Methods, apparatus, electronic equipment, and readable media for through-holes in gas turbine blades

Abstract

This disclosure discloses a method, apparatus, electronic device, and readable medium for drilling through holes in gas turbine blades. One specific embodiment of the method includes: clamping and fixing a gas turbine blade using a fixture; controlling a drilling device to drill holes in the gas turbine blade; controlling the fixture to move the gas turbine blade, after drilling the film cooling holes, to a preset position on a through-hole grinding machine tool; correcting and adjusting the position of the gas turbine blade on the through-hole grinding machine tool; acquiring a pre-established machine tool reference coordinate system; acquiring a device coordinate system created by the through-hole grinding equipment; performing spatial alignment processing on the machine tool reference coordinate system and the device coordinate system; extracting the geometric information set corresponding to at least one film cooling hole on the corrected and adjusted gas turbine blade; and controlling the through-hole grinding equipment to change the grinding tool to perform deburring and chamfering treatment on the film cooling holes. This embodiment improves the deburring and chamfering effect of film cooling holes on gas turbine blades.

Description

Technical Field

[0001] This invention relates to the field of computer technology, and more specifically to a method, apparatus, electronic device, and readable medium for through-holes in gas turbine blades. Background Technology

[0002] With the advancement of automation and precision manufacturing in the industrial sector, the demand for precise operation in the through-hole machining process of gas turbine blades, including through-hole drilling, deburring, and chamfering, is increasing. Through-hole drilling of gas turbine blades involves creating film gas flow holes and then deburring and chamfering these holes. Currently, the common method for through-hole drilling, deburring, and chamfering of gas turbine blades is to move the drilled gas turbine blade to a through-hole grinding machine after drilling, and then select deburring and chamfering tools based on general parameters.

[0003] However, when using the above method to create film gas holes in gas turbine blades and to remove burrs and chamfer the created film gas holes, the following technical problems often arise:

[0004] Directly after drilling, the gas turbine blades are moved to the through-hole grinding machine. However, due to potential blade position shifts after drilling the film cooling holes, and possible inconsistencies in the coordinate systems of the drilling and grinding equipment, the alignment accuracy between the grinding tool and the film cooling hole is insufficient, resulting in poor deburring and chamfering effects. Different film cooling holes have varying geometries and dimensions. While deburring and chamfering tools are selected based on general parameters, discrepancies between the selected tool and the hole's geometry and dimensions lead to a mismatch between the chosen tool and the deburring and chamfering requirements, resulting in poor deburring and chamfering effects.

[0005] The information disclosed in this background section is only intended to enhance the understanding of the background of the inventive concept, and therefore may contain information that does not form prior art known to those skilled in the art. Summary of the Invention

[0006] The summary portion of this disclosure is intended to provide a brief overview of the concepts, which will be described in detail in the detailed description portion. This summary portion is not intended to identify key or essential features of the claimed technical solutions, nor is it intended to limit the scope of the claimed technical solutions.

[0007] Some embodiments of this disclosure provide methods, apparatus, electronic devices, and computer-readable media for through-holes in gas turbine blades to address one or more of the technical problems mentioned in the background section above.

[0008] In a first aspect, some embodiments of this disclosure provide a method for drilling through holes in a gas turbine blade. The method includes: clamping and fixing the gas turbine blade using a fixture; controlling a drilling device to drill holes in the gas turbine blade to form film gas holes; controlling the fixture to move the gas turbine blade after drilling the film gas holes to a preset position on a through-hole grinding machine tool; identifying the position of at least one film gas hole on the gas turbine blade on the through-hole grinding machine tool to correct and adjust the position of the gas turbine blade on the through-hole grinding machine tool; obtaining a pre-established machine tool reference coordinate system; obtaining a device coordinate system created by the through-hole grinding machine; performing spatial alignment processing on the machine tool reference coordinate system and the device coordinate system to obtain spatial alignment mapping information; extracting a geometric information set corresponding to at least one film gas hole on the corrected and adjusted gas turbine blade; and, based on the geometric information set and the spatial alignment mapping information, controlling the through-hole grinding machine to change grinding tools to perform deburring and chamfering processing on the film gas holes.

[0009] Secondly, some embodiments of this disclosure provide a through-hole device for gas turbine blades. The device includes: a clamping unit configured to clamp and fix the gas turbine blade using a clamp; a drilling unit configured to control a drilling device to drill holes in the gas turbine blade to form film gas holes; a moving unit configured to control the clamp to move the gas turbine blade after the film gas holes have been drilled to a preset position on a through-hole grinding machine; and a position identification unit configured to identify the position of at least one film gas hole on the gas turbine blade on the through-hole grinding machine to correct and adjust the gas turbine blade on the through-hole grinding machine. The system comprises: a first acquisition unit configured to acquire a pre-established machine tool reference coordinate system; a second acquisition unit configured to acquire a device coordinate system created by the through-hole grinding equipment; a mapping space alignment unit configured to perform mapping space alignment processing on the machine tool reference coordinate system and the device coordinate system to obtain space alignment mapping information; and a control unit configured to extract a geometric information set corresponding to at least one film gas hole on the gas turbine blade after correction and adjustment, and based on the geometric information set and the space alignment mapping information, control the through-hole grinding equipment to change the grinding tool to perform deburring and chamfering processing on the film gas hole.

[0010] Thirdly, some embodiments of this disclosure provide an electronic device, including: one or more processors; and a storage device having one or more programs stored thereon, wherein when the one or more programs are executed by the one or more processors, the one or more processors implement the method described in any implementation of the first aspect above.

[0011] Fourthly, some embodiments of this disclosure provide a computer-readable medium having a computer program stored thereon, wherein the program, when executed by a processor, implements the method described in any of the implementations of the first aspect above.

[0012] The above-described embodiments of this disclosure have the following beneficial effects: the through-hole method for gas turbine blades according to some embodiments of this disclosure improves the deburring and chamfering effect. Specifically, the reason for the poor deburring and chamfering effect is that: directly after drilling, the gas turbine blade after drilling is moved to the through-hole grinding equipment. Since the blade clamping position may shift after drilling the film cooling hole, and the coordinate systems of the drilling equipment and the grinding equipment may not be consistent, the alignment accuracy between the grinding tool and the film cooling hole is insufficient, resulting in a poor deburring and chamfering effect. Different film cooling holes have different geometries and sizes. According to general parameters, a deburring and chamfering tool is selected for operation. However, the selected tool differs from the geometry and size of the film cooling hole, resulting in a mismatch between the selected tool and the deburring and chamfering requirements of the film cooling hole, leading to a poor deburring and chamfering effect. Based on this, the through-hole method for gas turbine blades according to some embodiments of this disclosure first uses a clamp to hold and fix the gas turbine blade. Then, the drilling equipment is controlled to drill holes in the gas turbine blade to form film cooling holes. Therefore, holes can be drilled on the gas turbine blade using a fixture and a drilling device to form film cooling holes. Then, the fixture is controlled to move the gas turbine blade, after the film cooling holes have been drilled, to a preset position on the through-hole grinding machine. This allows the gas turbine blade to be moved to the grinding machine for subsequent grinding of the film cooling holes. Next, the position of at least one film cooling hole on the gas turbine blade on the through-hole grinding machine is identified to correct and adjust the position of the gas turbine blade on the machine. This allows for position identification of the film cooling holes and correction of the gas turbine blade's position, reducing deviations from the preset position when gripping the gas turbine blade. A pre-established machine tool reference coordinate system is obtained. The equipment coordinate system created by the through-hole grinding equipment is also obtained. A spatial alignment process is performed on the machine tool reference coordinate system and the equipment coordinate system to obtain spatial alignment mapping information. This provides spatial alignment mapping information between the machine tool reference coordinate system and the equipment coordinate system, unifying the spatial reference between different devices. Subsequently, the geometric information set corresponding to at least one film cooling hole on the gas turbine blade after correction and adjustment is extracted. Based on the geometric information set and the aforementioned spatial alignment mapping information, the through-hole grinding equipment is controlled to switch grinding tools to perform deburring and chamfering on the film cooling holes. Thus, based on the actual geometric characteristics (such as shape and size) of each film cooling hole, i.e., geometric information, the grinding tool matching the deburring and chamfering requirements of the film cooling hole can be selected and called. Using a unified coordinate mapping relationship, i.e., spatial alignment mapping information, the grinding tool is driven to precisely move to the position of each film cooling hole for deburring and chamfering, improving the deburring and chamfering effect of the film cooling holes on the gas turbine blade. Furthermore, because the spatial alignment mapping information between the machine tool reference coordinate system and the aforementioned equipment coordinate system is obtained through position recognition correction, the positioning of the grinding tool relative to the film cooling hole is ensured, thus reducing alignment deviations caused by blade offset and coordinate system mismatch.Meanwhile, by selecting and changing tools based on the actual extracted geometric information set of film pores, the problem of mismatch between general tools and actual pore shapes can be avoided, ensuring that the grinding tools are adapted to the characteristics of film pores, thereby improving the deburring and chamfering effect of film pores on gas turbine blades. Attached Figure Description

[0013] The above and other features, advantages, and aspects of the embodiments of this disclosure will become more apparent from the accompanying drawings and the following detailed description. Throughout the drawings, the same or similar reference numerals denote the same or similar elements. It should be understood that the drawings are schematic, and elements are not necessarily drawn to scale.

[0014] Figure 1 This is a flowchart of some embodiments of the through-hole method for gas turbine blades according to the present disclosure;

[0015] Figure 2 This is a schematic diagram of the structure of some embodiments of the through-hole device for gas turbine blades according to the present disclosure;

[0016] Figure 3 This is a schematic diagram of the structure of an electronic device suitable for implementing some embodiments of the present disclosure. Detailed Implementation

[0017] Embodiments of this disclosure will now be described in more detail with reference to the accompanying drawings. While some embodiments of this disclosure are shown in the drawings, it should be understood that this disclosure can be implemented in various forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided to provide a more thorough and complete understanding of this disclosure. It should be understood that the accompanying drawings and embodiments of this disclosure are for illustrative purposes only and are not intended to limit the scope of protection of this disclosure.

[0018] It should also be noted that, for ease of description, only the parts relevant to the invention are shown in the accompanying drawings. Unless otherwise specified, the embodiments and features described in this disclosure can be combined with each other.

[0019] It should be noted that the concepts of "first" and "second" mentioned in this disclosure are used only to distinguish different devices, modules or units, and are not used to limit the order of functions performed by these devices, modules or units or their interdependencies.

[0020] It should be noted that the terms "a" and "a plurality of" used in this disclosure are illustrative rather than restrictive, and those skilled in the art should understand that, unless otherwise expressly indicated in the context, they should be understood as "one or more".

[0021] The names of messages or information exchanged between multiple devices in the embodiments of this disclosure are for illustrative purposes only and are not intended to limit the scope of such messages or information.

[0022] This disclosure will now be described in detail with reference to the accompanying drawings and embodiments.

[0023] Figure 1 A flow chart 100 of some embodiments of a through-hole method for gas turbine blades according to the present disclosure is shown. The through-hole method for gas turbine blades includes the following steps:

[0024] Step 101: Use a clamp to hold and fix the gas turbine blades.

[0025] In some embodiments, the execution subject (e.g., a computing device) of the through-hole method for gas turbine blades can clamp and fix the gas turbine blades using a fixture. The fixture can be a blade clamp for the gas turbine.

[0026] Step 102: Control the drilling equipment to drill holes in the gas turbine blades to form film gas holes.

[0027] In some embodiments, the aforementioned executing entity can control a drilling device to drill holes in the gas turbine blades to form film gas holes. The drilling device can be a laser drilling device or an electrical discharge machining (EDM) machine.

[0028] In some optional implementations of certain embodiments, the aforementioned execution entity can control the drilling equipment to drill holes in the gas turbine blades through the following steps to form film gas holes:

[0029] The first step is to obtain a pre-created 3D model of the gas turbine blade corresponding to the gas turbine blade. This 3D model includes annotations for the film cooling perforation parameters. The 3D model can be a gas turbine blade model created using CAD software. The film cooling perforation parameters can include individual parameter information and arrangement parameters for each film cooling perforation. Each parameter information represents the geometric parameters of a film cooling perforation (e.g., shape, aperture size). The arrangement parameters can include the position, spacing, and row spacing of each film cooling perforation.

[0030] The second step involves inputting the aforementioned 3D blade model into a preset CNC programming converter to obtain drilling task information. This preset CNC programming converter can be CAM software. The drilling task information can be a program file or instruction set generated by the CAM software based on the 3D blade model, capable of directly driving CNC drilling equipment (such as laser drilling equipment or EDM drilling machines) for processing.

[0031] The third step is to control the drilling equipment to perform the drilling task corresponding to the above-mentioned drilling task information, so as to control the drilling equipment to drill holes on the gas turbine blades to form film gas holes.

[0032] Step 103: Control the fixture to move the gas turbine blades after the film gas flow holes have been drilled to the preset position on the through hole grinding machine.

[0033] In some embodiments, the aforementioned execution entity can control the fixture to move the gas turbine blades after the film gas flow holes have been drilled to a preset position on the through-hole grinding machine tool.

[0034] In some optional implementations of certain embodiments, the aforementioned execution entity can control the fixture to move the gas turbine blades after the film gasifier holes have been drilled to a preset position on the through-hole grinding machine tool through the following steps:

[0035] The first step involves acquiring images of the fixture and depth maps using a depth camera fixed to the through-hole grinding machine. Each pixel in the fixture image corresponds one-to-one with a depth pixel in the depth map.

[0036] The second step is to perform fixture feature point recognition processing on the fixture image to obtain the two-dimensional coordinates of the feature points. In practice, OpenCV feature point detection technology can be used to perform fixture feature point recognition processing on the fixture image to obtain the two-dimensional coordinates of the feature points.

[0037] The third step is to obtain the calibration information of the depth camera whose image acquisition fixture is fixed. This calibration information may include the camera's intrinsic and extrinsic parameters. The intrinsic parameters can be an intrinsic parameter matrix. The extrinsic parameters can be the camera's extrinsic parameter matrix.

[0038] The fourth step involves generating the three-dimensional coordinates of the fixture feature points based on the aforementioned two-dimensional coordinates and calibration information. In practice, the depth pixel value where the two-dimensional coordinates of the feature points in the depth map are located can be determined as the Z-value of the Z-axis. Then, the camera's intrinsic and extrinsic parameters, the two-dimensional coordinates of the feature points, and the depth pixel value are input into the inverse projection formula from image coordinates and depth to camera coordinates. Through the inverse perspective projection transformation technique, the two-dimensional coordinates of the feature points are converted into the three-dimensional coordinates of the fixture feature points. These three-dimensional coordinates of the fixture feature points represent the three-dimensional coordinates of the feature points on the fixture in three-dimensional space.

[0039] The fifth step involves generating translational increment information based on the three-dimensional coordinates of the fixture feature points and the aforementioned preset fixed fixture feature points. In practice, the executing entity can determine the translational increment information as the difference between the three-dimensional coordinates of the fixture feature points and the preset fixed fixture feature points along each coordinate axis. For example, the three-dimensional coordinates of the fixture feature points could be (2, 4, 6), and the three-dimensional coordinates of the preset fixed fixture feature points could be (2, 4, 5). Then the translational increment information could be (2, 4, 5) - (2, 4, 6) = (0, 0, -1).

[0040] Step 6: Based on the aforementioned translational increment information, control the fixture to move the gas turbine blade, after the film cooling holes have been drilled, to a preset position on the through-hole grinding machine. In practice, the fixture can be controlled to move the gas turbine blade, after the film cooling holes have been drilled, according to the translational increment represented by the translational increment information, so as to move the gas turbine blade to the preset position on the through-hole grinding machine.

[0041] Step 104: Identify the position of at least one film gas hole on the gas turbine blade on the through hole grinding machine tool to correct and adjust the position of the gas turbine blade on the through hole grinding machine tool.

[0042] In some embodiments, the aforementioned execution entity may identify the position of at least one film gas hole on a gas turbine blade on a through-hole grinding machine tool in order to correct and adjust the position of the gas turbine blade on the through-hole grinding machine tool.

[0043] In some optional implementations of certain embodiments, the aforementioned execution entity may perform the following steps to identify the position of at least one film gas hole on the gas turbine blade on the through-hole grinding machine tool, so as to correct and adjust the position of the gas turbine blade on the through-hole grinding machine tool:

[0044] The first step involves scanning the gas turbine blades using a laser line scanner on a hole grinding machine to obtain point cloud data of the blade surface. This point cloud data represents the point cloud of the gas turbine blade. The point cloud data includes individual point cloud data points. Each point cloud data point represents the position and color of a point on the gas turbine blade. The point cloud data includes position and color information. The position information can be the point's three-dimensional coordinates in space. The color information can be the point's RGB color value.

[0045] The second step involves edge detection on the aforementioned blade surface point cloud data to obtain edge point cloud data, which includes information about each edge point. In practice, a 3D point cloud edge detection algorithm can be used to perform edge detection on the aforementioned blade surface point cloud data to obtain the edge point cloud data. The aforementioned edge point cloud data can be a subset of the point cloud data extracted from the blade surface point cloud data, describing the geometry of the blade edge.

[0046] The third step is to cluster the edge point information included in the aforementioned edge point cloud data to obtain individual edge point information groups. In practice, a clustering algorithm based on Euclidean distance can be used to cluster the edge point information included in the aforementioned edge point cloud data to obtain individual edge point information groups.

[0047] Fourth, for each edge point information group in the above edge point information groups, perform the following steps:

[0048] The first sub-step involves performing aperture fitting detection processing on the aforementioned edge point information group to obtain aperture fitting detection information. In practice, OpenCV contour geometric feature analysis and shape fitting techniques can be used to perform aperture fitting detection processing on the edge point information group to obtain aperture fitting detection information. The aperture fitting detection information can be an aperture type representing the aperture shape (e.g., elliptical, circular, Y-shaped, etc.).

[0049] The second sub-step involves deleting the aforementioned edge point information from the edge point information group in response to the determination that the aperture fitting detection information does not meet the preset fitting conditions, thereby updating each edge point information group. The preset fitting conditions can be that the aperture type represented by the aperture fitting detection information does not belong to a preset aperture type set.

[0050] The fifth step is to determine the updated edge point information groups as the updated edge point information group set.

[0051] Step 6: Generate the air-supported membrane vent location information based on each updated edge point information group in the updated edge point information group set. In practice, the average value of each location information included in the updated edge point information group can be used as the air-supported membrane vent location information. As an example, the location information included in the updated edge point information group can be (1, 4, 6), (3, 2, 3), (1, 4, 0). Then the average value of (1, 4, 6), (4, 1, 3), and (1, 4, 0) can be ((1+4+1) / 3, (4+1+4) / 3, (6+3+0) / 3), which is (2, 3, 3). (2, 3, 3) is the air-supported membrane vent location information.

[0052] Step 7: Based on the location information of each air film vent and a preset set of air film vent calibration location information, generate reference offset detection information. In practice, the aforementioned execution entity can determine the mean value of each air film vent location information as the mean air film vent location information. Then, determine the mean value of the preset set of air film vent calibration location information as the mean value calibration point location information. It should be noted that the method for solving the mean value is the same as the method for solving the air film vent location information. Afterwards, the vector obtained by subtracting the mean air film vent location information from the mean calibration point location information can be used to determine the reference offset detection information.

[0053] The eighth step involves correcting and adjusting the position of the gas turbine blades on the through-hole grinding machine based on the reference offset detection information. In practice, the fixture can be controlled to move the gas turbine blades according to the vector represented by the reference offset detection information to correct and adjust their position on the through-hole grinding machine.

[0054] Step 105: Obtain the pre-established machine tool reference coordinate system.

[0055] In some embodiments, the aforementioned executing entity can acquire a pre-established machine tool reference coordinate system. This machine tool reference coordinate system includes the pre-defined geometric center coordinates of the gas turbine blade, workpiece coordinates of at least three fixture feature points, and coordinates of at least one film cooling hole. The equipment coordinate system includes machining coordinates of at least three fixture feature points, with a one-to-one correspondence between the workpiece coordinates of the fixture feature points and the machining coordinates of the fixture feature points. The machine tool reference coordinate system can be a machine tool coordinate system. The workpiece coordinates of the at least three fixture feature points are also the pre-defined positions of the fixture feature points in the machine tool reference coordinate system. The coordinates of each film cooling hole can be the coordinates of a pre-defined center point of the film cooling hole. The equipment coordinate system can be the coordinate system of a through-hole grinding equipment. The workpiece coordinates of the fixture feature points can be the three-dimensional coordinates of the fixture feature points in the equipment coordinate system obtained by the through-hole grinding equipment through identification.

[0056] Step 106: Obtain the equipment coordinate system created by the through-hole grinding equipment.

[0057] In some embodiments, the execution entity may obtain a device coordinate system created by the through-hole grinding equipment. This device coordinate system may be a local coordinate system created by the through-hole grinding equipment.

[0058] Step 107: Perform spatial alignment processing on the machine tool reference coordinate system and the equipment coordinate system to obtain spatial alignment mapping information.

[0059] In some embodiments, the execution entity may perform spatial alignment processing on the machine tool reference coordinate system and the equipment coordinate system to obtain spatial alignment mapping information.

[0060] In some optional implementations of certain embodiments, the aforementioned execution entity may perform spatial alignment processing on the machine tool reference coordinate system and the device coordinate system through the following steps to obtain spatial alignment mapping information:

[0061] The first step is to determine the rigid body transformation matrix from the machine tool reference coordinate system to the equipment coordinate system based on the workpiece coordinates and machining coordinates of the at least three fixture feature points. The executing entity can determine the rigid body transformation matrix from the machine tool reference coordinate system to the equipment coordinate system using singular value decomposition.

[0062] The second step is to determine the rigid body transformation matrix as spatial alignment mapping information.

[0063] Step 108: Extract the geometric information set corresponding to at least one film gas hole on the gas turbine blade after correction and adjustment, and based on the geometric information set and spatial alignment mapping information, control the through hole grinding equipment to change the grinding tool to perform deburring and chamfering treatment on the film gas hole.

[0064] In some embodiments, the aforementioned execution entity can extract the geometric information set corresponding to at least one film gas hole on the gas turbine blade after correction and adjustment, and based on the geometric information set and the aforementioned spatial alignment mapping information, control the through-hole grinding equipment to change the grinding tools to perform deburring and chamfering treatment on the film gas hole.

[0065] In addressing the aforementioned technical problems in the application scenario of identifying the geometric information of film cooling holes in gas turbine blades, the following technical challenges often arise: Directly identifying the entire blade image against a background of complex curved surfaces and dense hole clusters is susceptible to interference from adjacent holes and blade texture; furthermore, due to the small size of the film cooling holes and limited overall image resolution, it is difficult to extract their precise edges, resulting in low accuracy in identifying the geometric information set of the film cooling holes. This application scenario requires the following characteristics: It should be suitable for identifying the geometric information of densely arranged film cooling holes. Faced with these technical problems, we have decided to adopt the following solution:

[0066] In some optional implementations of certain embodiments, the aforementioned execution entity can extract the geometric information set corresponding to at least one film gas hole on the corrected and adjusted gas turbine blade through the following steps:

[0067] The first step is to use a depth camera fixed on the through-hole grinding machine to capture images of the gas turbine blades on the machine as images to be extracted.

[0068] The second step involves performing the following steps for each of the at least one air film pore location coordinates mentioned above:

[0069] The first sub-step is to obtain the calibration information of the depth camera.

[0070] The second sub-step involves projecting the coordinates of the air film aperture based on the aforementioned calibration information to obtain its two-dimensional coordinates. The camera's intrinsic and extrinsic parameters, along with the air film aperture's coordinates, are then input into the perspective projection formula to obtain the air film aperture's two-dimensional coordinates.

[0071] The third sub-step involves cropping the image to be extracted based on the two-dimensional coordinates of the air film vent and preset rectangular cropping parameters, resulting in a cropped image containing one air film vent. The preset rectangular cropping parameters can be the length and width of the cropping rectangle. The image to be extracted can be cropped with the two-dimensional coordinates of the air film vent as the center point of the rectangle, and the length and width of the rectangle as the cropping length and width, respectively, to obtain a rectangular image containing one air film vent.

[0072] The fourth sub-step involves inputting the cropped image into a pre-trained downsampling extraction module sequence of the air-film pore feature extraction model to obtain various downsampling feature extraction information. Each downsampling extraction module in the sequence includes a convolutional layer and a pooling layer. The air-film pore feature extraction model includes the downsampling extraction module sequence, an upsampling fusion module sequence, a shape category classification layer, and a mask output layer. Each downsampling extraction module in the sequence corresponds to at least one upsampling fusion module in the upsampling fusion module sequence. Each downsampling extraction module in the sequence includes a convolutional layer and a pooling layer. In practice, for each downsampling extraction module in the sequence, the cropped image can be input into the convolutional layer of the downsampling extraction module for feature extraction, obtaining a feature map representing the cropped image. Then, the feature map is input into the pooling layer for pooling, and the pooled feature map is used as the downsampling feature extraction information.

[0073] The fifth sub-step involves, for each upsampling fusion module in the aforementioned upsampling fusion module sequence, inputting at least one downsampling feature extraction information from at least one downsampling extraction module corresponding to the aforementioned upsampling fusion module, along with the output information of the previous upsampling fusion module in the aforementioned upsampling fusion module sequence, into the aforementioned upsampling fusion module to obtain fused feature information. The fused feature information is then input into the next upsampling fusion module in the aforementioned upsampling fusion module sequence. Each upsampling fusion module in the aforementioned upsampling fusion module sequence can be a decoder. The fused feature information can be feature information from multiple sources; here, the fused feature information can be a comprehensive representation of at least one downsampling feature extraction information and the output information of the previous upsampling fusion module.

[0074] The sixth sub-step involves processing the air film pore fusion feature information output by the last upsampling fusion module in the above upsampling fusion module sequence.

[0075] The seventh sub-step involves inputting the aforementioned film pore fusion feature information into the shape category classification layer to obtain film pore shape identifiers. This classification layer can be a fully connected layer that takes the film pore fusion feature information as input and the film pore shape identifiers as output. The film pore shape identifiers can be identifiers representing the shape of the pore (e.g., ellipse, circle, Y-shape, etc.).

[0076] The eighth sub-step involves inputting the aforementioned air film aperture fusion feature information into the mask image output layer to obtain an air film aperture mask image. This mask image output layer can be a decoder that performs a transposed convolution operation on the air film aperture fusion feature information. The air film aperture mask image can be a mask image where the pixel value of the pixels in the region containing the air film aperture is 1, and the pixel value of the pixels in the remaining regions is 0.

[0077] The ninth sub-step involves generating the air film aperture size information based on the air film aperture mask image. In practice, the number of pixels with a pixel value of 1 in the air film aperture mask image can be used to determine the air film aperture size information.

[0078] The tenth sub-step involves determining the above-mentioned air film pore shape identifier and air film pore size information as the geometric information of the air film pore.

[0079] The third step is to define at least one extracted geometric information as a geometric information set. Each piece of geometric information in the set includes an identifier for the shape and size of the air film vent. The bed reference coordinate system contains predefined coordinates for at least one air film vent location. Each piece of geometric information in the set corresponds to one of the at least one air film vent location coordinates.

[0080] The above-described embodiments of this disclosure have the following beneficial effects: the through-hole method for gas turbine blades according to some embodiments of this disclosure improves the accuracy of geometric information set recognition of film diaphragm holes. Specifically, the reason for the low accuracy of geometric information set recognition of film diaphragm holes is that, in the context of complex curved surfaces and dense hole groups, directly recognizing the entire blade image will be affected by interference from adjacent holes and blade textures; at the same time, due to the small size of the film diaphragm holes, it is difficult to extract their precise edges under the condition of limited overall image resolution, resulting in low accuracy of geometric information set recognition of film diaphragm holes. Based on this, the plate recognition method of some embodiments of this disclosure firstly acquires an image of a gas turbine blade on a through-hole grinding machine tool using a depth camera fixed on the through-hole grinding machine tool as the image to be extracted. Then, for each of the at least one film diaphragm hole position coordinates, the following steps are performed: First, the calibration information of the depth camera is obtained. Thus, calibration information for converting the three-dimensional coordinates of the film diaphragm holes into two-dimensional image coordinates can be obtained. Second, based on the above calibration information, the film diaphragm hole position coordinates are projected to obtain the two-dimensional coordinates of the film diaphragm holes. Therefore, the location of the air film vent in the image can be determined. The third step involves cropping the image to be extracted based on the two-dimensional coordinates of the air film vent and preset rectangular cropping parameters, resulting in a cropped image containing only one air film vent. This cropped image isolates the single target air film vent from the complex blade background and dense vent clusters, eliminating interference from adjacent vents and blade textures, allowing the model to focus on a single target. The fourth step involves inputting the cropped image into a pre-trained sequence of downsampling extraction modules of the air film vent feature extraction model to obtain various downsampling feature extraction information. Each downsampling extraction module in the sequence includes a convolutional layer and a pooling layer. The air film vent feature extraction model includes the downsampling extraction module sequence, an upsampling fusion module sequence, a shape category classification layer, and a mask output layer. Each downsampling extraction module in the sequence corresponds to at least one upsampling fusion module in the sequence. Fifth step: For each upsampling fusion module in the above upsampling fusion module sequence, input at least one downsampling feature extraction information output by at least one downsampling extraction module corresponding to the above upsampling fusion module, and the output information of the previous upsampling fusion module in the above upsampling fusion module sequence into the above upsampling fusion module to obtain fused feature information, and input the fused feature information into the next upsampling fusion module in the above upsampling fusion module sequence. Sixth step: Input the air film pore fusion feature information output by the last upsampling fusion module in the above upsampling fusion module sequence.Therefore, multi-scale film film aperture fusion feature information that captures subtle edge and shape features of the cropped image can be obtained. Step 7: The above film film aperture fusion feature information is input into the shape category classification layer to obtain the film film aperture shape identifier. Step 8: The above film film aperture fusion feature information is input into the mask image output layer to obtain the film film aperture mask image. Step 9: Based on the film film aperture mask image, film film aperture size information is generated. Step 10: The above film film aperture shape identifier and the above film film aperture size information are determined as the geometric information of the film film aperture. Finally, at least one extracted geometric information is determined as the geometric information set. Because a single film film aperture image is cropped first, and then feature extraction and classification are performed using a feature extraction model, interference from adjacent apertures and blade textures is avoided. Simultaneously, edge information of the film film aperture can be extracted, thereby improving the accuracy of the geometric information set recognition of the gas turbine blade film film aperture.

[0081] In addressing the technical problems mentioned above by adopting technical solutions, the following technical issues often arise in the application scenario: automated deburring and chamfering of film cooling holes in gas turbine blades. When efficiently and precisely processing hundreds or thousands of densely packed, tiny film cooling holes with varying geometric specifications (shapes and sizes), manual or single-tool operation is not only inefficient and inconsistent, but also makes it difficult to ensure that the processing parameters (such as tool selection) of each film cooling hole match its geometric information. This can easily lead to unstable processing quality, uneven tool wear, or damage to the hole walls, resulting in poor deburring and chamfering effects for gas turbine blade film cooling holes. Therefore, this application scenario requires the following characteristics: suitability for deburring and chamfering dense groups of film cooling holes with diverse geometric specifications (specific shapes and sizes).

[0082] In some optional implementations of certain embodiments, the aforementioned execution entity can control the through-hole grinding equipment to change grinding tools based on the geometric information set and the aforementioned spatial alignment mapping information to perform deburring and chamfering treatment on the air film holes through the following steps: First, for each air film hole position coordinate in the aforementioned bed reference coordinate system that includes at least one pre-set air film hole position coordinate, perform the following mapping transformation steps:

[0083] The first sub-step involves mapping the position coordinates of the air-supported film hole to the air-supported film hole machining coordinates in the equipment coordinate system based on the spatial alignment mapping information. In practice, the air-supported film hole position coordinates (represented as a homogeneous coordinate column vector) can be multiplied by the rigid body transformation matrix represented by the spatial alignment mapping information to obtain the air-supported film hole machining coordinates.

[0084] The second sub-step involves determining the geometric information corresponding to the above-mentioned air film pore position coordinates as the target geometric information.

[0085] The third sub-step involves obtaining the shape identifiers of each grinding air film hole corresponding to each grinding tool in the aforementioned grinding equipment, wherein the tool identifiers in each tool identifier corresponding to each grinding tool correspond one-to-one with the shape identifiers of each grinding air film hole in the aforementioned shape identifiers.

[0086] The fourth sub-step involves identifying at least one target tool identifier based on the air film vent shape identifiers included in the aforementioned target geometric information, ensuring that at least one tool identifier meets a preset screening condition. This preset screening condition allows the tool identifier to correspond to the same grinding air film vent shape identifier as the air film vent shape identifier. For example, each tool identifier can be Tool 1, Tool 2, and Tool 3. Furthermore, Tool 1 corresponds to a "circular" grinding air film vent shape identifier, Tool 2 corresponds to an "elliptical" grinding air film vent shape identifier, and Tool 3 corresponds to a "square" grinding air film vent shape identifier.

[0087] The fifth sub-step involves obtaining at least one grinding air film hole size information corresponding to the at least one target tool identifier mentioned above, wherein the target tool identifier in the at least one target tool identifier corresponds one-to-one with the grinding air film hole size information in the at least one grinding air film hole size information.

[0088] The sixth sub-step involves determining the target grinding air film hole size information by combining the above-mentioned at least one grinding air film hole size information with the air film hole size information included in the above-mentioned geometric information.

[0089] The seventh sub-step involves identifying at least one tool identifier that corresponds to the target grinding air film hole size information as the target tool identifier.

[0090] The eighth sub-step involves controlling the through-hole grinding equipment to retrieve the grinding tool corresponding to the aforementioned target tool identifier, and using the grinding tool to deburr and chamfer the air film hole corresponding to the processing coordinates of the air film hole.

[0091] The above-described technical solution and its related content, as an inventive point of this disclosure, solve the technical problem of "poor deburring and chamfering effect of film blasting holes in gas turbine blades." Factors leading to poor deburring and chamfering effects of film blasting holes in gas turbine blades are often as follows: When hundreds or thousands of densely packed, tiny film blasting holes with varying geometric specifications (shape and size) require efficient and precise post-processing, manual or single-tool operation is not only inefficient and inconsistent, but also makes it difficult to ensure that the processing parameters (such as tool selection) of each film blasting hole match its geometric information. This easily leads to unstable processing quality, uneven tool wear, or damage to the hole wall, resulting in poor deburring and chamfering effects of film blasting holes in gas turbine blades. Solving these factors can improve the deburring and chamfering effect of film blasting holes in gas turbine blades. To achieve this effect, firstly, for each air film hole position coordinate in the aforementioned bed reference coordinate system, which includes at least one pre-defined air film hole position coordinate, the following mapping transformation steps are performed: Based on spatial alignment mapping information, the air film hole position coordinates are mapped to air film hole processing coordinates in the equipment coordinate system. This allows the air film hole position coordinates to be mapped to the equipment coordinate system. Next, the geometric information corresponding to the aforementioned air film hole position coordinates in the geometric information set is determined as the target geometric information. This allows the geometric information set of the air film holes and the geometric information corresponding to the position coordinates to be determined as the target geometric information. Then, the shape identifiers of each grinding air film hole corresponding to each grinding tool in the aforementioned grinding equipment are obtained, wherein the tool identifiers in each tool identifier corresponding to each grinding tool correspond one-to-one with the grinding air film hole shape identifiers in each grinding air film hole shape identifier. Next, based on the air film hole shape identifiers included in the aforementioned target geometric information, at least one tool identifier that meets the preset screening conditions is determined as at least one target tool identifier. Obtain at least one grinding air film hole size information corresponding to at least one target tool identifier, wherein the target tool identifier in the at least one target tool identifier corresponds one-to-one with the grinding air film hole size information in the at least one grinding air film hole size information. Then, determine the at least one grinding air film hole size information and the air film hole size information included in the geometric information as the target grinding air film hole size information. Then, determine the tool identifier corresponding to the target grinding air film hole size information in the at least one tool identifier as the target tool identifier. Thus, by obtaining the one-to-one correspondence between the grinding tool and the shape and size of the air film hole, and by filtering tools based on the target geometric information, the identifier of the tool suitable for the geometric features of the air film hole at the location coordinates of the air film hole is obtained, i.e., the target tool identifier. Finally, control the through hole grinding equipment to retrieve the grinding tool corresponding to the target tool identifier, and perform deburring and chamfering treatment on the air film hole corresponding to the processing coordinates of the air film hole using the grinding tool.Therefore, the grinding tool corresponding to the target tool can be retrieved to ensure that the most suitable tool is used for each film gas hole. This ensures that the processing parameters (such as tool selection) of each film gas hole match its precise geometric information, reducing processing quality problems caused by tool mismatch (such as unstable quality, uneven tool wear or damage to the hole wall), and improving the deburring and chamfering effect of film gas holes on gas turbine blades.

[0092] Further reference Figure 2 As an implementation of the methods shown in the figures, this disclosure provides some embodiments of a through-hole device for gas turbine blades, which are similar to... Figure 1 Corresponding to the method embodiments shown, the device can be specifically applied to various electronic devices.

[0093] like Figure 2 As shown, a through-hole device 200 for a gas turbine blade in some embodiments includes: a clamping unit 201, a drilling unit 202, a moving unit 203, a position recognition unit 204, a first acquisition unit 205, a second acquisition unit 206, a mapping space alignment unit 207, and a control unit 208. The clamping unit 201 is configured to clamp and fix the gas turbine blade using a clamp; the drilling unit 202 is configured to control a drilling device to drill holes in the gas turbine blade to form film gas holes; the moving unit 203 is configured to control the clamp to move the gas turbine blade after the film gas holes have been drilled to a preset position on the through-hole grinding machine tool; the position recognition unit 204 is configured to identify the position of at least one film gas hole on the gas turbine blade on the through-hole grinding machine tool to correct and adjust the position of the gas turbine blade on the through-hole grinding machine tool; the first acquisition unit 205 is configured to... The first acquisition unit 206 is configured to acquire a pre-established machine tool reference coordinate system; the second acquisition unit 206 is configured to acquire a device coordinate system created by the through-hole grinding equipment; the mapping space alignment unit 207 is configured to perform mapping space alignment processing on the machine tool reference coordinate system and the device coordinate system to obtain space alignment mapping information; the control unit 208 is configured to extract the geometric information set corresponding to at least one film gas hole on the gas turbine blade after correction and adjustment, and based on the geometric information set and the space alignment mapping information, control the through-hole grinding equipment to change the grinding tool to perform deburring and chamfering processing on the film gas hole.

[0094] It is understandable that the units described in the device 200 are related to the reference. Figure 1 The steps in the method described above correspond to each other. Therefore, the operations, features, and beneficial effects described above for the method also apply to the device 200 and the units contained therein, and will not be repeated here.

[0095] The following is for reference. Figure 3It shows a schematic diagram of the structure of an electronic device 300 suitable for implementing some embodiments of the present disclosure. Figure 3 The electronic device shown is merely an example and should not be construed as limiting the functionality and scope of the embodiments of this disclosure.

[0096] like Figure 3 As shown, the electronic device 300 may include a processing unit (e.g., a central processing unit, a graphics processing unit, etc.) 301, which can perform various appropriate actions and processes according to a program stored in a read-only memory (ROM) 302 or a program loaded from a storage device 308 into a random access memory (RAM) 303. The RAM 303 also stores various programs and data required for the operation of the electronic device 300. The processing unit 301, ROM 302, and RAM 303 are interconnected via a bus 304. An input / output (I / O) interface 305 is also connected to the bus 304.

[0097] Typically, the following devices can be connected to I / O interface 305: input devices 306 including, for example, touchscreens, touchpads, keyboards, mice, cameras, microphones, accelerometers, gyroscopes, etc.; output devices 307 including, for example, liquid crystal displays (LCDs), speakers, vibrators, etc.; storage devices 308 including, for example, magnetic tapes, hard disks, etc.; and communication devices 309. Communication device 309 allows electronic device 300 to communicate wirelessly or wiredly with other devices to exchange data. Although Figure 3 An electronic device 300 with various devices is shown; however, it should be understood that it is not required to implement or possess all of the devices shown. More or fewer devices may be implemented or possessed alternatively. Figure 3 Each box shown can represent a device or multiple devices as needed.

[0098] In particular, according to some embodiments of this disclosure, the processes described above with reference to the flowcharts can be implemented as computer software programs. For example, some embodiments of this disclosure include a computer program product comprising a computer program carried on a computer-readable medium, the computer program containing program code for performing the methods shown in the flowcharts. In such embodiments, the computer program can be downloaded and installed from a network via communication device 309, or installed from storage device 308, or installed from ROM 302. When the computer program is executed by processing device 301, it performs the functions defined in the methods of some embodiments of this disclosure.

[0099] It should be noted that, in some embodiments of this disclosure, the computer-readable medium may be a computer-readable signal medium or a computer-readable storage medium, or any combination thereof. A computer-readable storage medium may be, for example,—but not limited to—an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination thereof. More specific examples of a computer-readable storage medium may include, but are not limited to: an electrical connection having one or more wires, a portable computer disk, a hard disk, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, portable compact disk read-only memory (CD-ROM), optical storage device, magnetic storage device, or any suitable combination thereof. In some embodiments of this disclosure, a computer-readable storage medium may be any tangible medium containing or storing a program that can be used by or in conjunction with an instruction execution system, apparatus, or device. In some embodiments of this disclosure, a computer-readable signal medium may include a data signal propagated in baseband or as part of a carrier wave, carrying computer-readable program code. Such propagated data signals may take various forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination thereof. A computer-readable signal medium can be any computer-readable medium other than a computer-readable storage medium, which can send, propagate, or transmit a program for use by or in connection with an instruction execution system, apparatus, or device. The program code contained on the computer-readable medium can be transmitted using any suitable medium, including but not limited to: wires, optical fibers, RF (radio frequency), etc., or any suitable combination thereof.

[0100] In some implementations, clients and servers can communicate using any currently known or future-developed network protocol such as HTTP (Hypertext Transfer Protocol) and can interconnect with digital data communication (e.g., communication networks) of any form or medium. Examples of communication networks include local area networks (“LANs”), wide area networks (“WANs”), the Internet (e.g., the Internet of Things), and peer-to-peer networks (e.g., ad hoc peer-to-peer networks), as well as any currently known or future-developed networks.

[0101] The computer-readable medium may be included in an electronic device or may exist independently without being assembled into the electronic device. The computer-readable medium carries one or more programs that, when executed by the electronic device, cause the electronic device to: clamp and fix a gas turbine blade using a fixture; control a drilling device to drill holes in the gas turbine blade to form film gas holes; control the fixture to move the gas turbine blade with the film gas holes drilled to a preset position on a through-hole grinding machine tool; identify the position of at least one film gas hole on the gas turbine blade on the through-hole grinding machine tool to correct and adjust the position of the gas turbine blade on the through-hole grinding machine tool; acquire a pre-established machine tool reference coordinate system; acquire a device coordinate system created by the through-hole grinding machine; perform spatial alignment processing on the machine tool reference coordinate system and the device coordinate system to obtain spatial alignment mapping information; extract the geometric information set corresponding to at least one film gas hole on the corrected and adjusted gas turbine blade, and based on the geometric information set and the spatial alignment mapping information, control the through-hole grinding machine to change the grinding tools to perform deburring and chamfering processing on the film gas holes.

[0102] Computer program code for performing operations of some embodiments of this disclosure can be written in one or more programming languages ​​or a combination thereof. Programming languages ​​include object-oriented programming languages—such as Java, Smalltalk, and C++—and conventional procedural programming languages—such as the "C" language or similar programming languages. The program code can be executed entirely on the user's computer, partially on the user's computer, as a standalone software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In cases involving remote computers, the remote computer can be connected to the user's computer via any type of network—including a local area network (LAN) or a wide area network (WAN)—or can be connected to an external computer (e.g., via the Internet using an Internet service provider).

[0103] The flowcharts and block diagrams in the accompanying drawings illustrate the architecture, functionality, and operation of possible implementations of systems, methods, and computer program products according to various embodiments of this disclosure. In this regard, each block in a flowchart or block diagram may represent a module, segment, or portion of code containing one or more executable instructions for implementing a specified logical function. It should also be noted that in some alternative implementations, the functions indicated in the blocks may occur in a different order than those indicated in the drawings. For example, two consecutively indicated blocks may actually be executed substantially in parallel, and they may sometimes be executed in reverse order, depending on the functions involved. It should also be noted that each block in the block diagrams and / or flowcharts, and combinations of blocks in the block diagrams and / or flowcharts, can be implemented using a dedicated hardware-based system that performs the specified function or operation, or using a combination of dedicated hardware and computer instructions.

[0104] The units described in some embodiments of this disclosure can be implemented in software or hardware. The described units can also be housed in a processor; for example, a processor may be described as including a gripping unit, a punching unit, a moving unit, a position recognition unit, a first acquisition unit, a second acquisition unit, a mapping space alignment unit, and a control unit. The names of these units do not necessarily limit the specific unit; for example, a gripping unit may also be described as "a unit for gripping and fixing gas turbine blades using a clamp."

[0105] The functions described above in this document can be performed at least in part by one or more hardware logic components. For example, exemplary types of hardware logic components that can be used, without limitation, include: field-programmable gate arrays (FPGAs), application-specific integrated circuits (ASICs), application-specific standard products (ASSPs), system-on-a-chip (SoCs), complex programmable logic devices (CPLDs), and so on.

[0106] The above description is merely a selection of preferred embodiments of this disclosure and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of the invention involved in the embodiments of this disclosure is not limited to technical solutions formed by specific combinations of technical features, but should also cover other technical solutions formed by arbitrary combinations of technical features or their equivalents without departing from the inventive concept. For example, technical solutions formed by substituting features with (but not limited to) technical features with similar functions disclosed in the embodiments of this disclosure.

Claims

1. A method for creating a through-hole in a gas turbine blade, comprising: Gas turbine blades are clamped and fixed using fixtures; Control the drilling equipment to drill holes in the gas turbine blades to form film gas pores; The control fixture moves the gas turbine blade, after the film cooling holes have been drilled, to a preset position on the through-hole grinding machine tool. This movement includes: Images and depth maps of the fixture are captured by a depth camera fixed on a through-hole grinding machine. The fixture image is processed to identify fixture feature points, and the two-dimensional coordinates of the feature points are obtained. Acquire the calibration information of the camera whose image acquisition fixture is fixed; Based on the two-dimensional coordinates of the feature points and the calibration information, the three-dimensional coordinates of the fixture feature points are generated. Based on the three-dimensional coordinates of the fixture feature points and the three-dimensional coordinates of the preset fixed fixture feature points, translational incremental information is generated; Based on the translational increment information, the control fixture moves the gas turbine blade after the air film hole is drilled to a preset position on the through hole grinding machine tool. The position of at least one film gas hole on a gas turbine blade on a through-hole grinding machine tool is identified in order to correct and adjust the position of the gas turbine blade on the through-hole grinding machine tool. Obtain the pre-established machine tool reference coordinate system; Obtain the equipment coordinate system created by the through-hole grinding equipment; The machine tool reference coordinate system and the equipment coordinate system are subjected to spatial alignment processing to obtain spatial alignment mapping information. The machine tool reference coordinate system includes the predefined geometric center coordinates of the gas turbine blade, workpiece coordinates of at least three fixture feature points, and coordinates of at least one film cooling hole on the blade. The equipment coordinate system includes machining coordinates of at least three fixture feature points. The workpiece coordinates of the fixture feature points in the at least three fixture feature point workpiece coordinates correspond one-to-one with the machining coordinates of the fixture feature points in the at least three fixture feature point machining coordinates. The process of performing spatial alignment processing on the machine tool reference coordinate system and the equipment coordinate system to obtain spatial alignment mapping information includes: Based on the workpiece coordinates of the at least three fixture feature points and the machining coordinates of the at least three fixture feature points, determine the rigid body transformation matrix from the machine tool reference coordinate system to the equipment coordinate system; The rigid body transformation matrix is ​​determined as spatial alignment mapping information; Extract the geometric information set corresponding to at least one film gas hole on the gas turbine blade after correction and adjustment, and based on the geometric information set and the spatial alignment mapping information, control the through hole grinding equipment to change the grinding tools to perform deburring and chamfering treatment on the film gas hole.

2. The method according to claim 1, wherein, The controlled drilling equipment drills holes in the gas turbine blades to form film gas holes, including: Obtain a pre-created three-dimensional model of the blade corresponding to the gas turbine blade, wherein the three-dimensional model of the blade is marked with film gas pore parameters; The three-dimensional model of the blade is input into a preset CNC programming converter to obtain drilling execution task information; The drilling equipment is controlled to perform a drilling task corresponding to the drilling execution task information, so as to control the drilling equipment to drill holes on the gas turbine blade to form film gas holes.

3. The method according to claim 1, wherein, The step of identifying the position of at least one film gas hole on the gas turbine blade on the through-hole grinding machine tool, in order to correct and adjust the position of the gas turbine blade on the through-hole grinding machine tool, includes: The point cloud data of the blade surface is obtained by scanning the gas turbine blade with a laser line scanner on the hole grinding machine tool. Edge detection is performed on the point cloud data of the blade surface to obtain edge point cloud data, wherein the edge point cloud data includes information of each edge point; Clustering is performed on the edge point cloud data to obtain various edge point information groups; For each edge point information group in the aforementioned edge point information groups, perform the following steps: The edge point information group is subjected to aperture fitting detection processing to obtain aperture fitting detection information; In response to the determination that the aperture fitting detection information does not meet the preset fitting conditions, the edge point information is deleted from the edge point information group to update each edge point information group; The updated edge point information groups are defined as the updated edge point information group set; Based on each updated edge point information group in the updated edge point information group set, generate air film pore location information; Based on the location information of each air film pore and the preset air film pore calibration location information set, reference offset detection information is generated; Based on the reference offset detection information, the position of the gas turbine blades on the through hole grinding machine is corrected and adjusted.

4. The method according to claim 1, wherein, The step of identifying the position of at least one film gas hole on the gas turbine blade on the through-hole grinding machine tool, in order to correct and adjust the position of the gas turbine blade on the through-hole grinding machine tool, includes: Images of gas turbine blades on a through-hole grinding machine tool are collected as images to be inspected. The geometric center coordinates of the gas turbine blades in the image to be detected are used as the geometric center coordinates to be detected. The pre-defined geometric center coordinates of the gas turbine blades are used as the reference geometric center coordinates. Determine the difference between the coordinates of the geometric center to be detected and the coordinates of the reference geometric center; In response to determining that the difference value is greater than a preset threshold, the position of the gas turbine blade on the through hole grinding equipment is corrected and adjusted.

5. A through-hole device for implementing the method as described in any one of claims 1 to 4 for a gas turbine blade, comprising: The gripping unit is configured to grip and fix the gas turbine blades using clamps; The drilling unit is configured to control the drilling equipment to drill holes in the gas turbine blades to form film gas holes; The moving unit is configured to control the fixture to move the gas turbine blades after the film gas flow holes have been drilled to a preset position on the through hole grinding machine tool; The position recognition unit is configured to recognize the position of at least one film gas hole on a gas turbine blade on a through-hole grinding machine tool in order to correct and adjust the position of the gas turbine blade on the through-hole grinding machine tool. The first acquisition unit is configured to acquire a pre-established machine tool reference coordinate system; The second acquisition unit is configured to acquire the device coordinate system created by the through-hole grinding equipment; The mapping space alignment unit is configured to perform mapping space alignment processing on the machine tool reference coordinate system and the device coordinate system to obtain space alignment mapping information; The control unit is configured to extract a set of geometric information corresponding to at least one film gas hole on the gas turbine blade after correction and adjustment, and based on the set of geometric information and the spatial alignment mapping information, control the through hole grinding equipment to change the grinding tools to perform deburring and chamfering treatment on the film gas hole.

6. An electronic device, comprising: One or more processors; A storage device on which one or more programs are stored; When the one or more programs are executed by the one or more processors, the one or more processors implement the method as described in any one of claims 1 to 4.

7. A computer-readable medium having a computer program stored thereon, wherein, When the program is executed by the processor, it implements the method as described in any one of claims 1 to 4.

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