Blade aerodynamic profile generation method, device, equipment and blade

Abstract

The application provides a kind of blade aerodynamic profile generation method, device, equipment and blade, including determining profile control parameter code, respectively using spline interpolation method to generate preset group profile distribution data;Determine the fitness index of each group of blade profile scheme;In the fitness index of each group of blade profile scheme, select the optimal profile control parameter code;Based on the fitness index of each group of blade profile scheme, the control parameter code of each group of blade profile scheme is optimized respectively;Optimized worst profile control parameter code is replaced by optimal profile control parameter code, to obtain the optimized profile control parameter code of preset group;Until the optimized profile control parameter code meets the optimization iteration number, select the optimal profile control parameter code in the optimized profile control parameter code to generate blade aerodynamic profile distribution data, since blade aerodynamic profile distribution data is automatically generated and iterated, global optimization can be more efficiently realized.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of wind power generation, in particular to a blade aerodynamic shape generation method, device and equipment and a blade. BACKGROUND

[0002] The blade aerodynamic shape scheme has a significant influence on the whole machine load and power generation efficiency, and the aerodynamic shape design itself is a multi-objective optimization problem, which needs to be iteratively designed repeatedly. The current main technical means of blade aerodynamic shape design is to realize the cooperation of multiple professional software, and in the shape distribution adjustment and aerodynamic performance analysis and calculation, it involves repeated work such as data transmission and parameter adjustment. Therefore, the manual generation method of blade aerodynamic shape has low iteration efficiency and is difficult to realize global optimization. SUMMARY

[0003] The present application provides a blade aerodynamic shape generation method, device and equipment and a blade, which solves the defects of low iteration efficiency and difficulty in global optimization of the manual generation method of blade aerodynamic shape in the prior art.

[0004] The present application provides a blade aerodynamic shape generation method, comprising:

[0005] Based on the shape control parameter code and the predetermined blade shape constraint condition, the whole machine parameter, the standard airfoil aerodynamic parameter and the blade performance constraint condition, the fitness index of each group of blade shape scheme is determined;

[0006] In the fitness index of each group of blade shape scheme, the shape control parameter code corresponding to the optimal shape fitness index is selected;

[0007] Based on the fitness index of each group of blade shape scheme, the control parameter code of each group of blade shape scheme is optimized respectively;

[0008] The shape control parameter code corresponding to the optimal shape fitness index is replaced by the shape control parameter code corresponding to the worst shape fitness index after optimization, to obtain the optimized shape control parameter code of the preset group;

[0009] The optimized shape control parameter code is used as the new shape control parameter code, until the optimized shape control parameter code meets the optimization iteration number, and the optimal shape control parameter code is selected from the optimized shape control parameter code to generate the blade aerodynamic shape distribution data.

[0010] The application provides a blade aerodynamic profile generation method, which comprises the following steps of: determining the fitness index of each group of blade profile schemes based on profile control parameter coding, predetermined blade profile constraint conditions, whole machine parameters, standard airfoil aerodynamic parameters and blade performance constraint conditions, and comprising the following steps.

[0011] Determine the profile control parameter coding based on the profile control parameter range.

[0012] Determine the initial profile control point coordinates of a preset group based on the profile control parameter coding and the predetermined blade profile constraint conditions.

[0013] Generate the profile distribution data of the preset group by using a spline interpolation method based on the initial profile control point coordinates of the preset group.

[0014] Input the predetermined whole machine parameters, standard airfoil aerodynamic parameters and the profile distribution data of each group into a blade element momentum theory solver to determine the performance parameters, steady state power and steady state operating load of each group of blade profile schemes.

[0015] Determine the fitness index of each group of blade profile schemes based on the performance parameters, the steady state power, the steady state operating load and the predetermined blade performance constraint conditions.

[0016] The application provides a blade aerodynamic profile generation method, which comprises the following steps of: determining the profile control parameter coding based on the profile control parameter range.

[0017] Determine the profile control parameter range, wherein the profile control parameter range comprises a chord length distribution control parameter range, a twist angle distribution control parameter range and a relative thickness distribution control parameter range.

[0018] Randomly generate the profile control parameter coding based on the chord length distribution control parameter range, the twist angle distribution control parameter range and the relative thickness distribution control parameter range.

[0019] The application provides a blade aerodynamic profile generation method, which comprises the following steps of: inputting the predetermined whole machine parameters, standard airfoil aerodynamic parameters and the profile distribution data of each group into a blade element momentum theory solver to determine the performance parameters, steady state power and steady state operating load of each group of blade profile schemes.

[0020] Input the predetermined whole machine parameters, standard airfoil aerodynamic parameters and the profile distribution data of each group into a blade element momentum theory solver to determine the aerodynamic force borne by each blade element in each group of profile distribution data.

[0021] Integrate the aerodynamic force along the span direction to obtain the torque and thrust of each group of blade profile schemes.

[0022] Determine performance parameters, steady power and steady operating load of each group of blade profile scheme based on the torque and the thrust.

[0023] The performance parameters include maximum wind energy utilization rate and optimal tip speed ratio.

[0024] The steady power includes rated wind speed, wind energy utilization rate corresponding to the rated wind speed, maximum thrust of the wind wheel and thrust coefficient in the optimization zone.

[0025] The steady operating load includes angle of attack distribution of the blade under the rated wind speed.

[0026] The blade aerodynamic profile generation method provided by the application comprises the following steps:

[0027] The axial force coefficient is corrected by using axial induction factor.

[0028] The three-dimensional rotation effect is corrected by using airfoil lift coefficient and airfoil drag coefficient.

[0029] In the calculation of axial and tangential induction factors, the tip and root loss is corrected.

[0030] The blade aerodynamic profile generation method provided by the application comprises the following steps:

[0031] Determine Cp constraint judgment factor, thrust constraint judgment factor, tip speed ratio constraint judgment constraint, rated Cp evaluation coefficient, stall margin evaluation coefficient and thrust evaluation coefficient according to the performance parameters, the steady power, the steady operating load and the predetermined blade performance constraint condition of each group of blades.

[0032] Determine the fitness index of each group of blade profile scheme based on the Cp constraint judgment factor, the thrust constraint judgment factor, the tip speed ratio constraint judgment constraint, the rated Cp evaluation coefficient, the stall margin evaluation coefficient and the thrust evaluation coefficient.

[0033] The blade aerodynamic profile generation method provided by the application comprises the following steps:

[0034] Based on the fitness index of each group of blade shape scheme, the genetic algorithm is used to sequentially perform selection operation optimization, heuristic crossover operation optimization and non-uniform mutation operation optimization on each group of the shape distribution data, and new shape control parameter codes after single iteration are output.

[0035] The application further provides a blade aerodynamic shape generation device, comprising:

[0036] An evaluation module is configured to determine the fitness index of each group of blade shape scheme based on the shape control parameter codes and predetermined blade shape constraints, machine parameters, standard airfoil aerodynamic parameters and blade performance constraints.

[0037] An optimization module is configured to select the shape control parameter codes corresponding to the optimal shape fitness index from the fitness index of each group of blade shape scheme, optimize the control parameter codes of each group of blade shape scheme based on the fitness index of each group of blade shape scheme, and replace the shape control parameter codes corresponding to the worst shape fitness index after optimization with the shape control parameter codes corresponding to the optimal shape fitness index to obtain the optimized shape control parameter codes of a preset group.

[0038] A blade shape generation module is configured to use the optimized shape control parameter codes as new shape control parameter codes until the optimized shape control parameter codes meet the number of optimization iterations, select the optimal shape control parameter codes from the optimized shape control parameter codes, and generate blade aerodynamic shape distribution data.

[0039] The application further provides a blade, which is generated by using the blade aerodynamic shape generation method according to any one of the above.

[0040] The application further provides an electronic device, which comprises a memory, a processor, and a computer program stored in the memory and executable on the processor, and the processor implements the blade aerodynamic shape generation method according to any one of the above when executing the program.

[0041] The application further provides a non-transitory computer readable storage medium, which stores a computer program executable on a processor, and the computer program implements the blade aerodynamic shape generation method according to any one of the above when executed on the processor.

[0042] The application provides a blade aerodynamic profile generation method, device, equipment and blade. The method comprises the following steps: determining the fitness index of each group of blade profile schemes based on profile control parameter coding, predetermined blade profile constraint conditions, whole machine parameters, standard airfoil aerodynamic parameters and blade performance constraint conditions; selecting the profile control parameter coding corresponding to the optimal profile fitness index in the fitness index of each group of blade profile schemes; optimizing the control parameter coding of each group of blade profile schemes based on the fitness index of each group of blade profile schemes; replacing the profile control parameter coding corresponding to the worst profile fitness index after optimization with the profile control parameter coding corresponding to the optimal profile fitness index, to obtain the profile control parameter coding after optimization of a preset group; taking the profile control parameter coding after optimization as new profile control parameter coding, until the profile control parameter coding after optimization meets the optimization iteration number, and selecting the optimal profile control parameter coding from the profile control parameter coding after optimization to generate blade aerodynamic profile distribution data. Since the blade aerodynamic profile distribution data is automatically generated, the time and cost of manual design are reduced, and global optimization can be more efficiently realized through automatic iteration. BRIEF DESCRIPTION OF DRAWINGS

[0043] In order to more clearly illustrate the technical solutions in the application or prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description are some embodiments of the application, and other drawings can be obtained by those skilled in the art without creative effort.

[0044] Figure 1 FIG. 1 is a flowchart of the blade aerodynamic profile generation method provided by the application;

[0045] Figure 2 FIG. 2 is a control point coordinate diagram of chord length C provided by the application;

[0046] Figure 3 FIG. 3 is a control point coordinate diagram of torsion angle T provided by the application;

[0047] Figure 4 FIG. 4 is a control point coordinate diagram of relative thickness Th provided by the application;

[0048] Figure 5 FIG. 5 is a scheme comparison diagram of dimensionless chord length before and after optimization provided by the application;

[0049] Figure 6 FIG. 6 is a scheme comparison diagram of dimensionless torsion angle before and after optimization provided by the application;

[0050] Figure 7 FIG. 7 is a scheme comparison diagram of relative thickness before and after optimization provided by the application;

[0051] Figure 8 is a scheme comparison schematic diagram of the thrust coefficient optimized scheme provided by the application;

[0052] Figure 9 is a scheme comparison schematic diagram of the power coefficient optimized scheme provided by the application;

[0053] Figure 10 is a complete flow process schematic diagram of the blade aerodynamic shape generation method provided by the embodiment of the application;

[0054] Figure 11 is a structure schematic diagram of the blade aerodynamic shape generation device provided by the embodiment of the application;

[0055] Figure 12 is a structure schematic diagram of the electronic device provided by the application. DETAILED DESCRIPTION

[0056] In order to make the objects, technical schemes and advantages of the application clearer, the technical schemes in the application will be described clearly and completely below in combination with the drawings in the application. Obviously, the described embodiments are part of the embodiments of the application, rather than all the embodiments. Based on the embodiments in the application, all other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the application.

[0057] The application will be described below in combination with Figures 1 to 12 a blade aerodynamic shape generation method, device, equipment and blade.

[0058] Figure 1 is a flow process schematic diagram of the blade aerodynamic shape generation method provided by the application.

[0059] As Figure 1 shown, the blade aerodynamic shape generation method provided by the embodiment of the application, the execution subject can be a blade aerodynamic shape generation control system, and the method mainly includes the following steps:

[0060] 101, based on the shape control parameter coding and the predetermined blade shape constraint condition, the whole machine parameter, the standard airfoil aerodynamic parameter and the blade performance constraint condition, the fitness index of each group of blade shape scheme is determined.

[0061] In one specific implementation, the specific implementation can be: determining the shape control parameter code based on the shape control parameter range; determining the initial shape control point coordinates of the preset group based on the shape control parameter code and the predetermined blade shape constraint condition; respectively generating the preset group shape distribution data by using the spline interpolation method based on the initial shape control point coordinates of the preset group; inputting the predetermined whole machine parameter, the standard airfoil aerodynamic parameter and each group of shape distribution data into the blade momentum theory solver to respectively determine the performance parameter, the steady state power and the steady state operating load of each group of blade shape scheme; and determining the fitness index of each group of blade shape scheme according to the performance parameter, the steady state power, the steady state operating load of each group of blade shape scheme and the predetermined blade performance constraint condition.

[0062] Before determining the blade aerodynamic shape, first, the input parameters are determined, and the predetermined blade shape constraint condition, the blade performance constraint condition, the whole machine parameter and the standard airfoil aerodynamic parameter are inputted.

[0063] The blade shape constraint condition PRM_BS includes: blade length S t , maximum chord length C max , blade root length S r , blade root diameter C r , blade root twist angle T r , blade tip twist angle T t .

[0064] The blade performance constraint condition PRM_BP includes: wind energy utilization rate constraint Lim_C p , wind turbine thrust constraint Lim_F t , tip speed ratio constraint Lim_λ.

[0065] The whole machine parameter PRM_T includes: operating air density ρ, operating air viscosity μ, cut-in wind speed V in , cut-out wind speed V out , minimum wind turbine speed R_min, rated wind turbine speed R_rated, hub radius r_hub, blade installation angle A set , wind turbine cone angle A cone , generator rated torque TQ_G, generator rated speed R_G, gearbox speed ratio f_gearbox.

[0066] The standard airfoil aerodynamic parameter Data_foil includes: lift coefficient Cl, drag coefficient Cd and twist coefficient Cm of the standard airfoil at different angles of attack (range -180°-180°).

[0067] For the design of each blade aerodynamic shape, the distribution curves of the chord length, the twist angle and the relative thickness can be determined by 17 shape control parameters.

[0068] For example, chord length distribution control parameters include:

[0069] (1) Dimensionless position of maximum chord length DS_C max with a value range of 0.16-0.23.

[0070] (2) Dimensionless position of 2 / 3 maximum chord length DS_67C max with a value range of 0.45-0.6.

[0071] (3) Dimensionless position of 1 / 2 maximum chord length DS_50C max with a value range of 0.6-0.77.

[0072] (4) Dimensionless position of 1 / 3 maximum chord length DS_33C max with a value range of 0.8-0.9.

[0073] (5) Chord length corresponding to 99% span C_99DS; value range: 0.5-1.2.

[0074] Twist angle distribution control parameters include:

[0075] (1) Dimensionless position of 9 / 10 blade root twist angle DS_90T r = 0.07-0.14

[0076] (2) Dimensionless position of 3 / 10 blade root twist angle DS_30T r = 0.25-0.42

[0077] (3) Dimensionless position of 1 / 10 blade root twist angle DS_10T r = 0.35-0.65

[0078] (4) Dimensionless position of 0 degree twist angle DS_T0 = 0.55-0.8

[0079] (5) Dimensionless position of minimum twist angle DS_T min = 0.95-0.98

[0080] (6) Size of minimum twist angle T min = -1--5

[0081] Relative thickness distribution control parameters include:

[0082] (1) Dimensionless position of %60 thickness airfoil DS_60Th = 0.1-0.17

[0083] (2) Dimensionless position of %40 thickness airfoil DS_40Th = 0.2-0.3

[0084] (3) Non-dimensional position of the 35% thickness airfoil; DS_35Th = 0.2 ~ 0.4

[0085] (4) Non-dimensional position of the 30% thickness airfoil; DS_30Th = 0.4 ~ 0.65

[0086] (5) Non-dimensional position of the 25% thickness airfoil; DS_25Th = 0.75 ~ 0.9

[0087] (6) Non-dimensional position of the 21% thickness airfoil; DS_21Th = 0.9 ~ 0.98

[0088] Wherein, the spanwise coordinate corresponding to each control parameter is a non-dimensional value (actual spanwise position / blade length S t ).

[0089] And in order to avoid the profile control parameter range intersection caused by the profile distribution curve distortion, each control parameter needs to meet the following relationship between each other:

[0090] (1) DS_50C max ≥ DS_67C max + 0.1;

[0091] (2) DS_33C max ≥ DS_50C max + 0.15;

[0092] (3) DS_10T R ≥ DS_30T R + 0.1;

[0093] (4) DS_T0≥ DS_10T R + 0.1;

[0094] (5) DS_40Th≥ DS_60Th+ 0.05;

[0095] (6) DS_35Th≥ DS_40Th+ 0.1;

[0096] (7) DS_30Th≥ DS_35Th+ 0.1;

[0097] (8) DS_25Th≥ DS_30Th+ 0.2;

[0098] (9) DS_21Th≥ DS_25Th+ 0.1;

[0099] After the ranges of the shape control parameters, including the range of the chord length distribution control parameter, the range of the twist angle distribution control parameter and the range of the relative thickness distribution control parameter, are determined, the shape control parameter code encode can be determined based on the range of the chord length distribution control parameter, the range of the twist angle distribution control parameter and the range of the relative thickness distribution control parameter. The type of the shape control parameter code encode is a matrix of m*17, where m is the number of schemes of the shape cluster, as shown in equation (1):

[0100]

[0101] The initial shape control point coordinates of the preset group can be determined based on the shape control parameter code and the predetermined blade shape constraint condition PRM_BS, as follows:

[0102] Chord length control point coordinates: (0, C r ), (S r , C r ), (S t ×DS_C max , C max ), (S t ×DS_67C max , 0.67C max ), (S t ×DS_50C max , 0.5C max ), (S t ×DS_33C max , 0.33C max ), (0.99S t , C_99DS), (S t , 0.1);

[0103] Twist angle control point coordinates: (0, T r ), (S r , T r ), (S t ×DS_90T r , 0.9T r ), (S t ×DS_30T r , 0.3T r ), (S t ×DS_10T r , 0.1T r ), (S t ×DS_T0, 0), (S t ×DS_T min , Tmin ), (S t , t );

[0104] Relative thickness control point coordinates: (0, 100), (S r , 100), (S t ×DS_60Th, 60), (S t ×DS_40Th, 40), (S t ×DS_35Th, 35), (S t ×DS_30Th, 30), (S t ×DS_25Th, 25), (S t ×DS_21Th, 21), (S t , t ).

[0105] As shown in FIG. 2, FIG. 3 and FIG. 4, the control point coordinates of chord length C, twist angle T and relative thickness Th are shown respectively. Figure 2 Figure 3 Figure 4 Figure 2 , Figure 3 and Figure 4 , the control point coordinates can be clearly seen.

[0106] Based on the initial profile control point coordinates of the preset group, the preset group profile distribution data is generated by using the spline interpolation method. Then, based on the profile control point coordinates of the preset group, the Akima spline interpolation method is used to generate the profile distribution data, i.e. the aerodynamic profile distribution matrix GEO, as shown in formula (2):

[0107]

[0108] In the formula, the profile distribution data stores the chord length, twist angle and relative thickness corresponding to different span coordinates, and the type is a high-dimensional matrix of m×n×4, where m is the number of profile clusters, and n is the number of blade span coordinates. In addition, the tip chord length is fixed at 0.1m (i.e. C 1n , C 2n …C mn = 0.1), and the tip relative thickness Th t ≤ 21%, which is determined by the selected tip standard airfoil.

[0109] ​​​The performance parameters, steady power and steady operating load of each group of blade profile schemes are determined by inputting the predetermined overall machine parameters, standard airfoil aerodynamic parameters and each group of profile distribution data into the blade element momentum theory solver. The blade element momentum theory solver is a BEM (Boundary Element Method) solver. The predetermined overall machine parameters, standard airfoil aerodynamic parameters and each group of profile distribution data are input into the BEM solver. The performance parameters, steady power and steady operating load are calculated by the BEM solver. Each group of profile distribution data is calculated to obtain the corresponding results.

[0110] The fitness index of each group of blade profile schemes is determined according to the performance parameters, steady power, steady operating load of each group of blade profile schemes and the predetermined blade performance constraint conditions. After the performance parameters, steady power and steady operating load corresponding to each group of blade profile data are calculated by the BEM solver, the aerodynamic performance of each group of blade profile data can be evaluated to determine the fitness index FI of each group of blade profile schemes, including efficiency, load, stall and expandability, etc.

[0111] 102. In the fitness index of each group of blade profile schemes, the profile control parameter code corresponding to the optimal profile fitness index is selected.

[0112] After the fitness index of each group of blade profile schemes is calculated, the fitness index of each group is evaluated, and then the profile control code corresponding to the optimal profile fitness index is selected.

[0113] 103. Based on the fitness index of each group of blade profile schemes, the control parameter code of each group of blade profile schemes is optimized.

[0114] According to the fitness index of each group of blade profile schemes, each group of profile distribution data is optimized, i.e. iterative optimization is performed by using genetic algorithm. Through continuous iteration, the optimal profile distribution data is obtained.

[0115] 104. The profile control parameter code corresponding to the optimal profile fitness index is used to replace the profile control parameter code corresponding to the worst profile fitness index after optimization, to obtain the optimized profile control parameter code of the preset group.

[0116] Based on the fitness index of each group of blade shape schemes, a genetic algorithm is used to sequentially perform selection optimization, heuristic crossover optimization, and non-uniform mutation optimization on each group of shape distribution data, outputting the shape control parameter code after a single iteration. Then, all optimized shape control parameter codes are analyzed and judged, and the shape control parameter code corresponding to the worst fitness index is selected from all groups. Finally, the best shape control parameter code before optimization is used to replace the worst shape control parameter code after optimization, and iterative calculation is performed again, thus eliminating the worst shape control parameter code. Finally, through a preset number of iterations, the blade shape with the best aerodynamic performance, i.e., the highest fitness value, is obtained.

[0117] 105. Use the optimized shape control parameter code as the new shape control parameter code until the optimized shape control parameter code meets the number of optimization iterations. Then, select the optimal shape control parameter code from the optimized shape control parameter codes to generate blade aerodynamic shape distribution data.

[0118] Finally, using the optimized shape control point coordinates as the initial shape control point coordinates, iterative calculations are performed, repeating the operation: "Based on the shape control parameter encoding and pre-determined blade shape constraints, determine the initial shape control point coordinates of the preset group; based on the initial shape control point coordinates of the preset group, generate the shape distribution data of the preset group using the spline interpolation method; input the pre-determined overall parameters, standard airfoil aerodynamic parameters, and shape distribution data of each group to the blade element momentum theory solver to determine the performance parameters, steady-state power, and steady-state operating load of each group of blade shape schemes; based on the performance parameters, steady-state power, steady-state operating load, and pre-determined blade performance constraints of each group of blade shape schemes, determine the fitness index of each group of blade shape schemes, and apply this to each group of blade shape schemes." Among the fitness indices, the optimal shape control parameter code corresponding to the optimal shape fitness index is selected. Based on the fitness index of each group of blade shape schemes, the control parameter code of each group of blade shape schemes is optimized. The optimal shape control parameter code is used to replace the worst shape control parameter code after optimization, resulting in the optimized shape control parameter code for the preset group. This process continuously optimizes the shape data to ensure that the final data is more accurate and reliable. After the preset number of iterations is reached, the optimal shape control point coordinates can be selected from the final iteratively optimized shape control point coordinates. Spline interpolation is then used to generate shape distribution data, thus completing the design and generation of the final blade aerodynamic shape.

[0119] like Figure 5 The image shows a comparison of the solutions before and after the dimensionless chord length optimization. Figure 6 For the comparison of the schemes before and after the dimensionless twist angle optimization,Figure 7 For the relative thickness of the scheme before and after optimization, Figure 8 For the thrust coefficient of the optimized scheme, Figure 9 For the power coefficient of the optimized scheme, Figures 5 to 9 It can be concluded that the blade aerodynamic shape automatically designed and generated by the scheme of the present application can effectively adjust the error, and compared with manual design, the iteration efficiency is higher, and the calculated blade aerodynamic shape is more in line with the requirements.

[0120] The blade aerodynamic shape generation method provided in the embodiment comprises the following steps: determining the fitness index of each group of blade shape schemes based on the shape control parameter code and the pre-determined blade shape constraint condition, the whole machine parameter, the standard airfoil aerodynamic parameter and the blade performance constraint condition; selecting the shape control parameter code corresponding to the optimal shape fitness index in the fitness index of each group of blade shape schemes; optimizing the control parameter code of each group of blade shape schemes based on the fitness index of each group of blade shape schemes; replacing the shape control parameter code corresponding to the worst shape fitness index after optimization with the shape control parameter code corresponding to the optimal shape fitness index, to obtain the pre-determined group of optimized shape control parameter codes; taking the optimized shape control parameter code as a new shape control parameter code until the optimized shape control parameter code meets the optimization iteration number, and selecting the optimal shape control parameter code in the optimized shape control parameter code to generate blade aerodynamic shape distribution data. Since the blade aerodynamic shape distribution data are automatically generated, the time and cost of manual design are reduced, and the global optimization can be more efficiently realized through the automatic iteration mode.

[0121] Further, on the basis of the above-mentioned embodiment, in the embodiment, the pre-determined whole machine parameter, standard airfoil aerodynamic parameter and each group of shape distribution data are input into the blade momentum theory solver to determine the performance parameter, steady-state power and steady-state operating load of each group of blade shape schemes, comprising: inputting the pre-determined whole machine parameter, standard airfoil aerodynamic parameter and each group of shape distribution data into the blade momentum theory solver to determine the aerodynamic force received by each blade element in each group of shape distribution data; integrating the aerodynamic force along the span to obtain the torque and thrust of each blade shape scheme; and determining the performance parameter, steady-state power and steady-state operating load of each group of blade shape schemes based on the torque and thrust.

[0122] The performance parameter comprises the maximum wind energy utilization rate and the optimal tip speed ratio; the steady-state power comprises the rated wind speed, the wind energy utilization rate corresponding to the rated wind speed, the maximum thrust of the wind wheel and the thrust coefficient in the optimization zone; and the steady-state operating load comprises the attack angle distribution of the blade under the rated wind speed.

[0123] Specifically, the whole machine parameters PRM_T, standard airfoil aerodynamic parameters Data_foil and the shape distribution matrix GEO are transmitted to the BEM solver, and the aerodynamic force received by each blade element in all group shape distribution data is calculated in turn, and the blade torque TQ_B and thrust F are obtained by integrating along the span direction t After the above analysis and calculation, the following analysis and calculation are performed:

[0124] (1) Performance parameter calculation is performed to obtain the blade wind energy utilization rate C p and the corresponding relationship with the tip speed ratio λ to determine the maximum wind energy utilization rate C p _max and the corresponding optimal tip speed ratio λ_opt.

[0125] (2) Steady power calculation is performed to obtain the power EP, the rotor speed R, the pitch angle A pitch , the rotor thrust F t , the blade thrust coefficient C t , the blade power coefficient C p and the corresponding relationship with the wind speed V; the rated wind speed V rated , the rated wind speed corresponding wind energy utilization rate C p _rated, the maximum rotor thrust F t _max, and the optimal thrust coefficient C t _opt are determined.

[0126] (3) Steady state operating load calculation is performed to obtain the angle of attack AOA distribution of the blade under the rated wind speed, and the operating angle of attack AOA t corresponding to the 40% thickness airfoil (spanwise position = S 40 ×DS_40Th) is extracted.

[0127] Further, on the basis of the above embodiment, in this embodiment, the predetermined whole machine parameters, standard airfoil aerodynamic parameters and each group of shape distribution data are input to the blade momentum theory solver to determine the performance parameters, steady power and steady state operating load of each group of blade shape schemes, and further comprising: correcting the axial force coefficient by using the axial induction factor; correcting the three-dimensional rotation effect by using the airfoil lift / drag coefficient; and correcting the tip and root loss in the calculation of the axial and tangential induction factors.

[0128] In the calculation of the axial induction factor, a coefficient factor_t is multiplied to realize the correction of the axial force coefficient, as formula (3):

[0129]

[0130] In the formula, factor_t represents the axial force correction coefficient, and a is the axial induction factor.

[0131] The correction of three-dimensional rotational effects is achieved by a correction of the airfoil lift / drag coefficients:

[0132]

[0133] where AOA0is the angle of attack corresponding to zero lift coefficient, Cd0is the drag coefficient corresponding to 0° angle of attack, and the coefficients f iv l d Cl is the corrected lift coefficient, Cl denotes the lift coefficient, Cd denotes the drag coefficient, and AOA denotes the angle of attack. 3D

[0134] The correction of tip and hub losses is achieved by multiplying the axial and tangential induction factors by the coefficients factor_tip and factor_hub:

[0135]

[0136] where S is the rotational radius of the blade element, Ain is the inflow angle of the blade element, factor_tip denotes the tip loss correction coefficient, and factor_hub denotes the hub loss correction coefficient.

[0137] Further, on the basis of the above-mentioned embodiment, the fitness index of each group of blade shape schemes is determined according to the performance parameters, steady power, steady operating load and predetermined blade performance constraint conditions of each group of blade shape schemes, including: determining the Cp constraint judgment factor, the thrust constraint judgment factor, the tip speed ratio constraint judgment constraint, the rated Cp evaluation coefficient, the stall margin evaluation coefficient and the thrust evaluation coefficient according to the performance parameters, the steady power, the steady operating load and the predetermined blade performance constraint conditions of each group of blades; determining the fitness index of each group of blade shape schemes based on the Cp constraint judgment factor, the thrust constraint judgment factor, the tip speed ratio constraint judgment constraint, the rated Cp evaluation coefficient, the stall margin evaluation coefficient and the thrust evaluation coefficient.

[0138] Specifically, as shown in formula (6), it is a shape fitness index determination formula:

[0139] FI = L Cp · L Ft · L λ · E Cp · E stall · E Ft (6)

[0140] where FI denotes the shape fitness index, L Cp denotes the Cp constraint judgment factor, L Ft denotes the thrust constraint judgment factor, and L λ ​​​represents the tip speed ratio constraint judgment constraint, E Cp represents the rated Cp evaluation coefficient, E stall represents the stall margin evaluation coefficient, E Ft represents the thrust evaluation coefficient.

[0141] wherein, as formula (7), coefficient L Cp is used to judge whether the wind energy utilization rate peak value of the scheme corresponding to the shape distribution data satisfies the constraint condition Lim_C p , for the scheme that does not satisfy the constraint, directly excluded:

[0142]

[0143] as formula (8), coefficient L Ft is used to judge whether the thrust peak value of the scheme corresponding to the shape distribution data satisfies the constraint condition Lim_F t , the constraint has a relaxation margin of 2.5%, for the scheme that satisfies the relaxation constraint but does not satisfy the strong constraint, coefficient L Ft is reduced to 0.7:

[0144]

[0145] in the formula, F t _max represents the peak thrust.

[0146] as formula (9), coefficient L λ is used to judge whether the optimal tip speed ratio of the scheme corresponding to the shape distribution data satisfies the constraint condition Lim_λ, the constraint has a relaxation margin of 2.5%, for the scheme that satisfies the relaxation constraint but does not satisfy the strong constraint, coefficient L λ is reduced to 0.9:

[0147]

[0148] in the formula, λ_opt represents the tip speed ratio of the optimization zone.

[0149] as formula (10), coefficient E Cp is used to evaluate the aerodynamic efficiency of the scheme corresponding to the shape distribution data under the rated working condition, defined as the ratio of the rated wind energy utilization rate C p _rated and the Betz limit:

[0150]

[0151] as formula (11), coefficient E stall is used to evaluate the stall resistance performance of the scheme corresponding to the shape distribution data under the rated working condition (when the operating angle of attack is less than the stall angle of attack, the value of the index is close to 1, when the operating angle of attack is greater than the stall angle of attack, the value of the index presents exponential decline, and tends to 0 infinitely).

[0152]

[0153] AOA 40S is the stall angle of attack of the 40% thickness airfoil, AOA 40 represents the operating angle of attack of the 40% thickness airfoil.

[0154] The coefficient E Ft The load size for evaluating the profile scheme comprehensively reflects the peak thrust and the thrust in the optimization zone:

[0155]

[0156] F t _max represents the maximum thrust, C t _opt represents the thrust coefficient in the optimization zone.

[0157] Figure 10 is the complete flowchart of the blade aerodynamic profile generation method provided by the embodiment of the application.

[0158] As shown in Figure 10 , first, the profile control parameter code is randomly generated, and then the Akima spline interpolation method is used to generate profile distribution data based on the profile control parameter code and the blade profile constraints. Then, it is input into the BEM solver combined with the whole machine parameters and the standard airfoil aerodynamic parameters to perform performance parameter calculation to obtain the peak Cp, the optimal tip speed ratio, to perform steady power calculation to obtain the rated Cp, the peak thrust and the thrust coefficient, to perform steady operating load calculation to obtain the rated point attack angle distribution. Then, based on the calculation results of the BEM solver and the blade performance constraints, the aerodynamic performance of the blade profile scheme is evaluated, including the efficiency, the load, the stall and the expandability and other parameters, and the profile control parameter code corresponding to the profile scheme with the optimal performance evaluation is extracted. The profile scheme after performance evaluation is processed by the optimization algorithm, specifically, the advantage scheme is selected to recombine the profile control parameter code, the heuristic self-crossing transportation is updated to update the profile control parameter code, and the non-uniform mutation operation is updated to update the profile control parameter code. The profile control parameter code corresponding to the optimal profile scheme is used to replace the profile control parameter code of the worst profile design scheme in this iteration, so as to realize this optimization. It is judged whether the iteration step number is met, and when the iteration step number is met, the profile distribution data is generated by using the Akima spline interpolation method to complete the aerodynamic scheme design, otherwise the optimization iteration is continuously performed. As shown in Figure 8 , by continuously optimizing the control parameter code, the automatic execution is repeatedly circulated to ensure that the final obtained profile design scheme is the optimal profile design scheme.

[0159] Based on the same general inventive concept, the present application also protects a blade aerodynamic profile generating device. The blade aerodynamic profile generating device provided by the present application is described below, and the blade aerodynamic profile generating device described below can be correspondingly referred to the blade aerodynamic profile generating method described above.

[0160] Figure 11 FIG. 1 is a structural schematic diagram of a blade aerodynamic profile generating device provided by an embodiment of the present application.

[0161] As shown in FIG. 1, the blade aerodynamic profile generating device provided by an embodiment of the present application comprises: Figure 11 An evaluation module 1101 is configured to determine a fitness index of each group of blade profile schemes based on the profile control parameter encoding and predetermined blade profile constraints, machine parameters, standard airfoil aerodynamic parameters, and blade performance constraints.

[0162] An optimization module 1102 is configured to select a profile control parameter encoding corresponding to an optimal profile fitness index from the fitness index of each group of blade profile schemes, optimize the control parameter encoding of each group of blade profile schemes based on the fitness index of each group of blade profile schemes, and replace the profile control parameter encoding corresponding to the worst profile fitness index after optimization with the profile control parameter encoding corresponding to the optimal profile fitness index to obtain a preset group of optimized profile control parameter encodings.

[0163] A blade profile generating module 1103 is configured to use the optimized profile control parameter encoding as a new profile control parameter encoding until the optimized profile control parameter encoding meets an optimization iteration number, select an optimal profile control parameter encoding from the optimized profile control parameter encoding, and generate blade aerodynamic profile distribution data.

[0164]

[0165] ​The blade aerodynamic profile generation device provided in the embodiment comprises: determining fitness indexes of each group of blade profile schemes based on profile control parameter codes and predetermined blade profile constraint conditions, machine parameters, standard airfoil aerodynamic parameters, and blade performance constraint conditions; selecting a profile control parameter code corresponding to an optimal profile fitness index in the fitness indexes of each group of blade profile schemes; optimizing the control parameter codes of each group of blade profile schemes based on the fitness indexes of each group of blade profile schemes; replacing the profile control parameter code corresponding to the worst profile fitness index after optimization with the profile control parameter code corresponding to the optimal profile fitness index to obtain optimized profile control parameter codes of a preset group; and using the optimized profile control parameter codes as new profile control parameter codes until the optimized profile control parameter codes meet the number of optimization iterations, and selecting an optimal profile control parameter code from the optimized profile control parameter codes to generate blade aerodynamic profile distribution data. Since the blade aerodynamic profile distribution data are automatically generated, the time and cost of manual design are reduced, and global optimization can be more efficiently realized through automatic iteration.

[0166] Further, the evaluation module 1101 in the embodiment is specifically used for:

[0167] determining profile control parameter codes based on profile control parameter ranges;

[0168] determining initial profile control point coordinates of a preset group based on the profile control parameter codes and predetermined blade profile constraint conditions;

[0169] generating profile distribution data of the preset group by using a spline interpolation method based on the initial profile control point coordinates of the preset group;

[0170] inputting predetermined machine parameters, standard airfoil aerodynamic parameters, and each group of profile distribution data to a blade element momentum theory solver to determine performance parameters, steady-state power, and steady-state operating load of each group of blade profile schemes;

[0171] determining fitness indexes of each group of blade profile schemes according to the performance parameters, the steady-state power, the steady-state operating load of each group of blade profile schemes, and predetermined blade performance constraint conditions.

[0172] Further, the evaluation module 1101 in the embodiment is specifically used for:

[0173] determining profile control parameter ranges, wherein the profile control parameter ranges comprise chord length distribution control parameter ranges, twist angle distribution control parameter ranges, and relative thickness distribution control parameter ranges;

[0174] Randomly generate the profile control parameter code based on the chord length distribution control parameter range, the twist angle distribution control parameter range, and the relative thickness distribution control parameter range.

[0175] Further, the evaluation module 1101 in this embodiment is specifically further used for:

[0176] inputting the predetermined overall machine parameters, the standard airfoil aerodynamic parameters, and each set of the profile distribution data into a blade element momentum theory solver to determine the aerodynamic force on each blade element in each set of the profile distribution data;

[0177] integrating the aerodynamic force along the span to obtain the torque and the thrust of each blade profile scheme, respectively;

[0178] determining the performance parameter, the steady-state power, and the steady-state operating load of each blade profile scheme based on the torque and the thrust.

[0179] Further, the performance parameter in this embodiment includes the maximum wind energy utilization rate and the optimal tip speed ratio;

[0180] The steady-state power includes the rated wind speed, the wind energy utilization rate corresponding to the rated wind speed, the maximum thrust of the wind wheel, and the thrust coefficient in the optimization zone;

[0181] The steady-state operating load includes the angle of attack distribution of the blade at the rated wind speed.

[0182] Further, the evaluation module 1101 in this embodiment is specifically further used for:

[0183] correcting the axial force coefficient by using the axial induction factor;

[0184] correcting the three-dimensional rotation effect by using the airfoil lift / drag coefficient;

[0185] In the calculation of the axial and tangential induction factors, the tip and root losses are corrected.

[0186] Further, the evaluation module 1101 in this embodiment is specifically further used for:

[0187] determining the Cp constraint judgment factor, the thrust constraint judgment factor, the tip speed ratio constraint judgment constraint, the rated Cp evaluation coefficient, the stall margin evaluation coefficient, and the thrust evaluation coefficient according to the performance parameter, the steady-state power, the steady-state operating load, and the predetermined blade performance constraint condition of each blade;

[0188] determining the fitness index of each blade profile scheme based on the Cp constraint judgment factor, the thrust constraint judgment factor, the tip speed ratio constraint judgment constraint, the rated Cp evaluation coefficient, the stall margin evaluation coefficient, and the thrust evaluation coefficient.

[0189] Further, the optimization module 1102 in the embodiment is further configured to:

[0190] Based on the fitness index of each group of blade shape scheme, the genetic algorithm is used to sequentially perform selection operation optimization, heuristic crossover operation optimization and non-uniform mutation operation optimization on each group of the shape distribution data, and new shape control parameter codes after single iteration are output.

[0191] Based on the same overall inventive concept, the present application also protects a blade, which is generated by the blade aerodynamic shape generation method of any of the above embodiments.

[0192] Figure 12 An example of a schematic diagram of a physical structure of an electronic device is shown.

[0193] As Figure 12 shown, the electronic device can include a processor 1210, a communications interface 1220, a memory 1230 and a communications bus 1240, wherein the processor 1210, the communications interface 1220 and the memory 1230 complete mutual communication through the communications bus 1240. The processor 1210 can invoke a logical instruction in the memory 1230 to execute the blade aerodynamic shape generation method, which includes: determining a fitness index of each group of blade shape scheme based on shape control parameter codes and predetermined blade shape constraints, overall parameters, standard airfoil aerodynamic parameters and blade performance constraints; selecting a shape control parameter code corresponding to an optimal shape fitness index in the fitness index of each group of blade shape scheme; optimizing the control parameter codes of each group of blade shape scheme based on the fitness index of each group of blade shape scheme; replacing the control parameter codes corresponding to the worst shape fitness index after optimization with the control parameter codes corresponding to the optimal shape fitness index, to obtain optimized shape control parameter codes of a preset group; taking the optimized shape control parameter codes as new shape control parameter codes, until the optimized shape control parameter codes meet the optimization iteration number, and selecting an optimal shape control parameter code from the optimized shape control parameter codes to generate blade aerodynamic shape distribution data.

[0194] In addition, the logic instructions in the memory 1230 described above can be implemented in the form of a software function unit and sold or used as an independent product, which can be stored in a computer readable storage medium. Based on such understanding, the technical solutions of the present application essentially or the part that contributes to the prior art or part of the technical solutions can be embodied in the form of a software product. The computer software product is stored in a storage medium, including a number of instructions to make a computer device (which can be a personal computer, a server, or a network device, etc.) execute all or part of the steps of the method described in various embodiments of the present application. The foregoing storage medium includes: a U disk, a mobile hard disk, a read-only memory (ROM, Read-Only Memory), a random access memory (RAM, Random Access Memory), a magnetic disk or an optical disk, and various media that can store program codes.

[0195] In another aspect, the present application also provides a computer program product, which comprises a computer program stored on a non-transitory computer-readable storage medium, and the computer program comprises program instructions, and when the program instructions are executed by a computer, the computer can execute the blade aerodynamic profile generation method provided by the above-mentioned methods, and the method comprises the following steps: determining the fitness index of each group of blade profile schemes based on the profile control parameter code and the predetermined blade profile constraint condition, the whole machine parameter, the standard airfoil aerodynamic parameter and the blade performance constraint condition; selecting the profile control parameter code corresponding to the optimal profile fitness index in the fitness index of each group of blade profile schemes; optimizing the control parameter code of each group of blade profile schemes based on the fitness index of each group of blade profile schemes; replacing the profile control parameter code corresponding to the worst profile fitness index after optimization with the profile control parameter code corresponding to the optimal profile fitness index, to obtain the optimized profile control parameter code of a preset group; taking the optimized profile control parameter code as the new profile control parameter code, until the optimized profile control parameter code meets the optimization iteration number, and selecting the optimal profile control parameter code from the optimized profile control parameter code to generate the blade aerodynamic profile distribution data. In still another aspect, the present application also provides a non-transitory computer-readable storage medium, which stores a computer program, and the computer program is executed by a processor to implement the blade aerodynamic profile generation method provided by the above-mentioned methods, and the method comprises the following steps: determining the fitness index of each group of blade profile schemes based on the profile control parameter code and the predetermined blade profile constraint condition, the whole machine parameter, the standard airfoil aerodynamic parameter and the blade performance constraint condition; selecting the profile control parameter code corresponding to the optimal profile fitness index in the fitness index of each group of blade profile schemes; optimizing the control parameter code of each group of blade profile schemes based on the fitness index of each group of blade profile schemes; replacing the profile control parameter code corresponding to the worst profile fitness index after optimization with the profile control parameter code corresponding to the optimal profile fitness index, to obtain the optimized profile control parameter code of a preset group; taking the optimized profile control parameter code as the new profile control parameter code, until the optimized profile control parameter code meets the optimization iteration number, and selecting the optimal profile control parameter code from the optimized profile control parameter code to generate the blade aerodynamic profile distribution data.

[0196] The device embodiments described above are only illustrative, wherein the units illustrated as separate components can or can not be physically separated, and the components illustrated as units can or can not be physical units, i.e., they can be located in one place or distributed on multiple network units. Part or all of the modules can be selected to achieve the purpose of the present embodiment scheme according to actual needs. Those skilled in the art can understand and implement without creative labor.

[0197] Those skilled in the art can clearly understand the implementation of the various embodiments by means of software and necessary general hardware platforms through the above description of the embodiments, and of course, the embodiments can also be implemented by hardware. Based on such understanding, the above technical solutions, essentially or in other words, the part of the prior art that makes a contribution, can be embodied in the form of a software product, which can be stored in a computer readable storage medium, such as a ROM / RAM, a magnetic disk, an optical disk, etc., and includes a number of instructions to make a computer device (which can be a personal computer, a server, or a network device, etc.) execute the methods described in the various embodiments or some parts of the embodiments.

[0198] Finally, it should be noted that: the above examples are only used to illustrate the technical solutions of the present application, and not to limit them; although the present application has been described in detail with reference to the foregoing examples, those skilled in the art should understand that: it can still modify the technical solutions recorded in the foregoing examples, or make equivalent replacement for some of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the various embodiments of the present application.

Claims

1. A method of generating an aerodynamic profile of a blade, characterized by, The method comprises the following steps: determining the fitness index of each group of blade profile scheme based on the profile control parameter code and the predetermined blade profile constraint condition, the whole machine parameter, the standard airfoil aerodynamic parameter and the blade performance constraint condition; selecting the profile control parameter code corresponding to the optimal profile fitness index from the fitness index of each group of blade profile scheme; optimizing the control parameter code of each group of blade profile scheme based on the fitness index of each group of blade profile scheme; replacing the profile control parameter code corresponding to the worst profile fitness index after optimization with the profile control parameter code corresponding to the optimal profile fitness index, to obtain the optimized profile control parameter code of the preset group; selecting the optimal profile control parameter code from the optimized profile control parameter code until the optimized profile control parameter code meets the optimization iteration number, and generating the blade aerodynamic profile distribution data based on the optimal profile control parameter code.

2. The blade aerodynamic shape generating method according to claim 1, characterized by, The method for determining the fitness index of each group of blade profile scheme based on the profile control parameter code and the predetermined blade profile constraint condition, the whole machine parameter, the standard airfoil aerodynamic parameter and the blade performance constraint condition comprises the following steps: determining the profile control parameter code based on the profile control parameter range; determining the initial profile control point coordinates of the preset group based on the profile control parameter code and the predetermined blade profile constraint condition; generating the preset group profile distribution data by using the spline interpolation method based on the initial profile control point coordinates of the preset group; inputting the predetermined whole machine parameter, the standard airfoil aerodynamic parameter and each group of profile distribution data into the blade momentum theory solver to determine the performance parameter, the steady-state power and the steady-state operating load of each group of blade profile scheme, respectively; determining the fitness index of each group of blade profile scheme according to the performance parameter, the steady-state power, the steady-state operating load of each group of blade profile scheme and the predetermined blade performance constraint condition.

3. The blade aerodynamic shape generating method according to claim 2, characterized by, The method for determining the profile control parameter code based on the profile control parameter range comprises the following steps: determining the profile control parameter range, wherein the profile control parameter range comprises the chord length distribution control parameter range, the twist angle distribution control parameter range and the relative thickness distribution control parameter range; randomly generating the profile control parameter code based on the chord length distribution control parameter range, the twist angle distribution control parameter range and the relative thickness distribution control parameter range.

4. The blade aerodynamic shape generating method according to claim 2, characterized by, The method for inputting the predetermined whole machine parameter, the standard airfoil aerodynamic parameter and each group of profile distribution data into the blade momentum theory solver to determine the performance parameter, the steady-state power and the steady-state operating load of each group of blade profile scheme comprises the following steps: inputting the predetermined whole machine parameter, the standard airfoil aerodynamic parameter and each group of profile distribution data into the blade momentum theory solver to determine the aerodynamic force acting on each blade element in each group of profile distribution data; integrating the aerodynamic force along the span direction to obtain the torque and the thrust of each group of blade profile scheme, respectively; determining the performance parameter, the steady-state power and the steady-state operating load of each group of blade profile scheme based on the torque and the thrust.

5. The method of blade aerodynamic shape generation according to claim 4, characterized in that, The performance parameters include maximum wind energy utilization rate and optimal tip speed ratio; The steady-state power includes rated wind speed, wind energy utilization rate corresponding to the rated wind speed, maximum thrust of the wind wheel and thrust coefficient in the optimization zone; The steady-state operation load includes the angle of attack distribution of the blade under the rated wind speed.

6. The method of blade aerodynamic shape generation according to claim 4, characterized in that, The input pre-determined whole machine parameters, standard airfoil aerodynamic parameters and each set of the profile distribution data to the blade element momentum theory solver respectively determines the performance parameters, steady-state power and steady-state operation load of each set of blade profile scheme, and further comprises: The axial force coefficient is corrected by using the axial induction factor; The three-dimensional rotation effect is corrected by using the airfoil lift coefficient and airfoil drag coefficient; In the calculation of the axial and tangential induction factors, the tip and root losses are corrected.

7. The method of claim 2, wherein, The fitness index of each set of blade profile scheme is determined according to the performance parameters, the steady-state power, the steady-state operation load and the pre-determined blade performance constraint conditions, and comprises: The Cp constraint judgment factor, the thrust constraint judgment factor, the tip speed ratio constraint judgment constraint, the rated Cp evaluation coefficient, the stall margin evaluation coefficient and the thrust evaluation coefficient are determined according to the performance parameters, the steady-state power, the steady-state operation load and the pre-determined blade performance constraint conditions of each set of blade; The fitness index of each set of blade profile scheme is determined based on the Cp constraint judgment factor, the thrust constraint judgment factor, the tip speed ratio constraint judgment constraint, the rated Cp evaluation coefficient, the stall margin evaluation coefficient and the thrust evaluation coefficient.

8. The blade aerodynamic shape generating method according to any one of claims 1 to 7, characterized by, The control parameter coding of each set of the blade profile scheme is optimized based on the fitness index of each set of the blade profile scheme, and comprises: The genetic algorithm is used to sequentially perform selection operation optimization, heuristic crossover operation optimization and non-uniform mutation operation optimization on each set of the profile distribution data based on the fitness index of each set of the blade profile scheme, and new profile control parameter coding after single iteration is output.

9. A blade aerodynamic profile generating device, characterized by Comprise: The evaluation module is used to determine the fitness index of each set of blade profile scheme based on the profile control parameter coding and the pre-determined blade profile constraint conditions, whole machine parameters, standard airfoil aerodynamic parameters and blade performance constraint conditions; The optimization module is used to select the profile control parameter coding corresponding to the optimal profile fitness index from the fitness index of each set of blade profile scheme; The control parameter coding of each set of the blade profile scheme is optimized based on the fitness index of each set of the blade profile scheme; the profile control parameter coding corresponding to the optimal profile fitness index is used to replace the profile control parameter coding corresponding to the worst profile fitness index after optimization, to obtain the optimized profile control parameter coding of the preset group; The blade profile generation module is used to take the optimized profile control parameter coding as the new profile control parameter coding, until the optimized profile control parameter coding meets the optimization iteration number, and the optimal profile control parameter coding is selected from the optimized profile control parameter coding to generate the blade aerodynamic profile distribution data.

10. A vane, characterized by The blade is generated by the blade aerodynamic profile generation method according to any one of claims 1-8. The blade is generated by the blade aerodynamic profile generation method according to any one of claims 1-8.

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