Turbine cold air hole structured grid rapid generation method

Abstract

The invention discloses a turbine cold air hole structured grid rapid generation method, which comprises the following steps: acquiring mainstream computational grid data of a target turbine blade, and determining corresponding geometric feature parameters according to the cold air hole type of a target cold air hole; inputting the geometric characteristic parameters into a parameterized geometric model corresponding to the target cold air hole type to generate parameterized cold air hole geometry; based on the mainstream computational grid data, geometrically positioning the parameterized cold air holes to the surface of a target turbine blade; performing adjacent geometric interference check and processing on the parameterized cold air hole geometry; and calling a corresponding preset grid topology division strategy according to the type of the target cold air hole passing the adjacent geometric interference check, and generating a structured hexahedral grid attached to the boundary of the mainstream computational grid. According to the method, a high-quality structured grid is quickly and automatically generated according to a cooling geometric structure.

Description

Technical Field

[0001] This invention relates to the field of aerodynamic heat transfer design technology for aero-engine turbines, and more specifically to a method for rapid generation of structured meshes for turbine cooling air vents. Background Technology

[0002] Increasing turbine inlet temperature is an effective way to improve gas turbine cycle efficiency. To prevent excessively high inlet temperatures from causing turbine component ablation, thermal protection technology has emerged. The melting point of core components in today's most advanced aero engines is lower than the temperature of the internal combustion gases. If blades are exposed to the high temperature environment of the combustion gases for extended periods, uneven thermal stress distribution on the blade surface can easily occur, leading to localized ablation and severely shortening the engine's normal operating life. To ensure the normal operation of high-pressure turbines and prevent erosion from excessively high-temperature gases, a composite cooling method is often adopted to maintain the blade temperature within the material's allowable range. Depending on the location of the cooling gas distribution, this is divided into external cooling structures and internal cooling structures. Internal cooling refers to the direct entry of high-pressure gas from the compressor into the cooling cavity of the blade. With the cooperation of the spoiler and the impingement hole, the convection capacity of the fluid is used to absorb the heat energy outside the blade. Film cooling, as the main method of external cooling, refers to the flow of some of the internal cooling fluid through the film cooling holes on the blade body and tip and the slit cooling structure at the trailing edge. Under the action of the mainstream, a thin layer of cold gas with a certain thickness is formed on the coating surface, which isolates the hot gas from the blade, thereby playing a role in thermal protection. The progress and continuous innovation of cooling technology enable the core components of aero-engines to operate normally under high-temperature conditions, and form a thermal protection system with cooling technology as the main method and thermal barrier coating (TBC) as the auxiliary method.

[0003] The rapid increase in computing speed has significantly reduced the numerical simulation cycle. Researchers began using computational fluid dynamics (CFD) in the 1980s for the design of film cooling systems. Mesh generation for the cooling gas vents is a crucial component of CFD simulations, and mesh quality significantly impacts the accuracy of the results. Structured meshes, due to their good boundary layer resolution and relatively small mesh size, are widely used in turbine cooling CFD simulations. However, for turbine blades with complex internal cooling structures, generating high-quality structured meshes requires considerable time, leading to lengthy preliminary preparations for numerical simulations and impacting the progress of cooling structure optimization and design work.

[0004] Therefore, how to quickly and automatically generate high-quality structured meshes based on cooling geometry is a problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0005] In view of the above problems, the present invention proposes a method for rapid generation of turbine cooling gas vent structured mesh to overcome or at least partially solve the above problems.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: This invention provides a method for rapidly generating structured meshes for turbine cooling gas vents, comprising the following steps: Obtain the mainstream computational grid data of the target turbine blade, and determine the corresponding geometric feature parameters according to the type of the target cooling air holes; The geometric feature parameters are input into the parametric geometric model corresponding to the target air vent type to generate the parametric air vent geometry; and based on the mainstream computing grid data, the parametric air vent geometry is located on the surface of the target turbine blade. The parameterized air vent geometry is subjected to adjacent geometric interference checks and processing. Based on the type of the target cold air vents examined through adjacent geometric interference, the corresponding preset mesh topology partitioning strategy is invoked to generate a structured hexahedral mesh that fits the boundary of the mainstream computational mesh.

[0007] Furthermore, it also includes: the types of cooling vents include: cylindrical cooling vents, scoop-shaped cooling vents, and semi-slit cooling structures.

[0008] Furthermore, the parametric geometric model of the cylindrical cooling air vent is determined by the following steps: Obtain the first inner profile point located inside the turbine blade cavity, the first outer profile point located on the outer surface of the turbine blade, and the diameter of the cylindrical bore; The first inner point and the first outer point are respectively taken as the center of the circular cross-section of the cylindrical air vent at its outlet and inlet; The length and axial direction of the cylinder are determined by the line connecting the first inner point and the first outer point. The position of the cylinder on the outer surface of the turbine blade is determined based on the first outer shape point, and the radius of the cylindrical cooling air hole is determined based on the diameter of the cylindrical hole.

[0009] Furthermore, the parametric modeling of the scoop-shaped cold air vent is determined by the following steps: Obtain the second inner shape point and the second outer shape point for determining the cylindrical section in the scoop-shaped cold air vent; Six feature points of the scoop-shaped cooling air inlet were extracted from the three-dimensional geometric model of the turbine blade; among them: The first feature point, the second feature point, the third feature point, and the fourth feature point are the four nodes of the scoop hole outlet section; The plane formed by the third, fourth, fifth, and sixth feature points is the tangent plane of the scoop hole and the cylindrical hole; The plane formed by the first feature point, the second feature point, the fifth feature point, and the sixth feature point is parallel to the axis of the cylindrical hole; The line connecting the second inner point and the second outer point is used as the axis of the cylinder to determine the length of the cold air inlet section and the direction of the jet. The distance between the midpoint of the line connecting the fifth and sixth feature points and the second shape point is taken as the radius; The outlet of the winnowing basket is determined by the positions of the six feature points.

[0010] Furthermore, the parametric modeling of the semi-slit cooling structure is determined by the following steps: A local coordinate system is established based on three points on the blade pressure surface, where: the x-axis is formed by the line connecting points 1 and 2; the y-axis is formed by the line connecting points 2 and 3; and the z-axis is obtained by the cross product of the x-axis and the y-axis; the angle between the outlet hypotenuse and the x-axis is taken as the slit outlet expansion angle. In the local coordinate system, a stepped cross-sectional geometry is constructed based on the inlet height, inlet width, pressure side length, suction side length, and split outlet expansion angle of the semi-slit cooling structure.

[0011] Furthermore, the mesh topology strategy corresponding to the cylindrical cooling air vent includes: The cold air inlet section is determined based on the center and radius of the cylindrical cold air vent; a hexahedral structure is constructed in the main flow area of ​​the cylindrical cold air vent; both the cold air inlet section and the hexahedral structure are generated using an OH-type topology to form a mesh.

[0012] Furthermore, the mesh topology strategy corresponding to the scoop-shaped cold air vents includes: The geometric structure of the hopper-shaped air vent is divided into a cylindrical region and a triangular region. The triangular region includes a triangular cross-section and a tangent plane between the circular cross-section and the outer contour. An OH-type hybrid mesh topology is used for the cylindrical region. The triangular cross-section is partitioned using a Y-Block type. The tangent plane is partitioned using a combination of H-type and OH-type mesh topology.

[0013] Furthermore, the mesh topology strategy corresponding to the semi-slit cooling structure includes: The main body of the semi-slit cooling structure adopts an H-type mesh topology, and a Y-Block type partition is used in the triangular cut area of ​​the jet outlet.

[0014] Furthermore, for the cylindrical air vents, a structured hexahedral mesh that conforms to the boundary of the mainstream computational mesh is generated, specifically including: Determine the outlet location: Search for the closest point to the first shape point in the mainstream computational grid on the turbine blade surface; construct a local coordinate system based on the position of the closest point in the mainstream computational grid; determine the position of the first shape point in the local coordinate system; Calculate the outlet section: Based on the axis formed by the line connecting the first inner point and the first outer point, and combined with the angle between the axis and the normal vector of the turbine blade surface, calculate the elliptical cross-sectional shape and size of the cooling air hole at the turbine blade outlet. Determine the grid boundary: Based on the projection dimensions of the elliptical cross section in the main grid flow direction and span direction, determine the range of the six-sided outer boundary surrounding the cold air vent; Topology and Mesh Generation: Based on the first outer shape point, the first inner shape point, the elliptical cross section, and the outer boundary of the hexahedron, all contour points of the OH-type topology are generated, and structured mesh generation is completed based on the contour points. As can be seen from the above technical solution, compared with the prior art, this invention discloses a method for rapid generation of structured meshes for turbine cooling air vents, which has the following beneficial effects: In the parameterization stage of turbine cooling air holes, this invention uses only a few main geometric parameters to parametrically describe cylindrical holes, scoop-shaped cooling air holes, and semi-split structures, thus reducing the amount of geometric input.

[0015] Based on the structural characteristics of cylindrical holes, scoop-shaped cold air holes, and semi-split structures, this invention pre-defines the mesh topology and quickly generates structured meshes, reducing mesh generation time. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the rapid generation method for structured mesh of turbine cooling air holes provided in an embodiment of the present invention.

[0018] Figure 2 This is a schematic diagram of the cylindrical air vent structure provided in an embodiment of the present invention.

[0019] Figure 3 This is a schematic diagram of the scoop-shaped cold air jet outlet structure provided in an embodiment of the present invention.

[0020] Figure 4 This is a schematic diagram of the semi-slit cooling structure provided in an embodiment of the present invention.

[0021] Figure 5 This is a schematic diagram of a hexahedral structure constructed in the mainstream region of a cylindrical air vent, as provided in an embodiment of the present invention.

[0022] Figure 6 This is a schematic diagram of the grid division structure of a single scoop-shaped cold air vent provided in an embodiment of the present invention.

[0023] Figure 7 This is a schematic diagram of the complete sieve-shaped cold air vent grid division structure provided in an embodiment of the present invention.

[0024] Figure 8 This is a schematic diagram of the mesh division structure of a single split cooling hole provided in an embodiment of the present invention.

[0025] Figure 9 This is a schematic diagram of the complete slotted cooling grid division structure provided in an embodiment of the present invention.

[0026] Figure 10 This is a schematic diagram of the outer boundary of the cylindrical air vent provided in an embodiment of the present invention.

[0027] Figure 11 This is a schematic diagram showing the location of the turbine cooling air vents in an embodiment of the present invention.

[0028] Figure 12 This is a schematic diagram of the cylindrical air vent mesh provided in an embodiment of the present invention.

[0029] Figure 13 This is a schematic diagram of a semi-slit air film pore mesh provided in an embodiment of the present invention. Detailed Implementation

[0030] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0031] like Figure 1 As shown in the figure, an embodiment of the present invention discloses a method for rapid generation of structured meshes for turbine cooling gas vents, comprising the following steps: S1. Obtain the mainstream computational grid data of the target turbine blade, and determine the corresponding geometric feature parameters according to the type of the target cooling air hole; S2. Input the geometric feature parameters into the parametric geometric model corresponding to the target air vent type to generate the parametric air vent geometry; and locate the parametric air vent geometry to the target turbine blade surface based on mainstream computing grid data. S3. Perform adjacent geometric interference checks and processing on the parameterized air vent geometry; S4. Based on the type of the target cold air vents checked through adjacent geometric interference, call the corresponding preset mesh topology partitioning strategy to generate a structured hexahedral mesh that fits the boundary of the mainstream computing mesh.

[0032] S5. Output a structured hexahedral mesh and record the overlap information between it and the mainstream computational mesh.

[0033] Next, each of the above steps will be explained in detail.

[0034] In step S1 above, the mainstream computational grid data of the target turbine blade is obtained, and the corresponding geometric feature parameters are determined according to the type of the target cooling air hole; wherein, the cooling air hole type includes: cylindrical cooling air hole, scoop-shaped cooling air hole and semi-slit cooling structure.

[0035] In step S2 above, the geometric feature parameters are input into the parametric geometric model corresponding to the target cold air hole type to generate the parametric cold air hole geometry; and based on the mainstream computing grid data, the parametric cold air hole geometry is located on the surface of the target turbine blade. Parameterization of the cold air vent structure is a crucial step in determining the geometry of the cold air vent, achieving an accurate description of the geometry using a relatively small number of parameters. This invention parameterizes cylindrical, scoop-shaped, and semi-split structures of the cold air vent.

[0036] (1) The parametric geometric model of the cylindrical air vent is determined by the following steps: The process involves obtaining a first inner shape point P0 located within the turbine blade cavity, a first outer shape point P1 located on the outer surface of the turbine blade, and the diameter dc of the cylindrical orifice. The first inner shape point P0 and the first outer shape point P1 are respectively designated as the centers of the circular cross-sections at the outlet and inlet of the cylindrical cooling air orifice. The length and axial direction of the cylinder are determined by the line connecting the first inner shape point P0 and the first outer shape point P1. The position of the cylinder on the outer surface of the turbine blade is determined by the first outer shape point P0, and the geometric characteristics of the film cooling orifice are determined by the diameter dc of the cylindrical orifice, specifically the radius of the cylindrical cooling air orifice. The specific structure is as follows... Figure 2 As shown.

[0037] (2) The parametric modeling of the scoop-shaped cold air vents is determined by the following steps: The scoop-shaped film cooling orifice consists of a cylinder and a scoop-shaped outlet. The scoop-shaped expansion structure is composed of the flow expansion angle and the spanwise expansion angle, making the overall structure relatively complex. Because the line connecting the film cooling orifices has an inclination angle with the turbine radial direction, the outlet shape and expansion degree of the same film cooling orifice are not entirely consistent. To ensure the accuracy of parametric modeling, six main feature points of the scoop-shaped structure (such as...) are directly extracted from the three-dimensional geometric model of the turbine blade. Figure 3 (①-⑥) and obtain the second inner shape point ⑧ and the second outer shape point ⑦ used to determine the cylindrical section in the scoop-shaped cold air hole; wherein, the first feature point ①, the second feature point ②, the third feature point ③ and the fourth feature point ④ are the four nodes of the scoop hole outlet section; the plane formed by the third feature point ③, the fourth feature point ④, the fifth feature point ⑤ and the sixth feature point ⑥ is the tangent plane of the scoop hole and the cylindrical hole; the plane formed by the first feature point ①, the second feature point ②, the fifth feature point ⑤ and the sixth feature point ⑥ is parallel to the axis of the cylindrical hole; the shape of the scoop-shaped air film hole is mainly It consists of two parts: a cylindrical orifice and a scoop orifice. The shape parameters of the lower cylinder are consistent with those of the cylindrical film jet orifice. The line connecting the second inner point ⑧ and the second outer point ⑦ is used as the axis of the cylinder to determine the length of the cold air inlet section and the direction of the jet. To ensure that the line connecting the fifth feature point ⑤ and the sixth feature point ⑥ is tangent to the outlet edge of the cylindrical orifice, and to reduce modeling errors, the distance between the midpoint of the line connecting the fifth feature point ⑤ and the sixth feature point ⑥ and the second outer point ⑦ is used as the radius. The outlet of the scoop orifice is determined by the positions of six feature points ①-⑥. The specific structure of the jet outlet is as follows: Figure 3 As shown.

[0038] (3) The parametric modeling of the semi-split cooling structure is determined by the following steps: The semi-slit cooling structure involves cutting the trailing edge of the blade's pressure surface to form a stepped cross-section. To ensure jet uniformity, the exit section of the semi-slit structure has a certain expansion angle. The specific structure is as follows: Figure 4 As shown, the slit cooling is based on the design in a local coordinate system. Specifically, a local coordinate system is established based on three points on the pressure surface of the blade, where: the x-axis is formed by the line connecting points 1 and 2; the y-axis is formed by the line connecting points 2 and 3; and the z-axis is obtained by the cross product of the x-axis and the y-axis. The angle between the outlet hypotenuse and the x-axis is taken as the slit outlet expansion angle α, symbolizing the degree of expansion of the semi-slit outlet. In addition, in the local coordinate system, a stepped cross-sectional geometry is constructed based on the inlet height H1, inlet width L1, pressure side length L2, suction side length L3, and slit outlet expansion angle α of the semi-slit cooling structure.

[0039] In step S3 above, adjacent geometric interference checks and processing are performed on the parameterized cooling air hole geometry to ensure that it does not conflict with the existing cooling air holes on the blade. In step S4 above, based on the type of the target cold air hole checked by adjacent geometric interference, the corresponding preset mesh topology partitioning strategy is invoked to generate a structured hexahedral mesh that fits the boundary of the mainstream computing mesh.

[0040] (1) The above-mentioned preset grid topology partitioning strategy specifically includes: 1) The mesh topology strategies corresponding to cylindrical air vents include: Determine the air inlet section based on the center and radius of the cylindrical air vent; construct a structure like this in the main flow area of ​​the cylindrical air vent. Figure 5 The hexahedral structure shown ensures that the cold air inlet mesh fits snugly with the main mesh, improving the accuracy of overlapping mesh interpolation. Both the cold air inlet section and the hexahedral structure utilize OH-type topology to generate the mesh. Figure 5 Figure (a) shows a schematic diagram of the topology of a cylindrical air film pore. Figure 5 Figure (b) is a schematic diagram of a cylindrical air film pore grid.

[0041] 2) The grid topology strategies corresponding to the hopper-shaped air vents include: The geometry of the winnowing basket orifice consists of a cylindrical inlet section and a winnowing basket-shaped outlet section, with the circular cross-section tangent to the winnowing basket orifice. Figure 3 First, divide the sieve hole into cylindrical areas ( ). Figure 3 The cylindrical region containing the second inner point ⑧ and the second outer point ⑦, and the triangular region ( Figure 3 The region formed by feature points ①-⑥ in the middle. Figure 6 The cylindrical area uses an OH-type hybrid grid (black area). The triangular area is divided into two parts (blue and green areas). The green area has a triangular cross-section, so it is partitioned using a Y-Block grid. The blue area has a circular cross-section tangent to the outer contour, so the outermost layer uses an H-type grid. The inner areas are further divided using an OH grid. The complete hopper-shaped air vent grid structure is as follows: Figure 7 As shown.

[0042] 3) The mesh topology strategies corresponding to the semi-slit cooling structure include: The slit cooling structure primarily uses an H-type mesh topology, with a stepped distribution of the jet outlet cross-section and a triangular cut shape. To improve the mesh quality in the triangular region, a Y-Block type partitioning is employed. The boundary area between the cooling vents and the main flow channel is also ensured to be completely fitted with the main flow channel mesh. A schematic diagram of the mesh division structure for a single slit cooling vent is shown below. Figure 8 As shown in the diagram, the complete split-cut cooling mesh division structure is as follows: Figure 9 As shown.

[0043] (2) The above-mentioned generation of structured hexahedral meshes that conform to the boundary of the mainstream computational mesh specifically includes: 1) For cylindrical air vents, generate a structured hexahedral mesh that fits the boundary of the mainstream computational mesh, specifically including: Before meshing the cylindrical air film aperture, 32 contour points need to be determined first to complete the topological meshing of the model. The general calculation process is as follows: Determine the outlet location: Search for the closest point to the first shape point P1 (i.e., the location point) in the mainstream computational grid on the turbine blade surface; construct a local coordinate system based on the position of the closest point in the mainstream computational grid; determine the position of the first shape point P1 in the local coordinate system; specifically: Search the blade surface for the nearest point to the first shape point P1, and determine the position P of the nearest point in the blade computational mesh. I,J,K Where I, J, and K are the grid numbers in the x, y, and z directions; The region is used as the projection region, and the first shape point P1 is projected onto the turbine blade surface using radial basis functions; calculate The normal vector of the planar region formed by the four points Simultaneously calculate , Construct a local coordinate system and calculate the transformation matrix, then... The grid points and location points of the region are transformed into normal vectors using a transformation matrix. A vertical planar region; by Four points in the region are treated as a single calculation unit. The angles between the location point and the four vertices are calculated. If the sum of the four angles is 2π, then the location point is within that grid unit.

[0044] Calculate the outlet section: Based on the axis formed by the line connecting the first inner point and the first outer point, and combining the angle between the axis and the normal vector of the turbine blade surface, calculate the elliptical cross-sectional shape and size of the cooling air orifice at the turbine blade outlet; specifically: The line connecting the inner point and the outer point forms the axis. Calculate the axis With normal vector The included angle Then the radius of the major axis is Where dc is the diameter of the cylindrical hole; Construct a system with the location point as the origin and based on the axis. With normal vector The local coordinate system, where The discrete points of the elliptical boundary are calculated in the local coordinate system, and then the inverse matrix is ​​used to transform it to the global coordinate system. The same calculation method is used at the cold air inlet.

[0045] Determine the mesh boundary: Based on the projected dimensions of the elliptical cross-section in the mainstream mesh flow direction and span direction, determine the external boundary range of the six-sided structure surrounding the cooling air vents; specifically: Calculate the maximum length of the projection of the elliptical section onto the grid lines in the main I and J directions. l I and lJ The distance between the positioning point and the outer boundary is usually specified as 2. l I and 2 l J The jet direction can also be appropriately extended to 3. l I and 3 l J .

[0046] Topology and Mesh Generation: Based on the first outer shape point, the first inner shape point, the elliptical cross-section, and the outer boundary of the hexahedron, all contour points of the OH-type topology are generated, and structured meshing is completed based on the contour points. A schematic diagram of the outer boundary of the cylindrical air vent is shown below. Figure 10 As shown.

[0047] In step S5 above, a structured hexahedral mesh is output, and information on the overlapping area between the mesh and the main computational mesh is recorded.

[0048] The following specific embodiment will illustrate the rapid generation method of turbine cooling gas vent structured mesh provided by the present invention.

[0049] The mesh generation of the cooling air vents of a turbine (containing 4 rows of blades) is selected. The specific implementation of the present invention will then be described based on this example. The specific steps are as follows: Read in the geometric parameters of the turbine cooling air holes for each row of blades.

[0050] The structure of each turbine cooling vent is parameterized.

[0051] Structured mesh generation for each turbine cooling air vent.

[0052] Output all air vent meshes.

[0053] The location of the turbine air vents is as follows: Figure 11 As shown, the cylindrical air vent mesh is as follows Figure 12 As shown, the semi-slit air film pore mesh is as follows: Figure 13 As shown.

[0054] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the apparatus disclosed in the embodiments, since they correspond to the methods disclosed in the embodiments, the description is relatively simple; relevant parts can be referred to the method section.

[0055] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A method for fast generation of turbine cold hole structured grid, characterized in that, The method comprises the following steps: obtaining main flow calculation grid data of a target turbine blade, and determining corresponding geometric feature parameters according to a cold hole type of a target cold hole; inputting the geometric feature parameters into a parameterized geometric model corresponding to the target cold hole type to generate a parameterized cold hole geometry, and positioning the parameterized cold hole geometry to a surface of the target turbine blade based on the main flow calculation grid data; performing adjacent geometric interference checking and processing on the parameterized cold hole geometry; according to the type of the target cold hole passing through the adjacent geometric interference checking, calling a corresponding preset grid topology division strategy to generate a structured hexahedral grid conforming to a boundary of the main flow calculation grid.

2. The method of claim 1, wherein, Further comprising: the cold hole type comprises a cylindrical cold hole, a dustpan cold hole and a half-split cooling structure.

3. The method of claim 2, wherein, The parameterized geometric model of the cylindrical cold hole is determined by the following steps: obtaining a first inner point located in the inner cavity of the turbine blade, a first outer point located on the outer surface of the turbine blade, and a cylindrical hole diameter; the first inner point and the first outer point are respectively taken as the center of the circular cross section of the cylindrical cold hole at the outlet and the inlet thereof; determining the length and axis direction of the cylinder according to the connecting line of the first inner point and the first outer point; determining the position of the cylinder on the outer surface of the turbine blade according to the first outer point, and determining the radius of the cylindrical cold hole according to the cylindrical hole diameter.

4. The method of claim 2, wherein, The parameterized modeling of the dustpan cold hole is determined by the following steps: obtaining a second inner point and a second outer point for determining a cylindrical segment of the dustpan cold hole; extracting six feature points of the dustpan cold hole from a three-dimensional geometric model of the turbine blade; wherein: the first feature point, the second feature point, the third feature point and the fourth feature point are four nodes of the dustpan hole outlet cross section; the plane composed of the third feature point, the fourth feature point, the fifth feature point and the sixth feature point is a tangent plane of the dustpan hole and the cylindrical hole; the plane composed of the first feature point, the second feature point, the fifth feature point and the sixth feature point is parallel to the axis direction of the cylindrical hole; the connecting line of the second inner point and the second outer point is taken as the axis of the cylinder, which is used to determine the length of the cold hole inlet segment and the direction of the jet flow; the distance between the midpoint of the connecting line of the fifth feature point and the sixth feature point and the second outer point is taken as the radius; the dustpan hole outlet is determined by the positions of the six feature points.

5. The method of claim 2, wherein, The parameterized modeling of the half-split cooling structure is determined by the following steps: establishing a local coordinate system based on three points on the pressure surface of the blade, wherein: the x-axis is composed of the connecting line of point 1 and point 2; the y-axis is composed of the connecting line of point 2 and point 3; the z-axis is obtained by the cross product of the x-axis and the y-axis; the included angle between the outlet bevel and the x-axis is taken as the split hole outlet expansion angle; in the local coordinate system, a stepped cross-sectional geometry is constructed according to the inlet height, the inlet width, the pressure side length, the suction side length and the split hole outlet expansion angle of the half-split cooling structure.

6. The method of claim 3, wherein, the grid topology strategy corresponding to the cylindrical cold hole comprises: A cold gas inlet section is determined according to the center and radius of the cylindrical cold gas hole; a hexahedron structure is constructed in the main flow area of the cylindrical cold gas hole; and the cold gas inlet section and the hexahedron structure both adopt an O-H type topology structure to generate a grid.

7. The method of claim 4, wherein, The grid topology strategy corresponding to the dustpan type cold gas hole includes: The geometric structure of the dustpan type cold gas hole is divided into a cylindrical area and a triangular area, the triangular area includes a triangular cross section, and a tangent surface of a circular cross section and an outer contour; an O-H type hybrid grid topology is adopted for the cylindrical area; a Y-Block type partition is adopted for the triangular cross section; and an H type and O-H type combined grid topology is adopted for the tangent surface.

8. The method of claim 5, wherein, The grid topology strategy corresponding to the half-split slot cooling structure includes: The main body of the half-split slot cooling structure adopts an H type grid topology, and a Y-Block type partition is adopted in the triangular notch area of the jet flow outlet.

9. The method of claim 6, wherein, For the cylindrical cold gas hole, a structured hexahedron grid is generated to conform to the boundary of the main flow calculation grid, specifically including: Determining the outlet positioning: searching for a nearest point to the first outer shape point in the main flow calculation grid on the surface of the turbine blade; constructing a local coordinate system according to the position of the nearest point in the main flow calculation grid; and determining the position of the first outer shape point in the local coordinate system; Calculating the outlet cross section: based on the axis line formed by the first inner shape point and the first outer shape point, and the included angle between the axis line and the normal vector of the surface of the turbine blade, calculating the shape and size of the elliptical cross section of the cold gas hole at the outlet of the turbine blade; Determining the grid boundary: based on the projection size of the elliptical cross section in the streamwise and spanwise directions of the main flow grid, determining the outer boundary range of the hexahedron wrapping the cold gas hole; Generating topology and grid: based on the first outer shape point, the first inner shape point, the elliptical cross section and the hexahedron outer boundary, generating all contour points of the O-H type topology structure, and completing the structured grid division according to the contour points.

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