Positioning Method, Device and Storage Medium for Machining Gas Film Cooling Holes of Turbine Blades

Abstract

The present invention discloses a positioning method, device, and storage medium for machining film cooling holes in aircraft engine turbine blades. The positioning method includes: setting a theoretical coordinate system and a set of positioning points based on a three-dimensional model of the blade; installing the turbine blade on a CNC machine tool and measuring the actual point set corresponding to the preset positioning points; calculating a spatial transformation matrix from the theoretical coordinate system to the machine tool coordinate system based on the correspondence between the preset positioning point set and the actual measured point set; executing an iterative process of "on-machine measurement-calculation of spatial transformation-estimation of error" if the error after the spatial transformation is greater than a given threshold; and calculating the optimal positioning posture of the blade after completion, determining the position parameters of the film hole to be machined, and guiding the precise machining of the film hole. For CNC machining of aircraft engine turbine blades with complex curved surfaces, the present invention provides a precise and efficient digital positioning solution that can effectively solve the problems of large errors and low efficiency in machining film holes in turbine blades.

Description

Technical Field

[0001] The present invention belongs to the technical field of aero-engine turbine blade manufacturing, and specifically relates to a positioning method, device and storage medium for machining film cooling holes of turbine blades. Background Art

[0002] Turbine blades are key components for achieving the performance of aircraft turbofan engines. Due to their need to operate stably under extremely high temperatures and high speeds, aircraft engine turbine blades are typically designed as thin-walled structures with complex internal cavities and arrays of film cooling holes on the surface. Their outer contours are complex free-form surfaces that meet aerodynamic performance requirements. During engine operation, cool air flows from the turbine blade's internal cavity through hundreds of film cooling holes on its surface, forming a film layer on the blade's surface that insulates the high-temperature air and prevents the blade itself from reaching dangerously high temperatures.

[0003] Achieving high-precision machining of film cooling holes has an important impact on stabilizing the cooling performance of turbine blades and ensuring the safe and efficient operation of aircraft engines. Since turbine blades with complex curved surfaces and inner cavity structures usually adopt casting technology, there will be contour errors on the blade surface, and there will also be clamping and positioning errors when machining film cooling holes. If the machining program is directly generated according to the design drawings after the blades are installed on the CNC machine tool, the position and angle distribution of the film cooling holes after machining will be uneven and unreasonable, resulting in large machining errors. For a long time, in order to improve the machining positioning accuracy of turbine blades, the spatial position and posture of the blades on the machine tool are usually manually assisted in alignment and correction. However, the error of this method is still too large and the work efficiency is low, which cannot fully meet the needs of high-precision machining of turbine blade film cooling holes. Summary of the Invention

[0004] In response to the above-mentioned defects of the prior art, the first aspect of the present invention provides a method for precisely positioning a blade workpiece and determining the position of the film holes to be processed during the CNC machining of film cooling holes on turbine blades, thereby effectively solving the problem of large machining errors and low efficiency of the film hole array on the surface of the turbine blade.

[0005] A second aspect of the present invention provides a device for machining film cooling holes for turbine blades, which aims to implement the digital precision positioning method for machining film cooling holes for turbine blades provided in the embodiment of the first aspect.

[0006] A third aspect of the present invention provides a non-volatile computer-readable storage medium, which is intended to implement the digital precision positioning method for the turbine blade film cooling hole processing process provided by the embodiment of the first aspect.

[0007] A positioning method for machining a film cooling hole for a turbine blade according to an embodiment of the first aspect of the present invention includes:

[0008] S1, set the ideal three-dimensional model of the turbine blade, in which there is a theoretical coordinate system SYS0 and multiple preset positioning point sets Ω0 (n, x, y, z);

[0009] S2, installing the turbine blade on a CNC machine tool. On the turbine blade, there are obvious geometric features corresponding to the preset positioning points. Preliminary measurement is performed to obtain the set Ω1(n, x, y, z) corresponding to the preset positioning point set Ω0(n, x, y, z) in the CNC machine tool coordinate system SYS1.

[0010] S3, set an error function Φ as a representation of the deviation between Ω0(n,x,y,z) and Ω1(n,x,y,z), and set a threshold Φ(min) for the error function Φ;

[0011] S4, set a point set Ω and assign Ω1(n,x,y,z) to Ω;

[0012] S5, calculate the spatial transformation matrix M from SYS0 to SYS1 according to the preset positioning point set Ω0(n,x,y,z) and Ω;

[0013] S6, calculate the nominal position Ω0(n,x,y,z)* of the preset positioning point set Ω0(n,x,y,z) in the machine tool coordinate system SYS1 according to the spatial transformation matrix M;

[0014] S7, measuring the coordinates of the turbine blade on the CNC machine tool according to the coordinate data of each point of Ω0(n,x,y,z)*, obtaining the corresponding point set Ω2(n,x,y,z), and assigning Ω2(n,x,y,z) to Ω;

[0015] S8, calculate the specific value of the error function Φ based on Ω0(n,x,y,z)* and Ω;

[0016] S9, based on the threshold Φ(min) and the specific value of the error function Φ obtained in step S8, execute steps S5-S9 again until the specific value of the error function Φ obtained in step S8 is less than the threshold Φ(min);

[0017] S10, obtaining a best-fit position mapping relationship between the three-dimensional model of the turbine blade and the turbine blade actually installed on the CNC machine tool according to the spatial transformation matrix M;

[0018] S11, transforming the to-be-machined feature P on the three-dimensional model of the turbine blade into a corresponding surface position parameter P* of the turbine blade on the CNC machine tool according to the spatial transformation matrix M; and

[0019] S12, based on the position parameter P* on the machine tool coordinate system SYS1, edit the NC machining instructions to perform precision machining of the air film holes on the turbine blades.

[0020] Compared with the relevant technology, the positioning method for processing film cooling holes of turbine blades provided by the embodiment of the first aspect of the present invention has at least the following beneficial effects: Since the turbine blades of aircraft engines have extremely complex curved surface structures, the position accuracy of the workpiece after installation on the CNC machine tool is difficult to fully guarantee. The positioning method for processing film cooling holes of turbine blades provided by the embodiment of the first aspect of the present invention is a multiple iteration method based on on-machine measurement, which can accurately measure the spatial position and posture of the turbine blade on the CNC machine tool, thereby providing a precise and efficient digital tool for determining the machine tool positioning relationship of the turbine blade, and performing film hole positioning and processing.

[0021] In some embodiments, the feature P to be processed includes the coordinates of an air film hole.

[0022] In some embodiments, the specific method for calculating the spatial transformation matrix M from SYS0 to SYS1 based on the preset positioning point set Ω0 (n, x, y, z) and Ω is:

[0023] S510, calculate the centroid of two point sets Ω0(n, x, y, z) and Ω using formula (1):

[0024]

[0025] S520, solve the spatial transformation matrix M by using the singular value decomposition (SVD) method commonly used in linear algebra theory:

[0026]

[0027] In formula (2), H is the intermediate matrix, U, S, and V are the decomposition matrices obtained by processing H using SVD decomposition, R is the calculated rotation matrix, and T is the calculated translation matrix. The spatial transformation matrix M consists of two parts: R and T.

[0028] In some embodiments, the specific method for calculating the nominal position Ω0(n, x, y, z)* of the preset point set Ω0(n, x, y, z) in the machine tool coordinate system SYS1 according to the spatial transformation matrix M is:

[0029] The formula for calculating the nominal position Ω0(n, x, y, z)* using the spatial transformation matrix M and the preset point set Ω0(n, x, y, z) is shown in formula (3):

[0030] Ω0(n,x,y,z)*=R×Ω0(n,x,y,z)+T (3)

[0031] In some embodiments, a method for calculating a specific value of the error function Φ based on Ω0(n, x, y, z)* and Ω is:

[0032] The maximum distance between the point set Ω0(n,x,y,z)* in the machine tool coordinate system and the corresponding point in Ω is taken as the specific value of the error function Φ.

[0033] In some embodiments, according to the spatial transformation matrix M, the feature to be processed P on the three-dimensional model of the turbine blade is transformed into the corresponding surface position parameter P* of the turbine blade on the CNC machine tool as follows:

[0034] The formula for calculating the corresponding surface position parameter P* through the spatial transformation matrix M and the feature to be processed P is shown in formula (4):

[0035] P*=R×P+T (4)

[0036] In some embodiments, based on the position parameter P* on the machine tool coordinate system SYS1, a specific method for editing a NC machining instruction to perform precision machining of film holes on a turbine blade is as follows:

[0037] Import the position parameter P* on the machine tool coordinate system SYS1 into the NC machining program and generate NC machining instructions for machining.

[0038] According to the second aspect of the present invention, a turbine blade film cooling hole processing device is provided, which includes a control device, the control device includes a central processing unit and a memory, the memory stores a computer program, and the processor is used to implement the steps of the positioning method for processing the turbine blade film cooling hole described in the first aspect of the embodiment when executing the computer program.

[0039] According to the non-volatile computer-readable storage medium provided in the third embodiment of the present invention, the computer program is stored. When the computer program is executed by a processor, the positioning method for machining the film cooling hole of the turbine blade described in the first embodiment is implemented. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 is a flow chart of a positioning method for machining film cooling holes for turbine blades in one embodiment of the present invention;

[0041] Figure 2 Schematic diagram of selecting six positioning points on a turbine blade in a positioning method for machining film cooling holes for a turbine blade according to an embodiment of the present invention;

[0042] Figure 3 It is a schematic diagram of a turbine blade film cooling hole processing device and a turbine blade in one embodiment of the present invention.

[0043] Figure 4It is a schematic diagram of the iterative principle of the positioning method in one embodiment of the present invention.

[0044] DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0045] It should be understood that the terms used herein are for the purpose of describing specific example implementation examples only and are not intended to be limiting. Unless the context clearly indicates otherwise, the singular forms "one", "an", and "said" as used herein may also be meant to include plural forms. The terms "comprise", "include", "contain", and "have" are inclusive and therefore specify the presence of stated features, steps, operations, elements, and / or parts, but do not exclude the presence or addition of one or more other features, steps, operations, elements, parts, and / or combinations thereof. The method steps, processes, and operations described herein are not to be construed as necessarily requiring them to be performed in the specific order described or illustrated, unless the order of execution is clearly indicated. It should also be understood that additional or alternative steps may be used.

[0046] Although the terms first, second, third, etc. can be used in the text to describe multiple elements, components, regions, layers and / or sections, these elements, components, regions, layers and / or sections should not be limited by these terms. These terms can only be used to distinguish an element, component, region, layer or section from another region, layer or section. Unless the context clearly indicates otherwise, terms such as "first", "second" and other numerical terms do not imply order or sequence when used in the text. Therefore, the first element, component, region, layer or section discussed below can be referred to as the second element, component, region, layer or section without departing from the teaching of the example implementation embodiment.

[0047] For ease of description, spatially relative terms may be used herein to describe the relationship of one element or feature relative to another element or feature as shown in the figures, such as "inside," "outside," "inner side," "outer side," "lower," "upper," etc. Such spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures.

[0048] Film cooling is one of the most important cooling technologies for aircraft engine turbine blades. This technology is mainly achieved through film cooling holes on the turbine blades. Achieving high-precision machining of film cooling holes in turbine blades is of great significance for improving the performance and service life of aircraft engine turbine blades.

[0049] Turbine blades are usually formed by one-time precision casting. Due to the influence of thermal stress and blade surface structure during the casting process, there will be a certain contour error between the actual product of the turbine blade and the theoretical model. In the traditional process of machining the film cooling holes of turbine blades, the position and angle of the film cooling holes are mainly aligned manually. The alignment accuracy is low, which affects the production efficiency of the turbine blades. The existing method of aligning the film cooling holes using a three-coordinate measuring machine usually uses the three-coordinate measuring machine to measure the turbine blades, and then manually aligns the data on the computer, and then inputs it into the CNC machine tool for processing. Although the accuracy is high, the operation process is cumbersome and the degree of integration is not high. Therefore, the existing technology has certain limitations in achieving high-precision machining of turbine blade film cooling holes.

[0050] In view of this, the first aspect of the present invention provides a positioning method for processing turbine blade film cooling holes; the second aspect provides a turbine blade film cooling hole processing device, which is intended to implement the positioning method for processing turbine blade film cooling holes provided by the embodiment of the first aspect; the third aspect provides a non-volatile computer-readable storage medium, which is intended to implement the positioning method for processing turbine blade film cooling holes provided by the embodiment of the first aspect.

[0051] like Figure 1 As shown, a positioning method for machining a film cooling hole for a turbine blade according to an embodiment of the first aspect of the present invention includes:

[0052] S1, set the ideal three-dimensional model of the turbine blade, in which there is a theoretical coordinate system SYS0 and multiple preset positioning point sets Ω0 (n, x, y, z);

[0053] S2, installing the turbine blade on a CNC machine tool. There are obvious geometric features on the turbine blade corresponding to the preset positioning points. Preliminary measurement is performed to obtain the set Ω1(n, x, y, z) corresponding to the preset positioning point set Ω0(n, x, y, z) in the CNC machine tool coordinate system SYS1.

[0054] S3, set an error function Φ as a representation of the deviation between Ω0(n, x, y, z) and Ω1(n, x, y, z), and set a threshold Φ(min) for the error function Φ;

[0055] S4, set a point set Ω and assign Ω1(n,x,y,z) to Ω;

[0056] S5, calculate the spatial transformation matrix M from SYS0 to SYS1 according to the preset positioning point set Ω0(n,x,y,z) and Ω;

[0057] S6, calculate the nominal position Ω0(n, x, y, z)* of the preset positioning point set Ω0(n, x, y, z) in the machine tool coordinate system SYS1 according to the spatial transformation matrix M;

[0058] S7, measuring the coordinates of the turbine blade on the CNC machine tool according to the coordinate data of each point of Ω0(n,x,y,z)*, obtaining the corresponding point set Ω2(n,x,y,z), and assigning Ω2(n,x,y,z) to Ω;

[0059] S8, calculate the specific value of the error function Φ based on Ω0(n,x,y,z)* and Ω;

[0060] S9, based on the threshold Φ(min) and the specific value of the error function Φ obtained in step S8, execute steps S5-S9 again until the specific value of the error function Φ obtained in step S8 is less than the threshold Φ(min);

[0061] S10, obtaining a best-fit position mapping relationship between the three-dimensional model of the turbine blade and the turbine blade actually installed on the CNC machine tool according to the spatial transformation matrix M;

[0062] S11, transforming the to-be-machined feature P on the three-dimensional model of the turbine blade into a corresponding surface position parameter P* of the turbine blade on the CNC machine tool according to the spatial transformation matrix M; and

[0063] S12, based on the position parameter P* on the machine tool coordinate system SYS1, edit the NC machining instructions to perform precision machining of the air film holes on the turbine blades.

[0064] The positioning method for machining film cooling holes for turbine blades provided in accordance with the first embodiment of the present invention can achieve at least the following beneficial effects:

[0065] 1. After a few iterations of on-machine detection, the error can be effectively converged and the technical requirements can be met.

[0066] 2. The spatial transformation matrix from the blade coordinate system to the machine tool coordinate system is obtained through this method, and the coordinates of the film cooling holes are corrected to achieve high-precision machining of the film cooling holes.

[0067] 3. It performs well in extreme cases and can process special position points. The method can be integrated into CNC machine tools to simplify the operation process and improve processing efficiency.

[0068] Specifically, in an embodiment of the present invention, steps S1 to S4 can preprocess the turbine blade positioning step, and then steps S5 to S9 are performed based on the preset positioning point set Ω0(n, x, y, z) and its corresponding set Ω1(n, x, y, z). Steps S5 to S9 can be understood as an iterative process. When the specific value of the error function Φ is less than the threshold Φ(min), the iterative process can be terminated and the required spatial transformation matrix M can be output. Based on the spatial transformation matrix M obtained through the iterative process, subsequent calculations can be performed to obtain the position parameter P*, and based on the position parameter P*, precise machining of the turbine blade film hole can be achieved.

[0069] The iterative principle of the positioning method for machining the film cooling holes of turbine blades according to the embodiment of the present invention can be referred to Figure 4 Specifically, Figure 4 The error threshold judgment shown can be understood as corresponding to step S9 in the positioning method. When the specific value of the error function Φ obtained in step S8 is not less than the threshold Φ(min), steps S5-S9 can be executed again until the specific value of the error function Φ obtained in step S8 is less than the threshold Φ(min).

[0070] Reference below Figures 1 to 3 A blade positioning method according to an embodiment of the first aspect of the present invention is described.

[0071] Optionally, in some embodiments, the preset positioning point set Ω0(n,x,y,z) is configured to be at least 6.

[0072] Further optionally, in some embodiments, the feature P to be processed may include the coordinates of the air film hole, etc. However, the present design is not limited thereto, and in other embodiments, the feature P to be processed may also include other features.

[0073] In some embodiments, the spatial transformation matrix M from SYS0 to SYS1 is calculated based on the preset positioning point set Ω0(n,x,y,z) and Ω as follows:

[0074] S510, calculate the centroid of two point sets Ω0(n,x,y,z) and Ω by formula (1):

[0075]

[0076] S520, using the SVD decomposition method to solve the spatial transformation matrix M:

[0077]

[0078] In formula (2), H is the intermediate matrix, U, S, and V are the decomposition matrices obtained by processing H using SVD decomposition, R is the calculated rotation matrix, and T is the calculated translation matrix. The spatial transformation matrix M consists of two parts: R and T.

[0079] In some embodiments, the specific method for calculating the nominal position Ω0(n,x,y,z)* of the preset point set Ω0(n,x,y,z) in the machine tool coordinate system SYS1 according to the spatial transformation matrix M is:

[0080] The formula for calculating the nominal position Ω0(n,x,y,z)* using the spatial transformation matrix M and the preset point set Ω0(n,x,y,z) is shown in formula (3):

[0081] Ω0(n,x,y,z)*=R×Ω0(n,x,y,z)+T (3)

[0082] In some embodiments, a method for calculating a specific value of the error function Φ based on Ω0(n,x,y,z)* and Ω is as follows:

[0083] The maximum distance between the point set Ω0(n,x,y,z)* in the machine tool coordinate system and the corresponding point in Ω is taken as the specific value of the error function Φ.

[0084] It should be noted that after continuous iteration, the error function Φ can gradually be smaller than the threshold Φ(min), that is, the spatial distance between Ω0(n, x, y, z) and Ω is small enough to ensure the processing accuracy.

[0085] In some embodiments, according to the spatial transformation matrix M, the feature to be processed P on the three-dimensional model of the turbine blade is transformed into the corresponding surface position parameter P* of the turbine blade on the CNC machine tool as follows:

[0086] The formula for calculating the corresponding surface position parameter P* through the spatial transformation matrix M and the feature to be processed P is shown in formula (4):

[0087] P*=R×P+T (4)

[0088] In some embodiments, based on the position parameter P* on the machine tool coordinate system SYS1, editing the CNC machining instructions to perform precision machining of the air film holes on the turbine blades is specifically as follows: importing the position parameter P* on the machine tool coordinate system SYS1 into the CNC machining program, generating CNC machining instructions for machining.

[0089] According to the second aspect of the present invention, a turbine blade film cooling hole processing device is provided, which includes a control device, the control device includes a central processing unit and a memory, the memory stores a computer program, and the processor is used to implement the steps of the positioning method for processing the turbine blade film cooling hole described in the embodiment of the first aspect when executing the computer program.

[0090] The above-mentioned turbine blade film cooling hole processing device is based on the positioning method for turbine blade film cooling hole processing, which can realize the precise processing of turbine blade film holes.

[0091] It should be noted that the above-mentioned explanation of the embodiment and beneficial effects of the positioning method for machining turbine blade film cooling holes is also applicable to the turbine blade film cooling hole machining device of this embodiment. To avoid redundancy, it will not be elaborated here.

[0092] According to the non-volatile computer-readable storage medium provided in the third embodiment of the present invention, the computer program is stored. When the computer program is executed by a processor, the positioning method for machining the film cooling holes of the turbine blade described in the first embodiment is implemented.

[0093] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A positioning method for machining film cooling holes of turbine blades, characterized in that: include: S1, set an ideal three-dimensional model of the turbine blade, in which there is a theoretical coordinate system SYS0 and multiple preset positioning point sets Ω0 (n, x, y, z); S2, installing the turbine blade on a CNC machine tool. Obvious geometric features corresponding to the preset positioning points already exist on the turbine blade. Preliminary measurement is performed to obtain a set Ω1(n, x, y, z) corresponding to the preset positioning point set Ω0(n, x, y, z) in the CNC machine tool coordinate system SYS1. S3, set an error function Φ as a representation of the deviation between Ω0(n, x, y, z) and Ω1(n, x, y, z), and set a threshold Φ(min) for the error function Φ; S4, set a point set Ω, and assign Ω1(n, x, y, z) to Ω; S5, calculating the spatial transformation matrix M from SYS0 to SYS1 according to the preset positioning point set Ω0 (n, x, y, z) and Ω; S6, calculating the nominal position Ω0(n, x, y, z)* of the preset positioning point set Ω0(n, x, y, z) in the machine tool coordinate system SYS1 according to the spatial transformation matrix M; S7, measuring the coordinates of the turbine blade on a CNC machine tool according to the coordinate data of each point of Ω0(n, x, y, z)*, obtaining a corresponding point set Ω2(n, x, y, z), and assigning Ω2(n, x, y, z) to Ω; S8, calculating the specific value of the error function Φ based on Ω0(n, x, y, z)* and Ω; S9, based on the threshold Φ(min) and the specific value of the error function Φ obtained in step S8, execute steps S5-S9 again until the specific value of the error function Φ obtained in step S8 is less than the threshold Φ(min); S10, obtaining a best-fit position mapping relationship between the three-dimensional model of the turbine blade and the turbine blade actually installed on the CNC machine tool according to the spatial transformation matrix M; S11, transforming the feature to be processed P on the three-dimensional model of the turbine blade into the corresponding surface position parameter P* of the turbine blade on the CNC machine tool according to the spatial transformation matrix M; as well as S12, based on the position parameter P* on the machine tool coordinate system SYS1, edit the NC machining instructions to perform precision machining of the air film holes on the turbine blades.

2. The positioning method for machining film cooling holes of turbine blades according to claim 1, characterized in that: The number of the preset positioning point set Ω0(n, x, y, z) is configured to be at least 6.

3. The positioning method for machining film cooling holes of turbine blades according to claim 1, characterized in that: The feature P to be processed includes the coordinates of the air film hole.

4. The positioning method for machining film cooling holes of turbine blades according to claim 1, characterized in that: The spatial transformation matrix M from SYS0 to SYS1 is calculated based on the preset positioning point set Ω0 (n, x, y, z) and Ω as follows: S510, calculate the centroid of two point sets Ω0(n, x, y, z) and Ω using formula (1): S520, solve the spatial transformation matrix M by using the singular value decomposition (SVD) method commonly used in linear algebra theory: In formula (2), H is the intermediate matrix, U, S, and V are the decomposition matrices obtained by processing H using SVD decomposition, R is the calculated optimal rotation matrix, and T is the calculated translation matrix. The spatial transformation matrix M consists of two parts: R and T.

5. The positioning method for machining film cooling holes of turbine blades according to claim 1, characterized in that: According to the spatial transformation matrix M, the specific method for calculating the nominal position Ω0(n, x, y, z)* of the preset point set Ω0(n, x, y, z) in the machine tool coordinate system SYS1 is: The formula for calculating the nominal position Ω0(n,x,y,z)* using the spatial transformation matrix M and the preset point set Ω0(n,x,y,z) is shown in formula (3): Ω0(n,x,y,z)*=R×Ω0(n,x,y,z)+T (3).

6. The positioning method for machining film cooling holes of turbine blades according to claim 1, characterized in that: According to Ω0(n,x,y,z)* and Ω, the specific value of the error function Φ is calculated as: The maximum distance between the point set Ω0(n,x,y,z)* in the machine tool coordinate system and the corresponding point in Ω is the specific value of the error function Φ.

7. The positioning method for machining film cooling holes of turbine blades according to claim 1, characterized in that: According to the spatial transformation matrix M, the feature to be processed P on the three-dimensional model of the turbine blade is transformed into the corresponding surface position parameter P* of the turbine blade on the CNC machine tool: The formula for calculating the corresponding surface position parameter P* through the spatial transformation matrix M and the feature to be processed P is shown in formula (4): P*=R×P+T (4) .

8. The positioning method for machining film cooling holes for turbine blades according to any one of claims 1 to 7, characterized in that: Based on the position parameter P* on the machine coordinate system SYS1, the specific method for editing the NC machining instructions to perform precision machining of the film holes on the turbine blades is as follows: Import the position parameter P* on the machine tool coordinate system SYS1 into the CNC machining program to generate CNC machining instructions for machining.

9. A device for machining film cooling holes for turbine blades, characterized in that: The invention comprises a control device, which comprises a central processing unit and a memory, wherein the memory stores a computer program, and the processor is used to implement the steps of the positioning method for machining the film cooling hole of the turbine blade as described in any one of claims 1 to 8 when executing the computer program.

10. A non-volatile computer-readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, the positioning method for machining film cooling holes for turbine blades according to any one of claims 1 to 8 is implemented.

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