Clamping device for additive repair of high-pressure turbine blades of aircraft engines

Abstract

The present invention discloses a clamping device, and in particular discloses a clamping device for additive repair of high-pressure turbine blades of aircraft engines, which belongs to the technical field of design and manufacturing of aircraft engine repair and maintenance process equipment. Provided is a clamping device for additive repair of high-pressure turbine blades of aircraft engines, which has good heat dissipation effect and can effectively reduce the influence of uneven wall thickness and ribs on the molten pool at the blade tip. The clamping device comprises a base frame, a supporting and fixing frame, and a flexible clamping and heat dissipation mechanism, wherein the supporting and fixing frame is arranged on the base frame, and the flexible clamping and heat dissipation mechanism is movably arranged on the supporting and fixing frame; during the additive repair process of the high-pressure turbine blades, the high-pressure turbine blades supported on the corresponding parts of the supporting and fixing frame are clamped at their additive repair parts by the flexible clamping and heat dissipation mechanism.

Description

Technical Field

[0001] The invention relates to a clamping device, in particular to a clamping device used for additive repair of high-pressure turbine blades of an aero-engine, and belongs to the technical field of design and manufacturing of aero-engine repair and maintenance process equipment. Background Art

[0002] High-pressure turbine blades are key components of aircraft engine power energy devices, and any damage will have a serious impact on the flight safety of military and civil aviation. Under the harsh working environment of high-speed aerodynamic loads, centrifugal loads, vibration loads, and high-temperature gas erosion, the blades have a large number of cracks and wear defects at the blade tips after service, reducing the engine thrust. The blades are made of precision casting, with complex processes, low pass rates, and limited production. Therefore, the remanufacturing and repair of the blades has become a major breakthrough. High-vortex blade repair technology is a highly technical field internationally. Currently, only top companies such as GE and Rolls-Royce have relevant technical strength in the world. A domestic factory is the first domestic company to actually apply laser additive repair to engine blade repair, and is committed to researching and exploring the remanufacturing technology of various blades and parts in the engine.

[0003] During the manufacturing process of high-vortex blades, the casting core will be affected by the buoyancy of the liquid alloy, which will lead to a certain tolerance in the blade wall thickness. After the blades are in service, they will have different wear and tear conditions. During the repair of the blade tip, laser additives are prone to uneven heat dissipation conditions due to the complex shape of the blade tip and the existence of shape tolerances. The position of some blade reinforcement ribs is uncertain, and the ordinary tooling cannot fit the blade tip shape, resulting in poor heat dissipation. This causes the molten pool to be unstable during the cladding process, resulting in defects such as undercuts and collapse. How to solve the above technical problems in the modification process of high-vortex blades has become a technical problem that technicians in this field need to solve urgently. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide a clamping device for additive repair of high-pressure turbine blades of aircraft engines, which has good heat dissipation effect and can effectively reduce the influence of uneven wall thickness and rib plates on the molten pool at the blade tip.

[0005] The technical solution adopted to solve the above technical problems is: a clamping device for additive repair of high-pressure turbine blades of aircraft engines, the clamping device comprising a base frame, a supporting and fixing frame and a flexible clamping and heat dissipation mechanism, the supporting and fixing frame is arranged on the base frame, and the flexible clamping and heat dissipation mechanism is movably arranged on the supporting and fixing frame; during the additive repair process of the high-pressure turbine blades, the high-pressure turbine blades supported on the corresponding parts of the supporting and fixing frame are clamped at their additive repair parts by the flexible clamping and heat dissipation mechanism.

[0006] Furthermore, the base frame includes a base and supporting columns, and the base and the supporting columns are respectively fixedly connected to corresponding parts of the supporting fixing frame.

[0007] A preferred embodiment of the above scheme is that the supporting and fixing frame includes a supporting seat and a clamping mechanism mounting seat, the supporting seat is movably arranged on the base of the base frame, the clamping mechanism mounting seat is supported on the base frame through supporting columns, and the flexible clamping heat dissipation mechanism is movably arranged on the clamping mechanism mounting seat.

[0008] Furthermore, mutually adaptable mortise and tenon grooves are respectively arranged on the base and the support seat, and the support seat is movably arranged on the base through the tenon in cooperation with the mortise and tenon groove, and the base, the support column and the clamping mechanism mounting seat are an integrated printed structure.

[0009] A preferred embodiment of the above scheme is that the flexible clamping and heat dissipation mechanism includes a push rod locking assembly and a contoured clamping and heat dissipation assembly, and the contoured clamping and heat dissipation assembly is movably arranged on the clamping mechanism mounting seat through the push rod locking assembly; during the clamping process of the high-pressure turbine blades, the high-pressure turbine blades whose lower ends are supported on the support seat are clamped on the clamping mechanism mounting seat through the contoured clamping and heat dissipation assembly with the cooperation of the push rod locking assembly.

[0010] Furthermore, the push rod locking assembly includes at least two guide push rods and at least two groups of push rod locking blocks. A plurality of guide grooves equal in number to the number of guide push rods are provided on the clamping mechanism mounting seat. Each of the guide push rods is movably arranged at a corresponding position of the clamping mechanism mounting seat along the length direction through its guide rail in cooperation with the guide groove. The front end of each guide push rod is respectively hinged to the contoured clamping and heat dissipation assembly, and the push rod locking block is arranged at the rear end of the corresponding guide push rod.

[0011] A preferred embodiment of the above scheme is that the contoured clamping heat dissipation assembly at least comprises a parting hinge group and a clamping contoured contact group, and the clamping contoured contact group is movably arranged at the front end of the corresponding guide push rod through the parting hinge group.

[0012] Furthermore, the parting hinge group includes a blade back hinge group, a blade basin hinge group and a blade top hinge group, and a blade top hinge group mounting column is also provided on the clamping mechanism mounting seat, the blade back hinge group and the blade basin hinge group are respectively hinged in front of different guide push rods, the blade top hinge group is hinged on the clamping mechanism mounting seat through the blade top hinge group mounting column, and the clamping contour contact piece group is movably connected to the shape of the cross-section of the high-pressure turbine blade through the corresponding blade back hinge group, blade basin hinge group and spray top hinge group.

[0013] A preferred embodiment of the above scheme is that the push rod locking assembly also includes three groups of V-shaped guide springs, the blade back hinge group and the blade basin hinge group each include a main hinge and two auxiliary hinges, the blade top hinge group includes an auxiliary hinge, and the two auxiliary hinges are respectively hinged on one of the main hinges, and the main hinges are respectively hinged to the front ends of the corresponding guide push rods with the cooperation of the corresponding V-shaped guide springs, and the auxiliary hinge constituting the blade top hinge group is hinged to the mounting column of the blade top hinge group with the cooperation of the corresponding V-shaped guide springs, and the clamping contoured contact piece groups are respectively hinged on each of the auxiliary hinges.

[0014] Furthermore, each auxiliary hinge includes two hinged heads, and the clamping contour contact member group includes a plurality of contour contact blocks whose number is equal to the number of hinged heads on each auxiliary hinge. Each contour contact block forms an active flexible clamping contact surface through the auxiliary hinge and the main hinge in cooperation with the guide push rod and the V-shaped guide spring sheet.

[0015] The beneficial effects of the present invention are as follows: the technical solution provided by the present application is to set up a clamping device including a base frame, a support and fixing frame and a flexible clamping and heat dissipation mechanism, and the support and fixing frame is arranged on the base frame, and the flexible clamping and heat dissipation mechanism is movably arranged on the support and fixing frame; then, during the additive repair process of the high-pressure turbine blade, the high-pressure turbine blade supported on the corresponding part of the support and fixing frame is clamped at its additive repair part by the flexible clamping and heat dissipation mechanism. Since the clamping device of the present application can effectively improve the overall heat dissipation level of the blade tip through the flexible clamping and heat dissipation mechanism, the stability of the process is enhanced, the influence factor of the molten pool on the blade tip shape wall thickness and reinforcement ribs is reduced, and the blade additive repair process window and qualified rate are improved. Thereby, not only the heat dissipation effect is improved, but also the influence of the uneven wall thickness of the blade tip and the rib plate on the molten pool can be effectively reduced, so as to achieve the purpose of improving the blade additive repair process window and qualified rate.

[0016] The core of the clamping device of the present application consists of three main functional areas, namely, the fixed fulcrum formed by the support seat, the blade basin adaptive push rod and the blade back adaptive push rod. Its working method is to push the blade into the blade slot, and after contacting the fixed fulcrum, push the blade basin and blade back adaptive push rods and lock the position, and then use laser cladding to perform blade tip additive repair operations. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the front three-dimensional structure of the clamping device used for additive repair of high-pressure turbine blades of aircraft engines according to the present invention;

[0018] Figure 2 It is a schematic diagram of the rear three-dimensional structure of the clamping device used for additive repair of high-pressure turbine blades of an aircraft engine according to the present invention;

[0019] Figure 3 It is a front view of the clamping device for additive repair of high-pressure turbine blades of aircraft engines according to the present invention;

[0020] Figure 4 for Figure 3 Side view of

[0021] Figure 5 for Figure 3 A top view of

[0022] Figure 6 The figure is a schematic diagram of the clamping operation of the clamping device used for additive repair of high-pressure turbine blades of aircraft engines according to the present invention.

[0023] Marked in the figure are: base frame 1, support fixing frame 2, flexible clamping heat dissipation mechanism 3, high-pressure turbine blade 4, base 5, support column 6, support seat 7, clamping mechanism mounting seat 8, mortise and tenon 9, tenon 10, push rod locking assembly 11, contour clamping heat dissipation assembly 12, guide push rod 13, push rod locking block 14, guide groove 15, parting hinge group 16, clamping contour contact group 17, blade back hinge group 18, blade basin hinge group 19, blade top hinge group 20, blade top hinge group mounting column 21, V-shaped guide spring piece 22, main hinge frame 23, auxiliary hinge frame 24, hinge head 25, contour contact block 26. DETAILED DESCRIPTION

[0024] like Figure 1 to Figure 6The present invention provides a clamping device for additive repair of high-pressure turbine blades of aircraft engines, which has good heat dissipation effect and can effectively reduce the influence of uneven wall thickness and ribs on the molten pool at the blade tip. The clamping device comprises a base frame 1, a support and fixing frame 2 and a flexible clamping and heat dissipation mechanism 3, wherein the support and fixing frame 2 is arranged on the base frame 1, and the flexible clamping and heat dissipation mechanism 3 is movably arranged on the support and fixing frame 2; during the additive repair process of the high-pressure turbine blade 4, the high-pressure turbine blade 4 supported on the corresponding part of the support and fixing frame 2 is clamped by the flexible clamping and heat dissipation mechanism 3. The technical solution provided by the present application is to set a clamping device including a base frame, a support and fixing frame and a flexible clamping and heat dissipation mechanism, and the support and fixing frame is arranged on the base frame, and the flexible clamping and heat dissipation mechanism is movably arranged on the support and fixing frame; then during the additive repair process of the high-pressure turbine blade, the high-pressure turbine blade supported on the corresponding part of the support and fixing frame is clamped by the flexible clamping and heat dissipation mechanism. Since the clamping device of the present application can effectively improve the overall heat dissipation level of the blade tip through the flexible clamping heat dissipation mechanism, the process stability is enhanced, the influence factor of the molten pool on the blade tip shape, wall thickness and reinforcing ribs is reduced, and the blade additive repair process window and qualified rate are improved. This not only improves the heat dissipation effect, but also effectively reduces the influence of the uneven wall thickness and rib plate of the blade tip on the molten pool, achieving the purpose of improving the blade additive repair process window and qualified rate.

[0025] The core of the clamping device of the present application consists of three main functional areas, namely, the fixed fulcrum formed by the support seat, the blade basin adaptive push rod and the blade back adaptive push rod. Its working method is to push the blade into the blade slot, and after contacting the fixed fulcrum, push the blade basin and blade back adaptive push rods and lock the position, and then use laser cladding to perform blade tip additive repair operations.

[0026] In the above embodiment, in order to facilitate the free movement of the high-pressure turbine blade 4 during the clamping process, the base frame 1 described in the present application includes a base 5 and a support column 6, and the base 5 and the support column 6 are respectively fixedly connected to the corresponding parts of the support fixing frame 2. The support fixing frame 2 described in the present application includes a support seat 7 and a clamping mechanism mounting seat 8, the support seat 7 is movably arranged on the base 5 of the base frame 1, the clamping mechanism mounting seat 8 is supported on the base frame 1 through the support column 6, and the flexible clamping heat dissipation mechanism 3 is movably arranged on the clamping mechanism mounting seat 8. At the same time, the base 5 and the support seat 7 are respectively provided with mutually adapted mortise grooves 9 and tenons 10, and the support seat 7 is movably arranged on the base 5 through the tenons 10 in cooperation with the mortise grooves 9, and the base 5, the support column 6 and the clamping mechanism mounting seat 8 are an integrated printing structure. In this way, the structure of the clamping device of the present application can be made compact, and the free movement of the high-pressure turbine blade 4 during the clamping process can be facilitated.

[0027] Furthermore, as a key component of the clamping device of the present application, in order to achieve the clamping of the high-pressure turbine blades 4 and effectively diffuse the heat generated during the additive repair process to limit the deformation of the high-pressure turbine blades 4 during the repair process, the flexible clamping and heat dissipation mechanism 3 described in the present application includes a push rod locking assembly 11 and a contoured clamping and heat dissipation assembly 12, and the contoured clamping and heat dissipation assembly 12 is movably arranged on the clamping mechanism mounting seat 8 through the push rod locking assembly 11; during the clamping process of the high-pressure turbine blades 4, the high-pressure turbine blades 4 whose lower end seats are supported on the support seat 7 are clamped on the clamping mechanism mounting seat 8 through the contoured clamping and heat dissipation assembly 12 with the cooperation of the push rod locking assembly 11. Accordingly, in order to improve the reliability of clamping, the push rod locking assembly 11 described in the present application includes at least two guide push rods 13 and at least two groups of push rod locking blocks 14. A plurality of guide grooves 15 equal in number to the number of guide push rods 13 are provided on the clamping mechanism mounting seat 8. Each guide push rod 13 is movably arranged at a corresponding position of the clamping mechanism mounting seat 8 along the length direction through its guide rail in cooperation with the guide groove 15. The front end of each guide push rod 13 is respectively hinged to the profiled clamping heat dissipation assembly 12, and the push rod locking blocks 14 are arranged at the rear end of the corresponding guide push rod 13. The profiled clamping heat dissipation assembly 12 at least includes a parting hinge assembly 16 and a clamping profiled contact assembly 17. The clamping profiled contact assembly 17 is movably arranged at the front end of the corresponding guide push rod 13 through the parting hinge assembly 16.

[0028] At the same time, in order to improve the effectiveness of heat dissipation, the parting hinge group 16 described in the present application includes a blade back hinge group 18, a blade basin hinge group 19 and a blade top hinge group 20, and a blade top hinge group mounting column 21 is also provided on the clamping mechanism mounting seat 8. The blade back hinge group 18 and the blade basin hinge group 19 are respectively hinged in front of different guide push rods 13, and the blade top hinge group 20 is hinged on the clamping mechanism mounting seat 8 through the blade top hinge group mounting column 21. The clamping contoured contact piece group 17 is flexibly connected to the shape of the cross-section of the high-pressure turbine blade 4 through the corresponding blade back hinge group 18, blade basin hinge group 19 and spray top hinge group 20. Furthermore, in order to improve the degree of automation of the loose clamping during clamping, the push rod locking assembly 11 described in the present application also includes three groups of V-shaped guide springs 22, the blade back hinge group 18 and the blade basin hinge group 19 each include a main hinge 23 and two auxiliary hinges 24, the blade top hinge group 20 includes an auxiliary hinge 24, and the two auxiliary hinges 24 are respectively hinged on one of the main hinges 23, and the main hinges 23 are respectively hinged to the front ends of the corresponding guide push rods 13 with the cooperation of the corresponding V-shaped guide springs 22, and the auxiliary hinge 24 constituting the blade top hinge group 20 is hinged to the blade top hinge group mounting column 21 with the cooperation of the corresponding V-shaped guide springs 22, and the clamping contoured contact piece group 17 is respectively hinged on each of the auxiliary hinges 24. Combined with the shape of the cross-section of the high-pressure turbine blade, in order to improve the clamping performance and maximize the heat dissipation effect, each auxiliary hinge 24 of the present application includes two hinge heads 25, and the clamping contour contact member group 17 includes a plurality of contour contact blocks 26 whose number is equal to the number of hinge heads 25 on each auxiliary hinge 24. Each contour contact block 26 forms an active flexible clamping contact surface through the auxiliary hinge 24 and the main hinge 23 in cooperation with the guide push rod 13 and the V-shaped guide spring sheet 22.

[0029] In summary, the clamping device of the present application extensively uses SLM3D printing technology, has low manufacturing cost, good integrity, low difficulty in assembly and debugging, high efficiency, and can match high-vortex blades and other parts of different models by modifying the tenon and contact piece, and has a certain degree of versatility. The clamping method is simple, only need to push in the blade, push the push rod, make the contact block close to the blade, lock the push rod lock block, and the clamping operation can be completed. Through the two-stage parting hinge block, the deviation can be automatically corrected and the contact piece can be fitted to the blade for heat dissipation, avoiding the shortcomings of traditional tooling that requires customized positioning, difficult clamping, and poor fitting effect. Effectively reduce the labor intensity of operators and improve the efficiency and quality of high-vortex blade repair. Specific embodiments

[0031] The purpose of the present invention is to explore a new device for use in the process of engine blade additive manufacturing, in which poor heat dissipation leads to disordered blade microstructure, uncontrollable grain growth direction, and various macro problems resulting therefrom, such as undercut, collapse, and unfused defects. The present invention provides a device that can quickly adapt to and fit the blade profile, increase the heat dissipation area, reduce the influence of uneven wall thickness and ribs on the molten pool at the blade tip, thereby expanding the process window, improving the efficiency of blade additive manufacturing, and ensuring the quality of blade repair.

[0032] The objective of the present invention is achieved through the following technical solutions:

[0033] A flexible clamping device for additive repair of high-pressure turbine blades is designed, and its main structure includes: tenon base, slide rail bracket, push rod, push rod locking block, parting hinge block, contact block, guide elastic sheet, etc.

[0034] 1) Tenon base: The base has 4 mounting holes, which can fix the device well as a whole. The middle part of the base is designed with a tenon groove, which can limit the freedom of the high-vortex blade to be repaired to only the tenon groove direction, and provide an annular space for the slide rail bracket to enhance the overall structural strength;

[0035] 2) Slide rail bracket: The bottom of the slide rail bracket is connected to the tenon base, and the upper part is designed with a T-shaped slide groove to provide a single-degree-of-freedom motion structure for the push rod;

[0036] 3) Push rod: The push rod is used to move the structures such as the parting hinge block and the heat dissipation contact block forward and backward along the T-shaped slide groove. When it is far away from the blade, it can load and unload the high vortex blade. When it is close to the high vortex blade, it can be in close contact with the blade.

[0037] 4) Push rod lock block: lock the push rod at any position of the T-shaped slide slot through the cam mechanism;

[0038] 5) Parting hinge block: The parting hinge block consists of two levels, large and small. The first-level parting block provides large deviation correction for high-vortex blades and is connected to the second-level parting block through a hinge. The second-level parting block provides local small deviation correction for high-vortex blades and provides hinge connection points for the contact block;

[0039] 6) Contact block: According to the different blade states and process parameters, graphite or copper is used as the contact block material. The contact surface between the contact block and the blade is processed by the blade theoretical model, which can achieve conformal fitting with most blades. In addition, the two-stage parting hinge block is self-corrected. When approaching the blade profile, the position that first contacts the blade will serve as a fulcrum to convert the translational motion of the push rod into the rotational motion of multiple hinges, and finally achieve surface contact with the high-vortex blade, achieving good fit and heat dissipation;

[0040] 7) Guide elastic sheet: Guide elastic sheets are designed on both sides of the first and second level parting hinge blocks to roughly constrain the direction of the parting hinge blocks and keep the contact blocks in contact with the high vortex blades at a roughly correct angle.

[0041] Embodiment 1

[0042] The technical solution of the present application is further described in detail below in conjunction with the accompanying drawings, but the protection scope of the present application is not limited to the following.

[0043] The invention discloses an adaptive heat dissipation clamping device for high-pressure turbine rotor blades of an aero-engine, and its structure mainly comprises common parts such as a tenon base, a slide rail bracket, a push rod, a push rod locking block, a parting hinge block, a contact block schematic diagram, a guide elastic sheet, and a bearing.

[0044] The tenon base is used to pre-fix and limit the freedom of the blade so that the blade can only move in the tenon direction. The tenon base is connected to the slide rail bracket. The slide rail bracket and the push rod form a linear motion pair. The push rod locking block is responsible for locking the push rod at any position of the slide rail. When the push rod is pushed to make the contact block contact the blade body, the parting hinge block starts to rotate until the contact block is in good contact with the blade body. At this time, the push rod locking block is locked to complete the blade clamping.

[0045] When working it includes the following steps:

[0046] Push the blade in, push the push rod, make the contact block close to the blade, lock the push rod lock block, and the clamping operation is completed. Through the two-stage parting hinge block, the deviation can be automatically corrected and the heat can be dissipated by the contact piece fitting the blade.

[0047] The above is only a preferred embodiment of the present invention. It should be understood that the present invention is not limited to the form disclosed herein, and should not be regarded as excluding other embodiments, but can be used in various other combinations, modifications and environments, and can be modified within the scope of the concept described herein through the above teachings or the technology or knowledge of the relevant field. The changes and modifications made by those skilled in the art shall not deviate from the spirit and scope of the present invention, and shall be within the scope of protection of the claims attached to the present invention.

Claims

1. A clamping device for additive repair of high-pressure turbine blades of aircraft engines, characterized in that: The clamping device comprises a base frame (1), a supporting frame (2) and a flexible clamping and heat dissipation mechanism (3), wherein the supporting frame (2) is arranged on the base frame (1), and the flexible clamping and heat dissipation mechanism (3) is movably arranged on the supporting frame (2); during the additive repair process of the high-pressure turbine blade (4), the high-pressure turbine blade (4) supported on the corresponding part of the supporting frame (2) is clamped at its additive repair part by the flexible clamping and heat dissipation mechanism (3), The support fixing frame (2) comprises a support seat (7) and a clamping mechanism mounting seat (8), wherein the support seat (7) is movably arranged on a base (5) of the base frame (1), the clamping mechanism mounting seat (8) is supported on the base frame (1) via a support column (6), and the flexible clamping heat dissipation mechanism (3) is movably arranged on the clamping mechanism mounting seat (8). The flexible clamping and heat dissipation mechanism (3) comprises a push rod locking assembly (11) and a contoured clamping and heat dissipation assembly (12), wherein the contoured clamping and heat dissipation assembly (12) is movably arranged on the clamping mechanism mounting seat (8) through the push rod locking assembly (11); during the clamping process of the high-pressure turbine blade (4), the high-pressure turbine blade (4) whose lower end is supported on the support seat (7) is clamped on the clamping mechanism mounting seat (8) through the contoured clamping and heat dissipation assembly (12) in cooperation with the push rod locking assembly (11). The contour clamping heat dissipation assembly (12) comprises at least a parting hinge assembly (16) and a clamping contour contact assembly (17), wherein the clamping contour contact assembly (17) is movably arranged at the front end of the corresponding guide push rod (13) via the parting hinge assembly (16). The parting hinge assembly (16) comprises a blade back hinge assembly (18), a blade basin hinge assembly (19) and a blade top hinge assembly (20); a blade top hinge assembly mounting column (21) is further provided on the clamping mechanism mounting seat (8); the blade back hinge assembly (18) and the blade basin hinge assembly (19) are respectively hinged in front of different guide push rods (13); the blade top hinge assembly (20) is hinged on the clamping mechanism mounting seat (8) via the blade top hinge assembly mounting column (21); the clamping contour contact assembly (17) is movably connected to the cross-section shape of the high-pressure turbine blade (4) via the corresponding blade back hinge assembly (18), blade basin hinge assembly (19) and blade top hinge assembly (20); The clamping contoured contact member group (17) comprises a plurality of contoured contact blocks (26) whose number is equal to the number of hinged joints (25) on each auxiliary hinge frame (24), each contoured contact block (26) is made of graphite or copper, and the blade contact surface of each contoured contact block (26) is processed by a blade theoretical model.

2. The clamping device for additive repair of high-pressure turbine blades of an aircraft engine according to claim 1, characterized in that: The base frame (1) comprises a base (5) and a supporting column (6), and the base (5) and the supporting column (6) are respectively fixedly connected to corresponding parts of the supporting fixing frame (2).

3. The clamping device for additive repair of high-pressure turbine blades of an aircraft engine according to claim 1 or 2, characterized in that: Mutually adapted mortise grooves (9) and tenons (10) are respectively arranged on the base (5) and the support base (7); the support base (7) is movably arranged on the base (5) through the tenon (10) in cooperation with the mortise grooves (9); the base (5), the support column (6) and the clamping mechanism mounting base (8) are an integrated printed structure.

4. The clamping device for additive repair of high-pressure turbine blades of an aircraft engine according to claim 3, characterized in that: The push rod locking assembly (11) comprises at least two guide push rods (13) and at least two groups of push rod locking blocks (14). A plurality of guide grooves (15) whose number is equal to the number of the guide push rods (13) are provided on the clamping mechanism mounting seat (8). Each of the guide push rods (13) is movably arranged at a corresponding position of the clamping mechanism mounting seat (8) along a length direction through its guide rail in cooperation with the guide groove (15). The front end of each guide push rod (13) is respectively hinged to the contoured clamping heat dissipation assembly (12), and the push rod locking block (14) is arranged at the rear end of the corresponding guide push rod (13).

5. The clamping device for additive repair of high-pressure turbine blades of an aircraft engine according to claim 4, characterized in that: The push rod locking assembly (11) further includes three groups of V-shaped guide springs (22), the blade back hinge group (18) and the blade basin hinge group (19) each include a main hinge (23) and two auxiliary hinges (24), the blade top hinge group (20) includes an auxiliary hinge (24), the two auxiliary hinges (24) are respectively hinged on one of the main hinges (23), the main hinges (23) are respectively hinged to the front end of the corresponding guide push rod (13) with the cooperation of the corresponding V-shaped guide springs (22), the auxiliary hinge (24) constituting the blade top hinge group (20) is hinged to the blade top hinge group mounting column (21) with the cooperation of the corresponding V-shaped guide springs (22), and the clamping contour contact member group (17) is respectively hinged on each of the auxiliary hinges (24).

6. The clamping device for additive repair of high-pressure turbine blades of an aircraft engine according to claim 5, characterized in that: Each auxiliary hinge (24) comprises two hinged joints (25), and each of the contoured contact blocks (26) forms a movable flexible clamping contact surface through the auxiliary hinge (24) and the main hinge (23) in cooperation with the guide push rod (13) and the V-shaped guide spring sheet (22).

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