Method and device for determining aerodynamic performance data based on aeroelastic coupling model

Abstract

The invention discloses a method and device for determining aerodynamic performance data based on an aeroelastic coupling model, and relates to the technical field of wind power generation, and the method comprises the steps: obtaining blade deformation data obtained by monitoring blades of a power generation wind turbine unit; calculating aerodynamic performance data corresponding to the blade based on the blade deformation data and an aerodynamic calculation model, wherein the aerodynamic performance data at least comprises a surface acting force and a surface acting force moment of the blade; performing static analysis on the surface acting force and the surface acting force moment by using the structure solving model to obtain the deformation of the blade corresponding to the blade section of the structure solving model; an aeroelastic torsion angle corresponding to the deformation amount is used for updating an inflow angle of the blade required when the aerodynamic calculation model calculates aerodynamic performance data corresponding to the blade, an updated aerodynamic calculation model is obtained, and the aeroelastic torsion angle represents a torsion deformation angle caused by blade deformation; and calculating target aerodynamic performance data corresponding to the blade by using the updated aerodynamic calculation model.

Description

Technical Field

[0001] The present application relates to the technical field of wind power generation, and in particular to a method and device for determining aerodynamic performance data based on an aeroelastic coupling model. Background Art

[0002] As the demand for electrical equipment continues to surge, users' demand for electricity is also increasing. Current power generation technologies include wind power generation technology, thermal power generation technology, hydropower generation technology, nuclear power generation technology, solar power generation technology, etc. Among them, wind power generation is mainly achieved based on wind turbines. The blades of a wind turbine are a typical long and flexible structure. The structure of a wind turbine will undergo elastic deformation under the action of aerodynamic loads, and the aerodynamic load of the blades will also change accordingly. This process also forms a strongly coupled aerodynamic-structural dynamic phenomenon. As the blades deform, the flexible deformation and nonlinear deformation of the blades make the aeroelastic phenomenon more obvious. If flutter occurs, the blades will be severely damaged. Therefore, during the power generation process of the wind turbine, it is necessary to monitor the deformation state of the blades in real time so that timely maintenance can be carried out when the blades are abnormal to avoid the situation where power generation is affected by blade damage. In the related art, the calculation accuracy of the aeroelastic coupling model established for this dynamic phenomenon is too low, and the aerodynamic performance data of the blades when deformed cannot be accurately determined.

[0003] With regard to the technical problem in the related art that the aerodynamic performance data of the blade when deformed cannot be accurately determined, no effective solution has been proposed so far.

[0004] Therefore, it is necessary to improve the related technology to overcome the above-mentioned defects in the related technology. Summary of the invention

[0005] The embodiments of the present application provide a method and device for determining aerodynamic performance data based on an aeroelastic coupling model, so as to at least solve the technical problem that the aerodynamic performance data when the blade is deformed cannot be accurately determined.

[0006] According to one aspect of an embodiment of the present application, a method for determining aerodynamic performance data based on an aeroelastic coupling model is provided, wherein the aeroelastic coupling model at least includes an aerodynamic calculation model and a structural solution model, including: obtaining blade deformation data obtained by monitoring the blades of a power-generating wind turbine, wherein the blade deformation data at least includes the unit parameters of the power-generating wind turbine, the wind field parameters of the wind field where the blade is located, the airfoil lift and drag coefficient of the blade, and the moment coefficient of the blade; calculating aerodynamic performance data corresponding to the blade based on the blade deformation data and the aerodynamic calculation model, wherein the aerodynamic performance data at least includes The invention discloses a method for obtaining a surface force and a surface force moment of the blade by using the structural solution model to perform a static analysis on the surface force and the surface force moment of the blade to obtain the deformation of the blade section corresponding to the structural solution model; and obtains an updated aerodynamic calculation model by using the aeroelastic torsion angle corresponding to the deformation to update the aerodynamic calculation model to calculate the aerodynamic performance data corresponding to the blade, wherein the aeroelastic torsion angle represents the torsional deformation angle caused by the deformation of the blade; and obtains the target aerodynamic performance data corresponding to the blade by calculating using the updated aerodynamic calculation model.

[0007] In an exemplary embodiment, aerodynamic performance data corresponding to the blade is calculated based on the blade deformation data and the aerodynamic calculation model, including: generating the aerodynamic calculation model based on blade element theory; performing iterative calculation using the initial induction factor iteration formula of the aerodynamic calculation model, and obtaining the aerodynamic performance data corresponding to the current iterative calculation result when it is determined that the difference between two consecutive iterative calculation results is less than a preset difference.

[0008] In an exemplary embodiment, in the process of generating the aerodynamic calculation model based on the blade element theory, the method also includes: introducing a correction factor into the blade element theory to establish a two-dimensional model of the blades of the wind turbine, and determining the two-dimensional model as the aerodynamic calculation model, wherein the correction factor includes at least one of the following: a blade tip correction factor, a hub loss correction factor, and an induced correction factor.

[0009] In an exemplary embodiment, the initial induction factor iteration formula is expressed as follows:

[0010] a=p1 / (1+p1), a′=p2 / (1-p2);

[0011]

[0012] Where a and a′ are the initial induction factor iteration formulas, N is the number of blades, F is the loss factor, r is the radial position of the blade, c is the chord length corresponding to the radial position of the blade, φ is the inflow angle, C Lis a lift-drag coefficient of the blade airfoil, C D is another lift-drag coefficient of the airfoil of the blade.

[0013] In an exemplary embodiment, the method further includes: when the axial flow induction factor of the blade is greater than a preset value, updating the parameter p1 in the initial induction factor iteration formula to obtain an updated induction factor iteration formula;

[0014] Among them, the p1 is updated to H is the segmented control variable.

[0015] In an exemplary embodiment, before using the structural solution model to perform static analysis on the surface forces and the surface force moments, the method also includes: inputting the geometric dimensions and blade shape parameters of the blade in a parameter definition area of ​​the model building platform so that the model building platform creates an initial geometric model of the blade and displays the initial geometric model in a display area; using definition commands provided by the model building platform to define the mechanical properties of the initial geometric model, the shell unit type of the initial geometric model, and the boundary conditions of the initial geometric model to update the initial geometric model and obtain the structural solution model.

[0016] According to another aspect of an embodiment of the present application, there is also provided a device for determining aerodynamic performance data based on an aeroelastic coupling model, comprising: an acquisition module for acquiring blade deformation data obtained by monitoring the blades of a power-generating wind turbine, wherein the blade deformation data at least includes the unit parameters of the power-generating wind turbine, the wind field parameters of the wind field where the blade is located, the airfoil lift and drag coefficient of the blade, and the moment coefficient of the blade; a calculation module for calculating the aerodynamic performance data corresponding to the blade based on the blade deformation data and an aerodynamic calculation model, wherein the aerodynamic performance data at least includes the surface force and surface force of the blade moment; an analysis module, used to use a structural solution model to perform static analysis on the surface force and the surface force moment, and obtain the deformation of the blade section corresponding to the structural solution model; a first obtaining module, used to update the aerodynamic calculation model by using the aeroelastic torsion angle corresponding to the deformation to obtain the updated aerodynamic calculation model when calculating the aerodynamic performance data corresponding to the blade, and the aeroelastic torsion angle represents the torsional deformation angle caused by the deformation of the blade; a second obtaining module, used to calculate the target aerodynamic performance data corresponding to the blade using the updated aerodynamic calculation model.

[0017] According to another aspect of an embodiment of the present application, a computer-readable storage medium is provided, in which a computer program is stored, wherein the computer program is configured to execute the above-mentioned method for determining aerodynamic performance data based on the aeroelastic coupling model when running.

[0018] According to another aspect of an embodiment of the present application, an electronic device is also provided, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the method for determining aerodynamic performance data based on an aeroelastic coupling model through the computer program.

[0019] According to another aspect of the present application, a computer program product is provided, including a computer program, and when the computer program is executed by a processor, the steps in any one of the above method embodiments are implemented.

[0020] Through the present application, blade deformation data obtained by monitoring the blades of a power-generating wind turbine is acquired, wherein the blade deformation data at least includes the unit parameters of the power-generating wind turbine, the wind field parameters of the wind field where the blade is located, the airfoil lift and drag coefficient of the blade, and the moment coefficient of the blade; based on the blade deformation data and the aerodynamic calculation model, aerodynamic performance data corresponding to the blade is calculated, and the aerodynamic performance data at least includes the surface force and the surface force moment of the blade; the surface force and the surface force moment are statically analyzed using the structural solution model to obtain the blade corresponding to the structural solution model. The amount of deformation of the cross section; the inflow angle of the blade required when the aerodynamic calculation model is used to calculate the aerodynamic performance data corresponding to the blade by using the aeroelastic torsion angle corresponding to the deformation to obtain an updated aerodynamic calculation model, wherein the aeroelastic torsion angle represents the torsional deformation angle caused by the deformation of the blade; the target aerodynamic performance data corresponding to the blade is calculated using the updated aerodynamic calculation model, and a dynamic high-precision response aeroelastic model (i.e., an aeroelastic coupling model) under the aerodynamic-structural framework of the wind turbine is established, and the dynamic behavior of the blade and the unit under time-varying loads is further studied. The technical problem of not being able to accurately determine the aerodynamic performance data when the blade is deformed is thereby solved, and the accuracy of the aerodynamic performance data when the blade is deformed is improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present application and, together with the description, serve to explain the principles of the present application.

[0022] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, for ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0023] Figure 1 It is a hardware structure block diagram of a mobile terminal of a method for determining aerodynamic performance data based on an aeroelastic coupling model according to an embodiment of the present application;

[0024] Figure 2 is a flow chart of a method for determining aerodynamic performance data based on an aeroelastic coupling model according to an embodiment of the present application;

[0025] Figure 3 is a schematic diagram of a process for constructing an aerodynamic calculation model according to an embodiment of the present application;

[0026] Figure 4 is a schematic diagram of a flow chart of a blade aeroelastic coupling solution according to an embodiment of the present application;

[0027] Figure 5 is a schematic diagram of a gas-elastic torsion angle according to an embodiment of the present application;

[0028] Figure 6 It is a structural block diagram of a device for determining aerodynamic performance data based on an aeroelastic coupling model according to an embodiment of the present application. DETAILED DESCRIPTION

[0029] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present application.

[0030] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchangeable where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any of their variations are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device comprising a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0031] The method embodiments provided in the embodiments of the present application can be executed in a mobile terminal, a computer terminal or a similar computing device. Taking running on a mobile terminal as an example, Figure 1 1 is a hardware structure block diagram of a mobile terminal for determining aerodynamic performance data based on an aeroelastic coupling model according to an embodiment of the present application. Figure 1 As shown, the mobile terminal may include one or more ( Figure 1 Only one is shown in the figure) a processor 102 (the processor 102 may include but is not limited to a microprocessor or a processing device such as a programmable logic device (Field Programmable Gate Array, FPGA)) and a memory 104 for storing data, wherein the mobile terminal may also include a transmission device 106 and an input / output device 108 for communication functions. It can be understood by those skilled in the art that Figure 1 The structure shown is only for illustration and does not limit the structure of the mobile terminal. Figure 1 More or fewer components as shown, or with Figure 1 Different configurations shown.

[0032] The memory 104 can be used to store computer programs, for example, software programs and modules of application software, such as the computer program corresponding to the method for determining aerodynamic performance data based on the aeroelastic coupling model in the embodiment of the present application. The processor 102 executes various functional applications and data processing by running the computer program stored in the memory 104, that is, to implement the above method. The memory 104 may include a high-speed random access memory, and may also include a non-volatile memory, such as one or more magnetic storage devices, flash memory, or other non-volatile solid-state memory. In some instances, the memory 104 may further include a memory remotely arranged relative to the processor 102, and these remote memories may be connected to the mobile terminal via a network. Examples of the above-mentioned network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

[0033] The transmission device 106 is used to receive or send data via a network. The specific example of the above network may include a wireless network provided by a communication provider of the mobile terminal. In one example, the transmission device 106 includes a network adapter (Network Interface Controller, referred to as NIC), which can be connected to other network devices through a base station so as to communicate with the Internet. In one example, the transmission device 106 can be a radio frequency (RF) module, which is used to communicate with the Internet wirelessly.

[0034] In this embodiment, a method for determining aerodynamic performance data based on an aeroelastic coupling model is provided. The aeroelastic coupling model at least includes an aerodynamic calculation model and a structural solution model. Figure 2 is a flow chart of a method for determining aerodynamic performance data based on an aeroelastic coupling model according to an embodiment of the present application, such as Figure 2 As shown, the process includes the following steps:

[0035] Step S202: Acquire blade deformation data obtained by monitoring the blades of the power generation wind turbine, wherein the blade deformation data at least includes the unit parameters of the power generation wind turbine, the wind field parameters of the wind field where the blade is located, the airfoil lift and drag coefficient of the blade, and the moment coefficient of the blade;

[0036] Step S204: calculating aerodynamic performance data corresponding to the blade based on the blade deformation data and the aerodynamic calculation model, wherein the aerodynamic performance data at least includes the surface force and surface force moment of the blade;

[0037] For the above aerodynamic calculation model, for example, the BEM theory can be used to construct it. In the field of wind turbines, the BEM (Blade Element Momentum) theory is a method for analyzing and designing wind turbine blades. The BEM theory, also known as the blade element theory, is based on the Actuator Line / Disk Momentum Theory and the Thin Airfoil Theory. The blade is divided into several small sections (blade elements), the aerodynamic force on each blade element is calculated separately, and then these aerodynamic forces are integrated to obtain the performance of the entire blade.

[0038] Specifically: BEM theory considers the momentum change of airflow on the blade surface and calculates the aerodynamic force on the blade through the momentum theorem. BEM theory assumes that the curved shape of the blade can be approximated as a series of thin airfoils, thereby simplifying the aerodynamic calculation of the blade. BEM theory divides the blade into several small sections and calculates the aerodynamic force on each blade element separately. BEM theory integrates the aerodynamic forces on each blade element through integral solution to obtain the performance of the entire blade.

[0039] The BEM+ modified theory is a theory that adjusts and improves some viewpoints and methods based on the BEM theory, which can include the following aspects:

[0040] 1. Consider three-dimensional effects: The BEM+ modified theory may consider the three-dimensional effects of the blades, such as wake effect, blade torsion, etc., to improve the accuracy of the calculation.

[0041] 2. Consider unsteady effects: The BEM+ modified theory may consider unsteady effects, such as dynamic stall, fatigue load, etc., to better simulate actual working conditions.

[0042] 3. Consider the actual airfoil: BEM+ modified theory may use actual airfoil data instead of simplified thin wing theory to improve the accuracy of calculation.

[0043] 4. Consideration of aerodynamic noise and turbulence: BEM+ modified theory may consider the impact of aerodynamic noise and turbulence on wind turbine performance to optimize the design.

[0044] 5. Use of Computational Fluid Dynamics (CFD): The BEM+ modified theory may be combined with computational fluid dynamics (CFD) methods to more accurately simulate the complex flow around the blades.

[0045] Step S206: using the structural solution model to perform static analysis on the surface force and the surface force moment, to obtain the deformation of the blade section corresponding to the structural solution model;

[0046] Among them, for the structural solution model, the three-dimensional FEM model of the blade (i.e., the structural solution model) can be constructed based on the three-dimensional ply structure of the blade using APDL. APDL (ANSYS Parametric Design Language) is a parametric design language of the ANSYS software package, which is used to create and modify models, define material properties, apply loads and boundary conditions, and perform finite element analysis in ANSYS.

[0047] Step S208: obtaining an updated aerodynamic calculation model by updating the inflow angle of the blade required when the aerodynamic calculation model calculates the aerodynamic performance data corresponding to the blade using the aeroelastic torsion angle corresponding to the deformation, wherein the aeroelastic torsion angle represents the torsion deformation angle caused by the deformation of the blade;

[0048] Step S210: using the updated aerodynamic calculation model to calculate and obtain target aerodynamic performance data corresponding to the blade.

[0049] Through the above steps, after solving the deformation of the blade section, the torsional deformation of the blade under aerodynamic load and its influence on the aeroelastic response are comprehensively considered to construct a high-precision aeroelastic coupling model.

[0050] Through the present application, blade deformation data obtained by monitoring the blades of a power-generating wind turbine is acquired, wherein the blade deformation data at least includes the unit parameters of the power-generating wind turbine, the wind field parameters of the wind field where the blade is located, the airfoil lift and drag coefficient of the blade, and the moment coefficient of the blade; based on the blade deformation data and the aerodynamic calculation model, aerodynamic performance data corresponding to the blade is calculated, and the aerodynamic performance data at least includes the surface force and the surface force moment of the blade; the surface force and the surface force moment are statically analyzed using the structural solution model to obtain the blade corresponding to the structural solution model. The amount of deformation of the cross section; the inflow angle of the blade required when the aerodynamic calculation model is used to calculate the aerodynamic performance data corresponding to the blade by using the aeroelastic torsion angle corresponding to the deformation to obtain an updated aerodynamic calculation model, wherein the aeroelastic torsion angle represents the torsional deformation angle caused by the deformation of the blade; the target aerodynamic performance data corresponding to the blade is calculated using the updated aerodynamic calculation model, and a dynamic high-precision response aeroelastic model (i.e., an aeroelastic coupling model) under the aerodynamic-structural framework of the wind turbine is established, and the dynamic behavior of the blade and the unit under time-varying loads is further studied. The technical problem of not being able to accurately determine the aerodynamic performance data when the blade is deformed is thereby solved, and the accuracy of the aerodynamic performance data when the blade is deformed is improved.

[0051] Among them, based on the above steps S204 and S206, the process of solving the pneumatic module and the structural module independently can be realized, and through steps S208 and S210, linear interpolation can be used to transfer information on the coupling interface. In this process, through the coupling interface, the fluid domain transfers the model force and torque to the structural domain, and the structural domain feeds back the response after the action to the fluid domain, thereby realizing the coupled calculation of the model.

[0052] Optionally, in one embodiment, in combination Figure 3The following steps are shown to illustrate the process of calculating the aerodynamic performance data corresponding to the blade based on the blade deformation data and the aerodynamic calculation model:

[0053] Step S301, input wind turbine parameters, basic wind farm parameters, airfoil lift and drag coefficients, and moment coefficients.

[0054] Step S302, input the number of sections n, set i=1, and the initial induction factor is 0.

[0055] Step S303, determine whether i≤n is established. If i≤n, execute step S304. Otherwise, execute step S309.

[0056] Step S304, calculating the inflow angle and the angle of attack.

[0057] Step S305, calculating the corresponding lift-drag coefficient according to the angle of attack.

[0058] Step S306, further calculating the corrected induction factor.

[0059] Step S307, determine whether the difference between the modified induction factor and the initial induction factor is less than a threshold value. If the difference is less than the threshold value, execute step S308 to continue iterative calculation, otherwise, execute step S304.

[0060] Step S308, execute i=i+1, and execute step S303.

[0061] Step S309, integrating and solving the forces and moments on the blade surface.

[0062] In an exemplary embodiment, the above step S204 includes the following steps:

[0063] Step S11: generating the aerodynamic calculation model based on blade element theory;

[0064] Step S12: performing iterative calculation using the initial induction factor iteration formula of the aerodynamic calculation model, and obtaining aerodynamic performance data corresponding to the current iterative calculation result when it is determined that the difference between two consecutive iterative calculation results is less than a preset difference.

[0065] In an exemplary embodiment, in the process of generating the aerodynamic calculation model based on the blade element theory, a correction factor can also be introduced into the blade element theory to establish a two-dimensional model of the blades of the wind turbine, and the two-dimensional model is determined as the aerodynamic calculation model, wherein the correction factor includes at least one of the following: a blade tip correction factor, a hub loss correction factor, and an induced correction factor.

[0066] That is, in this embodiment, the initial induction factor iteration formula is expressed as follows:

[0067] a=p1 / (1+p1), a′=p2 / (1-p2);

[0068]

[0069] Where a and a′ are the initial induction factor iteration formulas, N is the number of blades, F is the loss factor, r is the radial position of the blade, c is the chord length corresponding to the radial position of the blade, φ is the inflow angle, C L is a lift-drag coefficient of the airfoil of the blade, and CD is another lift-drag coefficient of the airfoil of the blade.

[0070] It can be understood that the above loss factors may include but are not limited to tip loss factor and hub loss factor.

[0071] In an exemplary embodiment, after the above step S204, the following steps are further performed:

[0072] Step S21: when the axial flow induction factor of the blade is greater than a preset value, the parameter p1 in the initial induction factor iteration formula is updated to obtain an updated induction factor iteration formula;

[0073] Among them, the p1 is updated to H is the segmented control variable.

[0074] in,

[0075] In an exemplary embodiment, before using the structural solution model to perform static analysis on the surface force and the surface force moment, the following steps may be implemented:

[0076] Step S32: inputting the geometric dimensions and shape parameters of the blade in the parameter definition area of ​​the model building platform, so that the model building platform creates an initial geometric model of the blade, and displays the initial geometric model in the display area;

[0077] Step S32: using the definition command provided by the model building platform to define the mechanical properties of the initial geometric model, the shell unit type of the initial geometric model, and the boundary conditions of the initial geometric model, so as to update the initial geometric model and obtain the structural solution model.

[0078] Optionally, in this embodiment, the process of obtaining the structural solution model may be described in combination with the following contents, as follows:

[0079] 1. Open the ANSYS software and prepare to start creating the model.

[0080] 2. Use APDL language to define the geometric size and shape parameters of the blade.

[0081] 3. Use APDL commands to create the geometric model of the blade, which may include operations such as stretching (Extrude) and rotating (Revolve).

[0082] 4. Use APDL language to define the mechanical properties of blade materials, such as density, elastic modulus, Poisson's ratio, etc.

[0083] 5. Use APDL commands to mesh the blade geometry, select the appropriate shell element type, and define the element properties.

[0084] 6. Use APDL language to impose boundary conditions on the model, such as fixed constraints, symmetry constraints, etc.

[0085] 7. According to the analysis requirements, use APDL commands to apply loads on the model, such as force, pressure, temperature changes, etc.

[0086] 8. Specify the analysis type (such as static analysis, thermal analysis, nonlinear analysis, etc.).

[0087] 9. Use the APDL command to start the solution process, ANSYS will calculate and get the results.

[0088] 10. Use APDL commands to extract and analyze results, such as stress, strain, displacement, etc.

[0089] 11. Based on the analysis results, use APDL to adjust the model design and perform iterative optimization.

[0090] 12. Use APDL to output analysis reports and related documents.

[0091] This embodiment can utilize the flexibility and powerful functions of the APDL language to analyze complex finite elements, thereby allowing users to automate the model creation and analysis process through scripting without using a graphical user interface.

[0092] Obviously, the embodiments described above are only some embodiments of the present application, not all embodiments. In order to better understand the above method, the above process is described below in conjunction with the embodiments, but it is not intended to limit the technical solutions of the embodiments of the present application, specifically:

[0093] Further, in one embodiment, the process of determining the aerodynamic performance data based on the aeroelastic coupling model in the present application is described by the following steps:

[0094] Step 1: Establish aerodynamic calculation model.

[0095] The blade element theory (BEM theory) indicates that the force acting on the blade element is only affected by the aerodynamic performance of the airfoil and is related to the momentum of the gas flowing through the blade element ring. The airflow interference between adjacent blade elements in the radial direction of the blade is not considered, that is, each blade element ring remains independent in the radial direction. Therefore, the BEM theory ignores the three-dimensional effect of the blade.

[0096] In fact, although the axial induction factor is less consistent, the assumption of radial independence is certain. Therefore, the aerodynamic component of the blade plane in the axial direction is set as:

[0097]

[0098] And, the axial gas change rate of the wind wheel annulus is set to:

[0099] ρU ∞ (1-a)2πrδr2aU ∞ =4πρU ∞ 2 a(1-a)rδr(1-2).

[0100] It can be seen that the pressure reduction caused by the rotating wake is equal to the increase in dynamic pressure, that is:

[0101]

[0102] Therefore, the additional axial force on the ring is derived as:

[0103]

[0104] So we get the following formula:

[0105]

[0106] Simplifying formula (1-5), we get the following formula:

[0107]

[0108] Then, the axial wind wheel torque obtained from the aerodynamic force on the blade plane is as follows:

[0109]

[0110] And, the rate of change of angular momentum of the gas flowing through the ring is derived as follows:

[0111] ρU ∞ (1-a)Ωr2a′r2πrδr=4πρU ∞ (Ωr)a′(1-a)r 2 δr(1-8).

[0112] Equating the above torques yields:

[0113]

[0114] Simplifying formula (1-9) yields the following formula:

[0115]

[0116] In the formula, μ=r / R.

[0117] Then define the following equation:

[0118] C L cosφ+C d sinφ=C n (1-11).

[0119] C L sinφ-C d cosφ=C t (1-12).

[0120] The induction factors a and a' can be obtained from equations (1-6) and (1-10), and then a and a' can be solved by using the aerodynamic characteristics of the airfoil through an iterative process. Among them, equations (1-13) and (1-14) are derived from equations (1-6) and (1-10) for iterative calculation.

[0121]

[0122] The blade solidity σ represents the ratio of the blade area to the rotor area, which determines the aerodynamic performance of the rotor. r It means: the ratio of the total chord length of the blade at the radial position to the circumference of the ring at that radius.

[0123] After the BEM theory is combined with the blade tip and hub losses, the initial induction factor iteration formula changes to:

[0124] a=p1 / (1+p1) (1-16).

[0125] a′=p2 / (1-p2) (1-17).

[0126]

[0127] Where N is the number of blades, F is the tip and hub loss factor, r is the radial position of the blade, c is the chord length corresponding to the radial position of the blade, φ is the inflow angle, C L , C D are the lift and drag coefficients of the airfoil respectively.

[0128] When the axial flow induction factor is greater than 0.5, the wind wheel will be subjected to a higher load, and some basic assumptions of the BEM theory are no longer applicable to the calculation at this time. Therefore, appropriate corrections must be made to the calculation formula. At this time, p1 in formula (1-18) changes to:

[0129]

[0130] The definition of variable H is:

[0131]

[0132] Based on the above theory, including the correction of blade tip and hub loss factors and induced factors, Matlab is used to write a program to establish a two-dimensional model of wind turbine blades and calculate its corresponding aerodynamic performance. The specific construction process can refer to the above Figure 3 The build steps shown.

[0133] Step 2: Construct a structural solution model. The three-dimensional shell unit model of the blade (i.e., the structural solution model) was established using the APDL language.

[0134] Step 3: Couple the aerodynamic calculation model and the structural solution model to obtain an aeroelastic coupling model.

[0135] The torsion and bending structural deformations of the blades under the action of aerodynamic loads are fed back to the blade aerodynamic calculation model (i.e., in the angle of attack solution of the classical BEM theory, the effect of the aeroelastic torsion angle on the load on the model is added), so as to further study the influence of aeroelastic coupling characteristics on the performance and response of the blades.

[0136] Set α=φ-θ(1-22).

[0137] Among them, φ is the inflow angle, θ is the blade element installation angle of the blade, in, is the blade element twist angle; β is the pitch angle; δ is the torsional deformation angle caused by the deformation of the blade when the aeroelastic coupling effect is considered, referred to as the aeroelastic torsion angle.

[0138] In order to understand the aeroelastic torsion angle more intuitively, you can refer to Figure 5 The aeroelastic torsion angle is shown.

[0139] Among them, the gas elastic torsion angle can be calculated by the following formula:

[0140]

[0141] It should be noted that, in this embodiment, based on the aerodynamic calculation model and the three-dimensional structure solution model of the blade constructed in the above steps, the influence of the aeroelastic torsion angle is considered, and a high-precision blade aeroelastic coupling solution method is further provided. The specific steps are as follows: Figure 4 As shown:

[0142] Step S401, calculating the angle of attack by using the BEM theory to solve the corresponding lift and drag coefficient and moment coefficient;

[0143] Step S402, calculating the induction factor, and repeatedly iterating the calculation of the induction factor until a value that satisfies the accuracy is obtained;

[0144] Step S403, integrating and solving the force and moment of the blade cross section;

[0145] Step S404, using the structural solution model to load the force and moment;

[0146] Step S405, performing static analysis on the established structural solution model to extract the deformation on the blade cross section;

[0147] Step S406, subtract the deformation amounts before and after to obtain the deformation difference.

[0148] Step S407, determine whether the deformation difference is less than a threshold value. If yes, then end. If no, then execute step S408;

[0149] Step S408, import the deformation into the MATLAB program, calculate the change in the aerodynamic angle of attack caused by the change in the blade shape, that is, the aeroelastic torsion angle, and execute step S401.

[0150] The above steps of this embodiment use the BEM+correction method to construct an aerodynamic calculation model, and use APDL to construct a structural solution model of the blade, and then consider the torsional deformation of the blade under aerodynamic load and its influence on the aeroelastic response. Based on the two, a high-precision aeroelastic coupling model is obtained, which can improve the accuracy of the aerodynamic performance data of the blade, thereby improving the monitoring capability of the blade and reducing the probability of blade damage.

[0151] Through the description of the above implementation methods, those skilled in the art can clearly understand that the method according to the above embodiment can be implemented by means of software plus a necessary general hardware platform, and of course by hardware, but in many cases the former is a better implementation method. Based on such an understanding, the technical solution of the present application, or the part that contributes to the prior art, can be embodied in the form of a software product, which is stored in a storage medium (such as ROM / RAM, magnetic disk, optical disk), and includes a number of instructions for a terminal device (which can be a mobile phone, computer, server, or network device, etc.) to execute the methods of each embodiment of the present application.

[0152] In this embodiment, a device for determining aerodynamic performance data based on an aeroelastic coupling model is also provided, and the device is used to implement the above-mentioned embodiments and preferred implementation modes, and the descriptions that have been made will not be repeated. As used below, the term "module" can be a combination of software and / or hardware that implements a predetermined function. Although the devices described in the following embodiments are preferably implemented in software, the implementation of hardware, or a combination of software and hardware, is also possible and conceivable.

[0153] Figure 6 : is a structural block diagram of a device for determining aerodynamic performance data based on an aeroelastic coupling model according to an embodiment of the present application, the device comprising:

[0154] An acquisition module 602 is used to acquire blade deformation data obtained by monitoring the blades of the wind turbine, wherein the blade deformation data at least includes the unit parameters of the wind turbine, the wind field parameters of the wind field where the blade is located, the airfoil lift and drag coefficient of the blade, and the moment coefficient of the blade;

[0155] A calculation module 604, configured to calculate aerodynamic performance data corresponding to the blade based on the blade deformation data and an aerodynamic calculation model, wherein the aerodynamic performance data at least includes a surface force and a surface force moment of the blade;

[0156] An analysis module 606 is used to perform a static analysis on the surface force and the surface force moment using a structural solution model to obtain a deformation amount of a blade section of the blade corresponding to the structural solution model;

[0157] A first obtaining module 608 is configured to obtain an updated aerodynamic calculation model by updating the inflow angle of the blade required when the aerodynamic calculation model calculates the aerodynamic performance data corresponding to the blade using the aeroelastic torsion angle corresponding to the deformation, wherein the aeroelastic torsion angle represents a torsional deformation angle caused by the deformation of the blade;

[0158] The second obtaining module 610 is used to calculate and obtain the target aerodynamic performance data corresponding to the blade using the updated aerodynamic calculation model.

[0159] Through the above-mentioned device and the present application, the blade deformation data obtained by monitoring the blades of the power-generating wind turbine is obtained, wherein the blade deformation data at least includes the unit parameters of the power-generating wind turbine, the wind field parameters of the wind field where the blade is located, the airfoil lift and drag coefficient of the blade, and the moment coefficient of the blade; based on the blade deformation data and the aerodynamic calculation model, the aerodynamic performance data corresponding to the blade is calculated, and the aerodynamic performance data at least includes the surface force and the surface force moment of the blade; the surface force and the surface force moment are statically analyzed using the structural solution model to obtain the blade corresponding to the structural solution model. The deformation of the blade cross section; the inflow angle of the blade required when the aerodynamic calculation model is used to calculate the aerodynamic performance data corresponding to the blade by using the aeroelastic torsion angle corresponding to the deformation to obtain an updated aerodynamic calculation model, wherein the aeroelastic torsion angle represents the torsional deformation angle caused by the deformation of the blade; the target aerodynamic performance data corresponding to the blade is calculated using the updated aerodynamic calculation model, and a dynamic high-precision response aeroelastic model (i.e., an aeroelastic coupling model) under the aerodynamic-structural framework of the wind turbine is established considering the torsional deformation of the blade under aerodynamic loads and its influence on the aeroelastic response is established, and the dynamic behavior of the blade and the unit under time-varying loads is further studied. The technical problem of not being able to accurately determine the aerodynamic performance data when the blade is deformed is thereby solved, and the accuracy of the aerodynamic performance data when the blade is deformed is improved.

[0160] In an exemplary embodiment, the above-mentioned calculation module 604 is also used to generate the aerodynamic calculation model based on the blade element theory; use the initial induction factor iteration formula of the aerodynamic calculation model to perform iterative calculation, and when it is determined that the difference between two consecutive iterative calculation results is less than a preset difference, obtain the aerodynamic performance data corresponding to the current iterative calculation result.

[0161] In an exemplary embodiment, the calculation module 604 is also used to introduce correction factors into the blade element theory in the process of generating the aerodynamic calculation model based on the blade element theory, so as to establish a two-dimensional model of the blades of the wind turbine, and determine the two-dimensional model as the aerodynamic calculation model, wherein the correction factors include at least one of the following: blade tip correction factor, hub loss correction factor, and induced correction factor.

[0162] In an exemplary embodiment, the initial induction factor iteration formula is expressed as follows:

[0163] a=p1 / (1+p1), a′=p2 / (1-p2);

[0164]

[0165] Where a and a′ are the initial induction factor iteration formulas, N is the number of blades, F is the loss factor, r is the radial position of the blade, c is the chord length corresponding to the radial position of the blade, φ is the inflow angle, C L is a lift-drag coefficient of the blade airfoil, C D is another lift-drag coefficient of the airfoil of the blade.

[0166] In an exemplary embodiment, the calculation module 604 is further configured to obtain an updated induction factor iteration formula by updating a parameter p1 in the initial induction factor iteration formula when the axial flow induction factor of the blade is greater than a preset value;

[0167] Among them, the p1 is updated to H is the segmented control variable.

[0168] In an exemplary embodiment, the above-mentioned analysis module 606 is also used to input the geometric dimensions and blade shape parameters of the blade in the parameter definition area of ​​the model building platform before using the structural solution model to perform static analysis on the surface force and the surface force moment, so that the model building platform creates an initial geometric model of the blade and displays the initial geometric model in the display area; use the definition command provided by the model building platform to define the mechanical properties of the initial geometric model, the shell unit type of the initial geometric model, and the boundary conditions of the initial geometric model to update the initial geometric model and obtain the structural solution model.

[0169] An embodiment of the present application further provides a computer-readable storage medium, in which a computer program is stored, wherein the computer program is configured to execute the steps of any of the above method embodiments when running.

[0170] Optionally, in this embodiment, the storage medium may be configured to store a computer program for performing the following steps:

[0171] S1, obtaining blade deformation data obtained by monitoring blades of a power-generating wind turbine, wherein the blade deformation data at least includes unit parameters of the power-generating wind turbine, wind field parameters of a wind field where the blade is located, airfoil lift and drag coefficients of the blade, and moment coefficients of the blade;

[0172] S2, calculating aerodynamic performance data corresponding to the blade based on the blade deformation data and the aerodynamic calculation model, wherein the aerodynamic performance data at least includes the surface force and surface force moment of the blade;

[0173] S3, using the structural solution model to perform static analysis on the surface force and the surface force moment, to obtain a deformation amount of a blade cross section of the blade corresponding to the structural solution model;

[0174] S4, obtaining an updated aerodynamic calculation model by updating the inflow angle of the blade required for calculating the aerodynamic performance data corresponding to the blade by using the aeroelastic torsion angle corresponding to the deformation amount, wherein the aeroelastic torsion angle represents the torsional deformation angle caused by the deformation of the blade;

[0175] S5, using the updated aerodynamic calculation model to calculate and obtain target aerodynamic performance data corresponding to the blade.

[0176] In an exemplary embodiment, the computer-readable storage medium may include, but is not limited to, various media that can store computer programs, such as a USB flash drive, a read-only memory (ROM), a random access memory (RAM), a mobile hard disk, a magnetic disk or an optical disk.

[0177] For specific examples in this embodiment, reference may be made to the examples described in the above embodiments and exemplary implementation modes, and this embodiment will not be described in detail herein.

[0178] An embodiment of the present application further provides an electronic device, including a memory and a processor, wherein a computer program is stored in the memory, and the processor is configured to run the computer program to execute the steps in any one of the above method embodiments.

[0179] Optionally, in this embodiment, the processor may be configured to perform the following steps through a computer program:

[0180] S1, obtaining blade deformation data obtained by monitoring blades of a power-generating wind turbine, wherein the blade deformation data at least includes unit parameters of the power-generating wind turbine, wind field parameters of a wind field where the blade is located, airfoil lift and drag coefficients of the blade, and moment coefficients of the blade;

[0181] S2, calculating aerodynamic performance data corresponding to the blade based on the blade deformation data and the aerodynamic calculation model, wherein the aerodynamic performance data at least includes the surface force and surface force moment of the blade;

[0182] S3, using the structural solution model to perform static analysis on the surface force and the surface force moment, to obtain a deformation amount of a blade cross section of the blade corresponding to the structural solution model;

[0183] S4, obtaining an updated aerodynamic calculation model by updating the inflow angle of the blade required for calculating the aerodynamic performance data corresponding to the blade by using the aeroelastic torsion angle corresponding to the deformation amount, wherein the aeroelastic torsion angle represents the torsional deformation angle caused by the deformation of the blade;

[0184] S5, using the updated aerodynamic calculation model to calculate and obtain target aerodynamic performance data corresponding to the blade.

[0185] In an exemplary embodiment, the electronic device may further include a transmission device and an input / output device, wherein the transmission device is connected to the processor, and the input / output device is connected to the processor.

[0186] An embodiment of the present application further provides a computer program product, which includes a computer program. When the computer program is executed by a processor, the steps in any one of the above method embodiments are implemented.

[0187] An embodiment of the present application further provides another computer program product, including a non-volatile computer-readable storage medium, wherein the non-volatile computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the steps in any of the above method embodiments are implemented.

[0188] The embodiments of the present application also provide a computer program, which includes computer instructions, which are stored in a computer-readable storage medium; a processor of a computer device reads the computer instructions from the computer-readable storage medium, and the processor executes the computer instructions, so that the computer device executes the steps in any one of the above method embodiments.

[0189] For specific examples in this embodiment, reference may be made to the examples described in the above embodiments and exemplary implementation modes, and this embodiment will not be described in detail herein.

[0190] Obviously, those skilled in the art should understand that the above modules or steps of the present application can be implemented by a general computing device, they can be concentrated on a single computing device, or distributed on a network composed of multiple computing devices, they can be implemented by a program code executable by a computing device, so that they can be stored in a storage device and executed by the computing device, and in some cases, the steps shown or described can be executed in a different order from that herein, or they can be made into individual integrated circuit modules, or multiple modules or steps therein can be made into a single integrated circuit module for implementation. Thus, the present application is not limited to any specific combination of hardware and software.

[0191] The above is only a preferred implementation of the present application. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present application. These improvements and modifications should also be regarded as the scope of protection of the present application.

Claims

1. A method for determining aerodynamic performance data based on an aeroelastic coupling model, characterized in that: The aeroelastic coupling model at least includes an aerodynamic calculation model and a structural solution model, including: Acquiring blade deformation data obtained by monitoring blades of a power-generating wind turbine, wherein the blade deformation data at least includes unit parameters of the power-generating wind turbine, wind field parameters of a wind field where the blade is located, airfoil lift and drag coefficients of the blade, and moment coefficients of the blade; Calculating aerodynamic performance data corresponding to the blade based on the blade deformation data and the aerodynamic calculation model, wherein the aerodynamic performance data at least includes the surface force and the surface force moment of the blade; performing static analysis on the surface force and the surface force moment using the structural solution model to obtain the deformation amount of the blade section corresponding to the structural solution model; The updated aerodynamic calculation model is obtained by updating the inflow angle of the blade required when the aerodynamic calculation model calculates the aerodynamic performance data corresponding to the blade using the aeroelastic torsion angle corresponding to the deformation, wherein the aeroelastic torsion angle represents the torsion deformation angle caused by the deformation of the blade; The updated aerodynamic calculation model is used to calculate and obtain target aerodynamic performance data corresponding to the blade.

2. The method according to claim 1, characterized in that Calculating aerodynamic performance data corresponding to the blade based on the blade deformation data and the aerodynamic calculation model includes: Generate the aerodynamic calculation model based on blade element theory; Iterative calculation is performed using the initial induction factor iteration formula of the aerodynamic calculation model, and when it is determined that the difference between two consecutive iterative calculation results is less than a preset difference, aerodynamic performance data corresponding to the current iterative calculation result is obtained.

3. The method according to claim 2, characterized in that In the process of generating the aerodynamic calculation model based on blade element theory, the method further includes: A correction factor is introduced into the blade element theory to establish a two-dimensional model of the blades of the wind turbine, and the two-dimensional model is determined as the aerodynamic calculation model, wherein the correction factor includes at least one of the following: a blade tip correction factor, a hub loss correction factor, and an induced correction factor.

4. The method according to claim 2, characterized in that: The initial induction factor iteration formula is expressed as follows: a=p1 / (1+p1), a′=p2 / (1-p2); Among them, a and a′ are the initial induction factor iteration formulas, N is the number of blades, F is the loss factor, r is the radial position of the blade, c is the chord length corresponding to the radial position of the blade, φ is the inflow angle, C L is a lift-drag coefficient of the blade airfoil, C D is another lift-drag coefficient of the airfoil of the blade.

5. The method according to claim 4, characterized in that The method further comprises: When the axial flow induction factor of the blade is greater than a preset value, the parameter p1 in the initial induction factor iteration formula is updated to obtain an updated induction factor iteration formula; Among them, the p1 is updated to H is the segmented control variable.

6. The method according to claim 1, characterized in that Before using the structural solution model to perform static analysis on the surface force and the surface force moment, the method further includes: Inputting geometric dimensions and blade shape parameters of the blade in a parameter definition area of ​​the model building platform, so that the model building platform creates an initial geometric model of the blade, and displays the initial geometric model in a display area; The mechanical properties of the initial geometric model, the shell unit type of the initial geometric model, and the boundary conditions of the initial geometric model are defined using definition commands provided by the model building platform to update the initial geometric model and obtain the structural solution model.

7. A device for determining aerodynamic performance data based on an aeroelastic coupling model, characterized in that: include: An acquisition module, used to acquire blade deformation data obtained by monitoring the blades of the power generation wind turbine, wherein the blade deformation data at least includes the unit parameters of the power generation wind turbine, the wind field parameters of the wind field where the blade is located, the airfoil lift and drag coefficient of the blade, and the moment coefficient of the blade; a calculation module, used to calculate the aerodynamic performance data corresponding to the blade based on the blade deformation data and an aerodynamic calculation model, wherein the aerodynamic performance data at least includes the surface force and the surface force moment of the blade; An analysis module, used for performing a static analysis on the surface force and the surface force moment using a structural solution model to obtain a deformation amount of a blade section of the blade corresponding to the structural solution model; A first obtaining module is used to obtain an updated aerodynamic calculation model by updating the inflow angle of the blade required when the aerodynamic calculation model calculates the aerodynamic performance data corresponding to the blade using the aeroelastic torsion angle corresponding to the deformation, wherein the aeroelastic torsion angle represents the torsional deformation angle caused by the deformation of the blade; The second obtaining module is used to calculate and obtain the target aerodynamic performance data corresponding to the blade using the updated aerodynamic calculation model.

8. A computer-readable storage medium, characterized in that: The computer-readable storage medium includes a stored program, wherein the program executes the method according to any one of claims 1 to 6 when executed.

9. An electronic device comprising a memory and a processor, characterized in that: A computer program is stored in the memory, and the processor is configured to execute the method according to any one of claims 1 to 6 through the computer program.

10. A computer program product, comprising a computer program, characterized in that When the computer program is executed by a processor, the steps of the method described in any one of claims 1 to 6 are implemented.

Images