Methods for generating cold blade models, electronic devices, and storage media

Abstract

This application relates to the field of turbomachinery technology, and discloses a method for generating a cold-state blade model, an electronic device, and a storage medium. The method for generating the cold-state blade model includes the following steps: establishing a mapping relationship between the finite element points of the hot-state aerodynamic model and the finite element points of the hot-state intensity model; calculating the changes in the finite element points of the hot-state aerodynamic model under hot and cold conditions based on the mapping relationship and the changes in the finite element points of the hot-state intensity model under hot and cold conditions; and superimposing the finite element points of the hot-state aerodynamic model with the changes in the finite element points under hot and cold conditions to obtain an ordered cold-state blade model. Using the method of this application, a cold-state blade model composed of ordered points can be obtained. Furthermore, the cold-state blade model generation method of this application is simple to operate, has a high success rate, has low requirements for the distribution rules of random points in the cold-state airfoil finite element model, and yields good accuracy for the blade tip and root.

Description

Technical Field

[0001] This invention relates to the field of turbomachinery technology, and in particular to a method for generating a cold blade model, an electronic device, and a storage medium. Background Technology

[0002] An axial compressor is a type of turbomachinery used to convert mechanical energy into pressure potential energy. It typically includes an outer casing, an inner hub, and multiple stages of blades. Each stage consists of a row of rotor blades and a stator blade, arranged sequentially. The stator blades are fixed to the outer casing, while the rotor blades are mounted on the inner hub, which is connected to the power mechanism. It performs work on the working fluid, increasing its pressure. The rotor blades are rotating components, and during operation, they deform under the influence of centrifugal force, aerodynamic force, and thermal stress. The stator blades are non-rotating components, and they also deform under aerodynamic force and thermal stress. Deformation of both stator and rotor blades during operation leads to performance degradation. Therefore, during compressor design and manufacturing, the designed hot airfoil is converted to a cold airfoil. This cold airfoil is typically a chaotic solid finite element point, while the factory requires a production cross-section composed of ordered points. Summary of the Invention

[0003] This invention provides a method for generating a cold blade model, an electronic device, and a storage medium, which are used to provide a method for generating cold blade production coordinates composed of ordered points, so as to facilitate factory processing and production.

[0004] In a first aspect, the present invention provides a method for generating a cold-state blade model, the method comprising the following steps:

[0005] A mapping relationship is established between the finite element points of the thermal aerodynamic model of the blade and the finite element points of the thermal intensity model. Based on the mapping relationship and the change of the finite element points of the thermal intensity model under cold and hot conditions, the change of the finite element points of the thermal aerodynamic model under cold and hot conditions is calculated.

[0006] The finite element points of the hot aerodynamic model are superimposed with the changes of the finite element points of the hot aerodynamic model under hot and cold conditions to obtain an ordered cold blade model.

[0007] Specifically, in this application, the cold-state blade model is calculated based on the hot-state aerodynamic model. Since the finite element points of the hot-state aerodynamic model are ordered points, the resulting cold-state blade model is also composed of ordered points, which is convenient for factory processing and production. Specifically, in this application, a mapping relationship is first established between the finite element points of the hot-state aerodynamic model and the finite element points of the hot-state intensity model, thus establishing a connection between them. Then, based on this mapping relationship and the change in the finite element points of the hot-state intensity model between hot and cold states, the change in the finite element points of the hot-state aerodynamic model between hot and cold states is calculated. Finally, based on the hot-state aerodynamic model, the cold-state blade model is obtained by superimposing the finite element points of the hot-state aerodynamic model with its change. Compared to the method of sorting points in a cold blade model composed of random points, the method for generating production coordinates of cold blade profiles in this application is simple to operate, has a high success rate, short working time, low requirements on the distribution rules of random points in the finite element of cold blade profiles, and the accuracy of the obtained blade tip and root is better.

[0008] Optionally, a mapping relationship is established between the finite element points of the thermal aerodynamic model of the blade and the finite element points of the thermal intensity model; specifically, this includes the following steps:

[0009] The thermal intensity model is divided into hexahedral finite element elements, and the vertex of each finite element element is a finite element point of the thermal intensity model.

[0010] For each finite element point O of the thermal aerodynamic model, the following operations are performed: the finite element element E closest to the finite element point O is determined, and the projection point P closest to the projection point of the finite element point O on each surface of the finite element element E is determined.

[0011] Optionally, based on the mapping relationship and the changes in the finite element points of the thermal intensity model under hot and cold conditions, the changes in the finite element points of the thermal aerodynamic model under hot and cold conditions are calculated; specifically, this includes the following steps:

[0012] Based on the relationship between the global and local coordinates of the finite element element E, and the shape function F of the finite element element E in the local coordinates, calculate the change D between the hot and cold states of the projection point P in the global coordinate system. xyz The change D xyz It is approximated as the change in the finite element point O between the hot and cold states.

[0013] Optionally, the finite element element E closest to the finite element point O is determined, and the projection point P closest to the projection point of the finite element point O on each face of the finite element element E is determined; specifically, the following steps are included:

[0014] Find the n finite element elements that are closest to the finite element point O;

[0015] Project the finite element point O onto each face of the n finite element elements to determine the nearest projection point P and the finite element element E in which the projection point P is located.

[0016] Optionally, based on the relationship between the global and local coordinates of the finite element element E, and the shape function F of the finite element element E in the local coordinates, the change D between the hot and cold states of the projection point P in the global coordinate system is calculated. xyz Specifically, it includes the following steps:

[0017] The shape function F describes the relationship between the global and local coordinates of the finite element element E, as shown in the following formula:

[0018]

[0019]

[0020]

[0021] Where x, y, and z are the global coordinates of any point within the finite element element E, x i y i z i The coordinates of each vertex of the finite element element E are global coordinates; m, l, and n are local coordinates of each point on the equivalent hexahedron of the finite element element E; N is the global coordinates of each vertex of the finite element element E. i (m,l,n) is the shape function F of the finite element element E in local coordinates;

[0022] Based on the coordinates of each vertex of the finite element element E, and using the relationship between the global and local coordinates of the finite element element E, the shape function F of the finite element element E in the local coordinates is calculated:

[0023]

[0024] Where, m i l i n i These are the local coordinates of each vertex of the finite element element E-equivalent hexahedron;

[0025] Based on the shape function F and the relationship between the global and local coordinates of the finite element element E, the local coordinates LP of the global coordinates WP of the projection point P in the finite element element E are calculated.

[0026] The shape function F describes the relationship between the deformation of the finite element E in global coordinates and the deformation in local coordinates, as shown in the following formula:

[0027]

[0028]

[0029]

[0030] Substituting the local coordinates LP of the projection point P into the relationship between the deformation of the finite element E in the global coordinate system and the deformation in the local coordinate system, the change D of the projection point P in the global coordinate system is calculated. xyz .

[0031] Optionally, based on the shape function F and the relationship between the global and local coordinates of the finite element element E, the local coordinates LP of the global coordinates WP of the projection point P in the finite element element E are calculated; specifically, this includes the following steps:

[0032] Expand the shape function F at any point K(x0, y0, z0) in the global coordinate system using Taylor expansion, and ignore second-order and higher derivative terms to obtain a linear relationship between the global and local coordinates. Adjust the linear relationship between the global and local coordinates to obtain an iterative relationship:

[0033]

[0034]

[0035] Where Coor represents global coordinates, LCoor represents local coordinates, and J0 is the Jacobian matrix;

[0036] Based on the global coordinates WP of the projection point P, the virtual local coordinates VLP are approximately obtained using the iterative formula.

[0037] Based on the virtual local coordinates VLP, the virtual global coordinates VWP are calculated using the relationship between the global and local coordinates of the finite element element E.

[0038] Compare the global coordinates WP with the virtual global coordinates VWP. If |WP-VWP|<ε, then the virtual local coordinates VLP are considered to be the local coordinates LP corresponding to the projection point P. Otherwise, according to (WP-VWP), the new virtual local coordinates VLP are obtained using the iterative relationship, and the iteration is repeated until the virtual global coordinates VWP corresponding to the obtained virtual local coordinates VLP satisfy |WP-VWP|<ε.

[0039] Optionally, after obtaining the ordered cold blade model, the following steps are also included:

[0040] The airfoil section of the cold blade model is interpolated to a set section height to obtain a cold blade section of equal height.

[0041] Optionally, if the set section height is inside the airfoil section, cubic spline interpolation is used; if the set section height is outside the airfoil section, linear extrapolation is used.

[0042] Optionally, before establishing the mapping relationship between the finite element points of the thermal aerodynamic model of the blade and the finite element points of the thermal intensity model, the following steps are also included:

[0043] By using spline interpolation of the cross sections of the thermal aerodynamic model, new highest and lowest cross sections of the thermal aerodynamic model are obtained, and these new highest and lowest cross sections are located within the thermal intensity model.

[0044] Secondly, this application also provides an electronic device, which includes:

[0045] Memory, used to store executable instructions;

[0046] A processor for reading and executing executable instructions stored in memory to implement the method for generating a cold blade model as described in any of the preceding embodiments.

[0047] Thirdly, this application also provides a storage medium that, when the instructions in the storage medium are executed by an electronic device, enables the electronic device to perform the method for generating a cold blade model as described in any of the preceding claims. Attached Figure Description

[0048] To better understand the present invention, reference may be made to the embodiments shown in the following drawings. The components in the drawings are not necessarily to scale, and some related components may be omitted to emphasize and clearly illustrate the technical features of this disclosure. Furthermore, related elements or components may have different arrangements as known in the art.

[0049] Figure 1 A flowchart illustrating a method for generating a cold blade model according to an embodiment of the present invention;

[0050] Figure 2 This is a partial flowchart of a method for generating a cold blade model according to an embodiment of the present invention. Detailed Implementation

[0051] The technical solutions in the exemplary embodiments of this disclosure will be clearly and completely described below with reference to the accompanying drawings. The exemplary embodiments described herein are for illustrative purposes only and are not intended to limit the scope of protection of this disclosure. Therefore, it should be understood that various modifications and changes can be made to the exemplary embodiments without departing from the scope of protection of this disclosure.

[0052] This application provides a method for generating a cold-state blade model, such as... Figure 1 As shown, the method includes the following steps:

[0053] Step 101: Establish a mapping relationship between the finite element points of the thermal aerodynamic model of the blade and the finite element points of the thermal intensity model;

[0054] Step 102: Based on the mapping relationship and the changes in the finite element points of the thermal intensity model under hot and cold conditions, calculate the changes in the finite element points of the thermal aerodynamic model under hot and cold conditions.

[0055] Step 103: Superimpose the finite element points of the hot aerodynamic model with the changes of the finite element points of the hot aerodynamic model under hot and cold conditions to obtain an ordered cold blade model.

[0056] The 'hot-state strength model' and the 'hot-state aerodynamic model' are two physical models of a blade under hot conditions. These two models have roughly the same shape, but differ in the finite element points used to describe them, and consequently, their applications differ. Specifically, the finite element points of the hot-state strength model are disordered points, generally used for strength calculations, such as static strength verification or calculating the blade's natural frequencies. Furthermore, knowing the hot-state strength model allows us to obtain its deformation under both hot and cold conditions, as well as its strength model under cold conditions. The finite element points of the hot-state aerodynamic model are ordered points, generally used to calculate the aerodynamic parameters of the blade under operating conditions, such as in computational fluid dynamics numerical simulations. In related technologies, the cold-state strength model is generally calculated directly from the hot-state strength model. This cold-state strength model consists of disordered finite element points, which are then sorted to obtain the cold-state airfoil cross-section composed of ordered points. This method is cumbersome to operate, has a low success rate, is time-consuming, and has high requirements for the distribution rules of random points in the cold airfoil finite element method, resulting in poor accuracy of the obtained airfoil tip and root.

[0057] In this application, a cold-state blade model is calculated based on a hot-state aerodynamic model. Since the coordinate points of the hot-state aerodynamic model are ordered points, the resulting cold-state blade model is a cold-state airfoil composed of ordered points, which is convenient for factory processing and production. Specifically, in this application, a mapping relationship is first established between the finite element points of the hot-state aerodynamic model and the finite element points of the hot-state intensity model, thus establishing a connection between them. Then, based on this mapping relationship and the changes in the finite element points of the hot-state intensity model between hot and cold states, the changes in the finite element points of the hot-state aerodynamic model between hot and cold states are calculated. Finally, based on the hot-state aerodynamic model, the cold-state blade model is obtained by superimposing the finite element points of the hot-state aerodynamic model with its changes. Compared to the method of sorting the coordinate points of a cold blade model composed of random points, the method for generating a cold blade model in this application is simple to operate, has a high success rate, and takes less time. It has very low requirements for the distribution rules of random points in the finite element of the cold blade profile, and the accuracy of the obtained blade tip and root is better.

[0058] In some embodiments, step 101 specifically includes the following steps, such as... Figure 2 As shown:

[0059] Step 201 involves dividing the thermal intensity model into hexahedral finite element elements, with each vertex of the finite element element representing a finite element point of the thermal intensity model; that is, segmenting the thermal intensity model using the finite element method. Specifically, in other embodiments, the thermal intensity model can also be divided into finite element elements of other sizes, such as tetrahedral finite element elements. However, depending on the shape of the finite element elements, the specific algorithm for calculating the change in coordinates of the thermal aerodynamic model between the hot and cold states will differ.

[0060] Step 202: Perform the following operations on each finite element point O of the thermal aerodynamic model: determine the hexahedral finite element E that is closest to the finite element point O, and the projection point P that is closest to the projection point of the finite element point O on each face of the finite element element E.

[0061] Specifically, under the same global coordinate system, the outlines of the thermal intensity model and the thermal aerodynamic model roughly overlap. Therefore, a connection can be established between the finite element point O of the thermal aerodynamic model and the finite element element of the thermal intensity model, thereby forming a mapping relationship between the finite element point O of the thermal aerodynamic model and the finite element point of the thermal intensity model. Specifically, in this application, the connection between the points of the two models is established by finding the nearest projection point P of the finite element point O on the hexahedral finite element mesh surface, so that the change of the finite element point O of the thermal aerodynamic model between the cold and hot states can be obtained by calculating the deformation of the finite element element of the thermal intensity model between the cold and hot states.

[0062] For example, for example, the specific steps of step 202 are as follows:

[0063] Find the n hexahedral finite element elements that are closest to the finite element point O; specifically, n is a positive integer, for example, it can be 32 or 16.

[0064] Projecting finite element point O onto each face of n finite element elements, we determine the nearest projection point P and the finite element element E containing that projection point P. In other words, we find the projection point P and the nearest finite element element E that are closest to finite element point O. For example, if n is 32, then we project finite element point O onto 32*6 faces.

[0065] Based on the above embodiments, step 102 may include the following steps, such as... Figure 2 As shown:

[0066] Step 203: Based on the relationship between the global and local coordinates of the finite element element E, and the shape function F of the finite element element E in the local coordinates, calculate the change D between the hot and cold states of the projection point P in the global coordinate system. xyz The change D xyz It is approximated as the change of finite element point O between the hot and cold states.

[0067] 'Global coordinates' refer to the coordinates within the entire thermal intensity model coordinate system; 'local coordinates' refer to the coordinate system established based on the equivalent hexahedron of the hexahedral finite element element E. Specifically, the hexahedral finite element element E, with finite element points of the thermal intensity model as vertices, is generally not a regular hexahedron; therefore, in this application, a three-dimensional coordinate system is established based on the equivalent hexahedron of the hexahedral finite element element E. Specifically, the equivalent hexahedron of the hexahedral finite element element E is a regular hexahedron, which can be a regular hexahedron.

[0068] In this embodiment, since the distance between the finite element point O and its nearest projection point P is very small, the nearest projection point P is approximated as the finite element point O, and the change D of the nearest projection point P between the hot and cold states is considered as the finite element point O. xyz The change in finite element point O between hot and cold states is approximated, and the calculation error meets the accuracy requirements of factory processing and production. Furthermore, compared to the shape function of the finite element element in global coordinates, the shape function F of the finite element element E in local coordinates is easier to calculate and relatively simple to obtain. Therefore, in this embodiment, the shape function F of the finite element element E in local coordinates is used, and the relationship between the global and local coordinates of the finite element element E is utilized to obtain the change in projection point P in the global coordinate system.

[0069] For example, the specific steps of step 203 are as follows:

[0070] Step 301: The relationship between the global and local coordinates of the finite element element E is described by the shape function F, and the relationship (1) is as follows:

[0071]

[0072]

[0073]

[0074] Where x, y, and z are the global coordinates of any point within the finite element element E, x i y i z i These are the global coordinates of each vertex of the finite element element E; m, l, and n are the local coordinates of each point on the equivalent hexahedron of the finite element element E; N i (m,l,n) is the shape function F of the finite element element E in local coordinates;

[0075] Step 302: Based on the coordinates of each vertex of the finite element element E, the shape function F of the finite element element E in the local coordinates is calculated using the relationship between the global and local coordinates of the finite element element E. In other words, the shape function F can be calculated by substituting the coordinates of the eight vertices of the finite element element E into the relationship (1). Specifically, the formula for the shape function F is as follows:

[0076]

[0077] Where m, l, and n are the local coordinates of each point on the equivalent hexahedron of the finite element element E, m i l i n i These are the local coordinates of each vertex of the finite element element E-equivalent hexahedron;

[0078] Step 303: Based on the formula of the shape function F and the relationship between the global coordinates and local coordinates of the finite element element E (1), calculate the local coordinates LP of the global coordinates WP of the projection point P in the finite element element E.

[0079] Step 304: The relationship between the deformation of the finite element E in global coordinates and the deformation in local coordinates is described by the shape function F. The relationship (2) is as follows:

[0080]

[0081]

[0082]

[0083] Specifically, since the coordinate values ​​and changes in coordinate values ​​of any point within the finite element element E are isoparametric with respect to the shape function F, the shape function F can be used not only to describe the relationship between the global and local coordinates of the finite element element E, but also to describe the relationship between the changes in global coordinates and the changes in local coordinates.

[0084] Step 305: Substitute the local coordinates LP of the projection point P into the relationship (2) between the deformation of the finite element E in the global coordinate system and the deformation in the local coordinate system, and calculate the change D of the projection point P in the global coordinate system. xyz .

[0085] In some embodiments, step 303 may specifically include the following steps:

[0086] Expanding the shape function F at any point K(x0, y0, z0) in the global coordinate system using Taylor expansion, and ignoring second-order and higher derivative terms, we obtain the linear relationship formula (3) between the global and local coordinates:

[0087] Coor(x,y,z)=Coor(x0,y0,z0)+J0(LCoor(m,n,l)-LCoor(m0,n0,l0))

[0088]

[0089] Where Coor represents global coordinates, LCoor represents local coordinates, and J0 is the Jacobian matrix;

[0090] After adjusting the linear relationship (3) between global and local coordinates, we obtain the iterative relationship (4):

[0091]

[0092] The unique iterative formula (5) is as follows:

[0093]

[0094] Based on the global coordinates WP of the projection point P, the virtual local coordinates VLP are approximately obtained using the iterative relation (4); based on the virtual local coordinates VLP, the virtual global coordinates VWP are calculated using the relation (1) between the global and local coordinates of the finite element element E; in other words, the virtual local coordinates VLP are obtained by substituting the global coordinates WP into relation (4), and the virtual global coordinates VWP are obtained by substituting the virtual local coordinates VLP into relation (1).

[0095] Compare the global coordinates WP of the projection point P with the virtual global coordinates VWP. If |WP-VWP|<ε, then the virtual local coordinates VLP are considered to be the local coordinates LP corresponding to the projection point P. Otherwise, according to (WP-VWP), the new virtual local coordinates VLP are obtained using the iterative relationship (5), and the iteration is repeated until the virtual global coordinates VWP corresponding to the obtained virtual local coordinates VLP satisfy |WP-VWP|<ε. Specifically, the value of ε needs to meet the accuracy allowed by the processing and production, which can be at the micrometer level.

[0096] In some embodiments, this application may further include the following steps after step 103:

[0097] Step 104: Interpolate the airfoil section of the cold blade model to the set section height to obtain a cold airfoil section of equal height.

[0098] Specifically, the airfoil cross-section of existing hot aerodynamic models is not a constant-height surface. Consequently, the cold-state blade model obtained using this hot aerodynamic model also has a non-constant-height airfoil cross-section, making it impossible for manufacturing plants to directly process the blade based on its cross-section. In this embodiment, by performing interpolation operations on a set constant-height surface, ordered points of the constant-height cross-section that can be used for manufacturing can be obtained.

[0099] For example, step 104 may specifically include the following steps:

[0100] If the set section height is inside the airfoil section of the cold blade model, cubic spline interpolation is used; if the set section height is outside the airfoil section of the cold blade model, linear extrapolation is used.

[0101] In some embodiments, this application may further include the following steps before step 101:

[0102] Step 100: Use spline interpolation of the cross section of the thermal aerodynamic model to obtain the new highest and lowest cross sections of the thermal aerodynamic model. The new highest and lowest cross sections are located within the thermal intensity model.

[0103] For example, in step 100, cubic spline interpolation can be performed on the cross section of the thermal aerodynamic model.

[0104] Specifically, through the interpolation operation in step 100, the points at the root and tip of the hot aerodynamic model can be located within the hot intensity model, thereby ensuring that the points at the root and tip of the hot aerodynamic model can be projected onto the finite element elements of the hot intensity model, thus improving the accuracy of the blade tip and root of the final cold blade model.

[0105] This application provides a method for generating the coordinates of a cold-state airfoil section. Specifically, this method uses finite element method, isoparametric element interpolation, and other methods to quickly and efficiently obtain the cold-state airfoil section for factory processing and production. Furthermore, this method has low requirements for the finite element mesh and high interpolation accuracy.

[0106] Specifically, this method is not limited to the blade type; it can be either a compressor blade or a turbine blade. It also applies when the blade root is rounded, and if the rounding is a hexahedral mesh.

[0107] In addition, this application also provides an electronic device, which includes:

[0108] Memory, used to store executable instructions;

[0109] A processor is used to read and execute executable instructions stored in memory to implement the method for generating the cold blade model of any of the above.

[0110] Specifically, the electronic device can be a server or a terminal device with processing capabilities, capable of executing the program described above.

[0111] In addition, this disclosure also provides a storage medium that, when the instructions in the storage medium are executed by an electronic device, enables the electronic device to execute the method for generating a cold blade model as described above.

[0112] Other embodiments of this disclosure will readily occur to those skilled in the art upon consideration of the specification and practice of the invention disclosed herein. This disclosure is intended to cover any variations, uses, or adaptations of the invention that follow the general principles of this disclosure and include common knowledge or customary techniques in the art not disclosed herein. The specification and exemplary embodiments are to be considered exemplary only, and the true scope and spirit of this disclosure are indicated by the appended claims.

[0113] It should be understood that this disclosure is not limited to the precise structures described above and shown in the accompanying drawings, and various modifications and changes can be made without departing from its scope. The scope of protection of this disclosure is limited only by the appended claims.

Claims

1. A method for generating a cold-state blade model, characterized in that, Includes the following steps: Establish a mapping relationship between the finite element points of the thermal aerodynamic model of the blade and the finite element points of the thermal intensity model; Based on the mapping relationship and the changes in the finite element points of the thermal intensity model under hot and cold conditions, the changes in the finite element points of the thermal aerodynamic model under hot and cold conditions are calculated. The finite element points of the hot aerodynamic model are superimposed with the changes of the finite element points of the hot aerodynamic model under hot and cold conditions to obtain an ordered cold blade model. The process of establishing a mapping relationship between the finite element points of the thermal aerodynamic model of the blade and the finite element points of the thermal intensity model specifically includes the following steps: The thermal intensity model is divided into hexahedral finite element elements, and the vertex of each finite element element is a finite element point of the thermal intensity model. For each finite element point O of the thermal aerodynamic model, the following operations are performed: the finite element element E closest to the finite element point O is determined, and the projection point P closest to the projection point of the finite element point O on each face of the finite element element E is determined. The step of calculating the changes in the finite element points of the thermal aerodynamic model under cold and hot conditions based on the mapping relationship and the changes in the finite element points of the thermal intensity model under cold and hot conditions specifically includes the following steps: The relationship between the global and local coordinates of the finite element element E is described by the shape function F in local coordinates, as follows: Where x, y, and z are the global coordinates of any point within the finite element element E, x i y i z i The coordinates of each vertex of the finite element element E are global coordinates; m, l, and n are local coordinates of each point on the equivalent hexahedron of the finite element element E; N is the global coordinates of each vertex of the finite element element E. i (m,l,n) is the shape function F of the finite element element E in local coordinates; Based on the coordinates of each vertex of the finite element element E, and using the relationship between the global and local coordinates of the finite element element E, the shape function F of the finite element element E in the local coordinates is calculated: Where, m i l i n i These are the local coordinates of each vertex of the finite element element E-equivalent hexahedron; Based on the shape function F and the relationship between the global and local coordinates of the finite element element E, the local coordinates LP of the global coordinates WP of the projection point P in the finite element element E are calculated. The shape function F describes the relationship between the deformation of the finite element E in global coordinates and the deformation in local coordinates, as shown in the following formula: Where dx, dy, and dz are the changes in the global coordinates of any point within the finite element E, and dx i dy i dz i It is the change in the global coordinates of each vertex of the finite element element E; Substituting the local coordinates LP of the projection point P into the relationship between the deformation of the finite element E in the global coordinate system and the deformation in the local coordinate system, the change D of the projection point P in the global coordinate system is calculated. xyz The change D xyz It is approximated as the change in the finite element point O between the hot and cold states.

2. The method for generating a cold-state blade model as described in claim 1, characterized in that, Determine the finite element element E that is closest to the finite element point O, and the projection point P that is closest to the projection point of the finite element point O among the projection points of each face of the finite element element E; specifically including the following steps: Find the n finite element elements that are closest to the finite element point O; Project the finite element point O onto each face of the n finite element elements to determine the nearest projection point P and the finite element element E in which the projection point P is located.

3. The method for generating a cold-state blade model as described in claim 1, characterized in that, The step of calculating the global coordinates WP of the projection point P in the finite element element E based on the shape function F and the relationship between the global and local coordinates of the finite element element E includes the following steps: Expanding the shape function F at any point K(x0, y0, z0) in the global coordinate system using Taylor expansion, and ignoring second-order and higher derivative terms, yields a linear relationship between the global and local coordinates. Adjusting this linear relationship, we obtain an iterative relationship: Where Coor represents global coordinates, LCoor represents local coordinates, and J0 is the Jacobian matrix; Based on the global coordinates WP of the projection point P, the virtual local coordinates VLP are approximately obtained using the iterative formula. Based on the virtual local coordinates VLP, the virtual global coordinates VWP are calculated using the relationship between the global and local coordinates of the finite element element E. Compare the global coordinates WP with the virtual global coordinates VWP. If |WP-VWP| < If the virtual local coordinates VLP are true, then the virtual local coordinates VLP are considered to be the local coordinates LP corresponding to the projection point P; otherwise, according to WP-VWP, a new virtual local coordinate VLP is obtained using the iterative relationship, and the iteration is repeated until the virtual global coordinates VWP corresponding to the obtained virtual local coordinates VLP satisfy |WP-VWP| < .

4. The method for generating a cold-state blade model as described in claim 1, characterized in that, After obtaining the ordered cold blade model, the following steps are also included: The airfoil section of the cold blade model is interpolated to a set section height to obtain a cold blade section of equal height.

5. The method for generating a cold-state blade model as described in claim 4, characterized in that, If the set section height is inside the airfoil section, cubic spline interpolation is used; if the set section height is outside the airfoil section, linear extrapolation is used.

6. The method for generating a cold-state blade model as described in any one of claims 1-5, characterized in that, Before establishing the mapping relationship between the finite element points of the thermal aerodynamic model of the blade and the finite element points of the thermal intensity model, the following steps are also included: By using spline interpolation of the cross sections of the thermal aerodynamic model, new highest and lowest cross sections of the thermal aerodynamic model are obtained, and these new highest and lowest cross sections are located within the thermal intensity model.

7. An electronic device, characterized in that, include: Memory, used to store executable instructions; A processor for reading and executing executable instructions stored in memory to implement the method for generating a cold blade model as described in any one of claims 1 to 6.

8. A storage medium, characterized in that, When the instructions in the storage medium are executed by an electronic device, the electronic device is able to perform the method for generating a cold blade model as described in any one of claims 1 to 6.

Images