable clamp.

[0014] The turntable clamp includes an integrally formed I-shaped tabletop clamp, a bottom clamp, and a cylindrical connecting rod fixedly connected between the tabletop clamp and the bottom clamp. The length of the cylindrical connecting rod is adapted to the thickness of the turntable, and the diameter of the cylindrical connecting rod is adapted to the width of the assembly slot of the turntable.

[0015] The cam locking component includes a camshaft, which is horizontally rotatably mounted on one end of the table clamp, and a cam handle is fixedly mounted on the camshaft.

[0016] Furthermore, the low-position U-shaped clamp includes a left clamp plate and a right clamp plate that are integrally assembled into a U shape; the left clamp plate is fixed to the table clamp plate of the turntable clamp seat, and a slider is provided at the end of the left clamp plate facing the right clamp plate; the right clamp plate is slidably mounted on the slider of the left clamp plate, and a sliding groove is provided at the bottom of the right clamp plate to fit the slider; the left clamp plate and the right clamp plate are respectively provided with U-shaped clamp locking holes, and U-shaped clamp locking bolts are provided in the U-shaped clamp locking holes.

[0017] Furthermore, the blade positioning mechanism also includes a turntable limiting component; the turntable limiting component includes a first locking pin, a second locking pin, and a locking pin; the first locking pin and the second locking pin are fixed on the machine base and are located opposite each other on both sides of the turntable, and the top of the first locking pin and the second locking pin are provided with locking grooves; the locking pin is hinged in the groove on the circumferential surface of the turntable.

[0018] Furthermore, the blade positioning mechanism also includes a back support assembly disposed on the rotary table and located between the low-position clamping assemblies; the back support assembly includes an L-shaped backing plate.

[0019] Furthermore, the carriage mechanism includes an I-beam frame fixedly connected to the lifting mechanism, on which Y-axis slide rails and X-axis slide rails are arranged in a grid pattern; the Y-axis slide rails are arranged in the front-to-back direction and are integrally fixed to the I-beam frame; the X-axis slide rails are arranged in the left-to-right direction and can slide on the Y-axis slide rails, and the X-axis slide rails are fixed to the Y-axis slide rails by first fasteners provided on their side; a plurality of slide blocks are slidably arranged on the X-axis slide rails, and the slide blocks are fixed to the X-axis slide rails by second fasteners provided on their side.

[0020] Furthermore, the multi-station clamping table for off-site repair of aero-engine blades in this case also includes a detection component located at the center of the top surface of the table. The detection component includes a thickness gauge, which is mounted on a detection base via a universal gooseneck. The detection base is rotatably mounted on the table. The universal gooseneck and the thickness gauge are connected via a universal ball joint.

[0021] Preferably, a guide rod is vertically suspended diagonally on the bottom surface of the I-beam frame, and the guide rod corresponds to the guide hole set diagonally on the machine base.

[0022] Preferably, the high-position clamp assembly includes a high-position U-shaped clamp, which has the same structure as the low-position U-shaped clamp, and the high-position U-shaped clamp is fixed on the slide block of the X-axis slide rail.

[0023] Preferably, the inner sides of both the left and right clamping plates are provided with elastic skins; the side of the L-shaped backing plate that contacts the engine blades is also provided with elastic skins.

[0024] Preferably, the lifting mechanism includes a hydraulic lift, and the cantilever of the hydraulic lift is connected to the I-beam of the carriage mechanism.

[0025] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0026] 1) The multi-station clamping table for off-site repair of aero-engine blades in this case adjusts the direction of rotation of the turntable clamp, the front and rear positions of the turntable clamp, and the spacing of the U-shaped clamps to make the clamping position of the U-shaped clamps suitable for the curvature or arc of the engine blades, so that the engine blades are clamped more securely.

[0027] 2) The multi-station clamping table for off-site repair of aero-engine blades in this case adjusts the lifting of the carriage mechanism through the lifting mechanism, and adjusts the high-position clamping assembly to align and clamp the top of the engine blade on the machine table through the Y-axis slide rail and X-axis slide rail; and supports and clamps the bottom of the engine blade through a pair of low-position clamping assemblies; thereby clamping the engine blade and standing it upright on the machine table, which facilitates grinding and repair work.

[0028] 3) The multi-station clamping table used for off-site repair of aero-engine blades in this case adjusts the front and back of the engine blades by rotating the table. After the front of the engine blade is repaired, the table is rotated 180 degrees so that the back of the engine blade faces the workers, which facilitates further grinding and repair work and improves the grinding efficiency of the engine blades.

[0029] 4) The multi-station clamping table used for off-site repair of aero-engine blades in this case can detect whether the thickness of the blades after grinding and repair meets the repair standards provided by the aircraft manufacturer by using a thickness measuring instrument in the center of the table, thus ensuring the repair quality of the engine blades.

[0030] 5) The multi-station clamping table for off-site repair of aero-engine blades in this case can carry out blade grinding work at multiple stations simultaneously. Multiple engine blades of the same model can be ground synchronously without affecting each other, which is highly efficient. For engine blades of different models, the most reasonable clamping position can be achieved by adjustment, which has good versatility.

[0031] To provide a clearer understanding of the present invention, the preferred embodiments of the present invention will be described below in conjunction with the accompanying drawings. Attached Figure Description

[0032] Figure 1 This is a three-dimensional rendering of the present invention;

[0033] Figure 2 This is a schematic diagram of the front structure of the present invention;

[0034] Figure 3 This is a top view of the structure of the present invention;

[0035] Figure 4 This is a schematic diagram of the lifting mechanism and the carriage mechanism of the present invention;

[0036] Figure 5 This is an assembly position diagram of the machine tool, blade positioning mechanism, and detection components of the present invention;

[0037] Figure 6 , Figure 7 This is a schematic diagram of the blade positioning mechanism of the present invention;

[0038] Figure 8 , Figure 9 This is a schematic diagram of the low-position clamp assembly of the present invention;

[0039] Figure 10 This is a schematic diagram of the detection component of the present invention.

[0040] Attached image labels:

[0041] 1-Machine base; 11-Guide hole; 21-Hydraulic lift; 31-Y-axis slide rail; 32-X-axis slide rail; 33-Slide seat; 34-Guide rod; 41-Rotating table; 42-Rotating table clamp; 43-Low-position U-shaped clamp; 44-Cam locking component; 47-High-position U-shaped clamp; 411-Assembly slot; 421-Tabletop clamp; 422-Table bottom clamp; 423-Cylindrical connecting rod; 431-Left side Clamping plate, 432-right clamping plate, 433-slider, 434-slide groove, 435-U-shaped clamping bolt; 441-camshaft, 442-cam handle, 451-L-shaped backing plate, 461-first locking post, 462-second locking post, 463-locking pin; 481-thickness gauge, 482-universal gooseneck, 483-testing base, 484-universal ball joint; 9-engine blade. Detailed Implementation

[0042] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are used only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0043] Furthermore, if terms such as "first" or "second" are used for descriptive purposes only, they are mainly used to distinguish different devices, components or parts (the specific types and structures may be the same or different), and are not used to indicate or imply the relative importance or quantity of the indicated devices, components or parts, and should not be construed as indicating or implying relative importance.

[0044] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, the terms "installed," "equipped with," "sleeved / connected," "connected," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. For those skilled in the art, the specific meaning of the above terms in this invention can be understood according to the specific circumstances.

[0045] Please also refer to Figure 1-10The present invention provides a multi-station clamping platform for off-site repair of aero-engine blades, including a platform 1, a lifting mechanism disposed on one side of the platform 1, and a slide mechanism disposed above the platform 1 and driven by the lifting mechanism; the platform 1 is provided with several repair stations with the same structure, and each repair station is provided with a blade positioning mechanism.

[0046] The machine base 1 has diagonally provided guide holes 11 for cooperating with the guide rods of the carriage mechanism.

[0047] The lifting mechanism includes a hydraulic lift 21, and the cantilever of the hydraulic lift 21 is connected to the I-beam frame of the carriage mechanism.

[0048] The slide mechanism includes an I-beam frame fixedly connected to the hydraulic lift 21 cantilever. Y-axis slide rails 31 and X-axis slide rails 32 are arranged in a grid pattern on the I-beam frame. The Y-axis slide rails 31 are arranged in the front-to-back direction and are integrally fixed to the I-beam frame. The X-axis slide rails 32 are arranged in the left-to-right direction and can slide on the Y-axis slide rails 31. The X-axis slide rails 32 can be fixed to the Y-axis slide rails 31 by a first fastener provided on its side. A plurality of slide blocks 33 are slidably arranged on the X-axis slide rails 32. The slide blocks 33 can be fixed to the X-axis slide rails 32 by a second fastener provided on its side. The slide blocks 33 are used to install the high-position clamping assembly of the engine blades 9.

[0049] Furthermore, a guide rod 34 is vertically suspended diagonally on the bottom surface of the I-beam frame, corresponding to the guide hole 11 on the machine base 1. The guide rod 34 freely passes through the guide hole 11 on the machine base 1. With the cooperation of the guide rod 34 and the guide hole 11, it can be ensured that the I-beam frame of the hydraulic lift 21 driving the slide mechanism can move straight up and down above the machine base 1.

[0050] The blade positioning mechanism includes a rotary table 41 rotatably mounted on the machine base 1, a pair of low-position clamping assemblies symmetrically arranged on the table surface of the rotary table 41, a back support assembly arranged on the table surface of the rotary table 41 and located between the low-position clamping assemblies, a turntable limiting assembly symmetrically arranged on both sides of the rotary table 41, and a high-position clamping assembly arranged on the slide block 33 of the X-axis slide rail 32 and moving with the slide block 33.

[0051] The rotary table 41 has a pair of symmetrically arranged assembly slots 411 in the front-back direction. The pair of assembly slots 411 are used to assemble a pair of low-position clamping assemblies respectively. The assembly slots 411 penetrate the circumferential surface of the rotary table 41 from the front side, so that the low-position clamping assemblies can be installed on the rotary table 41 by passing through the assembly slots 411 from the front side of the rotary table 41.

[0052] The beneficial effects of this design are:

[0053] a. It facilitates the disassembly or replacement of the entire low-position fixture assembly, making it convenient to replace the low-position fixture assembly of different sizes with different models of engine blades to adapt to them, thereby enhancing the applicability of the fixture table in this case.

[0054] b. It facilitates the adjustment of the clamping position of a pair of low-position clamping components on the rotary table 41 in the front and rear directions, so that the low-position clamping components can adapt to the different curvatures of different parts on the engine blades, making the clamping of engine blades more reasonable and stable.

[0055] The low-position clamp assembly includes a turntable clamp 42, a low-position U-shaped clamp 43, and a pair of cam locking members 44. The turntable clamp 42 is installed in the assembly slot 411 of the turntable 41, the low-position U-shaped clamp 43 is located at the center of the top surface of the turntable clamp 42, and the cam locking members 44 are respectively located at both ends of the turntable clamp 42 and on both sides of the low-position U-shaped clamp 43.

[0056] The turntable clamp 42 includes an integrally formed I-shaped tabletop clamp 421, a bottom clamp 422, and a cylindrical connecting rod 423 fixedly connected between the tabletop clamp 421 and the bottom clamp 422. The length of the cylindrical connecting rod 423 is adapted to the thickness of the turntable 41, and the diameter of the cylindrical connecting rod 423 is adapted to the width of the assembly slot 411 of the turntable 41. In actual operation, the cylindrical connecting rod 423 of the assembled low-position clamp assembly is located on the turntable. The assembly slot 411 of the rotary table 41 is located on the top surface of the rotary table 41, and the bottom clamping plate 422 is located below the bottom surface of the rotary table 41. Since the cylindrical connecting rod 423 is a cylinder, the rotary table clamping seat 42 can be clamped on the assembly slot 411 of the rotary table 41, and its deflection direction can be adjusted with the cylindrical connecting rod 423 as the axis, further adapting to the different curvatures of different parts on the engine blade, and further making the clamping of the engine blade more stable.

[0057] The low-position U-shaped clamp 43 includes a left clamping plate 431 and a right clamping plate 432 that are integrally assembled into a U shape. The left clamping plate 431 is fixed on the table clamping plate 421 of the turntable clamping seat 42, and a slider 433 is provided at one end of the left clamping plate 431 facing the right clamping plate 432. The right clamping plate 432 is slidably mounted on the slider 433 of the left clamping plate 431. A groove 434 is provided at the bottom of the right clamping plate 432 to match the slider 433, so that the distance between the left clamping plate 431 and the right clamping plate 432 can be adjusted under the guidance of the slider 433 and the groove 434.

[0058] Furthermore, U-shaped clamping holes are provided on the left clamping plate 431 and the right clamping plate 432 respectively, and U-shaped clamping bolts 435 are provided in the U-shaped clamping holes. The U-shaped clamping bolts 435 are used to lock the low-position U-shaped clamp 43 with the width adjusted to a suitable position, so that the low-position U-shaped clamp 43 can adapt to the different thicknesses of different positions of the engine blades, further improving the stability of engine blade clamping.

[0059] Preferably, in this embodiment, the inner sides of both the left clamping plate 431 and the right clamping plate 432 are provided with elastic skins. During the clamping process, the elastic skins come into contact with the surface of the engine blades, so that the surface of the blades will not be damaged when the engine blades are clamped.

[0060] The cam locking component 44 includes a camshaft 441, which is horizontally rotatably mounted on one end of the tabletop clamping plate 421 of the turntable clamp 42. A cam handle 442 is fixedly mounted on the camshaft 441. In actual operation, the cam handle 442 is moved to rotate the camshaft 441. When the small-radius surface of the camshaft 441 is not in contact with the tabletop clamping plate 421 of the turntable clamp 42, the low-position clamping assembly is in an unlocked state, and can move within the assembly slot 411 of the turntable 41. When the surface of the camshaft 441 gradually increases in radius and gradually contacts the tabletop clamping plate 421 of the turntable clamp 42, the low-position clamping assembly is locked, thereby locking the adjusted low-position clamping assembly on the turntable 41 and clamping the engine blades.

[0061] The back support assembly includes an L-shaped back plate 451, which is fixed on the rotary table 41 and supports the engine blades from the back.

[0062] Preferably, in this embodiment, the side of the L-shaped backing plate 451 that contacts the engine blade is provided with an elastic skin to prevent damage to the blade surface during clamping or grinding.

[0063] The turntable limiting assembly includes a first locking pin 461, a second locking pin 462, and a locking pin 463. The first locking pin 461 and the second locking pin 462 are fixed on the machine base 1 and are located opposite each other on both sides of the turntable 41. Both the first locking pin 461 and the second locking pin 462 have locking slots at their tops. The locking pin 463 is hinged to a slot on the circumferential surface of the turntable 41. Initially, the locking pin 463 corresponds to the first locking pin 461 and is engaged in the slot of the first locking pin 461. When the operator has finished repairing the front side of the aircraft engine blade and is ready to repair the back side, they only need to lift the locking pin 463 and rotate the turntable 41 180 degrees to engage the locking pin 463 in the slot of the second locking pin 462. At this time, the back side of the engine blade faces outwards, making it easier for the operator in front of the machine base 1 to repair the back side of the engine blade.

[0064] The high-position clamping assembly includes a high-position U-shaped clamp 47, which has the same structure as the low-position U-shaped clamp 43 but is installed in a different position. These high-position U-shaped clamps 47 are respectively mounted and fixed on several slide blocks 33 of the X-axis slide rail 32 and move together with the slide blocks 33 of the X-axis slide rail 32. In actual operation, at any workstation, one high-position U-shaped clamp 47 clamps the top of the engine blade, two low-position U-shaped clamps 43 support and clamp the bottom of the engine blade, and the L-shaped backing plate 451 in the back support assembly supports the back of the engine blade, thus ensuring that the clamped engine blade is stably upright at the workstation, facilitating grinding and repair of the engine blade by the operator.

[0065] Furthermore, the multi-station clamping table for off-site repair of aero-engine blades according to the present invention also includes a detection component located at the center of the top surface of the table 1. This detection component includes a thickness gauge 481, which is mounted on a detection base 483 via a universal gooseneck 482. The detection base 483 is rotatably mounted on the table 1. The universal gooseneck 482 and the thickness gauge 481 are connected via a universal ball joint 484. After the operator completes the grinding of both sides of the engine blade, the thickness gauge 481 is moved to the required detection position to measure the thickness of the engine blade, thereby determining whether the thickness of the ground engine blade meets the repair standards provided by the aircraft manufacturer, ensuring the repair quality of the engine blade.

[0066] The working principle and beneficial effects of the multi-station clamping table for off-site repair of aero-engine blades in this case are as follows:

[0067] 1. Adjust the lifting mechanism of the carriage mechanism by lifting mechanism, and adjust the high-position clamping assembly to align and clamp the top of the engine blade on the machine base 1 by Y-axis slide rail 31 and X-axis slide rail 32; support and clamp the bottom of the engine blade by a pair of low-position clamping assemblies; so that the engine blade is clamped and erected on the machine base 1, which is convenient for grinding and repair work.

[0068] 2. During the positioning process of the engine blade, the rotation direction of the turntable clamp 42 can be adjusted by rotating it, the front and rear position of the turntable clamp 42 can be adjusted, and the spacing of the U-shaped clamps can be adjusted to make the clamping position of the U-shaped clamps suitable for the curvature of the engine blade, so that the engine blade is clamped more securely.

[0069] 3. Adjust the front and back of the engine blades by rotating the rotary table 41. After repairing the front of the engine blades, rotate the rotary table 41 180 degrees so that the back of the engine blades faces the workers, making it easier to carry out further grinding and repair work.

[0070] 4. After the engine blades have been ground and repaired, the thickness of the blades can be checked by the thickness gauge 481 in the center of the machine tool 1 to see if the thickness of the blades meets the repair standards provided by the aircraft manufacturer.

[0071] 5. Multiple workstations can simultaneously carry out blade grinding work, and multiple engine blades of the same model can be ground synchronously without affecting each other, resulting in high efficiency; for different models of engine blades, the most reasonable clamping position can be achieved through the adjustments in 1 to 3 above, which has good versatility.

[0072] The embodiments described above are merely examples of several implementations of the present invention, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these modifications and improvements all fall within the scope of protection of the present invention.

Claims

1. A multi-station clamping platform for off-site repair of aero-engine blades, comprising a platform (1), a lifting mechanism disposed on one side of the platform (1), a slide mechanism disposed above the platform (1) and driven by the lifting mechanism, and a detection component disposed at the center of the top surface of the platform (1); the platform (1) is provided with a plurality of repair stations, each repair station being provided with a blade positioning mechanism, characterized in that: The blade positioning mechanism includes a rotary table (41) rotatably mounted on the machine base (1), a pair of low-position clamping assemblies symmetrically mounted on the rotary table (41), a high-position clamping assembly mounted on the carriage mechanism, and a rotary table limiting assembly. The rotating table (41) has a pair of assembly slots (411) symmetrically arranged in the front and back directions, and the assembly slots (411) penetrate the circumferential surface of the rotating table (41) on the front side. The low-position clamp assembly includes a turntable clamp (42), a low-position U-shaped clamp (43), and a pair of cam locking members (44); the turntable clamp (42) is installed in the assembly through slot (411), the low-position U-shaped clamp (43) is located in the center of the top surface of the turntable clamp (42), and the cam locking members (44) are respectively located at both ends of the turntable clamp (42); The turntable clamp (42) includes an integrally formed I-shaped tabletop clamp (421), a bottom clamp (422), and a cylindrical connecting rod (423) fixedly connected between the tabletop clamp (421) and the bottom clamp (422). The length of the cylindrical connecting rod (423) is adapted to the thickness of the turntable (41), and the diameter of the cylindrical connecting rod (423) is adapted to the width of the mounting slot (411) of the turntable (41). The low-position U-shaped clamp (43) includes a left clamp plate (431) and a right clamp plate (432) that are integrally assembled into a U shape. The left clamp plate (431) is fixed on the table clamp plate (421) of the turntable clamp (42), and a slider (433) is provided on the end of the left clamp plate (431) facing the right clamp plate (432). The right clamp plate (432) is slidably mounted on the slider (433) of the left clamp plate (431), and a groove (434) is provided at the bottom of the right clamp plate (432) to fit the slider (433). U-shaped clamp locking holes are provided on the left clamp plate (431) and the right clamp plate (432), and U-shaped clamp locking bolts (435) are provided in the U-shaped clamp locking holes. The cam locking component (44) includes a camshaft (441), which is rotatably mounted on one end of the table clamp (421) in the horizontal direction, and a cam handle (442) is fixedly mounted on the camshaft (441). The high-position clamp assembly includes a high-position U-shaped clamp (47), which has the same structure as the low-position U-shaped clamp (43). The high-position U-shaped clamp (47) is fixed on the slide block (33) of the X-axis slide rail (32). The turntable limiting assembly includes a first locking post (461), a second locking post (462), and a locking pin (463); the first locking post (461) and the second locking post (462) are fixed on the machine base (1) and are located opposite each other on both sides of the turntable (41), and the top of the first locking post (461) and the second locking post (462) are both provided with locking grooves; the locking pin (463) is hinged in the groove on the circumferential surface of the turntable (41); The detection assembly includes a thickness detector (481), which is mounted on a detection base (483) via a universal gooseneck (482). The detection base (483) is rotatably mounted on the machine base (1). The universal gooseneck (482) and the thickness detector (481) are connected via a universal ball joint (484).

2. The multi-station clamping table for off-site repair of aero-engine blades according to claim 1, characterized in that: The blade positioning mechanism also includes a back support assembly disposed on the table surface of the rotary table (41) and located between the low-position clamping assemblies; the back support assembly includes an L-shaped backing plate (451).

3. The multi-station clamping table for off-site repair of aero-engine blades according to claim 2, characterized in that: The carriage mechanism includes an I-beam frame fixedly connected to the lifting mechanism. The I-beam frame is provided with a Y-axis slide rail (31) and an X-axis slide rail (32) arranged in a grid pattern. The Y-axis slide rail (31) is arranged in the front-to-back direction and is fixed integrally with the I-beam frame. The X-axis slide rail (32) is arranged in the left-to-right direction and can slide on the Y-axis slide rail (31). The X-axis slide rail (32) is fixed to the Y-axis slide rail (31) by a first fastener provided on its side. Several slide blocks (33) are slidably arranged on the X-axis slide rail (32). The slide blocks (33) are fixed to the X-axis slide rail (32) by a second fastener provided on its side.

4. The multi-station clamping table for off-site repair of aero-engine blades according to claim 3, characterized in that: A guide rod (34) is vertically suspended diagonally on the bottom surface of the I-beam frame, and the guide rod (34) corresponds to the guide hole (11) diagonally provided on the machine base (1).

5. A multi-station clamping table for off-site repair of aero-engine blades according to claim 4, characterized in that: The inner sides of the left side clamp (431) and the right side clamp (432) are both provided with elastic skin; the side of the L-shaped back plate (451) that contacts the engine blade is also provided with elastic skin.

6. A multi-station clamping table for off-site repair of aero-engine blades according to claim 5, characterized in that: The lifting mechanism includes a hydraulic lift (21) and an I-beam frame of a cantilever connecting carriage mechanism of the hydraulic lift (21).

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