Fan blade icing simulation method, device and equipment and storage medium

Abstract

The invention discloses a fan blade icing simulation method, device and equipment and a storage medium, and relates to the field of wind power generation, and the method comprises the steps: obtaining a full-size model of a target fan, and determining each target section corresponding to the target fan based on the full-size model; determining icing test parameters corresponding to each target section section by using a target scaling icing similarity method, and performing an icing simulation test on each target section section in the target wind tunnel based on the icing test parameters corresponding to each target section section so as to determine a section ice type corresponding to each target section section; and performing size reduction on the section ice shape of each target section section based on the full-size model so as to determine a target section ice shape corresponding to each section ice shape, and performing lofting connection on all the target section ice shapes so as to determine full-blade ice shape distribution of the target fan. According to the invention, icing simulation tests can be carried out on fans of various sizes in the phytotron.

Description

Technical Field

[0001] The present invention relates to the field of wind power generation, and in particular to a method, device, equipment and storage medium for simulating ice coating on wind turbine blades. Background Art

[0002] Icing not only affects power generation efficiency but also causes serious damage to wind turbine equipment and even safety incidents. Icing increases the weight of wind turbine blades, leading to increased mechanical loads on the blades and tower, potentially causing equipment damage. Furthermore, the ice shedding phenomenon caused by icing poses a threat to the surrounding environment and personnel. Icing poses a significant threat to the economic benefits and safety of wind farms, becoming a major constraint on the development of the wind power industry and a research hotspot in recent years. Scientific research on wind turbine blade icing primarily utilizes three methods: numerical simulation, field icing observations, and artificial climate chamber (ice wind tunnel) testing. Artificial climate chamber testing, by simulating icing conditions in the laboratory, allows for precise control of parameters such as temperature, humidity, and wind speed, enabling reproducible and systematic research. It is a key tool in current icing research. Artificial climate chamber testing not only validates numerical simulation results but also provides theoretical support for field observations, thus offering irreplaceable advantages in wind turbine icing research. However, with the continuous growth of wind turbine capacity and blade length, the limited space in artificial climate chambers has long been unable to accommodate full-size wind turbine blades. To conduct icing tests in an artificial climate chamber, blades must be scaled down. However, scaling tests are not simply geometric reductions; to ensure consistent icing characteristics before and after scaling, icing similarity criteria must be adhered to. Currently, research on icing similarity criteria has primarily focused on aircraft icing. Two challenges remain for wind turbine icing. One is that while relatively systematic similarity criteria have been established for aircraft icing, they only apply to linear motion blades, not rotary fans. Another issue is that existing similarity studies have been limited to scales of 1 to 1 / 6, which is insufficient for very large fans.

[0003] In summary, how to conduct icing simulation tests on wind turbines of various sizes in an artificial climate chamber is an urgent problem to be solved. Summary of the Invention

[0004] In view of this, the present invention aims to provide a method, device, equipment, and storage medium for simulating wind turbine blade icing, which can be used to simulate icing on wind turbines of various sizes in an artificial climate chamber. The specific scheme is as follows:

[0005] In a first aspect, the present application discloses a method for simulating icing on wind turbine blades, comprising:

[0006] Acquire a full-scale model of a target wind turbine, and determine target cross-sectional segments corresponding to the target wind turbine based on the full-scale model;

[0007] determining icing test parameters corresponding to each target cross-sectional segment using a target scaled icing similarity method, and conducting an icing simulation test on each target cross-sectional segment in a target wind tunnel based on the icing test parameters corresponding to each target cross-sectional segment to determine a cross-sectional ice type corresponding to each target cross-sectional segment;

[0008] The cross-sectional ice types of each target cross-sectional segment are restored to size based on the full-scale model to determine the target cross-sectional ice types corresponding to each cross-sectional ice type, and all the target cross-sectional ice types are connected and laid out to determine the full-blade ice type distribution of the target wind turbine.

[0009] Optionally, determining target cross-sectional segments corresponding to the target wind turbine based on the full-scale model includes:

[0010] Determining each section to be simulated corresponding to the target wind turbine based on the full-scale model;

[0011] Based on the wind tunnel size of the target wind tunnel, each of the sections to be simulated is reduced to obtain a corresponding reduced section, and based on the rotation radius of the target wind turbine, each of the reduced sections is stretched to determine each target section segment corresponding to the target wind turbine.

[0012] Optionally, the icing test parameters include incoming flow velocity, rotation speed, droplet diameter, liquid water content, test temperature and icing time.

[0013] Optionally, the determining of icing test parameters corresponding to each target cross-sectional segment by using a target scaled icing similarity method, and conducting an icing simulation test on each target cross-sectional segment in a target wind tunnel based on the icing test parameters corresponding to each target cross-sectional segment to determine the cross-sectional ice type corresponding to each target cross-sectional segment, includes:

[0014] The first scaled icing similarity method is used to determine the rime icing test parameters corresponding to each target cross-sectional segment. Based on the rime icing test parameters corresponding to each target cross-sectional segment, a rime icing simulation test is conducted on each target cross-sectional segment in a first target wind tunnel to determine the first cross-sectional ice type corresponding to each target cross-sectional segment.

[0015] Optionally, the determining of the rime icing test parameters corresponding to each target cross-sectional segment using the first scaled icing similarity method includes:

[0016] determining a test pressure, a test flow velocity, a test temperature, and a test liquid water content based on the full-scale model;

[0017] Matching the flow direction factors before and after the reduction based on the test flow velocity and the rotation radius reduction to determine the test rotation angular velocity;

[0018] Determine the droplet median diameter based on the cross-sectional chord length reduction ratio and the modified inertial parameter;

[0019] The rime icing time is determined based on the cross-sectional chord length reduction ratio and the test liquid water content.

[0020] Optionally, the determining of icing test parameters corresponding to each target cross-sectional segment by using a target scaled icing similarity method, and conducting an icing simulation test on each target cross-sectional segment in a target wind tunnel based on the icing test parameters corresponding to each target cross-sectional segment to determine the cross-sectional ice type corresponding to each target cross-sectional segment, includes:

[0021] The second scaled icing similarity method is used to determine the rain and rime icing test parameters corresponding to each target cross-sectional segment. Based on the rain and rime icing test parameters corresponding to each target cross-sectional segment, a rain and rime icing simulation test is conducted on each target cross-sectional segment in a second target wind tunnel to determine the second cross-sectional ice type corresponding to each target cross-sectional segment.

[0022] Optionally, the determining of the rime icing test parameters corresponding to each target cross-sectional segment using the second scaled icing similarity method includes:

[0023] determining a test pressure based on the full-scale model;

[0024] Determine the test incoming flow velocity and test rotation angular velocity based on the rotation radius reduction ratio, incoming flow velocity direction factor and resultant velocity;

[0025] Determine the test temperature based on the cross-sectional chord length reduction ratio, freezing rate, and relative thermal factor;

[0026] Determining the diameter of the test supercooled water droplet based on the cross-sectional chord length reduction ratio and the modified inertia parameter;

[0027] determining a test liquid water content based on the cross-sectional chord length reduction ratio and the relative thermal factor;

[0028] The rime icing time is determined based on the cross-sectional chord length reduction ratio, the test liquid water content, and the aggregation factor.

[0029] In a second aspect, the present application discloses a wind turbine blade icing simulation device, comprising:

[0030] a cross-sectional segment determination module, configured to obtain a full-scale model of a target wind turbine and determine target cross-sectional segments corresponding to the target wind turbine based on the full-scale model;

[0031] a cross-sectional ice type determination module, configured to determine icing test parameters corresponding to each target cross-sectional segment using a target scaled icing similarity method, and perform an icing simulation test on each target cross-sectional segment in a target wind tunnel based on the icing test parameters corresponding to each target cross-sectional segment to determine the cross-sectional ice type corresponding to each target cross-sectional segment;

[0032] An ice type distribution determination module is used to restore the cross-sectional ice type of each target cross-sectional segment based on the full-scale model to determine the target cross-sectional ice type corresponding to each cross-sectional ice type, and to loft and connect all the target cross-sectional ice types to determine the full-blade ice type distribution of the target wind turbine.

[0033] In a third aspect, the present application discloses an electronic device, comprising:

[0034] Memory, used to store computer programs;

[0035] The processor is configured to execute the computer program to implement the aforementioned wind turbine blade icing simulation method.

[0036] In a fourth aspect, the present application discloses a computer-readable storage medium for storing a computer program, wherein the computer program implements the aforementioned wind turbine blade icing simulation method when executed by a processor.

[0037] In this application, when simulating icing on a wind turbine blade, a full-scale model of a target wind turbine is obtained, and target cross-sectional segments corresponding to the target wind turbine are determined based on the full-scale model. Icing test parameters corresponding to each target cross-sectional segment are determined using a target-scale icing similarity method. Based on the icing test parameters corresponding to each target cross-sectional segment, icing simulation tests are conducted on each target cross-sectional segment in a target wind tunnel to determine the corresponding cross-sectional ice shape. The cross-sectional ice shape of each target cross-sectional segment is resized based on the full-scale model to determine the target cross-sectional ice shape corresponding to each cross-sectional ice shape. All target cross-sectional ice shapes are then connected and laid out to determine the ice shape distribution across the entire blade of the target wind turbine. Thus, this application selects the cross-sectional area to be studied from the full-scale model, appropriately reduces the airfoil at that cross-sectional area (specifically, the airfoil at that cross-sectional area can be accommodated in the target wind tunnel used for the icing test), and then stretches it into segments to obtain the corresponding target cross-sectional segments. These cross-sectional segments are sufficiently long to fully reflect the spanwise motion of the water film on the airfoil surface during rotation during the rotation test. Then, the target scaled icing similarity method is used to determine the icing test parameters corresponding to each target cross-sectional segment, that is, the relevant parameters of the icing test process, so that the icing test is carried out on each target cross-sectional segment in the target wind tunnel based on the icing test parameters corresponding to each target cross-sectional segment to determine the cross-sectional ice type corresponding to each target cross-sectional segment. Finally, all cross-sectional ice types are restored to size based on the full-scale model of the target wind turbine to obtain the target cross-sectional ice type, so that all target cross-sectional ice types are laid out and connected to obtain the ice type distribution of the rotating icing test of the entire blade of the target wind turbine. The present application only scales the cross-sectional chord length and avoids the problem of blade length. The object of scaling is changed from the entire blade to the airfoil section at a certain point of the blade, so that while reducing the rotation radius, there is no need to excessively reduce the airfoil section, and at the same time solves the limitations of the test site size and the accuracy of the scaled test. Moreover, the ice distribution of the entire large blade can be accurately obtained by modeling and restoring the results of multiple small-section icing tests. Compared with the general two-dimensional cross-sectional airfoil test, the device can also simulate the flow of surface water film under rotation. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are merely embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying any creative work.

[0039] Figure 1 This is a flow chart of a wind turbine blade icing simulation method disclosed in this application;

[0040] Figure 2This is a flow chart of a specific method for simulating icing on wind turbine blades disclosed in this application;

[0041] Figure 3 This is a schematic diagram of an ice cladding simulation test using a cross-section reduction rotation method disclosed in this application;

[0042] Figure 4 This is a schematic diagram of a simulation result of wind turbine blade icing under rime conditions disclosed in this application;

[0043] Figure 5 This is a schematic diagram of a simulation result of wind turbine blade icing under rime conditions disclosed in this application;

[0044] Figure 6 This is a schematic structural diagram of a wind turbine blade icing simulation device disclosed in this application;

[0045] Figure 7 This is a structural diagram of an electronic device disclosed in this application. DETAILED DESCRIPTION

[0046] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0047] Currently, research on icing similarity criteria has primarily focused on aircraft icing. Two challenges remain for wind turbine icing: While a relatively systematic similarity criterion has been established for aircraft icing, it only applies to linear airfoils and not to rotary wind turbines. Another challenge is that existing similarity studies are limited to scales of 1 to 1 / 6, which is insufficient for very large wind turbines. To address these technical issues, this application discloses a wind turbine blade icing simulation method capable of conducting icing simulation tests on wind turbines of various sizes in an artificial climate chamber.

[0048] See also Figure 1 As shown, an embodiment of the present invention discloses a method for simulating ice coating on wind turbine blades, comprising:

[0049] Step S11 : obtaining a full-scale model of a target wind turbine, and determining target cross-sectional segments corresponding to the target wind turbine based on the full-scale model.

[0050] In this embodiment, the wind turbine blades need to capture as much wind energy as possible while taking into account the overall structural strength. Therefore, a large blade length is usually required to increase the swept area, and the transverse section of the blade adopts a lift airfoil with a smaller chord length to meet the aerodynamic performance and lightweight requirements of the blade. If only a certain section of the airfoil is intercepted for testing, the required scaling factor is determined by the chord length and can be controlled within 10 times. Based on the above ideas, this embodiment uses the cross-sectional scaling rotation method to conduct an icing simulation test on the target wind turbine. The cross-sectional scaling rotation method only scales the cross-sectional chord length and avoids the problem of blade length. The object of scaling is changed from the entire blade to the airfoil section at a certain point on the blade, so that while reducing the rotation radius, there is no need to excessively reduce the airfoil section, and at the same time solves the limitations of the test site size and the accuracy of the scaling test.

[0051] In one specific embodiment, a full-scale model of the target wind turbine is first obtained, and then target cross-sectional segments corresponding to the target wind turbine are determined based on the full-scale model. Specifically, the target wind turbine's corresponding cross-sectional areas to be simulated are first determined based on the full-scale model; each cross-sectional area to be simulated is then reduced based on the wind tunnel dimensions of the target wind tunnel to obtain a corresponding reduced cross-sectional area; and finally, each reduced cross-sectional area is stretched based on the rotation radius of the target wind turbine to determine the target cross-sectional segments corresponding to the target wind turbine. In other words, this embodiment selects the cross-sectional area to be studied from the full-scale model, appropriately reduces the airfoil at that cross-sectional area (to the extent that it can fit within the target wind tunnel used for icing tests), and then stretches it into segments. The segment length should be greater than 1 / 4 of the rotation radius, and the cross-sectional segments should be sufficiently long to fully reflect the spanwise motion of the water film on the surface of the airfoil during the rotational motion during the rotational test.

[0052] Step S12: Determine icing test parameters corresponding to each target cross-sectional segment using a target scaled icing similarity method; and conduct an icing simulation test on each target cross-sectional segment in a target wind tunnel based on the icing test parameters corresponding to each target cross-sectional segment to determine the cross-sectional ice type corresponding to each target cross-sectional segment.

[0053] In this embodiment, blades in different regions of the target wind turbine have varying degrees of impact on the aerodynamic characteristics of the target wind turbine. Therefore, intensive sampling is required to identify more target cross-sectional segments in areas with a greater impact on aerodynamic characteristics, such as the blade tip. Fewer cross-sectional sampling is then required in areas with a lesser impact on aerodynamic characteristics, such as the blade root. After determining the target cross-sectional segments of the target wind turbine, the icing test parameters corresponding to each target cross-sectional segment can be determined using the target scaled icing similarity method. Icing test parameters include incoming flow velocity, rotational speed, droplet diameter, liquid water content, test temperature, and icing time. Two scales are used to determine the icing test parameters. The first scale is the cross-sectional chord length scale, which is used to calculate parameters such as droplet diameter, liquid water content, and icing time to ensure that the cross-sectional icing pattern and icing intensity are similar to those of the full-scale model. The second scale is the rotation radius scale, which is used to scale the rotating flow field and droplet motion to ensure that the two-phase flow field at the leading edge of the scaled blade section is identical to that of the full-scale model. It is understandable that wind turbines will face rime and sleet environments during actual operation. Therefore, it is necessary to carry out rime icing simulation tests and sleet icing simulation tests in the target wind tunnel respectively according to the characteristics of the rime and sleet environments.

[0054] In this embodiment, a first-scale icing similarity method is used to determine rime icing test parameters corresponding to each target cross-sectional segment. Based on the rime icing test parameters corresponding to each target cross-sectional segment, a rime icing simulation test is conducted on each target cross-sectional segment in a first target wind tunnel to determine the first cross-sectional ice type corresponding to each target cross-sectional segment. Specifically, determining the rime icing test parameters corresponding to each target cross-sectional segment using the first-scale icing similarity method may include: determining the test pressure, test incoming flow velocity, test temperature, and test liquid water content based on the full-scale model; matching the incoming flow direction factors before and after scaling based on the test incoming flow velocity and the rotation radius scaling to determine the test rotation angular velocity; determining the droplet median diameter based on the cross-sectional chord length scaling and the corrected inertia parameter; and determining the rime icing time based on the cross-sectional chord length scaling and the test liquid water content.

[0055] In other words, the scaled-down test parameters under rime conditions can be determined by the following steps:

[0056] 1) Select the test pressure , test flow velocity , test temperature and test liquid water content In the case of rime, 、 、 as well as All should be consistent with the full-size model.

[0057] 2) Calculate the test rotation angular velocity After the test flow velocity is selected, the rotating radius is scaled As the calculation scaling, by matching the flow direction factor before and after the scaling, the test rotating angular velocity can be obtained , and the calculation formula is as shown in the following formula:

[0058] ;

[0059] Wherein the subscript m represents the scaled parameter, and f represents the full-size parameter.

[0060] 3) Calculate the test droplet diameter. The corrected inertia parameter before and after the scaling is equal Method is used to select the median diameter of the droplet , wherein the scaling of the chord length of the section , is the rotating radius:

[0061] ;

[0062] For the icing condition of the fan, 0.39 is more appropriate, then:

[0063] .

[0064] 4) Calculate the test icing time. After the liquid water content αm of the scaling test is determined, the aggregation factor is limited, and The scaled icing time is obtained, wherein the scaling of the chord length of the section :

[0065] .

[0066] In this embodiment, the second scaling icing similarity method is used to determine the test parameters of the glaze icing corresponding to each target section, and the glaze icing simulation test of each target section is carried out in the second target wind tunnel based on the test parameters of the glaze icing corresponding to each target section, so as to determine the second section ice type corresponding to each target section. The second scaling icing similarity method is used to determine the test parameters of the glaze icing corresponding to each target section, including: determining the test pressure based on the full-size model; determining the test flow velocity and the test rotating angular velocity based on the rotating radius scaling, the flow velocity direction factor and the resultant velocity; determining the test temperature based on the chord length scaling of the section, the freezing rate and the relative thermal factor; determining the test supercooled water droplet diameter based on the chord length scaling of the section and the corrected inertia parameter; determining the test liquid water content based on the chord length scaling of the section and the relative thermal factor; and determining the glaze icing time based on the chord length scaling of the section, the test liquid water content and the aggregation factor.

[0067] In other words, the process for determining the test parameters for rime conditions is as follows:

[0068] 1) Select the test pressure ; Test pressure This is an optional setting and is usually kept consistent with the full-scale model at 1 atmosphere.

[0069] 2) Calculate the test flow velocity and test rotation speed ; By matching the incoming flow velocity direction factor Equal and combined speed If they are equal, we can solve the scaled angular velocity of rotation and incoming flow velocity , where the reduction ratio is the rotation radius reduction ratio :

[0070] .

[0071] 3) Calculate the test temperature ; By ensuring the freeze rate before and after scaling Equal to select the scaled test temperature , and ensure the relative thermal factor before and after scaling If they are equal, the scaled test temperature can be obtained The calculation formula is as follows, where the reduction ratio is the cross-section chord length reduction ratio .

[0072] .

[0073] 4) Calculate the diameter of the supercooled water droplet The calculation method is the same as that under rime conditions, using the inertia parameters corrected before and after scaling Matching method pairs Calculation is performed and the reduction ratio is the cross-section chord length reduction ratio. :

[0074] .

[0075] 5) Calculate the test liquid water content ; By ensuring the relative thermal factors before and after scaling Equal, we can get The calculation formula is: the reduction ratio is the cross-section chord length reduction ratio .

[0076] .

[0077] 6) Calculate the ice cover time after scaling; calculate the liquid water content of the scaling test After that, the scaled test icing time can be obtained by making the aggregation factor equal before and after scaling. The reduction ratio is still the cross-section chord length reduction ratio. .

[0078] .

[0079] In this embodiment, Figure 2 As shown in , after determining the icing parameters corresponding to each target cross-section, an icing simulation test can be conducted on each target cross-section in a target wind tunnel based on the icing test parameters corresponding to each target cross-section to determine the cross-sectional ice type corresponding to each target cross-section. Figure 3 The diagram below shows a schematic diagram of a cross-section rotation method icing simulation test. During the icing simulation test, a rotating device consisting of a rotating motor, three identical test airfoil stretch sections (also known as the target cross-section), and a support device is used to simulate icing on the target cross-section in a target wind tunnel. The rotating device comprises three rotating airfoil stretch sections. This design facilitates rotational balance, minimizing the impact of main body vibration on the test ice pattern. Furthermore, the ice patterns of the three sets of airfoil stretch sections can be compared to eliminate confounding factors, ensuring more accurate test results. After the test, to ensure that the ice pattern is not affected by spanwise turbulence, only the ice pattern of the center section of the test section is captured and compared with the ice patterns of the middle sections of the three airfoil stretch sections. If the ice patterns differ significantly, the test fails and requires retesting. If the cross-sectional ice patterns are substantially similar, the cross-sectional ice pattern corresponding to the target cross-section is considered to have been obtained.

[0080] Step S13: based on the full-scale model, the cross-sectional ice shape of each target cross-sectional segment is restored to size to determine the target cross-sectional ice shape corresponding to each cross-sectional ice shape, and all the target cross-sectional ice shapes are connected to determine the full-blade ice shape distribution of the target wind turbine.

[0081] In this embodiment, after obtaining the cross-sectional ice types corresponding to all target cross-sectional segments, the cross-sectional ice types of each target cross-sectional segment are restored to size based on the full-scale model to determine the target cross-sectional ice types corresponding to each cross-sectional ice type, and then all target cross-sectional ice types are arranged in sequence and connected by layout, thereby obtaining the full-blade ice type distribution of the target wind turbine. It can be understood that the icing simulation test is divided into a rime icing simulation test and a rime icing simulation test. Accordingly, the full-blade ice type distribution of the target wind turbine also includes the full-blade ice type distribution under a rime environment and the full-blade ice type distribution under a rime environment. Figure 4 (a) is a schematic diagram of the ice type distribution of the full blade at the 0.95R section of the full-scale model obtained under rime conditions, as shown in Figure 4(b) is a schematic diagram of the full-leaf ice shape distribution of the 1 / 2 scaled 0.95R section obtained under the fog icing environment, the section chord length is scaled by 1 / 2, and the rotating radius is scaled by 1 / 29. As can be seen from the figure, the full-leaf ice shape distribution of the large blade can also be accurately obtained by modeling and restoring using the results of multiple small-section icing tests. Compared with the general two-dimensional section airfoil test, the device can also simulate the flow of the surface water film under the rotating state. Figure 5 (a) is a schematic diagram of the full-leaf ice shape distribution of the full-size model 0.95R section obtained under the rain icing environment, as shown in the figure. Figure 5 (b) is a schematic diagram of the full-leaf ice shape distribution of the 1 / 2 scaled 0.95R section obtained under the fog icing environment, the section chord length is scaled by 1 / 2, and the rotating radius is scaled by 1 / 29. As can be seen from the figure, the full-leaf ice shape distribution of the large blade can also be accurately obtained by modeling and restoring using the results of multiple small-section icing tests. Compared with the general two-dimensional section airfoil test, the device can also simulate the flow of the surface water film under the rotating state.

[0082] It should be noted that, as shown in Figure 2 , if the number of target wind tunnels is small (for example, only 1), one target section of the target wind turbine can be determined each time, and icing simulation is performed on the target section, until all target sections of the target wind turbine are completed. Icing simulation is performed on the obtained section ice shape, and size restoration and lofting connection are performed to obtain the full-leaf ice shape distribution of the target wind turbine. If the number of target wind tunnels is sufficient, all target sections can be simultaneously subjected to icing simulation tests, thereby quickly determining the full-leaf ice shape distribution of the target wind turbine. The specific icing simulation test process can be adjusted according to actual needs.

[0083] As can be seen, the present application selects the section of the full-size model to be studied, appropriately scales the section airfoil (specifically, the target wind tunnel used for the icing test can be used as a standard) and stretches the section to obtain corresponding target sections. A long enough section can fully reflect the spanwise motion of the water film on the airfoil surface during the rotating motion. Then, the target scaling icing similarity method is used to determine the icing test parameters of each target section, that is, the related parameters of the icing test process, so as to perform icing tests on each target section in the target wind tunnel based on the icing test parameters of each target section, to determine the section ice shape corresponding to each target section. Finally, the target section ice shape is obtained by performing size restoration on all section ice shapes based on the full-size model of the target wind turbine, and lofting connection is performed on all target section ice shapes, thereby obtaining the ice shape distribution of the full-leaf rotating icing experiment of the target wind turbine. The present application only scales the section chord length and avoids the problem of blade length, and the scaling object is changed from the full-leaf blade to the airfoil section at a certain position of the blade, so that the rotating radius is reduced without excessively scaling the airfoil section, and the limitations of the test site size and the scaling test precision are solved. Moreover, the full-leaf icing distribution of the large blade can also be accurately obtained by modeling and restoring using the results of multiple small-section icing tests. Compared with the general two-dimensional section airfoil test, the device can also simulate the flow of the surface water film under the rotating state.

[0084] See also Figure 6 As shown, the present application discloses a wind turbine blade icing simulation device, comprising:

[0085] A cross-sectional segment determination module 11 is configured to obtain a full-scale model of a target wind turbine and determine target cross-sectional segments corresponding to the target wind turbine based on the full-scale model;

[0086] a cross-sectional ice type determination module 12, configured to determine icing test parameters corresponding to each target cross-sectional segment using a target scaled icing similarity method, and perform an icing simulation test on each target cross-sectional segment in a target wind tunnel based on the icing test parameters corresponding to each target cross-sectional segment, so as to determine the cross-sectional ice type corresponding to each target cross-sectional segment;

[0087] The ice type distribution determination module 13 is used to restore the cross-sectional ice type of each target cross-sectional segment based on the full-scale model to determine the target cross-sectional ice type corresponding to each cross-sectional ice type, and to connect all the target cross-sectional ice types to determine the full-blade ice type distribution of the target wind turbine.

[0088] As can be seen, this application selects the cross-section to be studied in the full-scale model, appropriately reduces the airfoil profile at that cross-section (specifically, the airfoil profile can be accommodated in the target wind tunnel used for the icing test as a standard), and then stretches it into segments to obtain corresponding target cross-section segments. The sufficiently long cross-section segments can fully reflect the spanwise motion of the water film on the surface of the airfoil profile during the rotational motion during the rotational test. The target scaled icing similarity method is then used to determine the icing test parameters corresponding to each target cross-section segment, i.e., the relevant parameters of the icing test process. Based on the icing test parameters corresponding to each target cross-section segment, an icing test is then conducted on each target cross-section segment in the target wind tunnel to determine the cross-sectional ice type corresponding to each target cross-sectional segment. Finally, based on the full-scale model of the target wind turbine, all cross-sectional ice types are restored to their original size to obtain the target cross-sectional ice type. All target cross-sectional ice types are then laid out and connected to obtain the ice type distribution for the rotating icing test of the entire blade of the target wind turbine. This application scales down only the cross-sectional chord length, avoiding the issue of blade length. The scaling target shifts from the entire blade to the airfoil section at a specific location on the blade. This reduces the radius of rotation without significantly reducing the airfoil section, simultaneously addressing limitations in test site size and scaling test accuracy. Furthermore, modeling and restoring the results of multiple small-section icing tests can accurately determine the ice distribution of the entire large blade. Compared to conventional two-dimensional airfoil tests, this device can also simulate the flow of water films on rotating surfaces.

[0089] In a specific implementation, the cross-section determination module 11 may specifically include:

[0090] The to-be-simulated face determining submodule is configured to determine each to-be-simulated cross section corresponding to the target wind turbine based on the full-size model.

[0091] The cross section segment determining submodule is configured to reduce each to-be-simulated cross section based on the wind tunnel size of the target wind tunnel to obtain a corresponding reduced cross section, and stretch each reduced cross section based on the rotating radius of the target wind turbine to determine each target cross section segment corresponding to the target wind turbine.

[0092] In an embodiment, the cross section ice type determining module 12 can specifically include:

[0093] The first cross section ice type determining submodule is configured to determine a glaze icing test parameter corresponding to each target cross section segment by using a first scaling icing similarity method, and perform a glaze icing simulation test on each target cross section segment in a first target wind tunnel based on the glaze icing test parameter corresponding to each target cross section segment to determine a first cross section ice type corresponding to each target cross section segment.

[0094] In an embodiment, the first cross section ice type determining submodule can specifically include:

[0095] The first parameter determining unit is configured to determine a test pressure, a test flow velocity, a test temperature, and a test liquid water content based on the full-size model;

[0096] The angular velocity determining unit is configured to match a flow direction factor before and after scaling based on the test flow velocity and the rotating radius scaling to determine a test rotating angular velocity;

[0097] The droplet diameter determining unit is configured to determine a droplet median diameter based on a cross section chord length scaling and a modified inertia parameter;

[0098] The first icing time determining unit is configured to determine a glaze icing time based on the cross section chord length scaling and the test liquid water content.

[0099] In an embodiment, the cross section ice type determining module 12 can specifically include:

[0100] The second cross section ice type determining submodule is configured to determine a rime icing test parameter corresponding to each target cross section segment by using a second scaling icing similarity method, and perform a rime icing simulation test on each target cross section segment in a second target wind tunnel based on the rime icing test parameter corresponding to each target cross section segment to determine a second cross section ice type corresponding to each target cross section segment.

[0101] In an embodiment, the second cross section ice type determining submodule can specifically include:

[0102] A test pressure determination unit is configured to determine a test pressure based on the full-size model;

[0103] A second parameter determination unit is configured to determine a test incoming flow velocity and a test rotating angular velocity based on the rotating radius scaling ratio, the incoming flow velocity direction factor and the resultant velocity;

[0104] A test temperature determination unit is configured to determine a test temperature based on the cross-sectional chord length scaling ratio, the freezing rate and the relative thermal factor;

[0105] A supercooled water droplet diameter determination unit is configured to determine a test supercooled water droplet diameter based on the cross-sectional chord length scaling ratio and the modified inertia parameter;

[0106] A test liquid water content determination unit is configured to determine a test liquid water content based on the cross-sectional chord length scaling ratio and the relative thermal factor;

[0107] A second icing time determination unit is configured to determine a raindrop icing time based on the cross-sectional chord length scaling ratio, the test liquid water content and the aggregation factor.

[0108] Further, the embodiment of the present application further discloses an electronic device, Figure 7 is an electronic device 20 structure diagram shown according to an exemplary embodiment, the contents in the figure cannot be considered as any limitation to the use range of the present application.

[0109] Figure 7 A structure schematic diagram of an electronic device 20 provided by the embodiment of the present application. The electronic device 20 specifically can include: at least one processor 21, at least one memory 22, a power supply 23, a communication interface 24, an input output interface 25 and a communication bus 26. Wherein, the memory 22 is used for storing computer programs, the computer programs are loaded and executed by the processor 21, to realize the related steps in the fan blade icing simulation method disclosed by any of the preceding embodiments. In addition, the electronic device 20 in the embodiment specifically can be an electronic computer.

[0110] In the embodiment, the power supply 23 is used for providing working voltage for each hardware device on the electronic device 20; the communication interface 24 can create a data transmission channel between the electronic device 20 and the external device, and the communication protocol followed by the communication interface 24 is any communication protocol applicable to the technical solution of the present application, which is not limited specifically herein; the input output interface 25 is used for obtaining external input data or outputting data to the outside world, and the specific interface type can be selected according to the specific application needs, which is not limited specifically herein.

[0111] In addition, the memory 22 can be a read-only memory, a random access memory, a magnetic or optical disk, etc. as a carrier for storing resources, and the resources stored thereon can include an operating system 221, a computer program 222, etc. The storage mode can be temporary storage or permanent storage.

[0112] The operating system 221 is used to manage and control each hardware device on the electronic device 20 and the computer program 222, and can be Windows Server, Netware, Unix, Linux, etc. In addition to the computer program capable of completing the fan blade icing simulation method executed by the electronic device 20 disclosed in any of the preceding embodiments, the computer program 222 can further include a computer program capable of completing other specific work.

[0113] Further, the present application also discloses a computer readable storage medium for storing a computer program; wherein the computer program is executed by a processor to implement the fan blade icing simulation method disclosed above. For the specific steps of the method, please refer to the corresponding content disclosed in the preceding embodiments, which will not be described here.

[0114] The embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. For the same or similar parts between the embodiments, please refer to each other. For the device disclosed in the embodiments, since it corresponds to the method disclosed in the embodiments, the description is relatively simple, and please refer to the method part for the relevant part.

[0115] The skilled person can further realize that the units and algorithm steps of the examples described in combination with the embodiments disclosed herein can be realized by electronic hardware, computer software or a combination of the two. In order to clearly show the interchangeability of hardware and software, the composition and steps of each example have been described in the above description. Whether the functions are realized by hardware or software depends on the specific application and design constraints of the technical solution. The skilled person can use different methods to realize the described functions for each specific application, but such implementation should not be considered beyond the scope of the present application.

[0116] The steps of the method or algorithm described in combination with the embodiments disclosed herein can be directly implemented by hardware, a software module executed by a processor, or a combination of the two. The software module can be placed in a random access memory (RAM), a memory, a read-only memory (ROM), an electrically programmable ROM, an electrically erasable programmable ROM, a register, a hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art.

[0117] Finally, it should be noted that, in this document, relational terms such as first and second, etc., are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or elements inherent to such process, method, article, or device. In the absence of further limitations, an element defined by the phrase "comprising a ..." does not exclude the presence of additional identical elements in the process, method, article, or device comprising the element.

[0118] The above is a detailed introduction to the technical solution provided by the present application. Specific examples are used herein to illustrate the principles and implementation methods of the present application. The description of the above embodiments is only used to help understand the method of the present application and its core idea. At the same time, for those skilled in the art, according to the ideas of the present application, there may be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as a limitation on the present application.

Claims

1. A method for simulating ice coating on wind turbine blades, characterized in that: include: Acquire a full-scale model of a target wind turbine, and determine target cross-sectional segments corresponding to the target wind turbine based on the full-scale model; determining icing test parameters corresponding to each target cross-sectional segment using a target scaled icing similarity method, and conducting an icing simulation test on each target cross-sectional segment in a target wind tunnel based on the icing test parameters corresponding to each target cross-sectional segment to determine a cross-sectional ice type corresponding to each target cross-sectional segment; The cross-sectional ice types of each target cross-sectional segment are restored to size based on the full-scale model to determine the target cross-sectional ice types corresponding to each cross-sectional ice type, and all the target cross-sectional ice types are connected and laid out to determine the full-blade ice type distribution of the target wind turbine.

2. The wind turbine blade icing simulation method according to claim 1, characterized in that: The determining of target cross-sectional segments corresponding to the target wind turbine based on the full-scale model includes: Determining each section to be simulated corresponding to the target wind turbine based on the full-scale model; Based on the wind tunnel size of the target wind tunnel, each of the sections to be simulated is reduced to obtain a corresponding reduced section, and based on the rotation radius of the target wind turbine, each of the reduced sections is stretched to determine each target section segment corresponding to the target wind turbine.

3. The wind turbine blade icing simulation method according to claim 1, characterized in that: The icing test parameters include incoming flow velocity, rotation speed, droplet diameter, liquid water content, test temperature and icing time.

4. The wind turbine blade icing simulation method according to claim 3, characterized in that: The method of determining icing test parameters corresponding to each target cross-sectional segment by using a target scaled icing similarity method, and conducting an icing simulation test on each target cross-sectional segment in a target wind tunnel based on the icing test parameters corresponding to each target cross-sectional segment to determine a cross-sectional ice type corresponding to each target cross-sectional segment includes: The first scaled icing similarity method is used to determine the rime icing test parameters corresponding to each target cross-sectional segment. Based on the rime icing test parameters corresponding to each target cross-sectional segment, a rime icing simulation test is conducted on each target cross-sectional segment in a first target wind tunnel to determine the first cross-sectional ice type corresponding to each target cross-sectional segment.

5. The wind turbine blade icing simulation method according to claim 4, characterized in that: The method of determining the rime icing test parameters corresponding to each target cross-sectional segment using the first scaled icing similarity method includes: determining a test pressure, a test flow velocity, a test temperature, and a test liquid water content based on the full-scale model; Matching the flow direction factors before and after the reduction based on the test flow velocity and the rotation radius reduction to determine the test rotation angular velocity; Determine the droplet median diameter based on the cross-sectional chord length reduction ratio and the modified inertial parameter; The rime icing time is determined based on the cross-sectional chord length reduction ratio and the test liquid water content.

6. The wind turbine blade icing simulation method according to claim 3, characterized in that: The method of determining icing test parameters corresponding to each target cross-sectional segment by using a target scaled icing similarity method, and conducting an icing simulation test on each target cross-sectional segment in a target wind tunnel based on the icing test parameters corresponding to each target cross-sectional segment to determine a cross-sectional ice type corresponding to each target cross-sectional segment includes: The second scaled icing similarity method is used to determine the rain and rime icing test parameters corresponding to each target cross-sectional segment. Based on the rain and rime icing test parameters corresponding to each target cross-sectional segment, a rain and rime icing simulation test is conducted on each target cross-sectional segment in a second target wind tunnel to determine the second cross-sectional ice type corresponding to each target cross-sectional segment.

7. The wind turbine blade icing simulation method according to claim 6, characterized in that: The method of determining the rime icing test parameters corresponding to each target cross-sectional segment using the second scaled icing similarity method includes: determining a test pressure based on the full-scale model; Determine the test incoming flow velocity and test rotation angular velocity based on the rotation radius reduction ratio, incoming flow velocity direction factor and resultant velocity; Determine the test temperature based on the cross-sectional chord length reduction ratio, freezing rate, and relative thermal factor; Determining the diameter of the test supercooled water droplet based on the cross-sectional chord length reduction ratio and the modified inertia parameter; determining a test liquid water content based on the cross-sectional chord length reduction ratio and the relative thermal factor; The rime icing time is determined based on the cross-sectional chord length reduction ratio, the test liquid water content, and the aggregation factor.

8. A wind turbine blade icing simulation device, characterized in that: include: a cross-sectional segment determination module, configured to obtain a full-scale model of a target wind turbine and determine target cross-sectional segments corresponding to the target wind turbine based on the full-scale model; a cross-sectional ice type determination module, configured to determine icing test parameters corresponding to each target cross-sectional segment using a target scaled icing similarity method, and perform an icing simulation test on each target cross-sectional segment in a target wind tunnel based on the icing test parameters corresponding to each target cross-sectional segment to determine the cross-sectional ice type corresponding to each target cross-sectional segment; An ice type distribution determination module is used to restore the cross-sectional ice type of each target cross-sectional segment based on the full-scale model to determine the target cross-sectional ice type corresponding to each cross-sectional ice type, and to loft and connect all the target cross-sectional ice types to determine the full-blade ice type distribution of the target wind turbine.

9. An electronic device, characterized in that: include: Memory, used to store computer programs; A processor is configured to execute the computer program to implement the wind turbine blade icing simulation method according to any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that Used to store a computer program, wherein when the computer program is executed by a processor, the wind turbine blade icing simulation method according to any one of claims 1 to 7 is implemented.

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