Wind turbine generator blade pneumatic simulation method and device based on icing and terminal equipment

Abstract

The invention provides a wind turbine generator blade pneumatic simulation method and device based on icing and terminal equipment, and relates to the technical field of fan blade simulation, and the method comprises the steps: obtaining the original geometric data of each section of a wind turbine generator blade, and carrying out the pneumatic simulation of the wind turbine generator blade based on the original geometric parameters, obtaining original aerodynamic parameters of each section; determining geometric data of the wind turbine generator blade under at least one icing condition, and performing pneumatic simulation on the wind turbine generator blade according to the geometric data under the icing condition to obtain pneumatic parameters of each section of the wind turbine generator blade under the icing condition; for each section, determining a correlation coefficient between the original aerodynamic parameters and the aerodynamic parameters under the icing condition; and obtaining an original pneumatic parameter experiment value of the corresponding section of the wind turbine generator blade, and performing preset operation on the original pneumatic parameter experiment value by using the correlation coefficient to obtain a target pneumatic parameter of the current section under the icing condition. According to the invention, the precision of blade icing simulation can be improved.

Description

Technical Field

[0001] The present application relates to the technical field of wind turbine blade simulation, and specifically to an aerodynamic simulation method for wind turbine blades based on icing, an aerodynamic simulation device for wind turbine blades based on icing, a computer-readable storage medium, and a terminal device. Background Art

[0002] In cold environments, wind turbine blades are prone to ice accumulation, which will affect the natural frequency, limit load and fatigue load of the unit. If the degree of ice accumulation on the three blades is different, it will lead to unbalanced impeller mass, forming unbalanced bending moment in the plane of rotation of the wind rotor, and then have an adverse effect on the unit's transmission chain and tower. At present, when calculating the performance of blade ice accumulation through wind turbine load calculation software, only the impact of ice accumulation on blade mass is considered, and its impact on aerodynamic performance is not considered. It is impossible to accurately simulate the impact of blade ice accumulation on wind turbine operation. Summary of the invention

[0003] The purpose of the embodiments of the present application is to provide an aerodynamic simulation method for wind turbine blades based on icing, an aerodynamic simulation device for wind turbine blades based on icing, a computer-readable storage medium and a terminal device to solve the above problems.

[0004] In order to achieve the above-mentioned object, the first aspect of the present application provides an aerodynamic simulation method for wind turbine blades based on ice coating, comprising: Acquire original geometric data of each cross section of the wind turbine blade, perform aerodynamic simulation on the wind turbine blade based on the original geometric parameters, and obtain original aerodynamic parameters of each cross section of the wind turbine blade; Determine geometric data of the wind turbine blade under at least one icing condition, perform aerodynamic simulation on the wind turbine blade based on the geometric data under the icing condition, and obtain aerodynamic parameters of each cross section of the wind turbine blade under the icing condition; For each cross section, determining a correlation coefficient between the original aerodynamic parameter and the aerodynamic parameter under the icing condition; The original aerodynamic parameter experimental value of the corresponding cross section of the wind turbine blade is obtained, and the original aerodynamic parameter experimental value is preset and calculated using the correlation coefficient to obtain the target aerodynamic parameter of the current cross section under the icing condition.

[0005] Optionally, before obtaining the original geometric data of each cross section of the wind turbine blade, the method further includes: Establishing a geometric model of the wind turbine blades; Determining a plurality of cross sections of the wind turbine blade based on a geometric model of the wind turbine blade; Obtaining the coordinates of the airfoil contour points of each section of the wind turbine blade, saving the coordinates of the airfoil contour points of each section into a geometric data file of a specified format, and determining the section number corresponding to each geometric data file; Obtain the original geometric data of each section of the wind turbine blade, including: The original geometric data of the corresponding section is obtained from the pre-stored geometric data file using the section number of each section as an index.

[0006] Optionally, performing aerodynamic simulation on the wind turbine blade group based on the original geometric parameters to obtain original aerodynamic parameters of each cross section of the wind turbine blade group includes: Using the original geometric parameters as input, calling preset simulation software through a preset data interface, and performing aerodynamic simulation on the wind turbine blade based on the simulation software; and The original aerodynamic parameters of each cross section of the wind turbine blade are received, wherein the original aerodynamic parameters of each cross section of the wind turbine blade are obtained by performing aerodynamic simulation on the wind turbine blade by the simulation calculation software.

[0007] Optionally, before performing aerodynamic simulation on the wind turbine blades using the geometric data under the icing condition, the method further comprises: Based on the geometric model of the wind turbine blade, determining the geometric model of the wind turbine blade under at least one icing condition; For each icing situation: Obtaining the coordinates of the airfoil contour points of each cross section of the wind turbine blade before ice coating; The coordinates of the airfoil contour points of the corresponding cross-section of the wind turbine blade after being covered with ice are determined based on the coordinates of the airfoil contour points of each cross-section of the wind turbine blade before being covered with ice, so that the coordinates of the airfoil contour points of the corresponding cross-section of the wind turbine blade after being covered with ice include the coordinates of all the airfoil contour points of the corresponding cross-section before being covered with ice, and the coordinates of the airfoil contour points after being covered with ice are on the same plane as the coordinates of all the airfoil contour points of the corresponding cross-section before being covered with ice.

[0008] Optionally, the aerodynamic parameters include: a lift coefficient, a drag coefficient, and a moment coefficient of a corresponding cross section; determining a correlation coefficient between the original aerodynamic parameters and the aerodynamic parameters under the icing condition includes: A first correlation coefficient between the lift coefficient of the aerodynamic parameters under the icing condition and the lift coefficient of the original aerodynamic parameters, a second correlation coefficient between the drag coefficient of the aerodynamic parameters under the icing condition and the drag coefficient of the original aerodynamic parameters, and a third correlation coefficient between the moment coefficient of the aerodynamic parameters under the icing condition and the moment coefficient of the original aerodynamic parameters are calculated.

[0009] Optionally, the first correlation coefficient is a ratio of the lift coefficient of the aerodynamic parameter under the icing condition to the lift coefficient of the original aerodynamic parameter; The second correlation coefficient is a ratio of the drag coefficient of the aerodynamic parameters under the icing condition to the drag coefficient of the original aerodynamic parameters; The third correlation coefficient is a ratio of the moment coefficient of the aerodynamic parameter in the icing condition to the moment coefficient of the original aerodynamic parameter.

[0010] Optionally, performing a preset operation on the original aerodynamic parameter experimental value using the correlation coefficient to obtain a target aerodynamic parameter of the current cross section under the icing condition includes: Performing a quadrature operation on the lift coefficient of the original aerodynamic parameter experimental value and the first correlation coefficient to obtain a target lift coefficient of the current cross section under the icing condition; Performing a quadrature operation on the drag coefficient of the original aerodynamic parameter experimental value and the second correlation coefficient to obtain a target drag coefficient of the current cross section under the icing condition; A quadrature operation is performed on the moment coefficient of the original aerodynamic parameter experimental value and the third correlation coefficient to obtain a target moment coefficient of the current cross section under the icing condition.

[0011] In a second aspect of the present application, there is provided an aerodynamic simulation device for wind turbine blades based on ice coating, comprising: A first data acquisition module is configured to acquire original geometric data of each cross section of a wind turbine blade, and perform aerodynamic simulation on the wind turbine blade based on the original geometric parameters to obtain original aerodynamic parameters of each cross section of the wind turbine blade; A second data acquisition module is configured to determine geometric data of the wind turbine blade under at least one icing condition, perform aerodynamic simulation on the wind turbine blade based on the geometric data under the icing condition, and obtain aerodynamic parameters of each cross section of the wind turbine blade under the icing condition; A correlation coefficient calculation module is configured to determine, for each cross section, a correlation coefficient between the original aerodynamic parameter and the aerodynamic parameter under the icing condition; The aerodynamic parameter calculation module is configured to obtain the original aerodynamic parameter experimental value of the corresponding cross-section of the wind turbine blade, perform a preset operation on the original aerodynamic parameter experimental value with the correlation coefficient, and obtain the target aerodynamic parameter of the current cross-section under the icing condition.

[0012] In a third aspect of the present application, a computer-readable storage medium is provided, which stores a computer program which, when executed by a processor, causes the processor to execute the above-mentioned aerodynamic simulation method for wind turbine blades.

[0013] In a fourth aspect of the present application, a terminal device is provided, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the above-mentioned aerodynamic simulation method for wind turbine blades when executing the computer program.

[0014] The embodiments provided in this application have the following beneficial effects: The present application performs aerodynamic simulation on the wind turbine blades under ice-covered conditions to obtain the aerodynamic parameters of the wind turbine blades under ice-covered conditions, thereby making it possible to correct the airfoil of the wind turbine blades and improve the accuracy of the blade ice-covered simulation.

[0015] Other features and advantages of the embodiments or implementations of the present application will be described in detail in the subsequent specific implementation section. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The accompanying drawings are used to provide a further understanding of the embodiments of the present application and constitute a part of the specification. Together with the following specific implementations, they are used to explain the embodiments of the present application, but do not constitute a limitation on the embodiments of the present application. In the accompanying drawings: Figure 1 A method flow chart of an aerodynamic simulation method for wind turbine blades based on ice coating according to an embodiment of the present application is schematically shown; Figure 2 A schematic diagram showing a comparison of airfoils before and after ice coating according to an embodiment of the present application is shown; Figure 3 A schematic diagram showing a comparison of aerodynamic parameters before and after icing according to an embodiment of the present application is shown; Figure 4 A schematic diagram of an aerodynamic simulation device for wind turbine blades based on ice coating according to an embodiment of the present application is schematically shown; Figure 5 A schematic diagram of the structure of a terminal device according to an embodiment of the present application is shown schematically.

[0017] Description of Reference Numerals 10-terminal device, 100-processor, 101-memory, 102-computer program. DETAILED DESCRIPTION

[0018] The specific implementation of the embodiment of the present application is described in detail below in conjunction with the accompanying drawings. It should be understood that the specific implementation described here is only used to illustrate and explain the embodiment of the present application, and is not used to limit the embodiment of the present application.

[0019] The airfoil of wind turbine blades has a direct impact on the operation of wind turbines. At present, when designing the airfoil of wind turbine blades, when simulating the load under ice-covered conditions, only the impact of ice on the blade mass is often considered, while the impact of ice on the aerodynamic performance of the blade is not considered. Therefore, when the designed wind turbine blades are operated under ice-covered conditions, it may affect the operation of the wind turbine and pose a safety hazard.

[0020] In order to solve the above problems, Figure 1 As shown, the first aspect of the present application provides an aerodynamic simulation method for wind turbine blades based on icing, comprising: S100, acquiring original geometric data of each cross section of the wind turbine blade, performing aerodynamic simulation on the wind turbine blade based on the original geometric parameters, and obtaining original aerodynamic parameters of each cross section of the wind turbine blade; S200, determining geometric data of a wind turbine blade under at least one icing condition, performing aerodynamic simulation on the wind turbine blade based on the geometric data under the icing condition, and obtaining aerodynamic parameters of each cross section of the wind turbine blade under the icing condition; S300, determining, for each cross section, a correlation coefficient between an original aerodynamic parameter and an aerodynamic parameter under an icing condition; S400, obtaining original aerodynamic parameter experimental values ​​of a corresponding cross section of a wind turbine blade, performing preset calculations on the original aerodynamic parameter experimental values ​​using correlation coefficients, and obtaining target aerodynamic parameters of the current cross section under an icing condition.

[0021] In this way, the present application obtains the aerodynamic parameters of the wind turbine blades under ice-covered conditions by performing aerodynamic simulation on the wind turbine blades under ice-covered conditions, thereby being able to correct the airfoil of the wind turbine blades and improve the accuracy of the blade ice-covered simulation.

[0022] Before step S100, the present application first establishes a geometric model of the wind turbine blade, and then determines multiple sections of the wind turbine blade based on the geometric model of the wind turbine blade, for example, determines multiple key sections that have a direct impact on the blade airfoil; after determining the key sections, the airfoil contour point coordinates of each section of the wind turbine blade are determined and obtained based on the constructed geometric model, and the airfoil contour point coordinates of each section are saved in a geometric data file of a specified format, and the section number corresponding to each geometric data file is determined. For example, assuming that there are sections 1, 2, and 3, the airfoil contour point coordinate data of section 1 is saved in the section1.dat file, the airfoil contour point coordinate data of section 2 is saved in the section2.dat file, and the airfoil contour point coordinate data of section 3 is saved in the section3.dat file, wherein section1, section2, and section3 can be used as the section numbers corresponding to the airfoil contour point coordinate data of each section, wherein the section1.dat file, the section2.dat file, and the section3.dat file are pre-stored in the same specified storage location, for example, in the same folder.

[0023] In step S100, the original geometric data of each section of the wind turbine blade is obtained, including: using the section number of each section as an index, obtaining the original geometric data of the corresponding section from the pre-stored geometric data file. For example, when obtaining the original geometric data of the wind turbine blade, that is, the airfoil contour point coordinates of each section, the section number of the section to be processed can be used as an index, and the airfoil contour point coordinate data files of all sections are queried from the designated storage location to determine whether there is a file with the same number as the current section. If so, the file is obtained, and the airfoil contour point coordinate data in the file is read as the original geometric data of the current section.

[0024] After the original geometric data of each section of the blade is obtained, in step S100, aerodynamic simulation is performed on the wind turbine blade group based on the original geometric parameters to obtain the original aerodynamic parameters of each section of the wind turbine blade, including: taking the original geometric parameters as input, calling the preset simulation calculation software through the preset data interface, and performing aerodynamic simulation on the wind turbine blade based on the simulation calculation software; and receiving the original aerodynamic parameters of each section of the wind turbine blade, the original aerodynamic parameters of each section of the wind turbine blade are obtained after the simulation calculation software performs aerodynamic simulation on the wind turbine blade. Among them, the simulation calculation software can be x.foil software, which is a software that calculates aerodynamic correlation coefficients through airfoil geometric data. After obtaining the airfoil contour point coordinate data of each section of the blade, the simulation software is called through the pre-constructed data interface, and the airfoil contour point coordinate data of the blade section is taken as input. The simulation software calculates the original aerodynamic parameters corresponding to each section based on the airfoil contour point coordinate data of each section.

[0025] like Figure 2 As shown, in step S200, after determining the original geometric data of the wind turbine blade, on the basis of the original geometric model of the wind turbine blade, the present application constructs at least one geometric model under ice conditions based on the thickness and shape of the ice according to different ice conditions, modifies the original airfoil geometric data according to the ice conditions, forms iced airfoil geometric data and saves it as a ".dat" file. For each ice condition: obtain the airfoil contour point coordinates of each section of the wind turbine blade before ice, and determine the airfoil contour point coordinates of the corresponding section of the wind turbine blade after ice based on the airfoil contour point coordinates of each section of the wind turbine blade before ice, so that the airfoil contour point coordinates of the corresponding section of the wind turbine blade after ice include all the airfoil contour point coordinates of the corresponding section before ice, and the airfoil contour point coordinates after ice are on the same plane as all the airfoil contour point coordinates of the corresponding section before ice. That is, the selection of the section of the newly established geometric model after ice needs to correspond one-to-one with the section of the original geometric model, and the section at the same position relative to the original geometric model is selected as the section under ice conditions.

[0026] It can be understood that the aerodynamic parameters include: the lift coefficient, drag coefficient and moment coefficient of the corresponding cross section. Through the x.foil software, the aerodynamic simulation of the wind turbine blade is performed with the geometric data under the icing condition, and the aerodynamic parameters of each cross section of the wind turbine blade under the icing condition can be obtained. In step S300, the correlation coefficient between the original aerodynamic parameters and the aerodynamic parameters under the icing condition is determined, including: calculating the first correlation coefficient between the lift coefficient of the aerodynamic parameters under the icing condition and the lift coefficient of the original aerodynamic parameters, the second correlation coefficient between the drag coefficient of the aerodynamic parameters under the icing condition and the drag coefficient of the original aerodynamic parameters, and the third correlation coefficient between the moment coefficient of the aerodynamic parameters under the icing condition and the moment coefficient of the original aerodynamic parameters. Among them, the first correlation coefficient is the ratio of the lift coefficient of the aerodynamic parameters under icing to the lift coefficient of the original aerodynamic parameters; the second correlation coefficient is the ratio of the drag coefficient of the aerodynamic parameters under icing to the drag coefficient of the original aerodynamic parameters; the third correlation coefficient is the ratio of the moment coefficient of the aerodynamic parameters under icing to the moment coefficient of the original aerodynamic parameters. That is, calculate aL=CL_2 / CL_1, aD=CD_2 / CD_1, aM=CM_2 / CM_1, among which aL is the first correlation coefficient, aD is the second correlation coefficient, aM is the third correlation coefficient, CL_1 is the original lift coefficient, CL_2 is the lift coefficient after icing, CD_1 is the original drag coefficient, CD_2 is the drag coefficient after icing, CM_1 is the original moment coefficient, and CM_2 is the moment coefficient after icing.

[0027] In step S400, the original aerodynamic parameter experimental values ​​of each section of the wind turbine blade can be obtained by conducting experiments on the wind turbine blade in advance, and the original aerodynamic parameter experimental values ​​are pre-calculated using correlation coefficients, such as Figure 3As shown, the target aerodynamic parameters of the current cross section under icing conditions are obtained, including: performing a quadrature operation on the lift coefficient and the first correlation coefficient of the original aerodynamic parameter experimental value to obtain the target lift coefficient of the current cross section under icing conditions; performing a quadrature operation on the drag coefficient and the second correlation coefficient of the original aerodynamic parameter experimental value to obtain the target drag coefficient of the current cross section under icing conditions; performing a quadrature operation on the moment coefficient and the third correlation coefficient of the original aerodynamic parameter experimental value to obtain the target moment coefficient of the current cross section under icing conditions. That is, CL'=CL×aL, CD'=CD×aD, CM'=CM×aM, wherein CL' is the target lift coefficient under icing conditions, CL is the lift coefficient of the original aerodynamic parameter experimental value, CD' is the target drag coefficient under icing conditions, CD is the drag coefficient of the original aerodynamic parameter experimental value, CM' is the target moment coefficient under icing conditions, and CM is the moment coefficient of the original aerodynamic parameter experimental value. Finally, after obtaining the geometric data and aerodynamic parameters of the ice-covered airfoil, they are input into the Bladed software for calculation, so as to analyze the output power, load distribution, vibration and fatigue of the wind turbine, which is conducive to the optimization design of the wind turbine blade airfoil. It can be understood that when the geometric data and aerodynamic parameters of the ice-covered airfoil are input into the Bladed software, the geometric data and aerodynamic parameters should be ensured to correspond.

[0028] like Figure 4 As shown, in a second aspect of the present application, there is provided an aerodynamic simulation device for wind turbine blades based on ice coating, comprising: A first data acquisition module is configured to obtain original geometric data of each cross section of the wind turbine blade, perform aerodynamic simulation on the wind turbine blade based on the original geometric parameters, and obtain original aerodynamic parameters of each cross section of the wind turbine blade; A second data acquisition module is configured to determine geometric data of the wind turbine blade under at least one icing condition, perform aerodynamic simulation on the wind turbine blade based on the geometric data under the icing condition, and obtain aerodynamic parameters of each cross section of the wind turbine blade under the icing condition; A correlation coefficient calculation module is configured to determine, for each cross section, a correlation coefficient between the original aerodynamic parameters and the aerodynamic parameters under icing conditions; The aerodynamic parameter calculation module is configured to obtain the original aerodynamic parameter experimental values ​​of the corresponding cross-section of the wind turbine blade, perform preset operations on the original aerodynamic parameter experimental values ​​with correlation coefficients, and obtain the target aerodynamic parameters of the current cross-section under icing conditions.

[0029] The technicians in the relevant field can clearly understand that for the convenience and simplicity of description, only the division of the above-mentioned functional units and modules is used as an example for illustration. In practical applications, the above-mentioned function allocation can be completed by different functional units and modules as needed, that is, the internal structure of the device can be divided into different functional units or modules to complete all or part of the functions described above. The functional units and modules in the embodiment can be integrated in a processing unit, or each unit can exist physically separately, or two or more units can be integrated in one unit. The above-mentioned integrated unit can be implemented in the form of hardware or in the form of software functional units. In addition, the specific names of the functional units and modules are only for the convenience of distinguishing each other, and are not used to limit the scope of protection of this application. The specific working process of the units and modules in the above-mentioned system can refer to the corresponding process in the aforementioned method embodiment, which will not be repeated here.

[0030] In a third aspect of the present application, a computer-readable storage medium is provided, which stores a computer program which, when executed by a processor, causes the processor to execute the above-mentioned aerodynamic simulation method for wind turbine blades.

[0031] In a fourth aspect of the present application, a terminal device is provided, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the above-mentioned aerodynamic simulation method for wind turbine blades when executing the computer program.

[0032] like Figure 5 FIG. 1 is a schematic diagram of a terminal device provided in an embodiment of the present application. Figure 5 As shown, the terminal device 10 of this embodiment includes: a processor 100, a memory 101, and a computer program 102 stored in the memory 101 and executable on the processor 100. When the processor 100 executes the computer program 102, the steps in the above method embodiment are implemented. Alternatively, when the processor 100 executes the computer program 102, the functions of each module / unit in the above device embodiments are implemented.

[0033] Exemplarily, the computer program 102 may be divided into one or more modules / units, one or more modules / units are stored in the memory 101, and are executed by the processor 100 to complete the present application. One or more modules / units may be a series of computer program instruction segments capable of completing specific functions, and the instruction segments are used to describe the execution process of the computer program 102 in the terminal device 10.

[0034] The terminal device 10 may be a computing device such as a desktop computer, a notebook, a PDA, or a cloud server. The terminal device 10 may include, but is not limited to, a processor 100 and a memory 101. Those skilled in the art will appreciate that Figure 5It is only an example of the terminal device 10 and does not constitute a limitation of the terminal device 10. It may include more or fewer components than shown in the figure, or a combination of certain components, or different components. For example, the terminal device may also include input and output devices, network access devices, buses, etc.

[0035] The processor 100 may be a central processing unit (CPU), or other general-purpose processors, digital signal processors (DSP), application-specific integrated circuits (ASIC), field-programmable gate arrays (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. A general-purpose processor may be a microprocessor or the processor may be any conventional processor, etc.

[0036] The memory 101 may be an internal storage unit of the terminal device 10, such as a hard disk or memory of the terminal device 10. The memory 101 may also be an external storage device of the terminal device 10, such as a plug-in hard disk, a smart media card (SMC), a secure digital (SD) card, a flash card (FlashCard), etc. equipped on the terminal device 10. Further, the memory 101 may also include both an internal storage unit of the terminal device 10 and an external storage device. The memory 101 is used to store computer programs and other programs and data required by the terminal device 10. The memory 101 may also be used to temporarily store data that has been output or is to be output.

[0037] Those skilled in the art will appreciate that the embodiments of the present application may be provided as methods, systems, or computer program products. Therefore, the present application may adopt the form of a complete hardware embodiment, a complete software embodiment, or an embodiment combining software and hardware. Moreover, the present application may adopt the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program codes.

[0038] It should also be noted that the terms "include", "comprises" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, commodity or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, commodity or device. In the absence of more restrictions, the elements defined by the sentence "comprises a ..." do not exclude the existence of other identical elements in the process, method, commodity or device including the elements.

[0039] The above are only embodiments of the present application and are not intended to limit the present application. For those skilled in the art, the present application may have various changes and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included within the scope of the claims of the present application.

Claims

1. An aerodynamic simulation method for wind turbine blades based on ice coating, characterized in that: include: Acquire original geometric data of each cross section of the wind turbine blade, perform aerodynamic simulation on the wind turbine blade based on the original geometric parameters, and obtain original aerodynamic parameters of each cross section of the wind turbine blade; Determine geometric data of the wind turbine blade under at least one icing condition, perform aerodynamic simulation on the wind turbine blade based on the geometric data under the icing condition, and obtain aerodynamic parameters of each cross section of the wind turbine blade under the icing condition; For each cross section, determining a correlation coefficient between the original aerodynamic parameter and the aerodynamic parameter under the icing condition; The original aerodynamic parameter experimental value of the corresponding cross section of the wind turbine blade is obtained, and the original aerodynamic parameter experimental value is preset and calculated using the correlation coefficient to obtain the target aerodynamic parameter of the current cross section under the icing condition.

2. The aerodynamic simulation method for wind turbine blades based on icing according to claim 1, characterized in that: Before obtaining the original geometric data of each cross section of the wind turbine blade, the method further includes: Establishing a geometric model of the wind turbine blades; Determining a plurality of cross sections of the wind turbine blade based on a geometric model of the wind turbine blade; Obtaining the coordinates of the airfoil contour points of each section of the wind turbine blade, saving the coordinates of the airfoil contour points of each section into a geometric data file of a specified format, and determining the section number corresponding to each geometric data file; Obtain the original geometric data of each section of the wind turbine blade, including: The original geometric data of the corresponding section is obtained from the pre-stored geometric data file using the section number of each section as an index.

3. The aerodynamic simulation method for wind turbine blades based on icing according to claim 1, characterized in that: Performing aerodynamic simulation on the wind turbine blade group based on the original geometric parameters to obtain original aerodynamic parameters of each cross section of the wind turbine blade group includes: Using the original geometric parameters as input, calling preset simulation software through a preset data interface, and performing aerodynamic simulation on the wind turbine blade based on the simulation software; and The original aerodynamic parameters of each cross section of the wind turbine blade are received, wherein the original aerodynamic parameters of each cross section of the wind turbine blade are obtained by performing aerodynamic simulation on the wind turbine blade by the simulation calculation software.

4. The aerodynamic simulation method for wind turbine blades based on icing according to claim 2, characterized in that: Before performing aerodynamic simulation on the wind turbine blades using the geometric data under the icing condition, the method further includes: Based on the geometric model of the wind turbine blade, determining the geometric model of the wind turbine blade under at least one icing condition; For each icing situation: Obtaining the coordinates of the airfoil contour points of each cross section of the wind turbine blade before ice coating; The coordinates of the airfoil contour points of the corresponding cross-section of the wind turbine blade after being covered with ice are determined based on the coordinates of the airfoil contour points of each cross-section of the wind turbine blade before being covered with ice, so that the coordinates of the airfoil contour points of the corresponding cross-section of the wind turbine blade after being covered with ice include the coordinates of all the airfoil contour points of the corresponding cross-section before being covered with ice, and the coordinates of the airfoil contour points after being covered with ice are on the same plane as the coordinates of all the airfoil contour points of the corresponding cross-section before being covered with ice.

5. The aerodynamic simulation method for wind turbine blades based on icing according to claim 1, characterized in that: The aerodynamic parameters include: lift coefficient, drag coefficient and moment coefficient of the corresponding cross section; determining the correlation coefficient between the original aerodynamic parameters and the aerodynamic parameters under the icing condition, including: A first correlation coefficient between the lift coefficient of the aerodynamic parameters under the icing condition and the lift coefficient of the original aerodynamic parameters, a second correlation coefficient between the drag coefficient of the aerodynamic parameters under the icing condition and the drag coefficient of the original aerodynamic parameters, and a third correlation coefficient between the moment coefficient of the aerodynamic parameters under the icing condition and the moment coefficient of the original aerodynamic parameters are calculated.

6. The aerodynamic simulation method for wind turbine blades based on icing according to claim 5, characterized in that: The first correlation coefficient is a ratio of the lift coefficient of the aerodynamic parameter under the icing condition to the lift coefficient of the original aerodynamic parameter; The second correlation coefficient is a ratio of the drag coefficient of the aerodynamic parameters under the icing condition to the drag coefficient of the original aerodynamic parameters; The third correlation coefficient is a ratio of the moment coefficient of the aerodynamic parameter in the icing condition to the moment coefficient of the original aerodynamic parameter.

7. The aerodynamic simulation method for wind turbine blades based on icing according to claim 6, characterized in that: The original aerodynamic parameter experimental value is preset and calculated using the correlation coefficient to obtain the target aerodynamic parameter of the current cross section under the icing condition, including: Performing a quadrature operation on the lift coefficient of the original aerodynamic parameter experimental value and the first correlation coefficient to obtain a target lift coefficient of the current cross section under the icing condition; Performing a quadrature operation on the drag coefficient of the original aerodynamic parameter experimental value and the second correlation coefficient to obtain a target drag coefficient of the current cross section under the icing condition; A quadrature operation is performed on the moment coefficient of the original aerodynamic parameter experimental value and the third correlation coefficient to obtain a target moment coefficient of the current cross section under the icing condition.

8. An aerodynamic simulation device for wind turbine blades based on ice coating, characterized in that: include: A first data acquisition module is configured to acquire original geometric data of each cross section of a wind turbine blade, and perform aerodynamic simulation on the wind turbine blade based on the original geometric parameters to obtain original aerodynamic parameters of each cross section of the wind turbine blade; A second data acquisition module is configured to determine geometric data of the wind turbine blade under at least one icing condition, perform aerodynamic simulation on the wind turbine blade based on the geometric data under the icing condition, and obtain aerodynamic parameters of each cross section of the wind turbine blade under the icing condition; A correlation coefficient calculation module is configured to determine, for each cross section, a correlation coefficient between the original aerodynamic parameter and the aerodynamic parameter under the icing condition; The aerodynamic parameter calculation module is configured to obtain the original aerodynamic parameter experimental value of the corresponding cross-section of the wind turbine blade, perform a preset operation on the original aerodynamic parameter experimental value with the correlation coefficient, and obtain the target aerodynamic parameter of the current cross-section under the icing condition.

9. A computer-readable storage medium storing a computer program which, when executed by a processor, causes the processor to execute the method for aerodynamic simulation of a wind turbine blade according to any one of claims 1 to 7.

10. A terminal device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the computer program, the wind turbine blade aerodynamic simulation method according to any one of claims 1 to 7 is implemented.

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