Turbine blade machining method and tool clamp

Abstract

The invention relates to the technical field of aviation turbine blade manufacturing, and particularly discloses a turbine blade machining method and a tool clamp. The turbine blade machining method comprises the steps that the surface of a to-be-machined blade is cleaned, a theoretical positioning point of the to-be-machined blade is determined, the tool clamp is designed according to the theoretical positioning point on the to-be-machined blade, and the to-be-machined blade is machined. Installing the to-be-machined blade on the tool clamp, retesting the to-be-machined blade by using optical detection equipment to obtain an actual positioning point, adjusting the position of the tool clamp, controlling the deviation value between the actual positioning point and the theoretical positioning point within a preset range value, and machining the to-be-machined blade into a finished product. According to the method, the optical detection equipment can be used for retesting the to-be-machined blade, and the position of the tool clamp is adjusted, so that the deviation value of the actual positioning point and the theoretical positioning point is controlled within the preset range value, and the problem that in the prior art, when the titanium-aluminum alloy turbine blade is machined, no positioning reference exists, and consequently the turbine blade qualification rate is poor is solved.

Description

Technical Field

[0001] The invention relates to the technical field of aviation turbine blade manufacturing, and in particular to a turbine blade processing method and a tooling fixture. Background Art

[0002] In recent years, with the development of commercial aircraft engines, in order to improve fuel economy, new materials with high strength, high stiffness and low density have begun to be widely used in engine parts. Among them, titanium aluminum alloy has high specific strength, high specific modulus and excellent oxidation resistance. It is the most promising lightweight and high temperature resistant structural material for aerospace. Titanium aluminum alloy is mainly used abroad to manufacture low-pressure turbine blades of aircraft engines, automotive supercharger turbines and exhaust valves.

[0003] Among them, the titanium-aluminum alloy solution has poor fluidity, high heat sensitivity and low casting qualification rate. Once the total length of the blade exceeds 300mm, the casting qualification rate drops to 3%-5%. For titanium-aluminum alloy turbine blades with a total length of more than 300mm, electron beam selective melting is generally used. Electron beam selective melting (EBSM) is a rapid manufacturing technology that uses high-energy and high-speed electron beams to selectively bombard metal powders, thereby melting and forming powder materials. Its process is similar to selective laser melting (SLM). The difference is that the processing heat source uses a high-energy electron beam. Its advantages are high energy utilization, large action depth, high material absorption rate, high forming efficiency, small part deformation, no metal support is required during the forming process, and the microstructure is denser. Compared with laser melting technology, its disadvantage is that it is difficult to obtain parts with high surface quality and low roughness, and precision processing is required later.

[0004] However, the titanium-aluminum alloy blank formed by electron beam welding in the prior art has poor plasticity, high hardness, low fracture toughness and low thermal conductivity at room temperature. The titanium-aluminum alloy blank formed by electron beam welding lacks a blank positioning reference in this process, and the finished turbine blades not only have high requirements on dimensional accuracy and surface roughness, but also the material is difficult to cut, and is prone to defects such as surface hardening, micro-pits, and micro-cracks. Summary of the invention

[0005] The purpose of the present invention is to provide a processing method and a tooling fixture for turbine blades, so as to solve the problem in the prior art that titanium-aluminum alloy turbine blades formed by electron beam welding lack positioning references, resulting in a poor turbine blade qualification rate.

[0006] In one aspect, the present invention provides a method for processing a turbine blade, the method comprising:

[0007] Clean the surface of the blade to be processed;

[0008] Obtaining the theoretical positioning point of the blade to be processed;

[0009] Design a fixture according to theoretical positioning points on the blade to be processed, and install the blade to be processed on the fixture, so that the fixture can limit the movement of the blade to be processed along the X-axis direction, the Y-axis direction and the Z-axis direction, and the rotation around the X-axis, the Y-axis and the Z-axis;

[0010] Use optical detection equipment to re-measure the blade to be processed, obtain the actual positioning point, and determine the deviation value between the actual positioning point and the theoretical positioning point;

[0011] Adjust the position of the fixture to control the deviation between the actual positioning point and the theoretical positioning point within a preset range;

[0012] Process the blades to be processed into finished products.

[0013] As an optional technical solution for the processing method of turbine blades, multiple theoretical positioning points of the blades to be processed are obtained, including:

[0014] According to the six-point positioning principle, six theoretical positioning points are obtained on the blade to be processed;

[0015] Among them, the six theoretical positioning points are A1, A2, A3, B1, B2, and C1. A1, A2, B1, and C1 are all located at the root of the blade to be processed, and A3 and B2 are located at the crown of the blade to be processed.

[0016] As an optional technical solution for the processing method of the turbine blade, the blade to be processed is mounted on a fixture, including:

[0017] The fixture comprises a base, a blade crown positioning part and a blade root positioning part, and the blade crown positioning part and the blade root positioning part are arranged on the base at intervals;

[0018] Installing the blade crown of the blade to be processed on the blade crown positioning part, and positioning the blade crown using the blade crown positioning part;

[0019] The blade root of the blade to be processed is mounted on the blade root positioning part, and the blade root is positioned by using the blade root positioning part.

[0020] As an optional technical solution for the processing method of the turbine blade, the position of the fixture is adjusted to compensate for the deviation between the actual positioning point and the theoretical positioning point, including:

[0021] The deviation between the actual positioning point and the theoretical positioning point is less than 0.1mm.

[0022] As an optional technical solution for the processing method of the turbine blade, the blade to be processed is processed into a finished product, including:

[0023] Use carbide cutters to perform rough machining on the blade roots of the blades to be machined;

[0024] The blade root that has been roughly machined is finely machined again to obtain the finished blade to be processed.

[0025] As an optional technical solution for the processing method of turbine blades, cleaning the surface of the blade to be processed includes:

[0026] Remove surface protrusions, burrs and pits from the blade to be processed.

[0027] On the other hand, the present invention provides a fixture, which is applied to the processing method of the turbine blade in any of the above schemes, and the fixture comprises:

[0028] Base;

[0029] A blade crown positioning part is arranged at one end of the base, and the blade crown positioning part includes a blade crown positioning seat and a first positioning structure and a second positioning structure arranged on the blade crown positioning seat, wherein the first positioning structure can abut against a theoretical positioning point A3 of the blade to be processed, and the second positioning structure can abut against a theoretical positioning point B2;

[0030] The blade root positioning part is arranged at the other end of the base, and the blade root positioning part includes a blade root positioning seat and a third positioning structure, a fourth positioning structure, a fifth positioning structure and a sixth positioning structure arranged on the blade root positioning seat. The third positioning structure can abut against the theoretical positioning point A1, the fourth positioning structure can abut against the theoretical positioning point A2, the fifth positioning structure can abut against the theoretical positioning point B1, and the sixth positioning structure can abut against the theoretical positioning point C1.

[0031] As an optional technical solution for the tooling fixture, the third positioning structure and the fourth positioning structure can be set telescopically, and the third positioning structure includes a first adjusting bolt and an abutment block. One end of the first adjusting bolt passes through the blade root positioning seat and cooperates with the blade root positioning seat thread. One end of the first adjusting bolt is connected to one end of the abutment block, and the other end of the abutment block can abut against the theoretical positioning point A1.

[0032] As an optional technical solution for the tooling fixture, the blade root positioning part also includes a seventh positioning structure, which includes a second adjusting bolt, a pressure block, a spherical top block and a guide block. The guide block has a circular groove, one end of the second adjusting bolt passes through the blade root positioning seat and is threadedly engaged with the blade root positioning seat, one end of the second adjusting bolt is connected to one end of the pressure block, the spherical top block is installed at the other end of the pressure block, the spherical top block is located in the circular groove, and the guide block can abut against the blade to be processed.

[0033] As an optional technical solution for the tooling fixture, the tooling fixture also includes a blade crown outlet side clamping seat and a blade root outlet side clamping seat. The blade crown outlet side clamping seat and the blade crown positioning seat are hinged and can clamp the blade crown. The blade root outlet side clamping seat and the blade root positioning seat are hinged and can clamp the blade root.

[0034] The beneficial effects of the present invention are:

[0035] The invention provides a method for processing a turbine blade, which comprises: firstly, cleaning the surface of the blade to be processed, then determining the theoretical positioning point of the blade to be processed, the purpose of which is to limit the degree of freedom of the blade to be processed, then designing a tooling fixture according to the theoretical positioning point on the blade to be processed, and installing the blade to be processed on the tooling fixture, using the tooling fixture to limit the movement of the blade to be processed along the X-axis direction, the Y-axis direction and the Z-axis direction and the rotation around the X-axis, the Y-axis and the Z-axis, using an optical detection device to re-measure the blade to be processed to obtain an actual positioning point, and judging the deviation value between the actual positioning point and the theoretical positioning point, then adjusting the position of the tooling fixture, so as to control the deviation value between the actual positioning point and the theoretical positioning point within a preset range value, and finally processing the blade to be processed into a finished product. By adopting the processing method of turbine blades provided by the present invention, optical detection equipment can be used to re-measure the blades to be processed, and the position of the tooling fixture can be adjusted so that the deviation value between the actual positioning point and the theoretical positioning point is controlled within a preset range value, thereby ensuring the dimensional stability of the blades to be processed, thereby improving the processing efficiency and the qualified rate, and effectively solving the problem in the prior art of lacking a positioning reference in titanium-aluminum alloy turbine blades formed by electron beam welding, resulting in a poor qualified rate of turbine blades. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 is a flow chart of a method for processing a turbine blade according to an embodiment of the present invention;

[0037] Figure 2 It is a schematic diagram of the structure in which a blade to be processed is installed on a fixture in an embodiment of the present invention;

[0038] Figure 3 is a cross-sectional view of a fixture in an embodiment of the present invention;

[0039] Figure 4 is a cross-sectional view of the fixture in another embodiment of the present invention;

[0040] Figure 5 A cross-sectional view of a partial structure of a blade root positioning portion in an embodiment of the present invention;

[0041] Figure 6 It is a schematic diagram of the structure of the seventh positioning structure part in an embodiment of the present invention;

[0042] Figure 7 Schematic diagram of the structure of the blade to be processed in an embodiment of the present invention.

[0043] In the figure:

[0044] 1. Blade to be processed; 11. Leaf crown; 12. Leaf root;

[0045] 2. Base;

[0046] 3. Blade crown positioning part; 31. Blade crown positioning seat; 32. First positioning structure; 33. Second positioning structure; 34. Eighth positioning structure;

[0047] 4. Blade root positioning part; 41. Blade root positioning seat; 42. Third positioning structure; 421. First adjusting bolt; 422. Abutment block; 43. Fourth positioning structure; 44. Fifth positioning structure; 45. Sixth positioning structure; 46. Seventh positioning structure; 461. Second adjusting bolt; 462. Pressing block; 463. Spherical top block; 464. Guide block;

[0048] 5. Compression seat on the outlet side of the blade crown; 51. First seat body; 52. First compression bolt; 53. First compression block; 54. First connecting block;

[0049] 6. Compression seat at the air outlet side of the blade root; 61. Second seat body; 62. Second compression bolt; 63. Second compression block; 64. Second connecting block. DETAILED DESCRIPTION

[0050] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0051] In the description of the present invention, it should be noted that the orientations or positional relationships indicated by the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance. Among them, the terms "first position" and "second position" are two different positions, and the first feature "above", "above" and "above" the second feature include the first feature being directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. The first feature "below", "below" and "below" the second feature include the first feature being directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0052] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it 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 it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0053] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.

[0054] like Figure 1 As shown, the present embodiment provides a method for processing a turbine blade, the method comprising: first, cleaning the surface of a blade 1 to be processed, then determining a theoretical positioning point of the blade 1 to be processed, the purpose of which is to limit the degree of freedom of the blade 1 to be processed, then designing a jig according to the theoretical positioning point on the blade 1 to be processed, and installing the blade 1 to be processed on the jig, using the jig to limit the movement of the blade 1 to be processed along the X-axis direction, the Y-axis direction and the Z-axis direction and the rotation around the X-axis, the Y-axis and the Z-axis, using an optical detection device to re-measure the blade 1 to be processed, obtaining an actual positioning point, and determining a deviation value between the actual positioning point and the theoretical positioning point, then adjusting the position of the jig, so as to control the deviation value between the actual positioning point and the theoretical positioning point within a preset range, and finally processing the blade 1 to be processed into a finished product. By adopting the processing method of turbine blades provided by the present invention, optical detection equipment can be used to re-measure the blade 1 to be processed, and the position of the tooling fixture can be adjusted so that the deviation value between the actual positioning point and the theoretical positioning point is controlled within a preset range value, thereby ensuring the dimensional stability of the blade 1 to be processed, thereby improving the processing efficiency and the qualified rate, and effectively solving the problem in the prior art that there is a lack of positioning reference in titanium-aluminum alloy turbine blades formed by electron beam welding, resulting in a poor qualified rate of turbine blades.

[0055] In this embodiment, a plurality of theoretical positioning points of the blade 1 to be processed are obtained, including: according to the six-point positioning principle, six theoretical positioning points are obtained on the blade 1 to be processed, so as to limit the movement of the blade 1 to be processed along the X-axis direction, the Y-axis direction and the Z-axis direction and the rotation around the X-axis, the Y-axis and the Z-axis; specifically, Figure 7 As shown, the six theoretical positioning points are A1, A2, A3, B1, B2, and C1, A1 and A2 and B1 and C1 are all located at the blade root 12 of the blade 1 to be processed, and A3 and B2 are located at the blade crown 11 of the blade 1 to be processed.

[0056] It should be noted that the six-point positioning principle means that in space, a rigid body has six degrees of freedom, including the freedom of movement along the three rectangular coordinate axes of X, Y, and Z and the freedom of rotation around these three coordinate axes. In order to completely determine the position of the rigid body, these six degrees of freedom must be eliminated. Usually, the six degrees of freedom of the rigid body are limited by setting six support points (i.e., positioning elements), where each support point limits a corresponding degree of freedom.

[0057] Specifically, the blade 1 to be processed is installed on a tooling fixture, including: the tooling fixture includes a base 2, a blade crown positioning part 3 and a blade root positioning part 4, and the blade crown positioning part 3 and the blade root positioning part 4 are arranged on the base 2 at intervals; in this solution, the blade crown 11 of the blade 1 to be processed can be installed on the blade crown positioning part 3, and the blade crown 11 is positioned by using the blade crown positioning part 3; at the same time, the blade root 12 of the blade 1 to be processed is installed on the blade root positioning part 4, and the blade root 12 is positioned by using the blade root positioning part 4, so as to ensure that the blade 1 to be processed can be stably installed.

[0058] In some embodiments, the position of the fixture is adjusted to compensate for the deviation between the actual positioning point and the theoretical positioning point, including: the deviation between the actual positioning point and the theoretical positioning point is less than 0.1 mm. Such an arrangement can ensure that the fixture can accurately clamp the theoretical positioning point, thereby ensuring the dimensional stability of the blade 1 to be processed, and improving the processing efficiency and qualified rate.

[0059] At the same time, in order to ensure that the blade 1 to be processed can be clamped in the same correct position each time, after pressing at each relative positioning position, it is necessary to use a 0.02 feeler gauge to detect the light leakage between the blade 1 to be processed and each positioning mechanism. No light leakage means that the clamping is correct, so that the relative position size required for the finished product can be processed.

[0060] Specifically, processing the blade 1 to be processed into a finished product includes: using a carbide tool to perform rough processing on the blade root 12 of the blade 1 to be processed; and fine processing the roughly processed blade root 12 again to obtain the finished blade 1 to be processed.

[0061] The specific steps are as follows: rough machining is performed on the tenon area of ​​the blade root 12 of the blade 1 to be machined. First, the bottom surface of the tenon is roughened using the bottom blade of a φ20 carbide end mill, with a linear speed of 60m / min, a feed of 0.1mm per tooth, and a cutting depth of 1mm; then, the non-working surface of the blade root and the lower surface of the edge plate are rough machined using the side blade of a carbide cutter; adaptive milling is used for the complex-shaped blade root intermediate weight-reducing groove, which automatically adjusts the cutting strategy and cutting parameters in real time according to the tool status, workpiece surface quality, and shape structure to reduce cutting force fluctuations and maintain good machining quality.

[0062] Then, the tenon area of ​​the blade root 12 of the blade 1 to be processed is finished, and the designed blade root tooth forming tool is used to finish the tenon working surface, non-working surface and lower surface of the edge plate, with a linear speed of 100m / min, a feed of 0.05mm per tooth, and a side edge cutting depth of 0.2mm.

[0063] Specifically, cleaning the surface of the blade 1 to be processed includes removing protrusions, burrs and pits on the surface of the blade 1 to be processed, so as to ensure the smoothness of the surface of the blade 1 to be processed.

[0064] like Figure 2 and Figure 7 As shown, this embodiment also provides a tooling fixture, which is applied to the processing method of the turbine blade in the above scheme, and the tooling fixture includes: a base 2, a blade crown positioning part 3 and a blade root positioning part 4. Among them, the blade crown positioning part 3 is arranged at one end of the base 2, and the blade crown positioning part 3 includes a blade crown positioning seat 31 and a first positioning structure 32 and a second positioning structure 33 arranged on the blade crown positioning seat 31. The first positioning structure 32 can abut against the theoretical positioning point A3 of the blade 1 to be processed, and the second positioning structure 33 can abut against the theoretical positioning point B2; such a setting can achieve the purpose of positioning the blade crown 11 of the blade 1 to be processed.

[0065] At the same time, the blade root positioning part 4 is arranged at the other end of the base 2, and the blade root positioning part 4 includes a blade root positioning seat 41 and a third positioning structure 42, a fourth positioning structure 43, a fifth positioning structure 44 and a sixth positioning structure 45 arranged on the blade root positioning seat 41, the third positioning structure 42 can abut against the theoretical positioning point A1, the fourth positioning structure 43 can abut against the theoretical positioning point A2, the fifth positioning structure 44 can abut against the theoretical positioning point B1, and the sixth positioning structure 45 can abut against the theoretical positioning point C1. In this way, the purpose of positioning the blade root 12 can be achieved to limit the movement of the blade 1 to be processed along the X-axis direction, the Y-axis direction and the Z-axis direction and the rotation around the X-axis, the Y-axis and the Z-axis.

[0066] Optionally, the blade crown positioning part 3 further includes an eighth positioning structure 34, which is telescopically arranged, and includes a telescopic nut and a telescopic block, one end of the telescopic nut penetrates into the blade crown positioning seat 31 and is threadedly matched with the blade crown positioning seat 31, one end of the telescopic nut is connected to one end of the telescopic block, and the other end of the telescopic block can abut against the blade crown 11. In this arrangement, the telescopic length of the eighth positioning structure 34 can be adjusted to further ensure the stability of the positioning of the blade crown 11.

[0067] Specifically, the third positioning structure 42 and the fourth positioning structure 43 can be telescopically arranged, and the third positioning structure 42 includes a first adjusting bolt 421 and an abutting block 422. One end of the first adjusting bolt 421 penetrates the blade root positioning seat 41 and is threadedly matched with the blade root positioning seat 41. One end of the first adjusting bolt 421 is connected to one end of the abutting block 422, and the other end of the abutting block 422 can abut against the theoretical positioning point A1. In this arrangement, the first adjusting bolt 421 can be screwed to adjust the abutting block 422 to abut against the theoretical positioning point A1.

[0068] In this embodiment, the blade root positioning part 4 also includes a seventh positioning structure 46, wherein the seventh positioning structure 46 includes a second adjusting bolt 461, a pressure block 462, a spherical top block 463 and a guide block 464, wherein the guide block 464 has a circular groove, one end of the second adjusting bolt 461 penetrates into the blade root positioning seat 41, and is threadedly matched with the blade root positioning seat 41, one end of the second adjusting bolt 461 is connected to one end of the pressure block 462, the spherical top block 463 is installed at the other end of the pressure block 462, the spherical top block 463 is located in the circular groove, and the guide block 464 can abut against the blade 1 to be processed. In this way, during the pressing process, the pressure block 462 can be freely adjusted in all directions according to the height of the contour of the blade 1 to be processed, so as to avoid long-term squeezing of the high point of the blade 1 to be processed to cause local compression deformation and fragmentation.

[0069] Specifically, the tooling fixture also includes a blade crown outlet side clamping seat 5 and a blade root outlet side clamping seat 6. The blade crown outlet side clamping seat 5 and the blade crown positioning seat 31 are hinged and can clamp the blade crown 11. The blade root outlet side clamping seat 6 and the blade root positioning seat 41 are hinged and can clamp the blade root 12.

[0070] Alternatively, if Figure 3 As shown, the blade crown outlet side clamping seat 5 includes a first seat body 51, a first clamping bolt 52, a first clamping block 53 and a first connecting block 54. The first seat body 51 and the blade crown positioning seat 31 are hinged. One end of the first clamping bolt 52 is inserted into the first connecting block 54 and the first seat body 51 in sequence, and is threadedly matched with the first seat body 51 and the first connecting block 54. One end of the first clamping bolt 52 is connected to the first clamping block 53. The first clamping block 53 can clamp the blade crown 11. The first connecting block 54 is connected to the first seat body 51 by bolts.

[0071] Alternatively, if Figure 4As shown, the blade root outlet side clamping seat 6 includes a second seat body 61, a second clamping bolt 62, a second clamping block 63 and a second connecting block 64. The second seat body 61 and the blade crown positioning seat 31 are hinged. One end of the second clamping bolt 62 is inserted into the second connecting block 64 and the second seat body 61 in sequence, and is threadedly matched with the second seat body 61 and the second connecting block 64. One end of the second clamping bolt 62 is connected to the second clamping block 63. The second clamping block 63 can clamp the blade crown 11. The second connecting block 64 is connected to the second seat body 61 by bolts.

[0072] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the embodiments here. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. A method for processing a turbine blade, characterized in that: include: Cleaning the surface of the blade (1) to be processed; Obtaining a theoretical positioning point of the blade (1) to be processed; A jig is designed according to theoretical positioning points on the blade to be processed (1), and the blade to be processed (1) is mounted on the jig, so that the jig can limit the movement of the blade to be processed (1) along the X-axis direction, the Y-axis direction and the Z-axis direction, and the rotation around the X-axis, the Y-axis and the Z-axis; Re-measure the blade (1) to be processed by using an optical detection device to obtain an actual positioning point, and determine a deviation value between the actual positioning point and the theoretical positioning point; Adjusting the position of the fixture to control the deviation between the actual positioning point and the theoretical positioning point within a preset range; The blade to be processed (1) is processed into a finished product.

2. The method for processing a turbine blade according to claim 1, characterized in that: Acquiring the plurality of theoretical positioning points of the blade to be processed (1) comprises: According to the six-point positioning principle, six theoretical positioning points are obtained on the blade (1) to be processed; The six theoretical positioning points are A1, A2, A3, B1, B2 and C1, A1 and A2 and B1 and C1 are all located at the blade root (12) of the blade to be processed (1), and A3 and B2 are located at the blade crown (11) of the blade to be processed (1).

3. The method for processing a turbine blade according to claim 1, characterized in that: The blade to be processed (1) is mounted on the fixture, comprising: The fixture comprises a base (2), a blade crown positioning portion (3) and a blade root positioning portion (4), wherein the blade crown positioning portion (3) and the blade root positioning portion (4) are arranged on the base (2) at intervals; The blade crown (11) of the blade to be processed (1) is mounted on the blade crown positioning portion (3), and the blade crown (11) is positioned using the blade crown positioning portion (3); The blade root (12) of the blade to be processed (1) is mounted on the blade root positioning portion (4), and the blade root (12) is positioned using the blade root positioning portion (4).

4. The method for processing a turbine blade according to claim 1, characterized in that: Adjusting the position of the fixture to compensate for the deviation between the actual positioning point and the theoretical positioning point includes: The deviation between the actual positioning point and the theoretical positioning point is less than 0.1 mm.

5. The method for processing a turbine blade according to claim 1, characterized in that: Processing the blade to be processed (1) into a finished product comprises: Using a carbide cutter to perform rough machining on the blade root (12) of the blade to be machined (1); The blade root (12) that has been roughly machined is finely machined again to obtain the finished blade (1) to be machined.

6. The method for machining a turbine blade according to claim 1, characterized in that: Cleaning the surface of the blade (1) to be processed comprises: The surface protrusions, burrs and pits of the blade (1) to be processed are removed.

7. A fixture, characterized in that: The method for processing a turbine blade according to any one of claims 1 to 6 is applied, wherein the fixture comprises: Base (2); A blade crown positioning portion (3) is arranged at one end of the base (2), the blade crown positioning portion (3) comprising a blade crown positioning seat (31) and a first positioning structure (32) and a second positioning structure (33) arranged on the blade crown positioning seat (31), the first positioning structure (32) being able to abut against a theoretical positioning point A3 of the blade to be processed (1), and the second positioning structure (33) being able to abut against the theoretical positioning point B2; A blade root positioning portion (4) is arranged at the other end of the base (2), and the blade root positioning portion (4) includes a blade root positioning seat (41) and a third positioning structure (42), a fourth positioning structure (43), a fifth positioning structure (44) and a sixth positioning structure (45) arranged on the blade root positioning seat (41), the third positioning structure (42) can abut against the theoretical positioning point A1, the fourth positioning structure (43) can abut against the theoretical positioning point A2, the fifth positioning structure (44) can abut against the theoretical positioning point B1, and the sixth positioning structure (45) can abut against the theoretical positioning point C1.

8. The fixture according to claim 7, characterized in that: The third positioning structure (42) and the fourth positioning structure (43) can both be telescopically arranged, and the third positioning structure (42) includes a first adjusting bolt (421) and an abutment block (422), one end of the first adjusting bolt (421) penetrates into the blade root positioning seat (41) and is threadedly matched with the blade root positioning seat (41), one end of the first adjusting bolt (421) is connected to one end of the abutment block (422), and the other end of the abutment block (422) can abut against the theoretical positioning point A1.

9. The fixture according to claim 7, characterized in that: The blade root positioning portion (4) also includes a seventh positioning structure (46), and the seventh positioning structure (46) includes a second adjusting bolt (461), a pressure block (462), a spherical top block (463) and a guide block (464), wherein the guide block (464) has a circular groove, one end of the second adjusting bolt (461) penetrates into the blade root positioning seat (41) and is threadedly matched with the blade root positioning seat (41), one end of the second adjusting bolt (461) is connected to one end of the pressure block (462), the spherical top block (463) is installed on the other end of the pressure block (462), the spherical top block (463) is located in the circular groove, and the guide block (464) can abut against the blade (1) to be processed.

10. The fixture according to claim 7, characterized in that: The tooling fixture further comprises a blade crown outlet side pressing seat (5) and a blade root outlet side pressing seat (6); the blade crown outlet side pressing seat (5) and the blade crown positioning seat (31) are hingedly connected and are capable of pressing the blade crown (11); the blade root outlet side pressing seat (6) and the blade root positioning seat (41) are hingedly connected and are capable of pressing the blade root (12).

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