Three-dimensional ice accretion reconstruction method and apparatus for fan blade, and device and storage medium

Abstract

A three-dimensional ice accretion reconstruction method and apparatus for a fan blade, and a device and a storage medium. The method comprises: using a cross-sectioning method to cut a fan blade, so as to obtain two-dimensional airfoil-section coordinate data of each position; performing airflow field calculation on each two-dimensional airfoil section, so as to obtain an external airflow velocity of each two-dimensional airfoil section; performing force analysis on water droplets, calculating impingement positions of the water droplets on each two-dimensional airfoil section, and then calculating a local water droplet impingement coefficient and a freeze fraction; on the basis of the local water droplet impingement coefficient, the freeze fraction and environmental parameters, acquiring the thickness of an ice accretion on each two-dimensional airfoil section and an ice accretion shape on each two-dimensional airfoil section; on the basis of the thicknesses of the ice accretions, updating the two-dimensional airfoil-section coordinate data; performing ice accretion calculation at the next time step until a preset condition is met; and performing lofting processing on each two-dimensional airfoil section, so as to obtain a three-dimensional ice accretion shape result of the fan blade. The increased thicknesses and shape of ice accretions of a fan blade under different working conditions are quickly obtained with a small amount of calculation.

Description

A method, apparatus, equipment, and storage medium for reconstructing three-dimensional icing on wind turbine blades.

[0001] This application claims priority to Chinese Patent Application No. 202411030527.9, filed on July 30, 2024, entitled "A Method, Apparatus, Device and Storage Medium for Three-Dimensional Icing Reconstruction of Wind Turbine Blades", the entire contents of which are incorporated herein by reference. Technical Field

[0002] This application relates to the field of wind power generation simulation technology, and in particular to a method, apparatus, equipment and storage medium for three-dimensional icing reconstruction of wind turbine blades. Background Technology

[0003] In recent years, wind power has become an important component of global renewable energy. Looking at development trends, wind power technology is constantly being improved and innovated, for example, by increasing turbine height, improving turbine efficiency, reducing costs, and providing reliable safety. Statistical analysis shows that icing is one of the major problems facing wind power generation, causing significant losses every year.

[0004] To study methods for preventing and controlling icing on wind turbine blades, extensive research has been conducted on the formation mechanism and influencing characteristics of icing on wind turbine blades. Icing on wind turbine blades mainly concentrates on the leading edge and is primarily formed by the collision and freezing of supercooled water droplets in the air. Li Zhiyu et al. from Chongqing University, in their numerical simulation of rime icing on 300kW large wind turbine blades, used the Lagrange method to calculate the water droplet collision coefficient on the blade surface. Liang Jian et al., based on FLUENT software, used the Euler method to solve for the water droplet collision coefficient on the wind turbine blade surface and verified the simulation results through artificial icing experiments. Their experimental results show that the icing range and morphology on the wind turbine blade surface vary significantly under different wind speeds, temperatures, and median water droplet diameters. FENSAP software is also frequently used for numerical simulations of icing growth on wind turbine blade surfaces and can map the distribution of water droplet collision coefficients. Jin et al. from the University of Tromsø, Norway, used FENSAP to simulate icing on wind turbine blade airfoils S826 and S832, and verified the results through wind tunnel tests. Their research indicated that under the same icing environment, the ice shape of the S832 wind turbine blade was more complex than that of the S826, and the difference in aerodynamic performance between the two airfoils was related to the icing thickness and type. Similarly, Galal M. Ibrahim et al. studied the proportion and similarity of icing on rotating wind turbine blades. They used FENSAP ICE software to perform numerical CFD icing simulations and tested the influence of wind turbine blade airfoil scaling methods on the icing results.

[0005] Icing development rate and icing quality are key parameters affecting the safe operation of wind turbines. However, the current application mainly uses CFD fluid dynamics simulation software to simulate the flow field analysis, water droplet collision and freezing involved in wind turbine icing. However, this process is relatively complex, and the large size of wind turbines and the large number of grids place certain demands on computer performance and computing time, which to some extent restricts the application of this technology in wind turbine engineering for icing prediction, early warning and prevention. Summary of the Invention

[0006] This application provides a method, apparatus, device, and storage medium for three-dimensional icing reconstruction of wind turbine blades, which enables the rapid acquisition of icing growth thickness and icing morphology of wind turbine blades under different operating conditions with relatively small computational load.

[0007] In view of this, the first aspect of this application provides a method for reconstructing three-dimensional icing on wind turbine blades, comprising:

[0008] S1. The wind turbine blades are sectioned using the cross-section cutting method to obtain the two-dimensional airfoil cross-section coordinate data at each position of the wind turbine blades;

[0009] S2. Based on the coordinate data of the two-dimensional airfoil section, the airflow field of each two-dimensional airfoil section of the wind turbine blade is calculated using the boundary element method to obtain the external airflow velocity of each two-dimensional airfoil section.

[0010] S3. Based on the external airflow velocity of each two-dimensional airfoil section, perform force analysis on the water droplet, calculate the collision position of the water droplet on the surface of each two-dimensional airfoil section, and calculate the local water droplet collision coefficient and freezing coefficient based on the collision position.

[0011] S4. Obtain the icing thickness and icing morphology of each two-dimensional airfoil section based on the local water droplet collision coefficient, the freezing coefficient, and environmental parameters.

[0012] S5. Update the coordinate data of the two-dimensional airfoil section according to the icing thickness of each two-dimensional airfoil section, and return to step S2 until the preset conditions are met, and then execute step S6.

[0013] S6. Lofting is performed on each two-dimensional airfoil section of the wind turbine blade to obtain the three-dimensional icing morphology of the wind turbine blade.

[0014] Optionally, the calculation process for the local water droplet collision coefficient includes:

[0015] The local droplet collision coefficient is obtained by calculating the ratio of the initial distance between adjacent water droplets to the relative distance between the collision positions of adjacent water droplets.

[0016] Optionally, the formula for calculating the freezing coefficient is:

[0017] In the formula, β3 is the freezing coefficient, ds is the relative distance between the collision points of adjacent water droplets; h c T is the convective heat transfer coefficient; w T and T represent the surface temperature of the fan blades and the ambient temperature, respectively; χ is the evaporation coefficient; e(T) w (T) represents temperature T w The saturated vapor pressure on the surface of the fan blades at temperature T; e(T) is the saturated vapor pressure on the surface of the fan blades at temperature T; β1 is the local water droplet collision coefficient; L f The latent heat of melting of ice; M c σ is the mass of the water droplet captured by the collision; ε is the emissivity; σ R is a constant; w is the liquid water content in the air; V is the wind speed; C w This is the specific heat of water.

[0018] Optionally, the formula for calculating the ice thickness is:

[0019] In the formula, h is the ice thickness, dt is the time step, and ρ i This represents the density of the ice layer.

[0020] Optionally, the step of updating the two-dimensional airfoil section coordinate data according to the icing thickness of each two-dimensional airfoil section further includes:

[0021] The moving average method was used to optimize the icing morphology.

[0022] The second aspect of this application provides a three-dimensional icing reconstruction device for wind turbine blades, comprising:

[0023] The sectioning unit is used to section the wind turbine blades using the cross-section sectioning method to obtain the two-dimensional airfoil section coordinate data at each position of the wind turbine blades;

[0024] The first calculation unit is used to calculate the airflow field of each two-dimensional airfoil section of the wind turbine blade based on the coordinate data of the two-dimensional airfoil section and to obtain the external airflow velocity of each two-dimensional airfoil section.

[0025] The second calculation unit is used to perform force analysis on the water droplets based on the external airflow velocity of each two-dimensional airfoil section, calculate the collision position of the water droplets on the surface of each two-dimensional airfoil section, and calculate the local water droplet collision coefficient and freezing coefficient based on the collision position.

[0026] The acquisition unit is used to acquire the icing thickness and icing morphology of each two-dimensional airfoil section based on the local water droplet collision coefficient, the freezing coefficient, and environmental parameters.

[0027] The update unit is used to update the coordinate data of the two-dimensional airfoil section according to the icing thickness of each two-dimensional airfoil section, and trigger the first calculation unit until the preset conditions are met, triggering the lofting processing unit.

[0028] The lofting processing unit is used to loft each two-dimensional airfoil section of the wind turbine blade to obtain the three-dimensional icing morphology of the wind turbine blade.

[0029] Optional, also includes:

[0030] The optimization unit is used to optimize the icing pattern using the moving average method.

[0031] Optionally, the formula for calculating the freezing coefficient is:

[0032] In the formula, β3 is the freezing coefficient, and d s h is the relative distance between the collision points of adjacent water droplets. c T is the convective heat transfer coefficient; w T and T represent the surface temperature of the fan blades and the ambient temperature, respectively; χ is the evaporation coefficient; e(T) w (T) represents temperature T w The saturated vapor pressure on the surface of the fan blades at temperature T; e(T) is the saturated vapor pressure on the surface of the fan blades at temperature T; β1 is the local water droplet collision coefficient; L f The latent heat of melting of ice; M c ε is the mass of the water droplet captured by the collision; ε is the emissivity; σ R is a constant; w is the liquid water content in the air; V is the wind speed; C w This is the specific heat of water.

[0033] A third aspect of this application provides an electronic device, the device including a processor and a memory;

[0034] The memory is used to store program code and transmit the program code to the processor;

[0035] The processor is used to execute any one of the three-dimensional icing reconstruction methods for wind turbine blades according to the instructions in the program code.

[0036] The fourth aspect of this application provides a computer-readable storage medium, characterized in that the computer-readable storage medium is used to store program code, which, when executed by a processor, implements the three-dimensional icing reconstruction method for wind turbine blades as described in any of the first aspects.

[0037] As can be seen from the above technical solutions, this application has the following advantages:

[0038] This application employs a cross-sectioning method to section the wind turbine blade, obtaining the coordinate data of the two-dimensional airfoil cross-sections at various locations on the blade. Then, the boundary element method is used to calculate the airflow field of each two-dimensional airfoil cross-section, obtaining the external airflow velocity for each cross-section. Based on the external airflow velocity of each cross-section, the forces acting on water droplets are analyzed, and the local water droplet collision coefficient and freezing coefficient are calculated. The icing thickness and icing morphology of each two-dimensional airfoil cross-section are obtained through local water droplet collision coefficient, freezing coefficient, and environmental parameters. Through iterative calculations, a lofting process is finally used to obtain the three-dimensional icing morphology of the wind turbine blade. This application uses the boundary element method without considering turbulence calculations to calculate the airflow field and water droplet motion field, simplifying the calculation of the water droplet collision coefficient within the allowable error range and reducing the three-dimensional flow field problem to multiple two-dimensional flow field calculation problems. This enables the rapid acquisition of the icing growth thickness and icing morphology of the wind turbine blade under different operating conditions with a relatively small computational load. Attached Figure Description

[0039] To more clearly illustrate the technical solutions in the embodiments of this application 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 some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0040] Figure 1 is a flowchart illustrating a three-dimensional icing reconstruction method for wind turbine blades provided in an embodiment of this application.

[0041] Figure 2 is a cross-sectional view of a wind turbine blade provided in an embodiment of this application;

[0042] Figure 3 is a schematic diagram of local collision coefficient calculation for a two-dimensional cross-section of a wind turbine blade provided in an embodiment of this application;

[0043] Figure 4 is a schematic diagram of the icing morphology of a two-dimensional cross-section of a wind turbine blade and the icing morphology of a three-dimensional cross-section provided in an embodiment of this application.

[0044] Figure 5 is a schematic diagram of a three-dimensional icing reconstruction device for wind turbine blades provided in an embodiment of this application. Detailed Implementation

[0045] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present application.

[0046] For ease of understanding, please refer to Figure 1. This application embodiment provides a method for reconstructing three-dimensional icing on wind turbine blades, including:

[0047] S1. The wind turbine blade is sectioned using the cross-section cutting method to obtain the two-dimensional airfoil cross-sectional coordinate data at each position of the wind turbine blade.

[0048] Referring to Figure 2, the wind turbine blades of the wind turbine can be sectioned using the cross-sectional cutting method to obtain the two-dimensional airfoil section coordinate data A at various positions of the wind turbine blades. i .

[0049] S2. Based on the coordinate data of the two-dimensional airfoil section, the boundary element method is used to calculate the airflow field of each two-dimensional airfoil section of the wind turbine blade to obtain the external airflow velocity of each two-dimensional airfoil section.

[0050] Based on two-dimensional airfoil section coordinate data A i The boundary element method is used to solve for the influence coefficients and disturbance potential data corresponding to the wind turbine blades. Based on the influence coefficients and disturbance potential data, and combined with the parameter relationship between the influence coefficients and disturbance potential data, the flow field disturbance potential data of each two-dimensional airfoil section of the wind turbine blades are calculated. Based on the parameter relationship between the flow field disturbance potential data and the airflow velocity, the airflow field is calculated for each two-dimensional airfoil section of the wind turbine blades to obtain the external airflow velocity u(u) of each two-dimensional airfoil section. x ,u y The potential function φ of the airflow field can be expressed as a uniform potential flow. and disturbance potential flow The sum of the airflow velocity u(u x ,u y Then it can be expressed as:

[0051] S3. Based on the external airflow velocity of each two-dimensional airfoil section, perform force analysis on the water droplet, calculate the collision position of the water droplet on the surface of each two-dimensional airfoil section, and calculate the local water droplet collision coefficient and freezing coefficient based on the collision position.

[0052] As shown in Figure 3, based on the initial water droplet and external airflow velocity, the force state of the water droplet is determined using the Lagrange algorithm. According to the force state, the water droplet's trajectory is tracked. When the water droplet collides with the surface of the wind turbine blade, the collision position and velocity are determined. Based on the collision velocity, the normal vector of the collision position, and the external airflow velocity, combined with the formula for calculating the local collision coefficient, the local collision coefficient of the water droplet at the collision position is obtained. Assuming the relative distance (initial gap) between two adjacent water droplets at infinity (unaffected by the airflow field) is ds0, and the relative distance at the collision position of these two adjacent water droplets on the wind turbine blade surface (i.e., the relative distance after the collision) is ds, the local water droplet collision coefficient β1 is obtained by calculating the ratio of the initial gap distance ds0 to the relative distance ds at the collision position.

[0053] If the mass of the water droplet captured by the collision is M c The frozen part is M f Then the expression for calculating the freezing coefficient β3 can be obtained as follows:

[0054] Further, based on the heat balance equation, we can obtain:

[0055] In the formula, h c The convective heat transfer coefficient is expressed in W / (m²). 2 ·℃); T w T and T represent the surface temperature of the fan blades and the ambient temperature, respectively, in K; χ is the evaporation coefficient, in J / (m²). 2 ·kPa); e(T w (T) represents temperature T w The saturated vapor pressure on the surface of the fan blades at temperature T is expressed in kPa; e(T) is the saturated vapor pressure on the surface of the fan blades at temperature T, expressed in kPa; L f ε is the latent heat of fusion of ice, expressed in J / kg; σ is the emissivity, preferably ε = 0.95; R is a constant; w is the liquid water content in the air, in kg / m³. 3 V represents wind speed, in m / s; C w Specific heat of water, expressed in J / (kg·℃);

[0056] Wherein, the mass of the captured water droplets is M c The calculation formula is: M c =β1wVS j dt

[0057] In the formula, dt is the time step, in seconds; S jThe unit line segment is the length of the two-dimensional cross-section of the wind turbine blade, which is divided into segments, in meters.

[0058] S4. Obtain the icing thickness and icing morphology of each two-dimensional airfoil section based on the local water droplet collision coefficient, freezing coefficient, and environmental parameters.

[0059] The icing thickness h of the two-dimensional cross-section is calculated based on environmental parameters such as wind speed V, ambient temperature T, and liquid water content w in the air, as well as the local water droplet collision coefficient β1, freezing coefficient β3, time step dt, and the relative distance ds between adjacent water droplet collision positions.

[0060] In the formula, ρ i This refers to the density of the ice layer, expressed in kg / m³. 3 After obtaining the icing thickness h of each two-dimensional airfoil section, the icing morphology of each two-dimensional airfoil section is drawn based on the icing thickness h.

[0061] S5. Update the coordinate data of the two-dimensional airfoil section according to the icing thickness of each two-dimensional airfoil section, and return to step S2 until the preset conditions are met, and then execute step S6.

[0062] Furthermore, before updating the coordinate data of the two-dimensional airfoil sections based on the icing thickness of each section, a moving average method can be used to optimize the icing morphology, ensuring the smoothness of the icing surface and providing conditions for icing calculations in the next time step. The icing coordinates replace the coordinates of the portion of the original (iced) wind turbine blade's two-dimensional airfoil section obscured by icing, forming new two-dimensional airfoil section coordinate data A. i+1 Using the new two-dimensional airfoil section coordinate data A i+1 For input, repeat steps S2 to S5 to calculate the icing thickness and icing morphology of each two-dimensional airfoil section of the wind turbine blade in the next time step t+dt, until the set maximum icing time is reached, and then execute step S6.

[0063] S6. Lofting is performed on each two-dimensional airfoil section of the wind turbine blade to obtain the three-dimensional icing morphology of the wind turbine blade.

[0064] As shown in Figure 4, the two-dimensional airfoil sections of the wind turbine blade are lofted to form a three-dimensional solid, thus obtaining the three-dimensional icing range, three-dimensional icing morphology, and icing quality of the wind turbine blade within the current time range.

[0065] This application employs a cross-sectional cutting method to section the wind turbine blade, obtaining the coordinate data of the two-dimensional airfoil cross-section at various locations of the blade. Then, the boundary element method is used to calculate the airflow field of each two-dimensional airfoil cross-section, obtaining the external airflow velocity for each cross-section. Based on the external airflow velocity, the force analysis of water droplets is performed, calculating the local water droplet collision coefficient and freezing coefficient. The icing thickness and icing morphology of each two-dimensional airfoil cross-section are obtained through the local water droplet collision coefficient, freezing coefficient, and environmental parameters. Through iterative calculations, a lofting process is finally used to obtain the three-dimensional icing morphology of the wind turbine blade. This application uses the boundary element method without considering turbulence calculations to calculate the airflow field and water droplet motion field, simplifying the calculation of the water droplet collision coefficient within the allowable error range and reducing the three-dimensional flow field problem to multiple two-dimensional flow field calculation problems. This enables the rapid acquisition of the icing growth thickness and icing morphology of the wind turbine blade under different operating conditions such as different wind speeds and different water droplet sizes with a relatively small computational load.

[0066] The above is an embodiment of a three-dimensional icing reconstruction method for wind turbine blades provided in this application. The following is an embodiment of a three-dimensional icing reconstruction device for wind turbine blades provided in this application.

[0067] Please refer to Figure 5. An embodiment of this application provides a three-dimensional icing reconstruction device for wind turbine blades, comprising:

[0068] The sectioning unit is used to section the wind turbine blades using the cross-section sectioning method to obtain the two-dimensional airfoil section coordinate data at each position of the wind turbine blades;

[0069] The first calculation unit is used to calculate the airflow field of each two-dimensional airfoil section of the wind turbine blade based on the coordinate data of the two-dimensional airfoil section and the boundary element method, so as to obtain the external airflow velocity of each two-dimensional airfoil section.

[0070] The second calculation unit is used to perform force analysis on water droplets based on the external airflow velocity of each two-dimensional airfoil section, calculate the collision position of water droplets on the surface of each two-dimensional airfoil section, and calculate the local water droplet collision coefficient and freezing coefficient based on the collision position.

[0071] The acquisition unit is used to obtain the icing thickness and icing morphology of each two-dimensional airfoil section based on the local water droplet collision coefficient, freezing coefficient and environmental parameters;

[0072] The update unit is used to update the coordinate data of the two-dimensional airfoil section according to the icing thickness of each two-dimensional airfoil section, and trigger the first calculation unit until the preset conditions are met, triggering the lofting processing unit.

[0073] The lofting unit is used to loft each two-dimensional airfoil section of the wind turbine blade to obtain the three-dimensional icing morphology of the wind turbine blade.

[0074] As a further improvement, the device also includes:

[0075] The optimization unit is used to optimize the icing pattern using the moving average method.

[0076] As a further improvement, the formula for calculating the freezing coefficient is:

[0077] In the formula, β3 is the freezing coefficient, and d s h is the relative distance between the collision points of adjacent water droplets. c T is the convective heat transfer coefficient; w T and T represent the surface temperature of the fan blades and the ambient temperature, respectively; χ is the evaporation coefficient; e(T) w (T) represents temperature T w The saturated vapor pressure on the surface of the fan blades at temperature T; e(T) is the saturated vapor pressure on the surface of the fan blades at temperature T; β1 is the local water droplet collision coefficient; L f The latent heat of melting of ice; M c σ is the mass of the water droplet captured by the collision; ε is the emissivity; σ R is a constant; w is the liquid water content in the air; V is the wind speed; C w This is the specific heat of water.

[0078] This application employs a cross-sectioning method to section the wind turbine blade, obtaining the coordinate data of the two-dimensional airfoil cross-sections at various locations on the blade. Then, the boundary element method is used to calculate the airflow field of each two-dimensional airfoil cross-section, obtaining the external airflow velocity for each cross-section. Based on the external airflow velocity of each cross-section, the forces acting on water droplets are analyzed, and the local water droplet collision coefficient and freezing coefficient are calculated. The icing thickness and icing morphology of each two-dimensional airfoil cross-section are obtained through local water droplet collision coefficient, freezing coefficient, and environmental parameters. Through iterative calculations, a lofting process is finally used to obtain the three-dimensional icing morphology of the wind turbine blade. This application uses the boundary element method without considering turbulence calculations to calculate the airflow field and water droplet motion field, simplifying the calculation of the water droplet collision coefficient within the allowable error range and reducing the three-dimensional flow field problem to multiple two-dimensional flow field calculation problems. This enables the rapid acquisition of the icing growth thickness and icing morphology of the wind turbine blade under different operating conditions with a relatively small computational load.

[0079] This application also provides an electronic device, which includes a processor and a memory;

[0080] The memory is used to store program code and transfer the program code to the processor;

[0081] The processor is used to execute the three-dimensional icing reconstruction method for wind turbine blades in the aforementioned method embodiment according to the instructions in the program code.

[0082] This application also provides a computer-readable storage medium for storing program code, which, when executed by a processor, implements the three-dimensional icing reconstruction method for wind turbine blades in the aforementioned method embodiments.

[0083] Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the specific working process of the above-described apparatus and unit can be referred to the corresponding process in the foregoing method embodiments, and will not be repeated here.

[0084] The terms “first,” “second,” “third,” “fourth,” etc. (if present) in the specification and accompanying drawings of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. Furthermore, the terms “comprising” and “having,” and any variations thereof, are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such process, method, product, or apparatus.

[0085] It should be understood that in this application, "at least one (item)" means one or more, and "more than" means two or more. "And / or" is used to describe the relationship between related objects, indicating that three relationships can exist. For example, "A and / or B" can represent three cases: only A exists, only B exists, and both A and B exist simultaneously, where A and B can be singular or plural. The character " / " generally indicates that the preceding and following related objects are in an "or" relationship. "At least one (item) of the following" or similar expressions refer to any combination of these items, including any combination of single or plural items. For example, at least one (item) of a, b, or c can represent: a, b, c, "a and b", "a and c", "b and c", or "a and b and c", where a, b, and c can be single or multiple.

[0086] In the several embodiments provided in this application, it should be understood that the disclosed apparatus and methods can be implemented in other ways. For example, the apparatus embodiments described above are merely illustrative; for instance, the division of units is only a logical functional division, and in actual implementation, there may be other division methods. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the coupling or direct coupling or communication connection shown or discussed may be through some interfaces; the indirect coupling or communication connection between apparatuses or units may be electrical, mechanical, or other forms.

[0087] The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the units can be selected to achieve the purpose of this embodiment according to actual needs.

[0088] Furthermore, the functional units in the various embodiments of this application can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated unit can be implemented in hardware or as a software functional unit.

[0089] If the integrated unit is implemented as a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or all or part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions for executing all or part of the steps of the methods described in the various embodiments of this application through a computer device (which may be a personal computer, server, or network device, etc.). The aforementioned storage medium includes: USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, optical disks, and other media capable of storing program code.

[0090] The above-described embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this application.

Claims

1. A method for reconstructing three-dimensional icing on wind turbine blades, characterized in that, include: S1. The wind turbine blades are sectioned using the cross-section cutting method to obtain the two-dimensional airfoil cross-section coordinate data at each position of the wind turbine blades; S2. Based on the coordinate data of the two-dimensional airfoil section, the airflow field of each two-dimensional airfoil section of the wind turbine blade is calculated using the boundary element method to obtain the external airflow velocity of each two-dimensional airfoil section. S3. Based on the external airflow velocity of each two-dimensional airfoil section, perform force analysis on the water droplet, calculate the collision position of the water droplet on the surface of each two-dimensional airfoil section, and calculate the local water droplet collision coefficient and freezing coefficient based on the collision position. S4. Obtain the icing thickness and icing morphology of each two-dimensional airfoil section based on the local water droplet collision coefficient, the freezing coefficient, and environmental parameters. S5. Update the coordinate data of the two-dimensional airfoil section according to the icing thickness of each two-dimensional airfoil section, and return to step S2 until the preset conditions are met, and then execute step S6. S6. Lofting is performed on each two-dimensional airfoil section of the wind turbine blade to obtain the three-dimensional icing morphology of the wind turbine blade.

2. The method for reconstructing three-dimensional icing on wind turbine blades according to claim 1, characterized in that, The calculation process for the local water droplet collision coefficient includes: The local droplet collision coefficient is obtained by calculating the ratio of the initial distance between adjacent water droplets to the relative distance between the collision positions of adjacent water droplets.

3. The method for reconstructing three-dimensional icing on wind turbine blades according to claim 1, characterized in that, The formula for calculating the freezing coefficient is: In the formula, β3 is the freezing coefficient, ds is the relative distance between the collision points of adjacent water droplets; h c T is the convective heat transfer coefficient; w T and T represent the surface temperature of the fan blades and the ambient temperature, respectively; χ is the evaporation coefficient; e(T) w (T) represents temperature T w The saturated vapor pressure on the surface of the fan blades at temperature T; e(T) is the saturated vapor pressure on the surface of the fan blades at temperature T; β1 is the local water droplet collision coefficient; L f The latent heat of melting of ice; M c σ is the mass of the water droplet captured by the collision; ε is the emissivity; σ R is a constant; w is the liquid water content in the air; V is the wind speed; C w This is the specific heat of water.

4. The method for reconstructing three-dimensional icing on wind turbine blades according to claim 1, characterized in that, The formula for calculating the ice thickness is: In the formula, h is the ice thickness, dt is the time step, and ρ i This represents the density of the ice layer.

5. The method for reconstructing three-dimensional icing on wind turbine blades according to claim 1, characterized in that, The step of updating the two-dimensional airfoil section coordinate data based on the icing thickness of each two-dimensional airfoil section includes, prior to: The moving average method was used to optimize the icing morphology.

6. A three-dimensional icing reconstruction device for wind turbine blades, characterized in that, include: The sectioning unit is used to section the wind turbine blades using the cross-section sectioning method to obtain the two-dimensional airfoil section coordinate data at each position of the wind turbine blades; The first calculation unit is used to calculate the airflow field of each two-dimensional airfoil section of the wind turbine blade based on the coordinate data of the two-dimensional airfoil section and to obtain the external airflow velocity of each two-dimensional airfoil section. The second calculation unit is used to perform force analysis on the water droplets based on the external airflow velocity of each two-dimensional airfoil section, calculate the collision position of the water droplets on the surface of each two-dimensional airfoil section, and calculate the local water droplet collision coefficient and freezing coefficient based on the collision position. The acquisition unit is used to acquire the icing thickness and icing morphology of each two-dimensional airfoil section based on the local water droplet collision coefficient, the freezing coefficient, and environmental parameters. The update unit is used to update the coordinate data of the two-dimensional airfoil section according to the icing thickness of each two-dimensional airfoil section, and trigger the first calculation unit until the preset conditions are met, triggering the lofting processing unit. The lofting processing unit is used to loft each two-dimensional airfoil section of the wind turbine blade to obtain the three-dimensional icing morphology of the wind turbine blade.

7. The three-dimensional icing reconstruction device for wind turbine blades according to claim 6, characterized in that, Also includes: The optimization unit is used to optimize the icing pattern using the moving average method.

8. The three-dimensional icing reconstruction device for wind turbine blades according to claim 6, characterized in that, The formula for calculating the freezing coefficient is: In the formula, β3 is the freezing coefficient, and d s h represents the relative distance between the collision points of adjacent water droplets. c T is the convective heat transfer coefficient; w T and T represent the surface temperature of the fan blades and the ambient temperature, respectively; χ is the evaporation coefficient; e(T) w (T) represents temperature T w The saturated vapor pressure on the surface of the fan blades at temperature T; e(T) is the saturated vapor pressure on the surface of the fan blades at temperature T; β1 is the local water droplet collision coefficient; L f The latent heat of melting of ice; M c σ is the mass of the water droplet captured by the collision; ε is the emissivity; σ R is a constant; w is the liquid water content in the air; V is the wind speed; C w This is the specific heat of water.

9. An electronic device, characterized in that, The device includes a processor and a memory; The memory is used to store program code and transmit the program code to the processor; The processor is used to execute the three-dimensional icing reconstruction method for wind turbine blades according to any one of the claims 1-5, based on the instructions in the program code.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium is used to store program code, which, when executed by a processor, implements the three-dimensional icing reconstruction method for wind turbine blades according to any one of claims 1-5.

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