Blade deformation rapid evaluation method, system, electronic device and storage medium

Abstract

The application relates to the technical field of wind turbine units, and particularly provides a blade deformation rapid evaluation method and system, an electronic device and a storage medium, and aims to solve the technical problems of a complex calculation process and a long time consumption of an existing method. To this end, the blade deformation rapid evaluation method comprises the following steps: acquiring a previously constructed aeroelastic model and a tip loss coefficient database; constructing a first mapping relationship based on the aeroelastic model and the tip loss coefficient database, wherein the first mapping relationship represents a linear response relationship between a blade deformation amount and aerodynamic force; constructing a second mapping relationship based on the aeroelastic model and the tip loss coefficient database, wherein the second mapping relationship represents a linear response relationship between the aerodynamic force and the blade deformation amount; and determining a blade deformation evaluation result based on the first mapping relationship and the second mapping relationship. The application can rapidly evaluate the deformation of a blade under different wind speed conditions, and effectively reduces the calculation amount.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of wind turbine, in particular to a blade deformation rapid evaluation method and system, electronic equipment and storage medium. BACKGROUND

[0002] With the growing demand for renewable energy worldwide, wind power has been rapidly developed as a clean and sustainable energy solution. In this context, as the core component of wind turbine to capture wind energy, the aspect ratio of the blade is increasing, which leads to a significant increase in structural flexibility, making the blade more prone to bending and twisting deformation when facing complex environmental conditions such as strong winds and turbulence. The dynamic response of the blade under wind load, including bending, twisting and vibration, not only leads to a decline in aerodynamic performance, but also may cause structural fatigue problems, and even cause failure in severe cases, thereby bringing safety hazards and economic losses. Therefore, how to accurately evaluate the deformation characteristics of flexible blades under different operating conditions has become a key challenge. At present, there are many methods to try to solve this problem, but these methods generally have high computational complexity and long time-consuming problems, which are difficult to be widely applied in engineering practice.

[0003] Accordingly, there is a need in the art for a new blade deformation rapid evaluation scheme to solve the above problems. SUMMARY

[0004] In order to overcome the above defects, the present application is proposed to solve or at least partially solve the technical problems of high computational complexity and long time-consuming of the prior art.

[0005] In a first aspect, a blade deformation rapid evaluation method is provided, the method comprising: obtaining a pre-constructed aeroelastic model and a tip loss coefficient database; constructing a first mapping relationship based on the aeroelastic model and the tip loss coefficient database, the first mapping relationship representing a linear response relationship between blade deformation and aerodynamic force; constructing a second mapping relationship based on the aeroelastic model and the tip loss coefficient database, the second mapping relationship representing a linear response relationship between aerodynamic force and blade deformation; determining a blade deformation evaluation result based on the first mapping relationship and the second mapping relationship.

[0006] In a technical solution of the above blade deformation rapid evaluation method, the first mapping relationship is constructed based on the aeroelastic model and the tip loss coefficient database, including: obtaining a first initial blade deformation amount, the first initial blade deformation amount representing the geometric shape of the blade in the undeformed state; based on the first initial blade deformation amount, the first initial aerodynamic force, the first blade deformation amount and the first corrected aerodynamic force are determined by using the aeroelastic model and the blade loss coefficient database; a first mapping relationship is established based on the first initial blade deformation amount, the first initial aerodynamic force, the first blade deformation amount and the first corrected aerodynamic force by using a linear fitting method.

[0007] In a technical solution of the above blade deformation rapid evaluation method, the aeroelastic model includes an aerodynamic model constructed based on the blade element momentum theory and a structural model constructed based on the geometric precise beam theory; the first initial aerodynamic force, the first blade deformation amount and the first corrected aerodynamic force are determined based on the first initial blade deformation amount by using the aeroelastic model and the tip loss coefficient database, including: the first initial aerodynamic force is determined based on the first initial blade deformation amount by using the aerodynamic model; the first blade deformation amount is determined based on the first initial aerodynamic force by using the structural model; the tip loss coefficient corresponding to the first blade deformation amount is determined by using a linear interpolation method based on the first blade deformation amount and the tip loss coefficient database; the first corrected aerodynamic force is determined based on the tip loss coefficient corresponding to the first blade deformation amount by using the aerodynamic model.

[0008] In a technical solution of the above blade deformation rapid evaluation method, the second mapping relationship is constructed based on the aeroelastic model and the tip loss coefficient database, including: the second initial aerodynamic force is determined by using the aeroelastic model, the second initial aerodynamic force representing the aerodynamic force of the blade in the undeformed state; the second initial blade deformation amount, the second aerodynamic force and the second blade deformation amount are determined based on the second initial aerodynamic force by using the aeroelastic model and the tip loss coefficient database; a second mapping relationship is established based on the second initial aerodynamic force, the second initial blade deformation amount, the second aerodynamic force and the second blade deformation amount by using a linear fitting method.

[0009] In one of the technical solutions of the above blade deformation rapid evaluation method, the aeroelastic model comprises an aerodynamic model constructed based on blade element momentum theory and a structural model constructed based on geometrically exact beam theory; the second initial blade deformation, the second aerodynamic force and the second blade deformation are determined based on the second initial aerodynamic force by using the aeroelastic model and a tip loss coefficient database, comprising: the second initial blade deformation is determined based on the second initial aerodynamic force by using the structural model; the second tip loss coefficient is determined based on the second initial blade deformation and the tip loss coefficient database by using a linear interpolation method; the second aerodynamic force is determined based on the second tip loss coefficient by using the aerodynamic model; the second blade deformation is determined based on the second aerodynamic force by using the structural model.

[0010] In one of the technical solutions of the above blade deformation rapid evaluation method, the blade deformation evaluation result is determined based on the first mapping relationship and the second mapping relationship, comprising: the aerodynamic force equation and the deformation equation are determined based on the first mapping relationship and the second mapping relationship; the aerodynamic force equation and the deformation equation are solved simultaneously to obtain the target blade deformation as the blade deformation evaluation result.

[0011] In one of the technical solutions of the above blade deformation rapid evaluation method, the aerodynamic force equation and the deformation equation are solved simultaneously to obtain the target blade deformation, comprising: the aerodynamic force equation and the deformation equation are solved simultaneously to obtain:

[0012]

[0013] ω = m2F + b2

[0014] wherein, b1 = F1, b2 = ω1 - m2F1, ω0 is the first initial blade deformation; ω1 is the first blade deformation; ω2 is the second blade deformation; F1 is the first initial aerodynamic force; F2 is the first corrected aerodynamic force; F is the target aerodynamic force; ω is the target blade deformation; the target blade deformation is determined by calculating the balance solution of the aerodynamic force and the blade deformation based on the simultaneous equations.

[0015] In a second aspect, a blade deformation rapid evaluation system is provided, and the system comprises: an acquisition module configured to acquire a pre-constructed aeroelastic model and a tip loss coefficient database; a first mapping relationship construction module configured to construct a first mapping relationship based on the aeroelastic model and the tip loss coefficient database, the first mapping relationship representing a linear response relationship between a blade deformation amount and an aerodynamic force; a second mapping relationship construction module configured to construct a second mapping relationship based on the aeroelastic model and the tip loss coefficient database, the second mapping relationship representing a linear response relationship between the aerodynamic force and the blade deformation amount; and a determination module configured to determine a blade deformation evaluation result based on the first mapping relationship and the second mapping relationship.

[0016] In a third aspect, an electronic device is provided, which comprises at least one processor; and a memory connected to the at least one processor in communication; wherein the memory stores a computer program, and the computer program is executed by the at least one processor to implement the method of any one of the technical solutions of the blade deformation rapid evaluation method.

[0017] In a fourth aspect, a computer readable storage medium is provided, which stores a plurality of program codes therein, and the program codes are adapted to be loaded and run by a processor to execute the method of any one of the technical solutions of the blade deformation rapid evaluation method.

[0018] The one or more technical solutions of the present application have at least one or more of the following beneficial effects:

[0019] The blade deformation rapid evaluation method provided by the present application comprises: acquiring a pre-constructed aeroelastic model and a tip loss coefficient database; constructing a first mapping relationship based on the aeroelastic model and the tip loss coefficient database, the first mapping relationship representing a linear response relationship between a blade deformation amount and an aerodynamic force; constructing a second mapping relationship based on the aeroelastic model and the tip loss coefficient database, the second mapping relationship representing a linear response relationship between the aerodynamic force and the blade deformation amount; and determining a blade deformation evaluation result based on the first mapping relationship and the second mapping relationship. The present application establishes a bidirectional linear mapping relationship (deformation amount→aerodynamic load, aerodynamic load→deformation amount) through the pre-constructed aeroelastic model and the tip loss coefficient database, realizes rapid closed-loop feedback of the deformation evaluation process, can rapidly evaluate the deformation of the blade under different wind speed conditions, effectively reduces the calculation amount, and provides data support for the development of wind power technology to a larger scale and more complex working conditions. BRIEF DESCRIPTION OF DRAWINGS

[0020] The disclosure of the present application will become more apparent with reference to the drawings. As can be readily appreciated by one skilled in the art, the drawings are only for purposes of illustration and are not intended to limit the scope of protection of the present application. Among them:

[0021] Figure 1 is a schematic diagram of the main steps of the blade deformation rapid evaluation method according to an embodiment of the present application;

[0022] Figure 2 is a schematic diagram of the velocity synthesis relationship and aerodynamic force under the condition of blade element rotation according to an embodiment of the present application;

[0023] Figure 3 is a schematic diagram of the beam deformation state according to an embodiment of the present application;

[0024] Figure 4 is a schematic diagram of the blade simplified as a beam model according to an embodiment of the present application;

[0025] Figure 5 is a schematic diagram of the relationship between the blade deformation and the aerodynamic force according to an embodiment of the present application;

[0026] Figure 6 is a schematic diagram of the relationship between the aerodynamic force and the blade deformation according to another embodiment of the present application;

[0027] Figure 7 is a schematic diagram of the main structure of the blade deformation rapid evaluation system according to an embodiment of the present application;

[0028] Figure 8 is a schematic diagram of the main structure of the electronic device according to an embodiment of the present application.

[0029] Reference signs:

[0030] 11: memory; 12: processor; 71: acquisition module; 72: first mapping relationship construction module; 73: second mapping relationship construction module; 74: determination module. DETAILED DESCRIPTION

[0031] Some embodiments of the present application will be described below with reference to the 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 scope of protection of the present application.

[0032] In the description of the present application, "module", "processor" can include hardware, software or a combination of both. A module can include hardware circuits, various suitable sensors, communication ports, memories, and can also include software parts such as program codes, and can be a combination of software and hardware. The processor can be a central processor, 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 can be implemented in software, hardware or a combination of both. The computer readable storage medium includes any suitable medium that can store program codes, such as magnetic disk, hard disk, optical disk, flash memory, read-only memory, 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 as "A and / or B", which can include only A, only B or A and B. The singular form of the term "one", "this" can also include the plural form.

[0033] With the gradual development of wind turbines towards large-scale, the aspect ratio of the blade is increasing, which leads to a significant increase in structural flexibility, making the blade more prone to bending and torsional deformation when facing complex environmental conditions such as strong winds and turbulence. The dynamic response of the blade under wind load, including bending, torsion and vibration, not only leads to a decline in aerodynamic performance, but also may cause structural fatigue problems, and in severe cases, even cause failure, thereby bringing safety hazards and economic losses. Therefore, how to accurately evaluate the deformation characteristics of flexible blades under different operating conditions has become a key challenge. At present, there are many methods to try to solve this problem, but these methods generally have high computational complexity and long time-consuming problems, which are difficult to be widely applied in engineering practice.

[0034] Therefore, the blade deformation rapid evaluation method provided by the present application includes: obtaining a pre-constructed aeroelastic model and a tip loss coefficient database; constructing a first mapping relationship based on the aeroelastic model and the tip loss coefficient database, the first mapping relationship representing a linear response relationship between blade deformation and aerodynamic force; constructing a second mapping relationship based on the aeroelastic model and the tip loss coefficient database, the second mapping relationship representing a linear response relationship between aerodynamic force and blade deformation; determining a blade deformation evaluation result based on the first mapping relationship and the second mapping relationship. The present application establishes a two-way linear mapping relationship (blade deformation→aerodynamic load, aerodynamic load→blade deformation) through the pre-constructed aeroelastic model and the tip loss coefficient database, realizes the rapid closed-loop feedback of the deformation evaluation process, can quickly evaluate the deformation of the blade under different wind speed conditions, effectively reduces the calculation amount, and provides data support for the development of wind power technology to larger scale and more complex working conditions.

[0035] Referring to the drawings Figure 1, Figure 1 is a main step flow diagram of a blade deformation rapid evaluation method according to an embodiment of the present application. As shown in Figure 1 , the blade deformation rapid evaluation method in the embodiment is suitable for rapid evaluation of flexible blade deformation, and mainly includes the following steps S101 to S104.

[0036] Step S101: Obtain a pre-constructed aeroelastic model and a tip loss coefficient database;

[0037] In the embodiment, the aeroelastic model includes an aerodynamic model constructed based on blade element momentum theory and a structural model constructed based on geometrically exact beam theory, and the tip loss coefficient database includes multiple sets of deformation amplitudes and corresponding tip loss coefficients.

[0038] Step S102: Construct a first mapping relationship based on the aeroelastic model and the tip loss coefficient database, the first mapping relationship representing a linear response relationship between blade deformation and aerodynamic force.

[0039] In the embodiment, the first mapping relationship (tip deformation amplitude→aerodynamic force) is used to describe the influence of tip deformation amplitude on aerodynamic force.

[0040] Step S103: Construct a second mapping relationship based on the aeroelastic model and the tip loss coefficient database, the second mapping relationship representing a linear response relationship between aerodynamic force and blade deformation;

[0041] In the embodiment, the second mapping relationship (aerodynamic force→tip deformation amplitude) is used to describe the influence of aerodynamic force on tip deformation amplitude.

[0042] Step S104: Determine a blade deformation evaluation result based on the first mapping relationship and the second mapping relationship.

[0043] Based on the method described in steps S101 to S104 above, the present application establishes a first mapping relationship (blade deformation amplitude→aerodynamic force) and a second mapping relationship (aerodynamic force→blade deformation amplitude) through a pre-constructed aeroelastic model and a tip loss coefficient database, realizes rapid closed-loop feedback of the deformation evaluation process, can rapidly evaluate blade deformation under different wind speed conditions, effectively reduces the amount of calculation, and provides data support for the development of wind power technology to larger scale and more complex working conditions.

[0044] The above steps S101 to S104 will be further described below.

[0045] For step S101, a pre-constructed aeroelastic model and a tip loss coefficient database are obtained.

[0046] Specifically, before implementing the blade deformation rapid evaluation method of the application, the aeroelastic model of the wind turbine blade is constructed in combination with the blade element momentum theory (BEM), the geometric exact beam theory (GEBT) and the tip loss factor, and the tip loss coefficient database is constructed by using the CFD numerical simulation method.

[0047] Specifically, the aerodynamic model is constructed based on the blade element momentum theory (BEM) and the tip loss factor is introduced, and the following assumptions are made:

[0048] The wind wheel is simplified as a plane disc composed of infinite blades;

[0049] The incoming flow is uniform and constant, i.e. the air compressibility is not considered;

[0050] The radial blade elements are independent of each other, there is no force between them and the radial flow of the flow field particles is ignored;

[0051] The influence of the wake induced velocity is ignored.

[0052] The axial velocity and the tangential velocity of the airflow will change after the airflow passes through the blade and the rotation plane of the wind wheel, and the axial induction factor a and the tangential induction factor b are introduced to reflect the reduction of the velocity of the airflow passing through the wind wheel.

[0053] Based on the axial induction factor a and the tangential induction factor b, the velocity synthesis relationship is established:

[0054]

[0055] Wherein, V is the free incoming flow velocity; φ is the incoming flow angle; Ω is the wind wheel speed; a is the axial induction factor; b is the tangential induction factor; r is the radius of the blade position where the blade element is located.

[0056] The velocity synthesis relationship and the aerodynamic force under the condition of blade element rotation are as shown in Figure 2 .

[0057] The relationship between the incoming flow angle φ and the attack angle α and the pitch angle β is defined as

[0058] α = φ - β

[0059] Wherein, α is the attack angle; φ is the incoming flow angle; β is the pitch angle.

[0060] The expression of the blade element micro-element lift dF l and the blade element micro-element resistance dF d is:

[0061]

[0062] Wherein, ρ is the air density, W is the incoming flow velocity, C is the chord length, C L is the airfoil lift coefficient, CD where C is the airfoil drag coefficient, and r is the radius at the blade position where the element is located.

[0063] The lift and drag forces on the element are decomposed into the plane of rotation of the wind turbine and the direction perpendicular to the plane of rotation of the wind turbine to obtain the normal force F n and the tangential force F t on the element:

[0064]

[0065] where C n is the normal force coefficient, and C t is the tangential force coefficient, which are expressed as:

[0066] C n = C L cos φ + C D sin φ

[0067] C t = C L sin φ - C D cos φ

[0068] The thrust and torque on the element at a distance r from the center of the wind turbine can be calculated by:

[0069]

[0070] where dT 叶素 is the thrust on the element, dM 叶素 is the torque on the element, and B is the number of blades.

[0071] According to the momentum theorem, the thrust and torque on a micro-element ring with a width of dr at a radius r of the wind turbine are:

[0072] dT 动量 = 4πρV 2 (1 - a)arbdr

[0073] dM 动量 = 4πρVΩ(1 - a)br 3 dr

[0074] But in reality, due to the limited number of fan blades, the blade disc will produce tip vortex shedding, and a part of the air flow from the lower surface of the blade to the upper surface, thus causing the secondary flow phenomenon of the inflow near the tip. The existence of these tip vortices makes the aerodynamic performance near the tip decrease sharply, and at this time the blade element momentum theory no longer meets the calculation requirements of the aerodynamic force near the blade tip. The energy loss caused by the tip vortex shedding will reduce the output power of the wind wheel. In order to make up for the calculation error caused by the tip vortex shedding, the concept of Prandtl tip loss factor is introduced. The tip loss factor F is expressed as:

[0075]

[0076] The tip loss factor F is applied to the thrust and torque equations of the momentum theorem to obtain the modified momentum equation:

[0077] dT 动量 =4πρV 2 (1-a)arFdr

[0078] dM 动量 =4πρVΩ(1-a)br 3 Fdr

[0079] Using dT 叶素 =dT 动量 , dM 叶素 =dM 动量 , the axial induction factor and the tangential induction factor are obtained as follows:

[0080]

[0081] In the calculation, first, the axial induction factor a and the tangential induction factor b are initialized, assuming a = b = 0; then the inflow angle φ is calculated according to the velocity synthesis relationship. After obtaining the inflow angle φ, the corresponding attack angle α of the airfoil is obtained, and the lift and drag coefficients under the corresponding attack angle are obtained by referring to the airfoil data table, so as to obtain the corresponding normal force coefficient and tangential force coefficient. The normal force coefficient, tangential force coefficient and inflow angle are substituted into the above a, b solving formula to obtain the axial induction factor a and the tangential induction factor b, and thus one iteration process is completed. Repeat this process until a and b converge. Then substitute the converged axial induction factor a and tangential induction factor b back into the thrust and torque formula of the micro-element ring to calculate the aerodynamic force on the blade element, and integrate the aerodynamic force on the blade element along the blade span to obtain the aerodynamic load on the blade and the wind wheel.

[0082] Based on the geometric exact beam theory (GEBT), a structural model is constructed, and the blade is simplified as a beam element, and the beam deformation state is shown in Figure 3 The nonlinear motion control equation of the geometric exact beam theory is as follows:

[0083]

[0084] where h and g are the linear and angular momentum in the inertial frame; F and M are the cross-sectional force and moment; u is the linear displacement of a point on the reference line; x0 is the position vector of the reference line point along the beam; f and m are the distributed force and moment applied on the beam structure; T is the transpose operator; the notation F' denotes the derivative with respect to the axial displacement; denotes the derivative with respect to time; the wavy operator defines the skew-symmetric tensor corresponding to the given vector.

[0085] The constitutive equations relate the velocity to the momentum and the one-dimensional strain measure to the cross-sectional result.

[0086]

[0087] where M is the 6x6 cross-sectional mass matrix and C is the 6x6 cross-sectional stiffness matrix; ε and k are the one-dimensional strain and curvature, respectively; ω is the angular velocity vector defined by the rotation tensor R, where ω = a x axial(RR T ), the vector a is associated with the second-order tensor A whose components are defined as:

[0088]

[0089] The one-dimensional strain ε and curvature k are defined as:

[0090]

[0091] where K = a x axial(RR0)'(RR0) T ) is the cross-sectional curvature vector decomposed in the inertial basis; x'0 is the derivative of the initial position vector with respect to the s-axis; u' is the derivative of the displacement vector with respect to the s-axis; R is the current rotation tensor and R0 is the initial rotation tensor; li is the unit vector in the xi direction in the inertial basis. The above equations collectively form the mathematical description of the geometrically exact beam elasticity problem.

[0092] The nonlinear governing equations of motion for the beam are solved by the Newton-Raphson method and the incremental equations are discretized by the Legendre spectral finite element method. The linearized form of the nonlinear governing equations of motion is given as follows:

[0093]

[0094] where, is the element mass matrix; is the rotation matrix; is the stiffness matrix; is the generalized element acceleration; is the generalized velocity, The generalized node displacement array increment; is expressed as an externally applied load; is expressed as an element force.

[0095] The time integration is calculated by using a generalized alpha time integrator:

[0096] |ΔU (i)T ( t+Δt R- t+Δt F (i-1) )|≤|ε E [ΔU (1)T ( t+Δt R- t F)]|

[0097] where ΔU is the increment of displacement vector, R is the externally applied node load vector; F is the node force vector corresponding to the internal element stress, ε E is the preset energy tolerance, the superscript on the left side of the variable indicates the time value, and the right side indicates the iteration number.

[0098] The three-dimensional rotation of the geometrically accurate beam theory can be expressed as Wiener-Milenkovic parameters, which are expressed by the following equation:

[0099]

[0100] where, is the rotation angle, and n is the unit vector of the rotation axis.

[0101] By simplifying the wind turbine blade into a beam element, inputting the corresponding structural parameters, and numerically realizing the node freedom through Legendre spectrum finite element, the trapezoidal integration method is used to model the wind turbine blade with a single element, and the Wiener-Milenkovic parameter is used to represent the three-dimensional rotation to obtain the linear displacement and angular displacement of each node of the blade. Secondly, the nonlinear motion control equation is solved by Newton-Raphson, and after linearization, the generalized alpha time integrator is used to determine whether the equation converges. The blade is simplified as a beam model as shown in Figure 4 .

[0102] The percentage of deformation variable is:

[0103]

[0104] where ω is the tip deformation, and l is the total length of the blade.

[0105] The construction of the tip loss coefficient database includes the following steps:

[0106] A plurality of groups of preset deformation amount blade geometry models are generated, each group of models corresponding to a different blade tip deformation amplitude value, and a corresponding CFD calculation grid is divided in the fluid domain; an unsteady CFD numerical simulation is performed on each deformation amount model to obtain the aerodynamic force corresponding to each deformation amount model; the aerodynamic force of each deformation amount model is divided by the aerodynamic force of the undeformed baseline model to generate an initial tip loss coefficient corresponding to each preset deformation amount; a correspondence between deformation amount and tip loss coefficient is established, and based on the simulation data of adjacent preset deformation amounts, a linear interpolation algorithm is used to calculate the tip loss coefficient corresponding to the intermediate deformation amount, forming continuous loss coefficient distribution data, and obtaining a tip loss coefficient database.

[0107] For adjacent known points (ω i , F extra(i) ), (ω i+1 , F extra(i+1) ), when the blade tip deformation amplitude ω is in the interval (ω i , ω i+1 ), the interpolation formula is:

[0108]

[0109] where ω is an arbitrary deformation amplitude in the interval (ω i , ω i+1 ).

[0110] For step S102, in one embodiment, the first mapping relationship is constructed based on the aeroelastic model and the tip loss coefficient database, including: obtaining a first initial blade deformation amount, the first initial blade deformation amount representing the geometric shape of the blade in the undeformed state; based on the first initial blade deformation amount, using the aeroelastic model and the blade loss coefficient database, determining a first initial aerodynamic force, a first blade deformation amount and a first corrected aerodynamic force; using a linear fitting method, based on the first initial blade deformation amount, the first initial aerodynamic force, the first blade deformation amount and the first corrected aerodynamic force, a first mapping relationship is established.

[0111] In one embodiment, the aeroelastic model comprises an aerodynamic model constructed based on blade element momentum theory and a structural model constructed based on geometrically exact beam theory; and the determining, based on the first initial blade deformation, the first initial aerodynamic force, the first blade deformation and the first corrected aerodynamic force by using the aeroelastic model and the tip loss coefficient database comprises: determining the first initial aerodynamic force by using the aerodynamic model based on the first initial blade deformation; determining the first blade deformation by using the structural model based on the first initial aerodynamic force; determining the tip loss coefficient corresponding to the first blade deformation by using a linear interpolation method based on the first blade deformation and the tip loss coefficient database; and determining the first corrected aerodynamic force by using the aerodynamic model based on the tip loss coefficient corresponding to the first blade deformation.

[0112] Specifically, when the blade has not been deformed, the blade deformation is 0, and the blade deformation is defined as the first initial blade deformation ω0, and the first initial aerodynamic force F1, the first blade deformation ω1 and the first corrected aerodynamic force F2 are calculated by using the aeroelastic model and the blade loss coefficient database based on the first initial blade deformation.

[0113] Specifically, the first initial aerodynamic force F1 is calculated by using the aerodynamic model based on the first initial blade deformation ω0, the blade will be deformed under the action of the first initial aerodynamic force F1, the first blade deformation ω1 under the action of the first initial aerodynamic force F1 is calculated by using the structural model, and the tip loss coefficient F extra under the first blade deformation ω1 is calculated by using an interpolation formula based on the first blade deformation ω1 and the tip loss coefficient database.

[0114] And the new values of the axial induction factor a and the tangential induction factor b are calculated by using the tip loss coefficient F extra

[0115]

[0116] F(r) = F extra *F, F(r) is the tip loss coefficient F extra and the tip loss factor F.

[0117] The new values of a and b are compared with the values of a and b in the previous iteration, if the new values of a and b are within the error range compared with the values of a and b in the previous iteration, the new values are taken; if not, the new values of a and b are taken as the values of a and b in the previous iteration, the new values of the axial induction factor a and the tangential induction factor b are recalculated, and the iteration is continued.

[0118] ​Based on the determined axial induction factor a and tangential induction factor b, the aerodynamic force on the blade element is calculated by substituting into the force and torque formulas of the micro-element ring. The aerodynamic load on the blade and the wind wheel is obtained by integrating the aerodynamic force on the blade element along the blade span, and the first corrected aerodynamic force F2 is obtained. At this time, two groups of data can be obtained: (ω0, F1), (ω1, F2). The relationship between the blade deformation and the aerodynamic force is as shown in Figure 5

[0119] Assuming that the relationship between the aerodynamic force and the deformation is linear, the first mapping relationship, i.e., the relationship between the blade deformation and the aerodynamic force, is established by a linear fitting method. The first mapping relationship is:

[0120] F = m1ω + b1

[0121] F1 = m1ω0 + b1

[0122] F2 = m1ω1 + b1

[0123] Wherein, F is the aerodynamic force, m1 and b1 are coefficients, ω is the blade deformation, F1 is the first initial aerodynamic force, ω0 is the first initial blade deformation, ω1 is the first blade deformation, and F2 is the first corrected aerodynamic force.

[0124] The two groups of data (ω0, F1) and (ω1, F2) are substituted into the first mapping relationship to solve the coefficients m1 and b1 of the first mapping relationship.

[0125] For step S103, in an embodiment, the second mapping relationship is constructed based on the aeroelastic model and the tip loss coefficient database, comprising: adopting the aeroelastic model to determine a second initial aerodynamic force, the second initial aerodynamic force representing the aerodynamic force of the blade in the undeformed state; based on the second initial aerodynamic force, adopting the aeroelastic model and the tip loss coefficient database to determine a second initial blade deformation, a second aerodynamic force and a second blade deformation; and adopting a linear fitting method to establish a second mapping relationship based on the second initial aerodynamic force, the second initial blade deformation, the second aerodynamic force and the second blade deformation.

[0126] ​In one embodiment, the aeroelastic model comprises an aerodynamic model constructed based on blade element momentum theory and a structural model constructed based on geometrically exact beam theory; and the determining the second initial blade deformation, the second aerodynamic force and the second blade deformation based on the second initial aerodynamic force comprises: determining the second initial blade deformation based on the second initial aerodynamic force by using the structural model; determining the second tip loss coefficient based on the second initial blade deformation and the tip loss coefficient database by using a linear interpolation method; determining the second aerodynamic force based on the second tip loss coefficient by using the aerodynamic model; and determining the second blade deformation based on the second aerodynamic force by using the structural model.

[0127] Specifically, the second initial aerodynamic force F1, which represents the aerodynamic force in the undeformed state of the blade, is calculated by the aerodynamic model, and the second initial aerodynamic force F1 is input into the structural model to obtain the second initial blade deformation ω1 of the blade under the second initial aerodynamic force F1.

[0128] After the deformation of the blade, the aerodynamic force acting on the blade changes, and the aerodynamic force needs to be re-evaluated. According to the second initial blade deformation ω1, the second tip loss coefficient F extra under the second initial blade deformation ω1 is calculated by using an interpolation formula in combination with the tip loss coefficient database, and the second aerodynamic force F2 is determined based on the second tip loss coefficient by using the aerodynamic model, and then the second aerodynamic force F2 is input into the structural model to calculate the second blade deformation ω2.

[0129] The first initial aerodynamic force in the embodiment is equal to the second initial aerodynamic force, the first corrected aerodynamic force is equal to the second aerodynamic force, and the first blade deformation is equal to the second initial blade deformation.

[0130] Assuming that the aerodynamic force and the blade deformation present a linear relationship, a second mapping relationship, i.e., a corresponding relationship between the aerodynamic force and the blade deformation, is established according to the second initial aerodynamic force, the second initial blade deformation, the second aerodynamic force and the second blade deformation, and the second mapping relationship is:

[0131] ω = m2F + b2

[0132] ω1 = m2F1 + b2

[0133] ω2 = m2F2 + b2

[0134] wherein F is the aerodynamic force, m2 and b2 are coefficients, ω is the blade deformation, F1 is the second initial aerodynamic force, F2 is the first corrected aerodynamic force, ω1 is the second initial blade deformation, and ω2 is the second blade deformation.

[0135] The two sets of data (F1, ω1) and (F2, ω2) are substituted into the second mapping relationship to solve the coefficients m2 and b2 of the second mapping relationship. The relationship between the aerodynamic force and the blade deformation is as shown in Figure 6

[0136] For step S104, in an embodiment, the blade deformation evaluation result is determined based on the first mapping relationship and the second mapping relationship, including: determining an aerodynamic force equation and a deformation equation based on the first mapping relationship and the second mapping relationship; and solving the aerodynamic force equation and the deformation equation to obtain a target blade deformation as the blade deformation evaluation result.

[0137] In an embodiment, the aerodynamic force equation and the deformation equation are solved to obtain the target blade deformation, including: solving the aerodynamic force equation and the deformation equation to obtain:

[0138] F = m1w + b1

[0139] ω = m2F + b2

[0140] wherein, b1 = F1, b2 = ω1 - m2F1, ω0 is the first initial blade deformation; ω1 is the first blade deformation; ω2 is the second blade deformation; F1 is the first initial aerodynamic force; F2 is the first corrected aerodynamic force; F is the target aerodynamic force; ω is the target blade deformation; and the target blade deformation is determined by calculating the balanced solution of the aerodynamic force and the blade deformation based on the simultaneous equations.

[0141] Specifically, the aerodynamic force equation is obtained through the first mapping relationship:

[0142] F = m1w + b1

[0143] The deformation equation is obtained through the second mapping relationship:

[0144] ω = m2F + b2

[0145] The aerodynamic force equation and the deformation equation are solved to obtain:

[0146] F = m1w + b1

[0147] ω = m2F + b2

[0148] The blade deforms under the action of the aerodynamic force, and the blade deformation changes the distribution of the aerodynamic force. Ultimately, in the iteration process, the aerodynamic force and the blade deformation converge to a balanced state, i.e., the aerodynamic force and the blade deformation are no longer changed. At this time, the aerodynamic force and the blade deformation are the target aerodynamic force F and the target blade deformation ω.

[0149] ​The method directly obtains the target aerodynamic force and the target blade deformation by solving the equilibrium state of the aeroelastic coupling through simultaneous equations, simplifies the mutual influence of the aerodynamic force and the deformation, avoids the inefficiency of the traditional iterative calculation, and realizes the rapid analysis of the blade deformation and the aerodynamic performance.

[0150] It should be noted that, although the above-mentioned embodiments are described in a specific order, those skilled in the art can understand that, in order to achieve the effects of the present application, the different steps do not have to be executed in such an order, and they can be executed simultaneously (in parallel) or in other orders, and these adjusted schemes are equivalent to the technical schemes described in the present application, and thus will fall within the protection scope of the present application.

[0151] Those skilled in the art can understand that all or part of the processes in the method of the above-mentioned embodiment can also be completed by a computer program instructing related hardware, and the computer program can be stored in a computer readable storage medium, and the computer program can implement the steps of the above-mentioned method embodiments when executed by a processor. The computer program includes computer program code, which can be in the form of source code, object code, executable files or some intermediate forms, etc. The computer readable storage medium can include any entity or device, medium, U disk, mobile hard disk, magnetic disk, optical disk, computer memory, read-only memory, random access memory, electrical carrier signal, telecommunication signal and software distribution medium, etc. that can carry the computer program code.

[0152] The present application also provides a blade deformation rapid evaluation system.

[0153] Referring to the drawings Figure 7 , Figure 7 is the main structure schematic diagram of the blade deformation rapid evaluation system according to an embodiment of the present application; as Figure 7 shown, the blade deformation rapid evaluation system of the present application includes an acquisition module 71, a first mapping relationship construction module 72, a second mapping relationship construction module 73 and a determination module 74. In some embodiments, one or more of the acquisition module 71, the first mapping relationship construction module 72, the second mapping relationship construction module 73 and the determination module 74 can be combined together to become one module.

[0154] In some embodiments, the obtaining module 71 can be configured to obtain a pre-constructed aeroelastic model and a tip loss coefficient database; the first mapping relationship construction module 72 can be configured to construct a first mapping relationship based on the aeroelastic model and the tip loss coefficient database, the first mapping relationship representing a linear response relationship between a blade deformation and an aerodynamic force; the second mapping relationship construction module 73 can be configured to construct a second mapping relationship based on the aeroelastic model and the tip loss coefficient database, the second mapping relationship representing a linear response relationship between the aerodynamic force and the blade deformation; and the determining module 74 can be configured to determine a blade deformation evaluation result based on the first mapping relationship and the second mapping relationship. In one implementation, the description of the functions can be referred to the description of steps S101 to S104.

[0155] The blade deformation rapid evaluation system described above is configured to perform the blade deformation rapid evaluation method described above. Figure 1 The blade deformation rapid evaluation method embodiments shown above have similar technical principles, technical problems to be solved and technical effects, and those skilled in the art can clearly understand that, for the convenience and brevity of description, the specific working process and related description of the blade deformation rapid evaluation system can refer to the description of the blade deformation rapid evaluation method embodiments, which will not be repeated here.

[0156] Another aspect of the present application also provides an electronic device.

[0157] In an embodiment of the electronic device according to the present application, the electronic device can include at least one processor; and a memory communicatively connected with the at least one processor; wherein the memory stores a computer program, and the computer program is executed by the at least one processor to implement the blade deformation rapid evaluation method described in any of the above embodiments. Refer to FIG. 1 for an exemplary illustration of the memory 11 and the processor 12 communicatively connected through a bus. Figure 8 , Figure 8 The memory 11 and the processor 12 are communicatively connected through a bus, as shown in an exemplary illustration in FIG. 1.

[0158] In some embodiments of the present application, the electronic device can further include at least one sensor, and the sensor is configured to sense information. The sensor is communicatively connected with any type of processor mentioned in the present application.

[0159] Another aspect of the present application also provides a computer readable storage medium.

[0160] In an embodiment of the computer readable storage medium according to the present application, the computer readable storage medium can be configured to store a program of the blade deformation rapid evaluation method of the above-mentioned method embodiments, which can be loaded and run by the processor to realize the above-mentioned blade deformation rapid evaluation method. For the convenience of illustration, only the parts related to the embodiments of the present application are shown, and the specific technical details not disclosed are referred to the method part of the embodiments of the present application. The computer readable storage medium can be a storage device formed by various electronic devices, and optionally, the computer readable storage medium in the embodiments of the present application is a non-transitory computer readable storage medium.

[0161] So far, the technical solution of the present application has been described in combination with one embodiment shown in the drawings, but those skilled in the art can easily understand that the protection scope of the present application is obviously not limited to these specific embodiments. Those skilled in the art can make equivalent changes or replacements to the related technical features without departing from the principles of the present application, and the technical solutions after these changes or replacements will fall within the protection scope of the present application.

Claims

1. A method for rapid evaluation of blade deformation, characterized by, The method includes: Obtain a pre-built aeroelastic model and a database of blade tip loss coefficients; A first mapping relationship is constructed based on the aeroelastic model and the blade tip loss coefficient database. The first mapping relationship characterizes the linear response relationship between blade deformation and aerodynamic force. A second mapping relationship is constructed based on the aeroelastic model and the blade tip loss coefficient database. The second mapping relationship characterizes the linear response relationship between aerodynamic force and blade deformation. Based on the first mapping relationship and the second mapping relationship, the blade deformation assessment result is determined; The step of determining the blade deformation assessment result based on the first mapping relationship and the second mapping relationship includes: determining the aerodynamic equation and the deformation equation based on the first mapping relationship and the second mapping relationship; solving the aerodynamic equation and the deformation equation simultaneously to obtain the target blade deformation amount, which is used as the blade deformation assessment result.

2. The blade deformation quick assessment method of claim 1, wherein, The construction of the first mapping relationship based on the aeroelastic model and the blade tip loss coefficient database includes: Obtain the first initial blade deformation amount, which characterizes the geometric shape of the blade in its undeformed state; Based on the first initial blade deformation, the first initial aerodynamic force, the first blade deformation, and the first corrected aerodynamic force are determined using an aeroelastic model and a blade loss coefficient database. A first mapping relationship is established using a linear fitting method based on the first initial blade deformation, the first initial aerodynamic force, the first blade deformation, and the first corrected aerodynamic force.

3. The blade deformation rapid assessment method of claim 2, wherein, The aeroelastic model includes an aerodynamic model based on leaf element momentum theory and a structural model based on geometrically accurate beam theory. The step of determining the first initial aerodynamic force, the first blade deformation, and the first corrected aerodynamic force based on the first initial blade deformation using an aeroelastic model and a blade tip loss coefficient database includes: Based on the first initial blade deformation, an aerodynamic model is used to determine the first initial aerodynamic force. Based on the first initial aerodynamic force, the deformation of the first blade is determined using a structural model; Based on the first blade deformation amount and the blade tip loss coefficient database, the blade tip loss coefficient corresponding to the first blade deformation amount is determined by linear interpolation method. Based on the tip loss coefficient corresponding to the deformation of the first blade, an aerodynamic model is used to determine the first corrected aerodynamic force.

4. The blade deformation quick assessment method of claim 1, wherein, The construction of the second mapping relationship based on the aeroelastic model and the blade tip loss coefficient database includes: A second initial aerodynamic force is determined using an aeroelastic model, which characterizes the aerodynamic force of the blade in its undeformed state. Based on the second initial aerodynamic force, the second initial blade deformation, the second aerodynamic force, and the second blade deformation are determined using an aeroelastic model and a blade tip loss coefficient database. A second mapping relationship is established using a linear fitting method based on the second initial aerodynamic force, the second initial blade deformation, the second aerodynamic force, and the second blade deformation.

5. The blade deformation rapid assessment method of claim 4, wherein, The aeroelastic model includes an aerodynamic model based on leaf element momentum theory and a structural model based on geometrically accurate beam theory. The second initial blade deformation, the second aerodynamic force and the second blade deformation are determined based on the second initial aerodynamic force by using an aeroelastic model and a tip loss coefficient database, including: The second initial blade deformation is determined based on the second initial aerodynamic force by using a structure model; The second tip loss coefficient is determined based on the second initial blade deformation and the tip loss coefficient database by using a linear interpolation method; The second aerodynamic force is determined based on the second tip loss coefficient by using an aerodynamic model; The second blade deformation is determined based on the second aerodynamic force by using a structure model.

6. The blade deformation quick assessment method of claim 1, wherein, The target blade deformation is obtained by solving the aerodynamic force equation and the deformation equation, including: The aerodynamic force equation and the deformation equation are solved to obtain: wherein, , , , , is a first initial blade deformation; is a first blade deformation; is a second blade deformation; is a first initial aerodynamic force; is a first corrected aerodynamic force; is a target aerodynamic force; is a target blade deformation; The target blade deformation is determined based on the balance solution of the aerodynamic force and the blade deformation calculated by the coupled equations.

7. A system for rapid blade deformation assessment, characterized by, The system comprises: An acquisition module configured to acquire a pre-constructed aeroelastic model and a tip loss coefficient database; A first mapping relationship construction module configured to construct a first mapping relationship based on the aeroelastic model and the tip loss coefficient database, the first mapping relationship representing a linear response relationship between the blade deformation and the aerodynamic force; A second mapping relationship construction module configured to construct a second mapping relationship based on the aeroelastic model and the tip loss coefficient database, the second mapping relationship representing a linear response relationship between the aerodynamic force and the blade deformation; A determination module configured to determine a blade deformation evaluation result based on the first mapping relationship and the second mapping relationship.

8. An electronic device comprising at least one processor and at least one memory adapted to store a plurality of program codes, characterized in that, The program code is adapted to be loaded and run by the processor to execute the blade deformation rapid evaluation method of any one of claims 1 to 6.

9. A computer readable storage medium having stored therein a plurality of program codes, characterized in that, The program code is adapted to be loaded and run by the processor to execute the blade deformation rapid evaluation method of any one of claims 1 to 6.

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