Aviation component repair device and repair method

Abstract

The present invention discloses an aviation component repair device and repair method, including a platform, a first clamping assembly, a second clamping assembly and a driving assembly, the first clamping assembly including a connecting frame and a plurality of clamping units arranged on the connecting frame, the clamping unit including a pressure head, a sliding cavity provided in the pressure head, a plurality of sliding cavity pressure plates provided at one end of the opening in the sliding cavity, the sliding cavity pressure plates and the sliding cavity are slidingly connected, and balls are filled between the sliding cavity pressure plates and the sliding cavity, the second clamping assembly including a bearing seat and one or more mounting templates arranged on the bearing seat, the mounting templates being provided with a positioning surface matching the turbine blade profile, the driving assembly being used to drive the first clamping assembly and the second clamping assembly to slide on the platform, and adapt to different positions of the turbine blade and different distances from the rear end of the pressure head through the sliding cavity pressure plates that can slide separately, thereby ensuring stable clamping and also ensuring that the surface of the turbine blade is not damaged.

Description

Technical Field

[0001] The present invention belongs to the technical field of aviation product repair tooling, and in particular relates to an aviation component repair device and a repair method. Background Art

[0002] Turbine blades are a crucial component of the turbine section of a gas turbine engine. These high-speed rotating blades are responsible for drawing high-temperature, high-pressure air into the combustor to maintain engine operation. Metal fatigue in the blades is a leading cause of engine failure.

[0003] The windward side of existing turbine blades is easily deformed due to wear and tear over time. When repairing, laser cladding is often used. During the cladding process, a fixture is required to fix the blade position. However, the existing fixture can only provide vertical extrusion force, and the blade sidewalls are curved. When subjected to vertical extrusion, they tend to slide in the tilt direction of the blade, resulting in poor fixing stability.

[0004] For example, patent document CN202020508281.2 mentions a clamping and positioning tool for aircraft engine turbine blades, the main purpose of which is to clamp the turbine blades through upper and lower clamping blocks, and then drive the turbine blades to rotate in the cleaning fluid through a high-speed rotating motor to achieve the cleaning of the blades. Although the patent mentions the clamping block design structure, this structure can only provide a vertical downward pressing force. In particular, the lateral centrifugal force of the turbine blades is not resolved, and there is a risk of stress concentration and damage to the turbine blades. Summary of the Invention

[0005] The purpose of the present invention is to provide an aviation component repair device and repair method to solve the problem that the existing clamp can only provide vertical extrusion force when fixing turbine blades, resulting in unstable clamping of the turbine blades and affecting the quality of blade repair.

[0006] The present invention is achieved through the following technical solutions:

[0007] In some embodiments, an aviation component repair device includes:

[0008] platform;

[0009] The first clamping assembly is arranged on the platform, including a connecting frame and multiple groups of clamping units arranged on the connecting frame, the clamping units are arranged at intervals along the longitudinal direction of the connecting frame, the clamping unit includes a pressure head, a sliding cavity is arranged in the pressure head, the sliding cavity is a cavity with an open end, a plurality of sliding cavity pressure plates are arranged at the open end of the sliding cavity, the sliding cavity pressure plates are slidably connected with the sliding cavity, one end of the sliding cavity pressure plate extends out of the sliding cavity, and the other end is filled with balls between the sliding cavity;

[0010] A second clamping assembly is provided on the platform and includes a bearing seat and one or more mounting templates provided on the bearing seat and arranged opposite to the first clamping assembly. The mounting templates are provided with positioning surfaces that match the profile of the turbine blade, and the positioning surfaces are arranged in the vertical direction;

[0011] The driving component is slidingly matched with the first clamping component, the second clamping component and the platform, and is used to drive the first clamping component and the second clamping component to slide on the platform and move toward or away from each other.

[0012] In some embodiments, a pendulum plate is rotatably connected to the side wall of at least one side of the pressure head, and the pendulum plate and the pressure head are connected at the rotational connection through a torsion spring. A limit plate is installed above the pendulum plate on the pressure head to limit the rotation of the pendulum plate.

[0013] In some embodiments, the clamping unit also includes an adjusting sleeve, which is arranged on the connecting frame, the pressure head is slidably arranged in the adjusting sleeve, a spring is arranged between the pressure head and the adjusting sleeve, and a locking member is arranged between the pressure head and the adjusting sleeve for fixing the pressure head on the adjusting sleeve.

[0014] In some embodiments, a column head and a hook are installed on the connecting frame, and a round hole and a slot that cooperate with the column head and the hook are respectively opened on the front side of the supporting seat.

[0015] In some embodiments, the positioning surface includes a first arc surface provided on one side of the mounting template and cooperating with the rear side contour surface of the turbine blade, and a second arc surface provided on the other side of the mounting template and cooperating with the front side contour surface of the turbine blade.

[0016] In some embodiments, a socket corresponding to the mounting template is provided on the support seat, and mirror-symmetrical plug-in brackets are installed at the upper and lower ends of the mounting template, and the mounting template can be horizontally plugged into the socket through the plug-in bracket.

[0017] In some embodiments, a tooth key is provided on the side wall of the insertion rack, a tooth groove head engaged with the tooth key is installed on the connecting frame, and a notch is provided on the socket to cooperate with the tooth groove head.

[0018] In some embodiments, the driving assembly includes a screw slide arranged on the platform, the screw slide includes a screw, a screw nut is sleeved on the screw, and the screw nut is fixed to the bottom end of the bearing seat.

[0019] In some embodiments, a locking assembly is provided on the screw rod for limiting the rotation of the screw rod.

[0020] In some embodiments, the locking assembly includes a rotating seat and an adapter seat, the rotating seat is provided with an adapter groove, the adapter seat includes an upper pressure plate and a lower pressure plate, the upper pressure plate and the lower pressure plate are respectively provided with threads that cooperate with the screw rod, the upper pressure plate and the lower pressure plate are connected by bolts, and an adapter ring that cooperates with the adapter groove is provided at one end of the lower pressure plate, and the rotating seat and the adapter ring are respectively provided with notches for the screw rod to pass through.

[0021] In some embodiments, one end of the upper pressing plate is provided with an inserting portion that can be inserted into the adapter slot.

[0022] In some embodiments, the platform further includes a repair assembly disposed on the platform, the repair assembly including a drive frame and a working portion disposed on the drive frame, the drive frame being configured to drive the working portion to move in multiple degrees of freedom on the drive frame;

[0023] The working part includes a laser head and a feeding unit for feeding. The feeding unit includes a feeding tube with one end bent toward the laser head. An annular cavity is formed in the feeding tube between the material and the feeding tube. An air supply pipe connected to the annular cavity is provided on the feeding tube, and the air supply pipe is connected to the pump.

[0024] In some embodiments, the working portion includes a suction unit for absorbing welding particles, the suction unit includes a suction tube with one end bent toward the laser head, and the suction tube is connected to the pump.

[0025] In some embodiments, a method for repairing an aviation component includes the following steps:

[0026] Fit the contour surface of one side of the turbine blade onto the positioning surface of the mounting template;

[0027] The driving assembly drives the first clamping assembly and the second clamping assembly closer to each other, so that the pressure heads of the respective clamping units are respectively pressed against the contour surface of the other side of the turbine blade, and the locking piece on the first clamping assembly is locked;

[0028] Repair work on turbine blades is performed using repair kits.

[0029] In some embodiments, it further includes:

[0030] After repairing any one side of the turbine blade, the turbine blade is removed and the direction of the mounting template is changed so that the other positioning surface on the mounting template is placed toward the first clamping assembly;

[0031] Fitting the contour surface of the other side of the turbine blade onto the positioning surface of the mounting template;

[0032] The driving assembly drives the first clamping assembly and the second clamping assembly closer to each other, so that the pressure heads of the respective clamping units are respectively pressed against the contour surface of the turbine blade, and the locking piece on the first clamping assembly is locked;

[0033] Repair of turbine blades using repair kits.

[0034] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0035] By fitting the turbine blade profile onto the positioning surface on the mounting template, it is ensured that the vulnerable windward end face and leeward end face of the turbine blade can be vertically and stably erected, and the driving component drives the first clamping component and the second clamping component to move in a relatively close direction, so that the turbine blade can be pressed and fixed on the second clamping component by the first clamping component; by arranging multiple groups of clamping units on the first clamping component, and improving the clamping units and the pressure head structure in the clamping units, each pressure head can be well adapted to the arc surface characteristics of the turbine blade at the clamping position at each action point, and each group of clamping units can be well adapted to the overall arc surface characteristics of the turbine blade, thereby achieving stable clamping of the turbine blade and ensuring the repair quality of the turbine blade.

[0036] Positioning surfaces are provided on the mounting template to mate with the contour surfaces on both sides of the turbine blade, enabling the device to stably clamp the turbine blade in two different states, thereby enabling comprehensive repair of the turbine blade. The mirror-symmetrical mounting brackets provided on the mounting template facilitate adjustment of the mounting template during repair operations, facilitating the switching of turbine blade clamping operations between different clamping states, and improving the efficiency of turbine blade clamping and repair.

[0037] The turbine blades are clamped by setting a screw slide, and the screw position is locked by setting a locking assembly to ensure the stability of the turbine blade clamping state during the post-clamping repair operation.

[0038] By setting the feed pipe, the discharge port of the feed pipe adopts a sandwich setting of an annular cavity, which can provide the trimming blank for the trimming end face of the turbine blade while cooling the blank that does not contact the trimming end face, avoiding the filamentous blank from breaking in the feed pipe due to laser heating, ensuring stable feeding, and the external pumping device sucks air on the other side while supplying air, and timely attracts and collects the blank that is vaporized due to laser heating at the trimming end face position, avoiding the atomized blank from falling on other positions of the turbine blade and solidifying into particles, causing damage to the surface smoothness of the turbine blade, and preventing secondary damage to the turbine blade during repair. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings in the embodiments will be briefly introduced below. It should be understood that the following drawings only illustrate certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying any creative work.

[0040] Figure 1 It is a schematic diagram of the overall structure of the present invention.

[0041] Figure 2 It is a schematic structural diagram of the first clamping assembly and the second clamping assembly of the present invention.

[0042] Figure 3 It is a schematic structural diagram of the clamping unit of the present invention.

[0043] Figure 4 for Figure 2 Schematic diagram of the cross-section of the middle structure

[0044] Figure 5 It is a structural schematic diagram of the first clamping assembly of the present invention.

[0045] Figure 6 Schematic diagram of the structure of the drive assembly of the present invention.

[0046] Figure 7 Schematic diagram of the disassembly of the locking assembly structure of the present invention.

[0047] Figure 8 Schematic diagram of the structure of the repair component of the present invention.

[0048] Among them: 1-bearing seat, 11-socket, 111-sliding groove, 112-notch, 12-pressing plate, 121-platform, 13-screw slide, 131-screw, 132-screw nut, 14-round hole, 15-slot, 2-second clamping assembly, 21-mounting template, 22-first arc surface, 23-second arc surface, 24-insertion rack, 241-tooth key, 3-first clamping assembly, 31-connecting frame, 311-tooth groove head, 312-hook, 313-column head, 32-locking assembly, 321-swivel seat, 322-upper pressure plate, 323-lower pressure plate, 324-rotating Connecting groove, 325-plug-in part, 326-adapter ring, 327-notch part, 33-adjusting sleeve, 331-pressure head, 332-screw groove, 333-spring, 334-screw, 34-telescopic rod, 341-sliding cavity pressure plate, 342-swing plate, 343-ball, 344-rectangular opening, 345-limiting plate, 346-lining, 347-sliding cavity, 4-feeding unit, 41-air supply pipe, 411-annular cavity, 42-feeding pipe, 421-first elbow, 43-suction pipe, 431-second elbow, 5-turbine blade, 6-drive frame, 61-laser head. DETAILED DESCRIPTION

[0049] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments.

[0050] Example 1

[0051] like Figure 1-8 As shown, an aviation component repair device includes:

[0052] platform;

[0053] The first clamping assembly 3 is arranged on the platform 121, including a connecting frame 31 and multiple groups of clamping units arranged on the connecting frame. The clamping units are arranged at intervals along the longitudinal direction of the connecting frame. The clamping unit includes a pressure head, and a sliding cavity 347 is provided in the pressure head. The sliding cavity 347 is a cavity with an open end. A plurality of sliding cavity pressure plates 341 are provided at the open end of the sliding cavity. The sliding cavity pressure plates 341 are slidably connected with the sliding cavity. One end of the sliding cavity pressure plate 341 extends out of the sliding cavity 347, and the other end is filled with a ball 343 between the sliding cavity 347 and the sliding cavity 347;

[0054] The second clamping assembly 2 is arranged on the platform 121, and includes a bearing seat 1 and one or more mounting templates 21 arranged on the bearing seat and opposite to the first clamping assembly 3. The mounting template 21 is provided with a positioning surface that matches the profile of the turbine blade 5, and the positioning surface is arranged in the vertical direction;

[0055] The driving component is slidingly matched with the first clamping component 3, the second clamping component 2 and the platform 121, and is used to drive the first clamping component 3 and the second clamping component 2 to slide on the platform 121 and move toward or away from each other.

[0056] In some embodiments, the sliding cavity pressure plate 341 is arranged in the sliding cavity 347 in a close-packed manner up and down, and an outward-turned convex edge is installed at the front end of the sliding cavity pressure plate 341. The sliding cavity 347 is filled with balls 343. By setting the balls 343, when the pressure head contacts and abuts the turbine blade 5, the sliding cavity pressure plate 341 at the front end of the pressure head can adaptively change its protruding distance along with the arc surface of the turbine blade 5, and can better conform to the turbine blade 5 and make sufficient contact to ensure that the turbine blade 5 is pressed by multi-point contact. After the turbine blade 5 is taken out, the squeezing force on the ball 343 disappears, and the ball 343 will roll under its own force, so that the sliding cavity pressure plate 341 returns to its original position.

[0057] In some preferred embodiments, the sliding cavity pressure plate 341 can be arranged in the sliding cavity 347 in an up-down, left-right, or up-down, left-right, and right-left manner. By setting multiple sliding cavity pressure plates 341, the sliding cavity pressure plates 341 can fit the turbine blades 5 more fully.

[0058] like Figure 3 As shown, a pendulum plate 342 is rotatably connected to the side wall of at least one side of the pressure head. The pendulum plate 342 and the pressure head are connected at the rotating connection by a torsion spring. A limit plate 345 is installed above the pendulum plate 342. A lining 346 is installed at the rear end of the pendulum plate 342. The swinging end of the pendulum plate 342 will adapt to the curvature of the turbine blade 5 and swing adaptively under pressure. After swinging, the pendulum plate 342 will apply downward pressure to the turbine blade 5 to ensure the stability of the position of the curved turbine blade 5 after being clamped from front to back.

[0059] like Figure 2-5 As shown, the clamping unit also includes an adjusting sleeve 33, which is arranged on the connecting frame 31, and the pressure head is slidably arranged in the adjusting sleeve 33. A spring 333 is installed at the front end of the telescopic rod 34, and the telescopic rod 34 is connected to the adjusting sleeve 33 through the spring 333. When the telescopic rod 34 slides in the adjusting sleeve 33 to perform a pressing operation on the turbine blade 5, the turbine blade 5 can be pre-pressed due to the elastic force of the spring 333. A locking member for fixing the pressure head on the adjusting sleeve is provided between the pressure head and the adjusting sleeve 33.

[0060] Furthermore, the adjustment sleeve 33 is hingedly connected to the connecting frame 31 , and the adjustment sleeve 33 can swing up and down on the connecting frame 31 , thereby increasing the range of motion of the clamping unit.

[0061] In some embodiments, the pressure head is a telescopic rod 34 , which can perform telescopic movement in the adjustment sleeve 33 to adapt to the profiles of different turbine blades 5 .

[0062] In some embodiments, the locking member can be a screw-nut assembly, a screw groove 332 is provided at the rear of the adjusting sleeve 33, a screw 334 with a nut is installed through the screw groove 332, and the bottom end of the screw 334 and the bottom end of the nut are respectively installed with a pressure head 331 that cooperates with the screw groove 332, and a rectangular opening 344 is provided at the front of the telescopic rod 34 for the screw 334 to pass through.

[0063] During the process of the connecting frame 31 moving backward to squeeze the turbine blades 5, the spring 333 will be compressed and cooperate with the telescopic rod 34 to pre-tighten the turbine blades 5. After all the telescopic rods 34 are fully in contact, they adapt to the arc shape of the turbine blades 5 to ensure full contact at multiple points to improve the compression stability. The screw 334 and the nut can be matched with the pressure head 331 to tighten and fix the adjustment sleeve 33 and the telescopic rod 34 to achieve further stable compression after pre-tightening.

[0064] like Figure 4-6 As shown, column heads 313 are installed on the rear sides of the left and right ends of the connecting frame 31, and a round hole 14 is opened on the front side of the supporting seat 1 to cooperate with the column head 313. A hook 312 is installed on the lower part of the connecting frame 31, and a slot 15 is opened on the front side of the supporting seat 1 to cooperate with the hook 312.

[0065] Through the cooperation of the column head 313 and the hook 312, the connecting frame 31 can be limited in sliding to ensure that the connecting frame 31 will not bend up when pressed from the rear to ensure a stable position. After the driving device moves forward fully, the connecting frame 31 can be completely separated from the supporting seat 1 and moved flexibly, which is convenient for inspection and replacement in subsequent use and easy maintenance.

[0066] like Figure 2 、 Figure 4 As shown, mirror-symmetrical racks 24 are respectively installed at the upper and lower ends of the mounting template 21, and a socket 11 with a sliding groove 111 is provided on the supporting seat 1. The rack 24 is horizontally plugged into the socket 11 through the sliding groove 111, and a tooth key 241 is provided on the side wall of the rack 24. A tooth groove head 311 that engages with the tooth key 241 of the rack 24 in the socket 11 is installed at the rear end of the connecting frame 31, and a notch 112 that cooperates with the tooth groove head 311 is provided on the front side of the socket 11.

[0067] The mounting template 21 is provided with a positioning surface that can fit with the turbine blade 5. Specifically, a first arc surface 22 consistent with the rear side contour of the turbine blade 5 is provided on one side of the mounting template 21, and a second arc surface 23 consistent with the front side contour of the turbine blade is provided on the other side. The first arc surface 22 and the second arc surface 23 can completely fit with the turbine blade 5.

[0068] The mounting template 21 is connected to the socket 11 via the bracket 24, restricting its forward and backward movement. The connecting bracket 31 synchronously drives the toothed head 311 to lock the bracket 24, ensuring the stable position of the mounting template 21. When the turbine blade end face needs to be modified, the turbine blade 5 is removed and the orientation of the mounting template 21 is reversed. The surface of the turbine blade 5 to be repaired is then fitted onto the positioning surface of the mounting template. The first clamping assembly is then repositioned to compress the turbine blade, and the repair is then carried out. The mirror-symmetrical arrangement of the bracket 24 reduces the number of steps required to flip the turbine blade 5 for repair, making the repair more efficient and improving work efficiency.

[0069] Example 2

[0070] like Figure 4 、 Figure 5As shown, the drive assembly includes a screw slide 13, which is located between the bearing seat 1 and the platform 121. A screw 131 is rotatably installed in the middle of the screw slide 13, and a screw nut 132 is sleeved on the outer side of the screw 131. The screw nut 132 is fixedly connected to the bottom end of the bearing seat 1, and a pressure plate 12 is provided on the platform 121 in front of the bearing seat 1.

[0071] The screw rod 131 can rotate to drive the supporting seat 1 forward. At this time, the supporting seat 1 and the connecting frame 31 are relatively far apart, which is convenient for reversing and replacing the turbine blades 5. After the reversing and replacing operations of the turbine blades 5 are completed, the rotating screw rod 131 drives the supporting seat 1 to move backward. At this time, the supporting seat 1 and the connecting frame 31 are relatively close, and the connecting frame is squeezed by the pressure plate 12 to ensure that the connecting frame 31 is firmly close to the supporting seat 1.

[0072] Furthermore, a locking assembly 32 is provided at the end of the screw rod 131 for limiting the rotation of the screw rod. After the connecting frame 31 moves backward to press the turbine blade 5, the position of the screw rod 131 is locked by the locking assembly 32, ensuring that the turbine blade 5 is clamped stably while also ensuring the stability of the position of the support seat 1, preventing the overall forward and backward movement of the support seat 1 and the turbine blade 5 during work from affecting the processing accuracy.

[0073] It is worth mentioning that Figure 7 As shown, the locking assembly includes a rotary seat 321 and an adapter seat, the rotary seat 321 is provided with an adapter groove 324, the adapter seat includes an upper pressure plate 322 and a lower pressure plate 323, the upper pressure plate 322 and the lower pressure plate 323 are respectively provided with threads that cooperate with the screw rod 131, the upper pressure plate 322 and the lower pressure plate 323 are connected by bolts, and an adapter ring 326 that cooperates with the adapter groove 324 is provided at one end of the lower pressure plate 323, and the rotary seat 321 and the adapter ring 326 are respectively provided with a notch portion 327 for the screw rod 131 to pass through.

[0074] The upper pressure plate 322 has left and right support ears, and the left and right support ears have screw holes. The upper pressure plate 322 and the lower pressure plate 323 are placed on both sides of the screw rod 131. The upper pressure plate 322 and the lower pressure plate 323 are tightened and fixed with bolts to tighten the screw rod 131, that is, the upper pressure plate 322 and the lower pressure plate 323 are clamped to the outside of the screw rod 131 by bolts to fix the screw rod 131.

[0075] There are notches 327 on the adapter ring 326 and the rotary seat 321, which can separate the locking assembly 32 and the pressure plate 12 from the screw rod 131 as a whole, and can be directly expanded and used on the finished screw slide 13. It has strong adaptability and can be disassembled and repaired separately. The upper pressure plate 322 can be removed separately to flexibly adjust the position of the screw rod 131, and the turbine blade 5 that has completed forward movement can be released from the pressure, making it more convenient to use.

[0076] Furthermore, a plug-in portion 325 is provided at the rear of the upper pressing plate 322 . The plug-in portion 325 is slidably plugged into the adapter groove 324 , and the bottom end of the plug-in portion 325 is in sliding contact with the top end of the lower pressing plate 323 .

[0077] The setting of the plug-in part 325 allows the upper pressure plate 322 to be inserted into the adapter groove 324, so that the left and right support ears of the upper pressure plate 322 can press against the front side wall of the screw-on seat 321, and quickly align the screw holes of the lower pressure plate 323 and the lower pressure plate, which facilitates the disassembly and assembly of the bolts and subsequent disassembly and assembly.

[0078] Example 3

[0079] The platform 121 is provided with a driving frame 6 at the rear end of the supporting seat 1. Figure 8 The driving frame 6 adopts a four-degree-of-freedom driving platform, the laser head 61 is installed at the front of the top of the driving frame 6, the feeding unit 4 includes a feeding pipe 42, and the bottom end of the feeding pipe 42 is installed with a first elbow 421 bent toward the direction of the laser head 61, and the middle of the first elbow 421 is provided with an annular cavity 411 with an open bottom end, and the top of the annular cavity 411 is connected to the air supply pipe 41.

[0080] Furthermore, the top of the air supply pipe 41 is connected to the pump through a pipeline. The drive frame 6 is located on the right side of the laser head 61 and is penetrated by a suction pipe 43. The bottom end of the suction pipe 43 is installed with a second elbow 431 bent toward the laser head 61.

[0081] The driving frame 6 can drive the laser head 61 to rise and fall, move forward and backward, left and right, and swing, so as to perform flexible processing of the turbine blade 5. The feed pipe 42 moves synchronously with the laser head 61 to ensure stable feeding, and the air supply pipe 41 cools the filamentous trimming blank near the welding position in the feed pipe 42 through the position of the annular cavity 411 to avoid the trimming blank from being broken in the feed pipe 42 due to excessive temperature, thereby ensuring stable feeding, cooling and solidifying the welding position, and improving welding efficiency; the suction pipe 43 can be bent toward the laser head 61 to absorb the atomized metal particles at the welding position, thereby avoiding the atomized blank from falling and solidifying into particles at other positions of the turbine blade 5, causing damage to the surface smoothness of the turbine blade 5, preventing secondary damage to the turbine blade during repair, and improving the quality of trimming.

[0082] The aviation component repair method comprises the following steps:

[0083] Fit the contour surface of one side of the turbine blade onto the positioning surface of the mounting template;

[0084] The driving assembly drives the first clamping assembly and the second clamping assembly closer to each other, so that the pressure heads of the respective clamping units are respectively pressed against the contour surface of the other side of the turbine blade, and the locking piece on the first clamping assembly is locked;

[0085] Repair work on turbine blades is performed using repair kits.

[0086] Aviation component repair methods also include turning over and repairing turbine blades:

[0087] After repairing any one side of the turbine blade, the turbine blade is removed and the direction of the mounting template is changed so that the other positioning surface on the mounting template is placed toward the first clamping assembly;

[0088] Fitting the contour surface of the other side of the turbine blade onto the positioning surface of the mounting template;

[0089] The driving assembly drives the first clamping assembly and the second clamping assembly closer to each other, so that the pressure heads of the respective clamping units are respectively pressed against the contour surface of the turbine blade, and the locking piece on the first clamping assembly is locked;

[0090] Repair of turbine blades using repair kits.

[0091] The mechanical and electronic control products involved in the two embodiments use finished equipment purchased on the market, and their supporting hydraulic systems, air supply systems, electronic control systems, solenoid valves and circuit pipelines can also be provided by the manufacturer. In addition, the power supply modules, circuits, electronic components and control modules involved in the present invention are all existing technologies, which can be fully implemented by those skilled in the art. Needless to say, the content protected by the present invention does not involve improvements to the internal structure and methods.

[0092] In the description of the present invention, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. used to indicate the orientation or position relationship are based on the orientation or position relationship shown in the accompanying drawings, or are the orientation or position relationship in which the product of the invention is usually placed when in use. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, they should not be understood as limiting the present invention.

[0093] Furthermore, the use of terms such as "horizontal" and "vertical" in the description of the present invention does not necessarily imply that the component must be absolutely horizontal or suspended, but rather that it can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal than "vertical" and does not mean that the structure must be completely horizontal, but rather that it can be slightly tilted.

[0094] It should also be noted that, in the description of the present invention, unless otherwise expressly specified or limited, the terms "disposed," "installed," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed connections, detachable connections, or integral connections; mechanical connections or electrical connections; direct connections or indirect connections through an intermediate medium; and internal connections between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention in specific contexts.

[0095] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Any simple modification or equivalent change made to the above embodiment based on the technical essence of the present invention shall fall within the scope of protection of the present invention.

Claims

1. An aviation component repair device, characterized in that: include: platform; A first clamping assembly (3), the first clamping assembly (3) is arranged on the platform, comprising a connecting frame (31) and a plurality of clamping units arranged on the connecting frame, the clamping units being arranged at intervals along the longitudinal direction of the connecting frame, the clamping units comprising a pressure head, a sliding cavity (347) being arranged in the pressure head, the sliding cavity (347) being a cavity with an opening at one end, a plurality of sliding cavity pressure plates (341) being arranged in the open end of the sliding cavity, the sliding cavity pressure plates (341) being connected to the sliding cavity (347) in a sliding fit, one end of the sliding cavity pressure plate (341) extending out of the sliding cavity (347), and a ball (343) being filled between the other end and the sliding cavity (347); a second clamping assembly, the second clamping assembly being arranged on the platform and comprising a bearing seat (1) and one or more mounting templates (21) arranged on the bearing seat and arranged opposite to the first clamping assembly (3), wherein the mounting template (21) is provided with a positioning surface that matches the profile of the turbine blade (5), and the positioning surface is arranged in the vertical direction; A driving assembly, wherein the first clamping assembly, the second clamping assembly and the platform are slidably matched, and the driving assembly is used to drive the first clamping assembly and the second clamping assembly to slide on the platform and move toward or away from each other; the clamping unit also includes an adjusting sleeve (33), the adjusting sleeve (33) is arranged on the connecting frame (31), the pressing head is slidably arranged in the adjusting sleeve (33), a spring (333) is arranged between the pressing head and the adjusting sleeve (33), and a locking member for fixing the pressing head on the adjusting sleeve (33) is arranged between the pressing head and the adjusting sleeve (33); The positioning surface comprises a first cambered surface (22) provided on one side of the mounting template (21) and cooperating with the rear profile surface of the turbine blade (5), and a second cambered surface (23) provided on the other side of the mounting template and cooperating with the front profile surface of the turbine blade.

2. The aviation component repair device according to claim 1, characterized in that: A swing plate (342) is rotatably connected to the side wall of at least one side of the pressure head. The swing plate (342) and the pressure head are connected at the rotational connection via a torsion spring. A limit plate (345) for limiting the rotation of the swing plate is installed above the pressure head and is located above the swing plate (342).

3. The aviation component repair device according to claim 1, characterized in that: The connecting frame (31) is provided with a column head (313) and a hook (312), and a circular hole (14) and a slot (15) are provided on the front side of the bearing seat (1) to match the column head (313) and the hook (312).

4. The aviation component repair device according to claim 1, characterized in that: The bearing seat (1) is provided with a socket (11) corresponding to the mounting template, and the mounting template (21) is provided with mirror-symmetrical plug-in racks (24) at the upper and lower ends, respectively. The mounting template can be horizontally plugged into the socket (11) through the plug-in racks (24).

5. The aviation component repair device according to claim 4, characterized in that: The side wall of the inserting frame (24) is provided with a tooth key (241), the connecting frame (31) is provided with a tooth groove head (311) engaged with the tooth key (241), and the socket (11) is provided with a notch (112) matched with the tooth groove head (311).

6. The aviation component repair device according to claim 1, characterized in that: The drive assembly comprises a screw slide (13) arranged on a platform, the screw slide comprises a screw (131), a screw nut (132) is sleeved on the screw (131), and the screw nut (132) is fixed to the bottom end of the bearing seat (1).

7. The aviation component repair device according to claim 6, characterized in that: The screw rod (131) is provided with a locking assembly (32) for limiting the rotation of the screw rod.

8. The aviation component repair device according to claim 7, characterized in that: The locking assembly includes a rotary seat (321) and an adapter seat, the rotary seat (321) is provided with an adapter groove (324), the adapter seat includes an upper pressure plate (322) and a lower pressure plate (323), the upper pressure plate (322) and the lower pressure plate (323) are respectively provided with threads that cooperate with the screw rod (131), the upper pressure plate (322) and the lower pressure plate (323) are connected by bolts, and one end of the lower pressure plate (323) is provided with an adapter ring (326) that cooperates with the adapter groove (324), and the rotary seat (321) and the adapter ring (326) are respectively provided with a notch portion (327) for the screw rod (131) to pass through.

9. The aviation component repair device according to claim 8, characterized in that: One end of the upper pressing plate (322) is provided with an inserting portion (325) capable of being inserted into the adapter groove (324).

10. The aviation component repair device according to claim 1, characterized in that: Also included is a repair component arranged on the platform, the repair component comprising a drive frame (6) and a working part arranged on the drive frame, the drive frame (6) being used to drive the working part to move in multiple degrees of freedom on the drive frame; The working part comprises a laser head (61) and a feeding unit (4) for feeding material. The feeding unit (4) comprises a feeding pipe (42) with one end bent toward the laser head (61). An annular cavity is formed in the feeding pipe (42) between the material and the feeding pipe. An air supply pipe (41) communicating with the annular cavity is provided on the feeding pipe (42). The air supply pipe (41) is connected to a pump.

11. The aviation component repair device according to claim 10, characterized in that: The working part comprises a suction unit for absorbing welding particles, the suction unit comprises a suction tube (43) with one end bent toward the laser head (61), and the suction tube (43) is connected to a pump.

12. A method for repairing aviation components according to the aviation component repair device according to any one of claims 1 to 11, characterized in that: The following steps are involved: Fit the contour surface of one side of the turbine blade onto the positioning surface of the mounting template; The driving assembly drives the first clamping assembly and the second clamping assembly closer to each other, so that the pressure heads of the respective clamping units are respectively pressed against the contour surface of the other side of the turbine blade, and the locking piece on the first clamping assembly is locked; Repair work on turbine blades is performed using repair kits.

13. The aviation component repair method according to claim 12, characterized in that: Also includes: After repairing any one side of the turbine blade, the turbine blade is removed and the direction of the mounting template is changed so that the other positioning surface on the mounting template is placed toward the first clamping assembly; Fitting the contour surface of the other side of the turbine blade onto the positioning surface of the mounting template; The driving assembly drives the first clamping assembly and the second clamping assembly closer to each other, so that the pressure heads of the respective clamping units are respectively pressed against the contour surface of the turbine blade, and the locking piece on the first clamping assembly is locked; Repair of turbine blades using repair kits.

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