A method for modeling and assembling a compressor blade and disk combination

Abstract

The application provides a combined modeling and assembling method for compressor blades and a wheel disc, relates to the technical fields of compressors, three-dimensional surveying and reverse modeling, and comprises the following steps: initially aligning surveying data of a blade root of a compressor blade and a tenon groove of a wheel disc in three dimensions, determining a stretching direction and a symmetry axis of the blade root and the tenon groove according to the surveying data, constructing the contour lines of the blade root and the tenon groove by using point cloud data of the blade root and the tenon groove and the symmetry axis, determining a three-dimensional entity model of the blade root and the tenon groove by using the constructed contour lines and the stretching direction, and finally adjusting the spatial position of the blade root model to realize the assembling and alignment of the compressor blade and the tenon groove of the wheel disc. Compared with the independent modeling method for the compressor blade and the wheel disc, the combined modeling method saves the step of adjusting the contour lines of the blade root model and the tenon groove model of the wheel disc, and the modeling and assembling accuracy is improved due to the mutual comparison and reference of the compressor blade root and the tenon groove of the wheel disc during the modeling process.

Description

Technical Field

[0001] This application relates to the fields of compressor, 3D mapping and reverse modeling technology, and in particular to a method for combined modeling and assembly of compressor blades and disks. Background Technology

[0002] When performing 3D mapping and reverse engineering of compressor blades and their rotors, the contact area between the compressor blade root and the rotor is difficult to map due to the fit between them. A common practice is to remove the compressor blade from the rotor's tenon, perform 3D mapping on both the compressor blade with its root and the compressor rotor with its tenon, and then reverse model both based on the mapping data. The resulting rotor and compressor blade models are then reassembled. While this method avoids 3D alignment based on the compressor blade and rotor mapping data, it makes it difficult to accurately locate the rotation axis of the blade root hub surface during reverse engineering. Furthermore, during the later assembly of the compressor blade model and rotor, the shape of the rotor's tenon needs to be adjusted according to the blade root shape to ensure proper contact alignment between the blade root and the rotor's tenon working surfaces.

[0003] While 3D alignment of the compressor blades and rotor data before model building can solve the problems of blade root rotation axis positioning and subsequent adjustments to the models after assembly, the small spacing between the compressor rotor's tenon and groove allows only a limited amount of data to be obtained through 3D scanning. Furthermore, noise in the scanned data makes 3D alignment of the compressor blades and rotor difficult. Therefore, it is necessary to develop a new reverse modeling and assembly method for compressor blades and rotor to address the cumbersome and inaccurate reverse modeling and assembly process. Summary of the Invention

[0004] This application aims to at least partially address one of the technical problems in the related art.

[0005] Therefore, one objective of this application is to propose a method for modeling and assembling a compressor blade and a rotor disk, including:

[0006] S1. Obtain the three-dimensional point cloud data of the compressor blade and the three-dimensional point cloud data of the compressor disk, and perform three-dimensional alignment on the three-dimensional point cloud data of the blade and the three-dimensional point cloud data of the disk to obtain the three-dimensional point cloud combination data of the compressor blade and the disk generated after three-dimensional alignment. In the three-dimensional point cloud combination data, the bottom surface of the compressor blade root and the bottom surface of the tenon groove of the disk are in the same plane.

[0007] S2, the blade three-dimensional point cloud data is divided into blade root three-dimensional point cloud data corresponding to the blade root and the remaining blade three-dimensional point cloud data other than the blade root three-dimensional point cloud data, and the wheel disk three-dimensional point cloud data is divided into tenon groove three-dimensional point cloud data corresponding to the wheel disk tenon groove structure and the remaining wheel disk three-dimensional point cloud data other than the tenon groove three-dimensional point cloud data.

[0008] S3. Based on the remaining three-dimensional point cloud data of the compressor disk, construct a local model of the compressor disk, wherein the local model of the compressor disk does not include the tenon and slot structure; and based on the remaining three-dimensional point cloud data of the blade, construct a compressor blade model, wherein the compressor blade model does not include the blade root structure.

[0009] S4. Based on the three-dimensional point cloud data of the blade root and the three-dimensional point cloud data of the tenon groove, determine the blade root stretching direction and the wheel disk tenon groove stretching direction, and determine the axis of symmetry between the blade root and the wheel disk tenon groove according to the blade root stretching direction and the wheel disk tenon groove stretching direction.

[0010] S5. Using the normal plane of the blade root stretching direction or the wheel disk tenon groove stretching direction as the section, extract the three-dimensional point cloud data of the blade root and the three-dimensional point cloud data of the tenon groove. Based on the extracted three-dimensional point cloud data of the blade root and the three-dimensional point cloud data of the tenon groove, combine the axis of symmetry to draw the blade root contour line and the wheel disk tenon groove contour line.

[0011] S6. Based on the blade root profile and the blade root stretching direction, construct a blade root model; and based on the wheel disk tenon and groove profile, the wheel disk tenon and groove stretching direction, and the compressor wheel disk local model, construct an overall compressor wheel disk model.

[0012] S7, adjust the spatial position of the blade root model until the working surface of the blade root model is in contact with and aligned with the overall model of the compressor wheel;

[0013] S8. Trim the upper end face and the front and rear axial end faces of the blade root model, and merge the trimmed blade root model with the compressor blade model into a whole to obtain a complete compressor blade and disk assembly model.

[0014] Further, the step of constructing a local model of the compressor disk based on the remaining three-dimensional point cloud data of the disk includes: determining the rotation axis of the disk based on the remaining three-dimensional point cloud data of the disk; intercepting the disk contour point cloud data with a target plane passing through the disk rotation axis; constructing the compressor disk contour profile using the intercepted disk contour point cloud data; and then performing reverse reconstruction of the local model of the compressor disk to obtain the local model of the compressor disk after reverse reconstruction.

[0015] Furthermore, the step of constructing a compressor blade model based on the remaining three-dimensional point cloud data of the blade includes: uniformly selecting N blade height sections along the blade height direction based on the remaining three-dimensional point cloud data of the blade; constructing blade profiles using the point cloud data extracted from the N blade height sections; and performing reverse reconstruction of the compressor blade model based on the N blade profiles to obtain the compressor blade model obtained after reverse reconstruction.

[0016] Further, the step of performing three-dimensional alignment on the three-dimensional point cloud data of the blade and the three-dimensional point cloud data of the turbine disk to obtain the three-dimensional point cloud combination data of the compressor blade and the turbine disk after three-dimensional alignment includes: establishing a first spatial rectangular coordinate system corresponding to the compressor turbine disk based on the three-dimensional point cloud data of the turbine disk; establishing a second spatial rectangular coordinate system corresponding to the compressor blade based on the three-dimensional point cloud data of the blade; and performing coordinate transformation on the three-dimensional point cloud data of the blade and the three-dimensional point cloud data of the turbine disk based on the first spatial rectangular coordinate system and the second spatial rectangular coordinate system to obtain the three-dimensional point cloud combination data.

[0017] Furthermore, when N blade height sections are uniformly selected along the blade height direction of the compressor blade, the N blade height sections are parallel to the blade root section or blade tip section, and N is a positive integer greater than 10.

[0018] Furthermore, when drawing the leaf root contour line and the wheel disk tenon contour line based on the extracted leaf root three-dimensional point cloud data and the tenon groove three-dimensional point cloud data, combined with the axis of symmetry, the drawing plane is the normal plane of the leaf root or tenon groove stretching direction. When drawing, it is necessary to ensure that the working surface contour lines of the leaf root and the wheel disk tenon groove are parallel and the bottom contour lines are collinear.

[0019] Furthermore, when drawing the leaf root contour line and the wheel mortise contour line based on the extracted leaf root three-dimensional point cloud data and the tenon groove three-dimensional point cloud data, combined with the axis of symmetry, the contour lines of a portion of the leaf root or wheel mortise groove are first drawn, and the contour lines of another portion are obtained by mirror symmetry through the axis of symmetry determined in step S4. When drawing the leaf root contour line, its radial contour line needs to be appropriately extended, and the leaf root contour line group is closed.

[0020] Furthermore, when constructing the blade root model based on the blade root profile and the blade root stretching direction, and when constructing the compressor disk overall model based on the disk tenon and slot profile, the disk tenon and slot stretching direction, and the compressor disk local model, the stretching method is used.

[0021] Furthermore, when adjusting the spatial position of the blade root model in step S7, the compressor blade model determined in step S3 also needs to move along with the blade root model. The direction of movement is the axis of symmetry between the blade root and the wheel disk tenon, and the distance of movement is the distance between the working surfaces of the blade root and the wheel disk tenon along the axis of symmetry. After adjusting the spatial positions of the compressor blade model and the blade root model, the working surfaces of the blade root and the wheel disk tenon are aligned.

[0022] Furthermore, the trimming of the upper end face and the front and rear axial end faces of the blade root model includes: trimming the upper end face of the blade root model with a rotating surface constructed by the rotation axis of the compressor disk and the hub surface profile; and trimming the front and rear end faces of the blade root model with the front and rear axial end faces of the compressor disk model.

[0023] This application achieves at least the following beneficial effects: 1. The method for combined modeling and assembly of compressor blades and rotor disks proposed in this application involves preliminary three-dimensional alignment of the compressor blade root and rotor disk tenon groove mapping data, determining the common stretching direction and axis of symmetry of the blade root and tenon groove based on the mapping data, and then constructing the contour lines of the blade root and tenon groove using the point cloud data of the blade root and tenon groove and their axis of symmetry obtained by the stretching direction plane. The three-dimensional solid model of the blade root and rotor disk tenon groove is then determined using the constructed contour lines and stretching direction. Finally, the spatial position of the blade root model is adjusted to achieve the assembly alignment of the compressor blade root and rotor disk tenon groove. Compared with the independent modeling of compressor blades and rotor disks, the combined modeling method eliminates the final step of adjusting the contour lines of the blade root model and rotor disk tenon groove model. Furthermore, because the compressor blade root and rotor disk tenon groove are compared and referenced each other during the modeling process, the accuracy of modeling and assembly is significantly improved.

[0024] 2. In the combined modeling and assembly method of compressor blades and disk proposed in this application, before modeling the compressor blades and disk, the blade root and tenon groove models are initially aligned in three dimensions by establishing a corresponding spatial rectangular coordinate system. After alignment, the bottom planes of the compressor blade root and the disk tenon groove coincide, the axial end faces of the compressor blade root and the disk tenon groove coincide, and the symmetrical planes of the compressor blade root and the disk tenon groove coincide. The compressor blade root and the disk tenon groove only have a certain spatial position difference in the radial direction. After the modeling is completed, only the radial spatial position of the compressor blade root model needs to be adjusted to achieve the assembly alignment of the blade root and the disk tenon groove, eliminating the tedious positioning and adjustment steps.

[0025] 3. In the combined modeling and assembly method of compressor blades and disks proposed in this application, when drawing the contour lines of the compressor blade root model and the disk tenon and groove model, while ensuring that the contour lines pass through as much point cloud data as possible, the working surface contour lines of the blade root model and the tenon and groove model are parallel and their bottom plane contour lines are collinear. Subsequently, when assembling and aligning the compressor blade root model and the disk tenon and groove, only the spatial position of the compressor blade root model needs to be adjusted without adjusting the contour lines of the blade root or tenon and groove.

[0026] 4. In the combined modeling and assembly method of compressor blades and disks proposed in this application, when trimming the upper surface of the three-dimensional solid model of the compressor blade root, the final position of the blade root model is first determined based on the contact alignment between the blade root and the working surface of the tenon groove. Then, the upper surface of the compressor blade root is trimmed using the rotating surface constructed by the compressor disk rotation axis and the hub surface profile. Compared with the separate modeling method, this overcomes the defect of difficulty in determining the rotation axis and hub surface profile of the blade root model.

[0027] 5. In the combined modeling and assembly method of compressor blade and disk proposed in this application, the determined stretching direction and axis of symmetry are the common stretching direction and axis of symmetry of compressor blade root and disk tenon groove. Finally, when adjusting the spatial position of blade root model, it is only necessary to ensure that the working surfaces of blade root model and disk tenon groove model are in contact and aligned to achieve the assembly of the two, which significantly improves the accuracy of modeling and assembly. Attached Figure Description

[0028] The above and / or additional aspects and advantages of this application will become apparent and readily understood from the following description of the embodiments taken in conjunction with the accompanying drawings, wherein:

[0029] Figure 1 This is a schematic diagram illustrating an exemplary embodiment of a method for modeling and assembling a compressor blade and a disk, as shown in one embodiment of this application.

[0030] Figure 2 This is a schematic diagram of three-dimensional point cloud data of a compressor disk obtained by three-dimensional mapping, as shown in one embodiment of this application.

[0031] Figure 3 This is a schematic diagram of the blade root portion in the three-dimensional point cloud data of a compressor blade obtained by three-dimensional mapping, as shown in one embodiment of this application.

[0032] Figure 4 This is a schematic diagram showing the determination of the stretching direction and axis of symmetry of the compressor blade root and the wheel disc tenon groove.

[0033] Figure 5 This is a schematic diagram of the compressor blade root profile and the wheel disc tenon profile shown in one embodiment of this application.

[0034] Explanation of reference numerals in the attached figures:

[0035] 1. Side end face of the wheel disk tenon groove; 2. Axial end face of the wheel disk tenon groove; 3. Bottom surface of the wheel disk tenon groove; 4. Side end face of the compressor blade root; 5. Axial end face of the compressor blade root; 6. Bottom surface of the compressor blade root; 7. Outline of the wheel disk tenon groove; 8. Outline of the compressor blade root. Detailed Implementation

[0036] The embodiments of this application are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application.

[0037] Figure 1 This is a schematic diagram of an exemplary embodiment of a method for modeling and assembling a compressor blade and a rotor disk as shown in this application. Figure 1 As shown, the method for modeling and assembling the compressor blades and disk includes the following steps:

[0038] S101, acquire the three-dimensional point cloud data of the compressor blade and the three-dimensional point cloud data of the compressor disk, and perform three-dimensional alignment on the three-dimensional point cloud data of the blade and the disk, and acquire the three-dimensional point cloud combination data of the compressor blade and the disk generated after three-dimensional alignment, wherein the blade root bottom surface of the compressor blade and the tenon groove bottom surface of the disk are in the same plane in the three-dimensional point cloud combination data.

[0039] Figure 2 This is a schematic diagram of three-dimensional point cloud data of a compressor disk obtained through three-dimensional mapping, as shown in one embodiment of this application. Figure 2 As shown, based on the three-dimensional point cloud data of the compressor disk, a first plane P1 and a second plane P2 are established passing through the two end faces 1 of the disk tenon groove, a third plane P3 is established passing through the bottom surface 3 of the disk tenon groove, and a fourth plane P4 is established passing through the axial end face 2 of the disk tenon groove. The midpoint between the first plane P1 and the second plane P2 is denoted as P5, and plane P5 intersects the third plane P3 and the fourth plane P4 at a first intersection point O. A first spatial rectangular coordinate system C1 is established with the first intersection point O as the origin, and the third plane P3 and the fourth plane P4 as the normal planes of the z-axis and y-axis, respectively.

[0040] akin, Figure 3 This is a schematic diagram of the blade root portion in three-dimensional point cloud data of a compressor blade obtained through three-dimensional mapping, as shown in one embodiment of this application. Figure 3As shown, based on the 3D point cloud data of the compressor blade root portion, a first plane P1' and a second plane P2' are established passing through the two end faces 4 of the blade root, a third plane P3' is established passing through the bottom surface 6 of the blade root, and a fourth plane P4' is established passing through the axial end face 5 of the blade root. The midpoint between the first plane P1' and the second plane P2' is denoted as P5', and plane P5' intersects the third plane P3' and the fourth plane P4' at a first intersection point O'. A second spatial rectangular coordinate system C1' is established with the first intersection point O' as the origin, and the third plane P3' and the fourth plane P4' as the normal planes of the z-axis and y-axis, respectively.

[0041] By transforming coordinates, the 3D point cloud data of the compressor blade in the second spatial rectangular coordinate system C1' is aligned to the first spatial rectangular coordinate system C1, resulting in a combined 3D point cloud data of the compressor blade and the rotor after preliminary 3D alignment. At this point, the bottom surface 6 of the compressor blade root and the bottom surface 3 of the rotor tenon groove are on the same plane.

[0042] S102, divide the blade 3D point cloud data into blade root 3D point cloud data corresponding to the blade root and the remaining blade 3D point cloud data excluding the blade root 3D point cloud data, and divide the wheel disk 3D point cloud data into tenon groove 3D point cloud data corresponding to the wheel disk tenon groove structure and the remaining wheel disk 3D point cloud data excluding the tenon groove 3D point cloud data.

[0043] S103. Based on the remaining three-dimensional point cloud data of the compressor disk, construct a local model of the compressor disk, wherein the local model of the compressor disk does not include the tenon and slot structure. Based on the remaining three-dimensional point cloud data of the blades, construct a compressor blade model, wherein the compressor blade model does not include the blade root structure.

[0044] Based on the remaining 3D point cloud data of the compressor disk, select as many regular point cloud data as possible on the rotating surface of the compressor disk to determine the rotation axis of the disk. Use a target plane passing through the rotation axis of the disk to intercept the remaining 3D point cloud data of the disk to obtain the disk contour point cloud data. The selected target plane should avoid passing through the tenon and groove structure of the disk as much as possible to obtain a sufficient amount of disk contour point cloud data. Construct the compressor disk contour profile using the intercepted disk contour point cloud data, and then perform reverse reconstruction of the local model of the compressor disk to obtain the local model of the compressor disk after reverse reconstruction. The local model of the compressor disk obtained at this time does not include the tenon and groove structure.

[0045] Based on the remaining 3D point cloud data of the blade, N blade height sections are uniformly selected along the blade height direction of the compressor blade. The blade profile is constructed using the point cloud data extracted from these N blade height sections, and the compressor blade model is then reverse-reconstructed based on these N blade profiles to obtain the reverse-reconstructed compressor blade model. The N blade height sections are parallel to either the blade root section or the blade tip section, and N is a positive integer greater than 10. When uniformly selecting N blade height sections along the compressor blade height direction, a starting plane P, approximately parallel to the blade root, is constructed near the chamfer region of the compressor blade. s Construct a plane P in the near-leaf tip region. s Parallel termination plane P e and in the initial plane P s With the termination plane P e Several parallel and evenly distributed blade height sections are inserted in the middle to obtain N blade height sections.

[0046] S104. Based on the three-dimensional point cloud data of the blade root and the three-dimensional point cloud data of the tenon groove, the stretching direction of the blade root and the stretching direction of the wheel disk tenon groove are determined, and the axis of symmetry between the blade root and the wheel disk tenon groove is determined according to the stretching direction of the blade root and the stretching direction of the wheel disk tenon groove.

[0047] Figure 4 This application shows a schematic diagram illustrating the determination of the stretching direction and axis of symmetry between the compressor blade root and the rotor tongue, as follows: Figure 4 As shown, construct a plane P parallel to the bottom surface 6 of the compressor blade root. 3l ', plane P 3l 'The intersection with the compressor blade root side end face 4 results in the blade root side end face 4 on plane P 3l The point cloud data within the specified area is used to construct a straight line, which represents the stretching direction n1 of the compressor blade root. A normal plane P is then constructed based on the stretching direction n1. n normal plane P n The line L1, which intersects the plane of symmetry P5' of the compressor blade root, is the axis of symmetry of the compressor blade root. The final stretching direction n1 and the axis of symmetry L1 are the common stretching direction and axis of symmetry of the compressor blade root and the wheel disc tenon.

[0048] S105, using the normal plane of the blade root stretching direction or the wheel disk tenon groove stretching direction as the section, extract the three-dimensional point cloud data of the blade root and the three-dimensional point cloud data of the tenon groove. Based on the extracted three-dimensional point cloud data of the blade root and the tenon groove, combine the axis of symmetry to draw the outline of the blade root and the outline of the wheel disk tenon groove.

[0049] Figure 5 This is a schematic diagram illustrating the compressor blade root profile and the wheel disc tenon profile of one embodiment of this application, as shown below. Figure 5 As shown, the normal plane P of the constructed blade root stretching direction or wheel mortise stretching direction n1 is...n Extract the 3D point cloud data of the leaf root and the 3D point cloud data of the tenon groove, and then, based on the extracted 3D point cloud data of the leaf root and the 3D point cloud data of the tenon groove, plot the data on the normal plane P. n Draw the outline of the leaf root and the outline of the wheel mortise and tenon. When drawing, ensure that the working surface outlines of the leaf root and the wheel mortise and tenon are parallel and the bottom outlines are collinear.

[0050] When drawing the leaf root contour lines and the wheel mortise and tenon contour lines, first draw the contour lines of part of the leaf root or wheel mortise and tenon, and obtain the contour lines of another part by mirror symmetry through the axis of symmetry L1 determined in step S104. When drawing the leaf root contour lines, it is necessary to extend its radial contour lines appropriately and close the leaf root contour line group.

[0051] S106. Based on the blade root profile and blade root stretching direction, construct the blade root model. Based on the rotor groove profile, rotor groove stretching direction, and compressor rotor local model, construct the compressor rotor overall model.

[0052] Based on the compressor blade root profile 8 and the blade root stretching direction n1, the blade root model is constructed using a stretching method.

[0053] Based on the contour line 7 of the wheel disk tenon and groove, the stretching direction n1 of the wheel disk tenon and groove, and the local model of the compressor wheel disk, the overall model of the compressor wheel disk is constructed by stretching.

[0054] S107, Adjust the spatial position of the blade root model until the working surface of the blade root model is in contact with and aligned with the overall model of the compressor wheel.

[0055] When adjusting the spatial position of the blade root model, the compressor blade model determined in step S103 also needs to move along with the blade root model. The direction of movement is the axis of symmetry L1 between the blade root and the wheel disk tenon groove, and the distance H is the distance between the working surfaces of the blade root and the wheel disk tenon groove along the axis of symmetry. After adjusting the spatial position of the compressor blade model and the blade root model, the working surfaces of the blade root and the wheel disk tenon groove are aligned.

[0056] S108, the upper end face and the front and rear axial end faces of the blade root model are trimmed, and the trimmed blade root model is merged with the compressor blade model into a whole to obtain a complete compressor blade and disk assembly model.

[0057] The rotating surface constructed by the rotating axis and hub profile of the compressor disk is used to trim the upper surface of the blade root model; the front and rear axial end faces of the compressor disk model are used to trim the front and rear end faces of the blade root model. The trimmed blade root model is then combined with the compressor blade model into a whole to obtain a complete compressor blade and disk assembly model.

[0058] This application achieves at least the following beneficial effects: 1. The method for combined modeling and assembly of compressor blades and rotor disks proposed in this application involves preliminary three-dimensional alignment of the compressor blade root and rotor disk tenon groove mapping data, determining the common stretching direction and axis of symmetry of the blade root and tenon groove based on the mapping data, and then constructing the contour lines of the blade root and tenon groove using the point cloud data of the blade root and tenon groove and their axis of symmetry obtained by the stretching direction plane. The three-dimensional solid model of the blade root and rotor disk tenon groove is then determined using the constructed contour lines and stretching direction. Finally, the spatial position of the blade root model is adjusted to achieve the assembly alignment of the compressor blade root and rotor disk tenon groove. Compared with the independent modeling of compressor blades and rotor disks, the combined modeling method eliminates the final step of adjusting the contour lines of the blade root model and rotor disk tenon groove model. Furthermore, because the compressor blade root and rotor disk tenon groove are compared and referenced each other during the modeling process, the accuracy of modeling and assembly is significantly improved.

[0059] 2. In the combined modeling and assembly method of compressor blades and disk proposed in this application, before modeling the compressor blades and disk, the blade root and tenon groove models are initially aligned in three dimensions by establishing a corresponding spatial rectangular coordinate system. After alignment, the bottom planes of the compressor blade root and the disk tenon groove coincide, the axial end faces of the compressor blade root and the disk tenon groove coincide, and the symmetrical planes of the compressor blade root and the disk tenon groove coincide. The compressor blade root and the disk tenon groove only have a certain spatial position difference in the radial direction. After the modeling is completed, only the radial spatial position of the compressor blade root model needs to be adjusted to achieve the assembly alignment of the blade root and the disk tenon groove, eliminating the tedious positioning and adjustment steps.

[0060] 3. In the combined modeling and assembly method of compressor blades and disks proposed in this application, when drawing the contour lines of the compressor blade root model and the disk tenon and groove model, while ensuring that the contour lines pass through as much point cloud data as possible, the working surface contour lines of the blade root model and the tenon and groove model are parallel and their bottom plane contour lines are collinear. Subsequently, when assembling and aligning the compressor blade root model and the disk tenon and groove, only the spatial position of the compressor blade root model needs to be adjusted without adjusting the contour lines of the blade root or tenon and groove.

[0061] 4. In the combined modeling and assembly method of compressor blades and disks proposed in this application, when trimming the upper surface of the three-dimensional solid model of the compressor blade root, the final position of the blade root model is first determined based on the contact alignment between the blade root and the working surface of the tenon groove. Then, the upper surface of the compressor blade root is trimmed using the rotating surface constructed by the compressor disk rotation axis and the hub surface profile. Compared with the separate modeling method, this overcomes the defect of difficulty in determining the rotation axis and hub surface profile of the blade root model.

[0062] 5. In the combined modeling and assembly method of compressor blade and disk proposed in this application, the determined stretching direction and axis of symmetry are the common stretching direction and axis of symmetry of compressor blade root and disk tenon groove. Finally, when adjusting the spatial position of blade root model, it is only necessary to ensure that the working surfaces of blade root model and disk tenon groove model are in contact and aligned to achieve the assembly of the two, which significantly improves the accuracy of modeling and assembly.

[0063] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application.

[0064] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0065] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0066] Although embodiments of this application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting this application. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of this application.

Claims

1. A method for modeling and assembling a compressor blade and a rotor disk, characterized in that, include: S1. Obtain the three-dimensional point cloud data of the compressor blade and the three-dimensional point cloud data of the compressor disk, and perform three-dimensional alignment on the three-dimensional point cloud data of the blade and the three-dimensional point cloud data of the disk to obtain the three-dimensional point cloud combination data of the compressor blade and the disk generated after three-dimensional alignment. In the three-dimensional point cloud combination data, the bottom surface of the compressor blade root and the bottom surface of the tenon groove of the disk are in the same plane. S2, the blade three-dimensional point cloud data is divided into blade root three-dimensional point cloud data corresponding to the blade root and the remaining blade three-dimensional point cloud data other than the blade root three-dimensional point cloud data, and the wheel disk three-dimensional point cloud data is divided into tenon groove three-dimensional point cloud data corresponding to the wheel disk tenon groove structure and the remaining wheel disk three-dimensional point cloud data other than the tenon groove three-dimensional point cloud data. S3, based on the remaining three-dimensional point cloud data of the compressor disk, construct a local model of the compressor disk, wherein the local model of the compressor disk does not include the tenon and slot structure; and based on the remaining three-dimensional point cloud data of the blade, construct a compressor blade model, wherein the compressor blade model does not include the blade root structure. S4. Based on the three-dimensional point cloud data of the blade root and the three-dimensional point cloud data of the tenon groove, determine the blade root stretching direction and the wheel disk tenon groove stretching direction, and determine the axis of symmetry between the blade root and the wheel disk tenon groove according to the blade root stretching direction and the wheel disk tenon groove stretching direction. S5, using the normal plane of the blade root stretching direction or the wheel disk tenon stretching direction as a section, extract the three-dimensional point cloud data of the blade root and the three-dimensional point cloud data of the tenon. Based on the extracted three-dimensional point cloud data of the blade root and the three-dimensional point cloud data of the tenon, combine the axis of symmetry to draw the blade root contour line and the wheel disk tenon contour line. S6. Based on the blade root profile and the blade root stretching direction, construct a blade root model; and based on the wheel disk tenon and groove profile, the wheel disk tenon and groove stretching direction, and the compressor wheel disk local model, construct an overall compressor wheel disk model. S7, Adjust the spatial position of the blade root model until the blade root model is in contact and aligned with the working surface of the compressor wheel disk integral model; S8, the upper end face and the front and rear axial end faces of the blade root model are trimmed, and the trimmed blade root model is merged with the compressor blade model into a whole to obtain a complete compressor blade and disk assembly model.

2. The method according to claim 1, characterized in that, The step of constructing a local model of the compressor disk based on the remaining three-dimensional point cloud data of the disk includes: Based on the remaining three-dimensional point cloud data of the roulette wheel, determine the rotation axis of the roulette wheel; The compressor disk contour point cloud data is intercepted by the target plane passing through the disk rotation axis. The compressor disk contour profile is constructed by using the intercepted disk contour point cloud data, and then the local model of the compressor disk is reverse reconstructed to obtain the local model of the compressor disk after reverse reconstruction.

3. The method according to claim 1, characterized in that, The construction of the compressor blade model based on the remaining three-dimensional point cloud data of the blade includes: Based on the remaining three-dimensional point cloud data of the blade, N blade height sections are uniformly selected along the blade height direction of the compressor blade. The blade profile is constructed by extracting point cloud data from N blade height sections, and the compressor blade model is reverse reconstructed based on the N blade profiles to obtain the compressor blade model after reverse reconstruction.

4. The method according to claim 1, characterized in that, The step of performing three-dimensional alignment on the three-dimensional point cloud data of the blade and the three-dimensional point cloud data of the rotor to obtain the combined three-dimensional point cloud data of the compressor blade and rotor after three-dimensional alignment includes: Based on the three-dimensional point cloud data of the compressor disk, a first spatial rectangular coordinate system corresponding to the compressor disk is established. Based on the three-dimensional point cloud data of the blades, a second spatial rectangular coordinate system corresponding to the compressor blades is established. Based on the first spatial rectangular coordinate system and the second spatial rectangular coordinate system, coordinate transformation is performed on the three-dimensional point cloud data of the blade and the three-dimensional point cloud data of the wheel to obtain the three-dimensional point cloud combination data.

5. The method according to claim 3, characterized in that, When N blade height sections are uniformly selected along the blade height direction of the compressor blade, the N blade height sections are parallel to the blade root section or blade tip section, and N is a positive integer greater than 10.

6. The method according to any one of claims 1-5, characterized in that, When drawing the leaf root contour line and the wheel disk tenon contour line based on the extracted leaf root three-dimensional point cloud data and the tenon groove three-dimensional point cloud data, combined with the axis of symmetry, the drawing plane is the normal plane of the leaf root or tenon groove stretching direction. When drawing, it is necessary to ensure that the working surface contour lines of the leaf root and the wheel disk tenon groove are parallel and the bottom contour lines are collinear.

7. The method according to any one of claims 1-5, characterized in that, When drawing the leaf root contour line and the wheel mortise contour line based on the extracted leaf root 3D point cloud data and the tenon groove 3D point cloud data, combined with the axis of symmetry, the contour lines of a portion of the leaf root or wheel mortise groove are first drawn, and the contour lines of another portion are obtained by mirror symmetry through the axis of symmetry determined in step S4. When drawing the leaf root contour line, its radial contour line needs to be extended and the leaf root contour line group needs to be closed.

8. The method according to any one of claims 1-5, characterized in that, When constructing the blade root model based on the blade root profile and the blade root stretching direction, and when constructing the compressor disk overall model based on the disk tenon and slot profile, the disk tenon and slot stretching direction, and the compressor disk local model, the stretching method is used.

9. The method according to any one of claims 1-5, characterized in that, When adjusting the spatial position of the blade root model in step S7, the compressor blade model determined in step S3 also needs to move along with the blade root model. The direction of movement is the axis of symmetry between the blade root and the wheel disk tenon, and the distance of movement is the distance between the working surfaces of the blade root and the wheel disk tenon along the axis of symmetry. After adjusting the spatial position of the compressor blade model and the blade root model, the working surfaces of the blade root and the wheel disk tenon are aligned.

10. The method according to any one of claims 2-5, characterized in that, The trimming of the upper end face and the front and rear axial end faces of the leaf root model includes: The rotating surface constructed by the rotating shaft and hub profile of the compressor disc is used to trim the upper surface of the blade root model; The front and rear axial end faces of the compressor disc model are used to trim the front and rear end faces of the blade root model.

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