Blade aerodynamic performance analysis method, system, control device and storage medium

Abstract

The present application relates to the technical field of fan blades, and specifically provides a blade aerodynamic performance analysis method, system, control device and storage medium, aiming to solve the technical problem of low calculation accuracy when performing aerodynamic analysis on blades in the prior art. To this end, the blade aerodynamic performance analysis method of the present application includes: obtaining t of each blade element of the blade to be analyzed n Adhesion vortex strength; based on all t n The strength of the attached vortex determines the blade's t n Vorticity field; based on the preset airfoil database and t n Vorticity field, determine the blade element t n Aerodynamic loads; based on the preset beam model and t n Aerodynamic loads, determine the blade element t n Displacement; based on t n Aerodynamic loads and t n The present invention can analyze the aerodynamic force of flexible blades when they are greatly deformed, and at the same time improve the calculation accuracy of the aerodynamic elasticity of the blades, thereby providing accurate analysis data for analyzing the aerodynamic performance of the blades.

Description

Technical Field

[0001] The present application relates to the technical field of fan blades, and specifically provides a blade aerodynamic performance analysis method, system, control device and storage medium. Background Art

[0002] Blades are the most critical components in wind turbines. During the operation of wind turbines, wind turbine blades will be subjected to the coupling effects of aerodynamic force, inertial force and elastic force at the same time, causing the blades to produce multi-degree-of-freedom coupled vibrations and aggravating the nonlinear deformation of the blades.

[0003] With the trend of large-scale wind turbines, the length of blades has gradually developed into ultra-long flexible blades of hundreds of meters. The deformation of large wind turbine blades is often large, and the blade element momentum theory in traditional technology has large errors in calculating large deformation blades. In addition, with the rise of offshore floating wind turbines, the reliability of blade element momentum theory in calculating the aerodynamic load of blades under floating platforms has also been questioned. The lack of aerodynamic force calculation accuracy seriously affects the accuracy of blade aeroelastic analysis and seriously endangers the safety of unit operation.

[0004] Accordingly, the art requires a new blade aerodynamic performance analysis method, system, control device and storage medium solution to solve the above problems. Summary of the invention

[0005] In order to overcome at least one of the above-mentioned defects, the present application is proposed to provide a blade aerodynamic performance analysis method, system, control device and storage medium that solve or at least partially solve the technical problem of low calculation accuracy when performing aerodynamic analysis on blades in the prior art.

[0006] In a first aspect, the present application provides a method for analyzing aerodynamic performance of a blade, the method comprising:

[0007] Get the t of each leaf element of the leaf to be analyzed n Adhesion vortex strength, where the t n is the nth moment and 0≤n≤y;

[0008] Based on all the n The strength of the attached vortex determines the t of the blade n vorticity field;

[0009] Based on the preset airfoil database and the t n The vorticity field determines the t of the blade element n Aerodynamic loads;

[0010] Based on the preset beam model and the t n Aerodynamic load, determine the blade element t n Displacement;

[0011] Based on the n Aerodynamic loads and the t n displacement, and performing aerodynamic performance analysis on the blade.

[0012] In one technical solution of the above blade aerodynamic performance analysis method, when determining the t of the blade element, n After the displacement, the method further comprises:

[0013] Based on the t of all the leaf elements n displacement, and determine the attachment vortex strength of the blade element as t n+1 Attachment vortex strength;

[0014] The step of determining the vorticity field is performed to obtain the t of the blade. n+1 vorticity field;

[0015] The step of determining the aerodynamic load and displacement is performed to obtain the t of the blade element. n+1 Aerodynamic loads and t n+1 Displacement;

[0016] Repeat the steps of determining the attachment vortex strength, vorticity field, aerodynamic load and displacement until n=y;

[0017] Based on all the aerodynamic loads and all the displacements, an aerodynamic performance analysis is performed on the blade.

[0018] In a technical solution of the above-mentioned blade aerodynamic performance analysis method, the t of each blade element of the blade to be analyzed is obtained. n The strength of the attached vortex includes:

[0019] For each of the leaf elements, obtain the t of the leaf element n Relative inflow velocity;

[0020] Based on the preset blade parameters and the t n Relative inflow velocity, the blade element t n Attachment vortex strength;

[0021] Traverse all the leaf elements and obtain the t of each leaf element n Adhesion vortex strength.

[0022] In a technical solution of the above blade aerodynamic performance analysis method, for each blade element, the t of the blade element is obtained. n Relative inflow velocities include:

[0023] Get the t of the leaf element n-1 Displacement and t n-1 Induced velocity, where the t n-1 For the t n the moment before;

[0024] Based on the n-1 displacement, determine the t of the blade element n Spatial location;

[0025] Based on the preset incoming flow speed, the preset rotation speed, the t n The spatial position and the t n-1 The induction speed determines the t of the leaf element n Relative inflow velocity.

[0026] In a technical solution of the above-mentioned blade aerodynamic performance analysis method, the method further includes:

[0027] If n=0, then the t of the leaf element n-1 displacement and the t n-1 The induction speed is 0, and the t n The spatial position is the preset initial position.

[0028] In a technical solution of the above-mentioned blade aerodynamic performance analysis method, the preset airfoil database and the t n The vorticity field determines the t of the blade element n Aerodynamic loads include:

[0029] Based on the n The vorticity field determines the t of the blade element n Induction speed;

[0030] Based on the preset incoming flow speed, the preset rotation speed and the t n The induction speed determines the t of the leaf element n Angle of attack;

[0031] Modifying the preset airfoil database to obtain a modified airfoil database;

[0032] Based on the modified airfoil database and the t n Angle of attack, determine the t of the blade element n Aerodynamic load, where the t n The aerodynamic load includes at least the t of the blade element. n Tangential force and t n Normal force.

[0033] In a technical solution of the above blade aerodynamic performance analysis method, the preset beam model and the t n Aerodynamic load, determine the blade element t n Displacement includes:

[0034] Based on the preset beam model, a forced vibration equation is constructed, which can be expressed as Wherein, [M] is the preset mass matrix, [C] is the preset damping matrix, [K] is the preset stiffness matrix, and P(t) is the t n Aerodynamic load, is the t of the leaf element n Displacement acceleration, is the t of the leaf element n Displacement speed, x is the t of the blade element n Displacement distance;

[0035] Based on the empirical mode decomposition and the forced vibration equation, the dynamic response of the blade is determined to obtain the t of the blade element. n Displacement.

[0036] In a second aspect, the present application provides a blade aerodynamic performance analysis system, the system comprising:

[0037] An acquisition module is configured to acquire the t of each leaf element of the leaf to be analyzed. n Adhesion vortex strength, where the t n is the nth moment and 0≤n≤y;

[0038] A processing module, the processing module is configured to: based on all the t n The strength of the attached vortex determines the t of the blade n Vorticity field; Based on the preset airfoil database and the t n The vorticity field determines the t of the blade element n Aerodynamic loads; based on the preset beam model and the t n Aerodynamic load, determine the blade element t n Displacement;

[0039] An analysis module is configured to n Aerodynamic loads and the t n displacement, and performing aerodynamic performance analysis on the blade.

[0040] In a third aspect, a control device is provided, which includes a processor and a storage device, wherein the storage device is suitable for storing multiple program codes, and the program codes are suitable for being loaded and run by the processor to execute the blade aerodynamic performance analysis method described in any one of the technical solutions of the above-mentioned blade aerodynamic performance analysis method.

[0041] In a fourth aspect, a computer-readable storage medium is provided, wherein a plurality of program codes are stored therein, wherein the program codes are suitable for being loaded and run by a processor to execute the blade aerodynamic performance analysis method described in any one of the technical solutions of the above-mentioned blade aerodynamic performance analysis method.

[0042] The above one or more technical solutions of the present application have at least one or more of the following beneficial effects:

[0043] In the technical solution for implementing the present application, the vortex field of the blade is first determined, and then the aerodynamic load of each blade element on the blade is determined based on a preset airfoil database. Finally, the displacement of the blade element is determined based on a preset beam model, and the aerodynamic load data and displacement in the calculation process are used for the aerodynamic performance analysis of the blade. By calculating the vortex field of the blade, the interaction between the blade and the fluid can be accurately described, and the calculated vortex field includes the distribution and evolution in three-dimensional space so that the three-dimensional effect of the blade can be considered. Based on the vortex field, the precise aerodynamic load can be determined. By determining the displacement of the blade element, the performance of the blade under actual dynamic conditions, such as deformation, vibration, and interaction with other objects of the blade, can be described. Based on the precise aerodynamic load data and displacement, the aerodynamic performance analysis of the blade is performed to obtain precise analysis results.

[0044] Furthermore, in the implementation of the technical solution of the present application, by iteratively calculating the vortex field, aerodynamic load, and displacement of the blade, the actual aerodynamic performance and blade deformation can be gradually approached, and each iteration will be corrected according to the previous result, so that the calculation result is more accurate. Moreover, by repeating the iterative calculation, the force of the fluid on the blade and the influence of the blade deformation on the flow field can be gradually determined, thereby more accurately simulating the fluid-solid coupling phenomenon.

[0045] Furthermore, in the implementation of the technical solution of the present application, the complex blade structure can be simplified into a system with limited degrees of freedom by using a preset beam model, which simplifies the calculation process and makes the analysis of the dynamic response and deformation behavior of the blade more direct and efficient. By using the preset beam model, the nonlinear characteristics and boundary conditions of the material can be considered, so that the displacement of the blade can be accurately predicted when the blade is subjected to complex aerodynamic loads. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] The disclosure of the present application will become more easily understood with reference to the accompanying drawings. It is easy for those skilled in the art to understand that these drawings are only for illustrative purposes and are not intended to limit the scope of protection of the present application. In addition, similar numbers in the drawings are used to represent similar components, among which:

[0047] Figure 1 is a schematic flow chart of the main steps of a method for analyzing blade aerodynamic performance according to an embodiment of the present application;

[0048] Figure 2 is a schematic diagram of a program flow of a blade aerodynamic performance analysis method according to an embodiment of the present application;

[0049] Figure 3is a schematic diagram of a preset beam model according to an embodiment of the present application;

[0050] Figure 4 It is a schematic diagram of the main structure block diagram of a blade aerodynamic performance analysis device according to an embodiment of the present application.

[0051] Reference numerals list :

[0052] 11: Acquisition module; 12: Processing module; 13: Analysis module. DETAILED DESCRIPTION

[0053] Some embodiments of the present application are described below with reference to the accompanying drawings. Those skilled in the art should understand that these embodiments are only used to explain the technical principles of the present application and are not intended to limit the protection scope of the present application.

[0054] In the description of the present application, "module" and "processor" may include hardware, software or a combination of the two. A module may include hardware circuits, various suitable sensors, communication ports, memory, and may also include software parts, such as program code, or a combination of software and hardware. The processor may be a central processing unit, a microprocessor, an image processor, a digital signal processor or any other suitable processor. The processor has data and / or signal processing functions. The processor may be implemented in software, hardware or a combination of the two. Non-temporary computer-readable storage media include any suitable medium that can store program code, such as a disk, a hard disk, an optical disk, a flash memory, a read-only memory, a random access memory, etc. The term "A and / or B" means all possible combinations of A and B, such as only A, only B or A and B. The term "at least one A or B" or "at least one of A and B" has a similar meaning to "A and / or B" and may include only A, only B or A and B. The singular terms "one" and "the" may also include plural forms.

[0055] Please see attached Figure 1 , Figure 1 FIG. 1 is a flow chart of the main steps of a method for analyzing blade aerodynamic performance according to an embodiment of the present application. Figure 1 As shown, the blade aerodynamic performance analysis method in the embodiment of the present application mainly includes the following steps S1 to S5.

[0056] Step S1: Obtain the t of each leaf element of the leaf to be analyzed n Attachment vortex strength;

[0057] In this embodiment, the blade to be analyzed is a blade of a wind turbine generator set. The blade to be analyzed in this application can be an actual blade or a simulation model of an actual blade, which is not limited here. The lift line method is combined with the free vortex wake method, wherein the blade is simplified into an attached vortex line based on the lift line method, and the attached vortex line is used to equivalently replace the interference of the blade in space. Based on the free vortex wake method, the blade is discretized into a number of blade element segments, namely the blade elements in this application. Because the blade will move and deform under the influence of wind, analyzing it is a dynamic process, and it is necessary to consider the dimension of time. Here, t n is the nth moment and 0≤n≤y, where y is a positive integer.

[0058] The attached vortex strength refers to the strength of the attached vortex, wherein the attached vortex is a vortex flow field formed around the blade surface. In this embodiment, each blade element is attached to a vortex, and the attached vortex strength refers to the amount of circulation per unit length on the attached vortex line. Therefore, the attached vortex strength can be obtained in real time or simulated by a sensor, a simulation program, etc., or can be obtained through a certain calculation process.

[0059] In one embodiment, the step of obtaining the adhesion vortex strength may be: for each blade element, obtaining the t n Relative inflow velocity; based on preset blade parameters and t n Relative inflow velocity, the blade element t n Attachment vortex strength; traverse all blade elements and obtain the t of each blade element n Attachment vortex strength. In this embodiment, the blade parameters may include at least one of geometric parameters, performance parameters, and material properties; the relative inflow velocity refers to the projection velocity of the incoming flow velocity on the blade, that is, when the blade rotates around the axis, it will disturb the incoming flow, so that the incoming flow forms a flow field with uneven velocity around the blade. Each point on the blade will be affected by the velocity of the incoming flow, but due to the movement of the blade itself, the velocity of the incoming flow on the blade is not in one direction. Therefore, the relative inflow velocity is used to describe the incoming flow velocity at each point on the blade.

[0060] In another embodiment, the step of obtaining the relative inflow velocity may be: obtaining the t of the blade element n-1 Displacement and t n-1 Induced velocity, where t n-1 t n The previous moment; based on t n-1 displacement, determine the t of the blade element n Spatial position; based on preset flow velocity, preset rotation speed, t n Spatial position and t n-1 Induction speed, determine the t of leaf element nRelative inflow velocity. In this embodiment, blade element displacement refers to the motion trajectory of the blade element relative to its initial position during operation, which can be linear, nonlinear, translational or rotational; induced velocity refers to the change in the incoming flow velocity caused by blade movement. In this embodiment, if n = 0, i.e. the initial moment, then the t of the blade element n-1 Displacement and t n-1 The induced velocity is 0, and t n The spatial position is the preset initial position.

[0061] Step S2: Based on all t n The strength of the attached vortex determines the blade's t n vorticity field;

[0062] In this embodiment, the vorticity field refers to the spatial distribution of vorticity at a certain moment. When the attached vortex strength of each blade element is known, the vorticity field of the blade can be determined based on the Kutta-Joukowski theorem.

[0063] Step S3: Based on the preset airfoil database and t n Vorticity field, determine the blade element t n Aerodynamic loads;

[0064] The airfoil refers to the cross-sectional shape of the blade, and the airfoil database refers to a data set containing various airfoil shapes and their related parameters. In this embodiment, the preset airfoil data may be modified, for example, the two-dimensional airfoil database is modified using the BL dynamic stall model to obtain a preset airfoil database, which improves the simulation accuracy relative to the traditional static two-dimensional airfoil database. Aerodynamic load refers to the aerodynamic force acting on the blade, which at least includes lift (tangential force) and drag (normal force).

[0065] In one embodiment, the step of determining the aerodynamic load of the blade element may include: based on t n Vorticity field, determine the blade element t n Induced speed; based on the preset flow speed, preset rotation speed and t n Induction speed, determine the t of leaf element n Angle of attack; modify the preset airfoil database to obtain a modified airfoil database; based on the modified airfoil database and t n Angle of attack, determine the blade element t n Aerodynamic load, where t n The aerodynamic load includes at least the blade element t n Tangential force and t n Normal force.

[0066] Step S4: Based on the preset beam model and t n Aerodynamic loads, determine the blade element t n Displacement;

[0067] In this embodiment, the preset beam model may be an Euler beam model or a Timoshenko beam model, which is not limited here. When the Euler beam model is adopted, the mode decomposition method is used to solve the blade time domain deformation.

[0068] In one embodiment, the step of determining the blade element displacement may include: constructing a forced vibration equation based on a preset beam model, and the forced vibration equation may be represented as: Where [M] is the preset mass matrix, [C] is the preset damping matrix, [K] is the preset stiffness matrix, and P(t) is t n Aerodynamic loads, t n Displacement acceleration, t n Displacement velocity, x is the t of the blade element n Displacement distance; Based on the empirical mode decomposition and forced vibration equation, determine the dynamic response of the blade to obtain the t of the blade element n Displacement.

[0069] Step S5: Based on t n Aerodynamic loads and t n displacement, and conduct aerodynamic performance analysis on the blades;

[0070] In this embodiment, the aerodynamic load and displacement data at the current moment are collected to perform aerodynamic performance analysis. In one embodiment, aerodynamic load data and displacement data at multiple moments can also be obtained, and aerodynamic performance analysis can be performed using data at multiple moments to obtain more accurate analysis results: based on the t n displacement, determine the blade element's attachment vortex strength as t n+1 The strength of the attached vortex; the step of determining the vorticity field is performed to obtain the blade t n+1 Vorticity field; perform the steps of determining aerodynamic loads and displacements to obtain the t of the blade element n+1 Aerodynamic loads and t n+1 displacement; repeating the steps of determining the attachment vortex strength, vorticity field, aerodynamic load and displacement until n=y; performing aerodynamic performance analysis on the blade based on all aerodynamic loads and all displacements.

[0071] exist Figure 1 Based on the embodiments shown, please refer to the attached Figure 2 and attached Figure 3 ,in, Figure 2 is a schematic diagram of a program flow of a blade aerodynamic performance analysis method according to an embodiment of the present application, Figure 3 is a schematic diagram of a preset beam model according to an embodiment of the present application. Figure 2 and Figure 3 As shown, the program flow of the blade aerodynamic performance analysis method of the present application can be described as:

[0072] 1. Free vortex wake method and its correction part:

[0073] The lift line method is combined with the free vortex wake method, and the Kutta-Joukowski theorem is used to solve the attachment vortex strength after setting the incoming flow velocity:

[0074]

[0075] Γ bound is the strength of the attached vortex for each blade element, u rel is the blade relative inflow velocity, C l is the lift coefficient of the airfoil, c is the chord length of the airfoil, and Δl is the blade element length.

[0076] The spatial vorticity field evolving with time is solved according to Kelvin's theorem, and the induced velocity on each blade element is solved according to Bio-Savort's theorem:

[0077]

[0078] U induced is the induced velocity, Γ is the vortex intensity, dl is the vortex line length, and r is the distance between the node and the blade element in space.

[0079] The angle of attack is obtained according to the velocity distribution on the cross section. The two-dimensional airfoil database is modified based on the BL dynamic stall model. Based on the modified airfoil database, the corresponding relationship between the angle of attack and the airfoil lift is established to determine the normal force Ft and tangential force Fn of the blade element cross section.

[0080] 2. Solve the preset beam model part:

[0081] The blade is fixed on the hub, so it can be simplified into a cantilever beam. The continuous beam model is discretized into a beam model with N degrees of freedom. Its forced vibration equation can be written as follows:

[0082]

[0083] Among them, [M], [C], and [K] are the mass matrix, damping matrix, and stiffness matrix respectively; P(t) is the external force, that is, the normal force Ft and tangential force Fn of each blade element section together constitute the load column vector. is the acceleration of blade element deformation, is the speed of blade element deformation, and {x} is the distance of blade element deformation.

[0084] Because the mode of the beam is independent of the external force, the modal decomposition method can be used to solve the natural frequencies of the blades. Taking a single degree of freedom as an example, let the displacement of a point on the beam be X(x, t), and set X(x, t) = φ(x)Y(t). According to the cantilever beam node force balance equation and boundary conditions, the general solution of φ(x) is obtained.

[0085]

[0086] Among them, A1 is a constant, L is the cantilever beam length.

[0087] The displacement response of the system can be expressed by the vibration mode vector and the corresponding weight coefficient:

[0088] {X}=[φ]{η}

[0089] Substituting in and orthogonalizing, we get:

[0090]

[0091] By solving this equation, the motion response of the multi-degree-of-freedom system can be obtained.

[0092] Due to [M * ]、[C * ]、[K * ] are all diagonal matrices, so the above equation can be decoupled. For the i-th order vibration, the expression is as follows:

[0093]

[0094] Solve for the weight coefficient η of the i-th order i And by adding the vibration displacements of each mode, the motion response of the cantilever beam can be obtained.

[0095] 3. Iterative calculation part:

[0096] The tangential force coefficient Fn and normal force coefficient Ft obtained by the free vortex wake method at the current moment are introduced into the blade motion equation; the motion equation of each mode is solved to obtain the generalized coordinate (weight coefficient) η i The blade displacement at this time step can be obtained by superimposing the time domain solutions under all modes. The blade displacement (twist angle, position change in the blade element node space) is imported into the free vortex wake method calculation step to calculate the aerodynamic forces Fn and Ft after deformation. Repeat the above steps until the residual converges to the set value and enter the calculation of the next moment.

[0097] Based on the above steps S1 to S5, it can be known that the present application first determines the vortex field of the blade, then determines the aerodynamic load of each blade element on the blade based on a preset airfoil database, and finally determines the displacement of the blade element based on a preset beam model, and uses the aerodynamic load data and displacement in the calculation process for the aerodynamic performance analysis of the blade. By calculating the blade vortex field, the interaction between the blade and the fluid can be accurately described, and the calculated vortex field includes the distribution and evolution in three-dimensional space so that the three-dimensional effect of the blade can be considered, and the precise aerodynamic load can be determined based on the vortex field. By determining the displacement of the blade element, the performance of the blade under actual dynamic conditions, such as deformation, vibration, and interaction with other objects of the blade, can be described. Based on the precise aerodynamic load data and displacement, the aerodynamic performance analysis of the blade is performed to obtain precise analysis results.

[0098] It should be pointed out that although the various steps in the above embodiments are described in a specific order, those skilled in the art can understand that in order to achieve the effect of the present application, different steps do not have to be executed in such an order. They can be executed simultaneously (in parallel) or in other orders. These changes are within the scope of protection of the present application.

[0099] Furthermore, the present application also provides a blade aerodynamic performance analysis system.

[0100] See attached Figure 4 , Figure 4 FIG. 1 is a main structural block diagram of a blade aerodynamic performance analysis system according to an embodiment of the present application. Figure 4 As shown, the blade aerodynamic performance analysis system in the embodiment of the present application mainly includes an acquisition module 11, a processing module 12 and an analysis module 13. In some embodiments, one or more of the acquisition module 11, the processing module 12 and the analysis module 13 can be combined into one module. In some embodiments, the acquisition module 11 can be configured to acquire the t of each blade element of the blade to be analyzed. n Adhesion vortex strength, where the t n is the nth moment and 0≤n≤y. The processing module 12 may be configured to n The strength of the attached vortex determines the t of the blade n Vorticity field; Based on the preset airfoil database and the t n The vorticity field determines the t of the blade element n Aerodynamic loads; based on the preset beam model and the t n Aerodynamic load, determine the blade element t n The analysis module 13 may be configured to n Aerodynamic loads and the t n displacement, and performing aerodynamic performance analysis on the blade.

[0101] The blade aerodynamic performance analysis system is used to perform Figure 1 The blade aerodynamic performance analysis method embodiment shown in the figure has similar technical principles, technical problems solved and technical effects produced. Technicians in this technical field can clearly understand that for the convenience and conciseness of description, the specific working process and related instructions of the blade aerodynamic performance analysis system can refer to the contents described in the embodiment of the blade aerodynamic performance analysis method, which will not be repeated here.

[0102] It is understood by those skilled in the art that all or part of the processes in the method for implementing the above-mentioned embodiment of the present application can also be completed by instructing the relevant hardware through a computer program, and the computer program can be stored in a computer-readable storage medium. When the computer program is executed by the processor, the steps of each of the above-mentioned method embodiments can be implemented. Among them, the computer program includes computer program code, and the computer program code can be in source code form, object code form, executable file or some intermediate form. The computer-readable storage medium may include: any entity or device, medium, U disk, mobile hard disk, disk, optical disk, computer memory, read-only memory, random access memory, electric carrier signal, telecommunication signal and software distribution medium that can carry the computer program code. It should be noted that the content contained in the computer-readable storage medium can be appropriately increased or decreased according to the requirements of legislation and patent practice in the jurisdiction. For example, in some jurisdictions, according to legislation and patent practice, computer-readable storage media do not include electric carrier signals and telecommunication signals.

[0103] Furthermore, the present application also provides a control device. In a control device embodiment according to the present application, the control device includes a processor and a storage device, the storage device can be configured to store a program for executing the blade aerodynamic performance analysis method of the above method embodiment, and the processor can be configured to execute the program in the storage device, which includes but is not limited to the program for executing the blade aerodynamic performance analysis method of the above method embodiment. For ease of explanation, only the parts related to the embodiment of the present application are shown. For specific technical details not disclosed, please refer to the method part of the embodiment of the present application. The control device can be a control device device formed by various electronic devices.

[0104] Furthermore, the present application also provides a computer-readable storage medium. In a computer-readable storage medium embodiment according to the present application, the computer-readable storage medium can be configured to store a program for executing the blade aerodynamic performance analysis method of the above-mentioned method embodiment, and the program can be loaded and run by the processor to implement the above-mentioned blade aerodynamic performance analysis method. For ease of explanation, only the parts related to the embodiment of the present application are shown. For specific technical details not disclosed, please refer to the method part of the embodiment of the present application. The computer-readable storage medium can be a storage device formed by various electronic devices. Optionally, the computer-readable storage medium in the embodiment of the present application is a non-temporary computer-readable storage medium.

[0105] Further, it should be understood that since the setting of each module is only for illustrating the functional units of the device of the present application, the physical devices corresponding to these modules may be the processor itself, or a part of the software in the processor, a part of the hardware, or a part of the combination of software and hardware. Therefore, the number of each module in the figure is only schematic.

[0106] It is understood by those skilled in the art that each module in the device can be adaptively split or merged. Such splitting or merging of specific modules will not cause the technical solution to deviate from the principle of the present application, and therefore, the technical solutions after splitting or merging will fall within the protection scope of the present application.

[0107] So far, the technical solutions of the present application have been described in conjunction with the preferred embodiments shown in the accompanying drawings. However, it is easy for those skilled in the art to understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the protection scope of the present application.

Claims

1. A method for analyzing blade aerodynamic performance, characterized in that: The method comprises: Get the t of each leaf element of the leaf to be analyzed n The strength of the attached vortex, where t n is the nth moment and 0≤n≤y, where y is a positive integer; Based on all the n The strength of the attached vortex determines the t of the blade n vorticity field; Based on the preset airfoil database and the t n The vorticity field determines the t of the blade element n Aerodynamic loads; Based on the preset beam model and the t n Aerodynamic load, determine the blade element t n Displacement; Based on the t of all the leaf elements n displacement, and determine the attachment vortex strength of the blade element as t n+1 Attachment vortex strength; The step of determining the vorticity field is performed to obtain the t of the blade. n+1 vorticity field; The step of determining the aerodynamic load and displacement is performed to obtain the t of the blade element. n+1 Aerodynamic loads and t n+1 Displacement; Repeat the steps of determining the attachment vortex strength, vorticity field, aerodynamic load and displacement until n=y; Based on all the aerodynamic loads and all the displacements, performing an aerodynamic performance analysis on the blade; Performing aerodynamic performance analysis on the blade based on the aerodynamic loads at all times and the displacements at all times; The preset beam model is an Euler beam model, and the n Aerodynamic load, determine the blade element t n Displacement includes: Based on the Euler beam model, a forced vibration equation is constructed, which can be expressed as Wherein, [M] is the preset mass matrix, [C] is the preset damping matrix, [K] is the preset stiffness matrix, and P(t) is the t n Aerodynamic load, is the t of the leaf element n Displacement acceleration, is the t of the leaf element n Displacement speed, x is the t of the blade element n Displacement distance; Based on the empirical mode decomposition and the forced vibration equation, the dynamic response of the blade is determined to obtain the t of the blade element. n Displacement.

2. The blade aerodynamic performance analysis method according to claim 1, characterized in that: The method of obtaining the t of each leaf element of the leaf to be analyzed is as follows: n The strength of the attached vortex includes: For each of the leaf elements, obtain the t of the leaf element n Relative inflow velocity; Based on the preset blade parameters and the t n Relative inflow velocity, the blade element t n Attachment vortex strength; Traverse all the leaf elements and obtain the t of each leaf element n Attachment vortex strength.

3. The blade aerodynamic performance analysis method according to claim 2, characterized in that: For each of the leaf elements, obtain the t of the leaf element n Relative inflow velocities include: Get the t of the leaf element n-1 Displacement and t n-1 Induced velocity, where the t n-1 For the t n the moment before; Based on the n-1 displacement, determine the t of the blade element n Spatial location; Based on the preset incoming flow speed, the preset rotation speed, the t n The spatial position and the t n-1 The induction speed determines the t of the leaf element n Relative inflow velocity.

4. The blade aerodynamic performance analysis method according to claim 3, characterized in that: If n=0, then the t of the leaf element n-1 displacement and the t n-1 The induction speed is 0, and the t n The spatial position is the preset initial position.

5. The blade aerodynamic performance analysis method according to claim 1, characterized in that: The method is based on the preset airfoil database and the t n The vorticity field determines the t of the blade element n Aerodynamic loads include: Based on the n The vorticity field determines the t of the blade element n Induction speed; Based on the preset incoming flow speed, the preset rotation speed and the t n The induction speed determines the t of the leaf element n Angle of attack; Modifying the preset airfoil database to obtain a modified airfoil database; Based on the modified airfoil database and the t n Angle of attack, determine the t of the blade element n Aerodynamic load, where the t n The aerodynamic load includes at least the t n Tangential force and t n Normal force.

6. A blade aerodynamic performance analysis system, characterized in that: The system comprises: An acquisition module is configured to acquire the t of each leaf element of the leaf to be analyzed. n The strength of the attached vortex, where t n is the nth moment and 0≤n≤y, where y is a positive integer; A processing module, the processing module is configured to: based on all the t n The strength of the attached vortex determines the t of the blade n Vorticity field; Based on the preset airfoil database and the t n The vorticity field determines the t of the blade element n Aerodynamic loads; based on the preset beam model and the t n Aerodynamic load, determine the blade element t n Displacement; based on the t of all the blade elements n displacement, and determine the attachment vortex strength of the blade element as t n+1 Attachment vortex strength; Execute the step of determining the vorticity field to obtain the t of the blade n+1 Vorticity field; performing the step of determining the aerodynamic load and displacement to obtain the blade element t n+1 Aerodynamic loads and t n+1 displacement; repeating the steps of determining the attachment vortex strength, vorticity field, aerodynamic load and displacement until n=y; performing aerodynamic performance analysis on the blade based on all the aerodynamic loads and all the displacements; the preset beam model is an Euler beam model, and the preset beam model and the t n Aerodynamic load, determine the blade element t n The displacement includes: based on the Euler beam model, constructing a forced vibration equation, which can be expressed as Wherein, [M] is the preset mass matrix, [C] is the preset damping matrix, [K] is the preset stiffness matrix, and P(t) is the t n Aerodynamic load, is the t of the leaf element n Displacement acceleration, is the t of the leaf element n Displacement speed, x is the t of the blade element n displacement distance; based on the empirical mode decomposition and the forced vibration equation, determining the dynamic response of the blade to obtain the blade element t n Displacement; An analysis module is configured to perform aerodynamic performance analysis on the blade based on the aerodynamic loads at all times and the displacements at all times.

7. A control device, comprising a processor and a storage device, wherein the storage device is suitable for storing a plurality of program codes, characterized in that: The program code is suitable for being loaded and run by the processor to execute the blade aerodynamic performance analysis method according to any one of claims 1 to 5.

8. A computer-readable storage medium storing a plurality of program codes, characterized in that: The program code is suitable for being loaded and run by a processor to execute the blade aerodynamic performance analysis method according to any one of claims 1 to 5.

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