Blade aerodynamic profile design system and design method

Abstract

The application provides a blade aerodynamic profile design system and method, and the blade aerodynamic profile design system comprises a data loading module and a profile output module; the data loading module is used for reading an input file, and the input file comprises standard airfoil coordinate point clouds, standard airfoil aerodynamic parameters, a blade profile database, mechanical and electrical loss curves, airfoil trailing edge thickness correction curves and data extraction cross sections; if the data loading module determines that the input file is a finalized blade profile scheme, the input file is transmitted to the profile output module, and the profile output module generates a blade cross section airfoil, a three-dimensional space point cloud and a model file of a downstream application program; in this way, the blade cross section airfoil, the three-dimensional space point cloud and the model file of the downstream application program are directly generated by the profile output module, so that the blade aerodynamic profile design, expansion and output efficiency can be effectively improved.

Description

Technical Field

[0001] The present invention relates to the technical field of blade design, and in particular to a blade aerodynamic shape design system and a design method. Background Art

[0002] Blade aerodynamic shape design requires extensive analytical calculations and repetitive operations. Optimizing design solutions through program development and streamlining the design process can improve blade aerodynamic performance and save time and costs. However, generating the blade's 3D shape typically requires high-precision point cloud interpolation methods, combined with relative thickness and trailing edge thickness corrections to improve blade shape modeling efficiency and accuracy, resulting in relatively low blade shape output efficiency. Summary of the Invention

[0003] The present invention provides a blade aerodynamic shape design system and a design method, which are used to solve the defect of low blade shape output efficiency in the prior art.

[0004] The present invention provides a blade aerodynamic shape design system, comprising: a data loading module and a shape output module;

[0005] The data loading module is used to read input files, which include standard airfoil coordinate point clouds, standard airfoil aerodynamic parameters, blade shape database, mechanical and electrical loss curves, airfoil trailing edge thickness correction curves and data extraction sections;

[0006] If the data loading module determines that the input file is a finalized blade shape solution, the input file is transmitted to the shape output module, and the shape output module generates a blade cross-section airfoil, a three-dimensional space point cloud, and a model file for a downstream application.

[0007] According to a blade aerodynamic shape design system provided by the present invention, the model file includes: a Focus file, a CATIA file and a Bladed file;

[0008] The generation of blade cross-section airfoil, 3D point cloud and model files for downstream applications includes:

[0009] Based on the input file, a standard airfoil, a shape difference algorithm and a correction algorithm are defined, an execution script file of a target software is generated, and the target software is called to calculate the blade cross-section airfoil;

[0010] Based on the blade cross-section airfoil and the blade shape database, generating a Focus file by formatting output;

[0011] Based on the blade cross-section airfoil and the blade shape database, determining a three-dimensional point cloud of the blade, and generating a CATIA file by formatting output;

[0012] Based on the standard airfoil aerodynamic parameters and the blade profile database, a Bladed file is output by formatting.

[0013] The blade aerodynamic profile design system provided by the application further comprises a profile expansion module.

[0014] If the data loading module determines that the input file is a profile design scheme that needs to be expanded, the input file is transmitted to the profile expansion module to obtain an expanded profile design scheme, and the profile expansion module transmits the expanded profile design scheme to the profile output module as the profile scheme of the blade that has been finalized.

[0015] The profile expansion module is used to receive the input file transmitted by the data loading module, and then performs interactive adjustment and fairing processing on the profile design scheme that needs to be expanded, and performs a blade element momentum theory solution, and finally outputs the final expanded scheme and the performance of the expanded scheme as the expanded profile design scheme.

[0016] The blade aerodynamic profile design system provided by the application further comprises a profile design module.

[0017] If the aerodynamic profile of the blade needs to be initially designed, the data loading module transmits the input file to the profile design module, and after obtaining an automatically designed profile scheme, the profile design module transmits the automatically designed profile scheme to the profile expansion module.

[0018] The profile design module is used to receive the input file transmitted by the data loading module, and then determine a profile generation algorithm based on profile control parameters, design algorithm parameters and performance index constraints, and automatically design the initial aerodynamic profile design scheme based on the profile generation algorithm to obtain an initial profile design scheme.

[0019] The blade aerodynamic profile design system provided by the application further comprises an aerodynamic performance analysis module.

[0020] The aerodynamic performance analysis module is used to output basic operating parameters, aerodynamic performance parameters and steady-state operating loads of the blade based on a blade element momentum theory solver.

[0021] The blade aerodynamic profile design system provided by the application further comprises a stall performance analysis module.

[0022] The stall performance analysis module is used to output operating angle of attack distribution, Reynolds number distribution and circulation distribution of the blade under different incoming flow wind speeds based on a blade element momentum theory solver.

[0023] The blade aerodynamic profile design system according to the present application further comprises a scheme comparison module.

[0024] The scheme comparison module is used for graphical comparison of different aerodynamic design schemes, and outputs aerodynamic profile distribution, basic operation parameters, aerodynamic performance parameters and steady-state operation load parameters.

[0025] The present application further provides a blade aerodynamic profile design method, comprising:

[0026] reading an input file, wherein the input file comprises standard airfoil coordinate point cloud, standard airfoil aerodynamic parameters, blade profile database, mechanical and electrical loss curves, airfoil trailing edge thickness correction curves and data extraction cross section;

[0027] if it is determined that the input file is a finalized blade profile scheme, the input file is transmitted to a profile output module, and the profile output module generates a blade cross-section airfoil, a three-dimensional space point cloud and a model file of a downstream application program.

[0028] The blade aerodynamic profile design system according to the present application comprises a data loading module and a profile output module; the data loading module is used for reading an input file, wherein the input file comprises standard airfoil coordinate point cloud, standard airfoil aerodynamic parameters, blade profile database, mechanical and electrical loss curves, airfoil trailing edge thickness correction curves and data extraction cross section; if the data loading module determines that the input file is a finalized blade profile scheme, the input file is transmitted to the profile output module, and the profile output module generates a blade cross-section airfoil, a three-dimensional space point cloud and a model file of a downstream application program; the blade cross-section airfoil, the three-dimensional space point cloud and the model file of the downstream application program are directly generated through the profile output module, without using high-order precision point cloud difference method, thereby effectively improving the blade profile output efficiency. BRIEF DESCRIPTION OF DRAWINGS

[0029] In order to more clearly illustrate the technical solutions in the present application or prior art, the following will briefly introduce the drawings needed in the embodiments or prior art description. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative effort.

[0030] Figure 1 is a structural schematic diagram of the blade aerodynamic profile design system according to the present application;

[0031] Figure 2 is a display interface of the profile output module according to the embodiment of the present application;

[0032] Figure 3This is the display interface of the appearance expansion module provided by the embodiment of the present invention;

[0033] Figure 4 This is the display interface of the appearance design module provided by the embodiment of the present invention;

[0034] Figure 5 yes Figure 4 The fitness display interface in ;

[0035] Figure 6 yes Figure 4 The optimization algorithm display interface in ;

[0036] Figure 7 yes Figure 4 Optimization result display interface;

[0037] Figure 8 yes Figure 4 Random result display interface;

[0038] Figure 9 This is the display interface of the aerodynamic performance analysis module provided by the embodiment of the present invention;

[0039] Figure 10 This is the display interface of the stall performance analysis module provided by an embodiment of the present invention;

[0040] Figure 11 This is the display interface of the solution comparison module provided in the embodiment of the present invention;

[0041] Figure 12 This is the display interface of the appearance design module provided by the embodiment of the present invention;

[0042] Figure 13 yes Figure 12 The display interface of the airfoil parameter panel;

[0043] Figure 14 yes Figure 12 The display interface of the whole machine parameter panel;

[0044] Figure 15 yes Figure 12 The display interface of the solver settings panel in;

[0045] Figure 16 It is a schematic diagram of the principle of the aerodynamic shape design system provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0046] To make the objectives, technical solutions, and advantages of the present invention more clear, the technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the embodiments described are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts shall fall within the scope of protection of the present invention.

[0047] The following combination Figures 1 to 16 The present invention describes a blade aerodynamic shape design system and design method.

[0048] Figure 1 It is a structural schematic diagram of the blade aerodynamic shape design system provided by the present invention.

[0049] like Figure 1 As shown, an embodiment of the present invention provides a blade aerodynamic shape design system, including: a data loading module 1 and a shape output module 4; the data loading module 1 is used to read an input file, the input file including a standard airfoil coordinate point cloud, standard airfoil aerodynamic parameters (lift, drag, torsion coefficient), a blade shape database (chord length, twist angle, relative thickness, pitch axis, pre-bend, forward / backward sweep), mechanical and electrical loss curves, airfoil trailing edge thickness correction curve (relationship between relative thickness and trailing edge thickness) and a data extraction section (for extracting the blade spanwise coordinates of the data); if the data loading module 1 determines that the input file is a finalized blade shape scheme, the input file is transmitted to the shape output module 4, and the shape output module 4 generates a blade cross-section airfoil, a three-dimensional space point cloud and a model file of a downstream application.

[0050] In a specific implementation process, the data loading module will first read the input file. The input file is the content entered by the user himself, which is mainly divided into three situations. One is the finalized shape design scheme, that is, the overall blade shape scheme is known and only needs to be output through the blade aerodynamic shape design system. One is the shape design scheme that needs to be expanded, that is, the blade shape cannot be output directly, and the blade shape needs to be further expanded and optimized. One is the initial startup design, that is, the blade shape needs to be designed from the most basic steps, and then expanded and finally output.

[0051] Among them, the data loading module is used to start the loading of design files, appearance parameter statistics and graphical display.

[0052] The loading of design files includes: (1) loading the initial shape of a blade (chord length, twist angle, relative thickness, pitch axis, pre-bend, forward / backward sweep) from a database or a custom path as basic data; for the design work of the initial shape, the blade shape can be omitted; (2) loading additional data, including the trailing edge thickness correction curve and data extraction coordinates; when calculating the three-dimensional (3D) point cloud coordinates of the blade, the correction curve corrects the trailing edge thickness of airfoils with different relative thicknesses to achieve the effect of blade trailing edge modification; the data extraction section is used to select the spanwise coordinates of the blade for which output data is required; (3) loading loss correction data, including electrical loss and mechanical loss, and the type of loss is power or torque.

[0053] Shape parameter statistics: Perform statistics on the loaded shape data, and output blade length, blade root length, maximum chord length, maximum chord length coordinates, blade root shape, blade root twist angle, 0 degree twist angle coordinates and pre-bending data.

[0054] Graphical display: Displays the top view of the loaded blade's shape distribution (reflecting the distribution of the blade's chord length, leading / trailing edge lines, and forward / backward sweep), the side view of the shape distribution (reflecting the distribution of the blade's absolute thickness and pre-bend), the twist angle distribution diagram, and the relative thickness distribution diagram.

[0055] Therefore, after determining that the input file is a finalized shape design scheme, the 3D shape and related model files, that is, the blade cross-section airfoil, three-dimensional space point cloud and model files of downstream applications are directly generated through the shape output module.

[0056] Furthermore, the model files include: Focus files, CATIA files and Bladed files; model files for blade section airfoil, three-dimensional space point cloud and downstream applications are generated, including: based on the input file, standard airfoil, shape difference algorithm and correction algorithm are defined, the execution script file of the target software is generated, and the target software is called to calculate the blade section airfoil; based on the blade section airfoil and blade shape database, the Focus file is generated through formatted output; based on the blade section airfoil and blade shape database, the three-dimensional space point cloud of the blade is determined, and the CATIA file is generated through formatted output; based on the aerodynamic parameters of the standard airfoil and the blade shape database, the Bladed file is output through formatted output.

[0057] Specifically, the blade cross-section airfoil is generated by standard airfoil difference calculation. The difference method includes linear and nonlinear difference. The nonlinear difference is calculated by automatically generating target software (such as X-foil) to execute the script and call the software. At the same time, the relative thickness of each difference section can be corrected according to the shape distribution parameters, thereby improving the difference accuracy.

[0058] Meanwhile, the profile output module has a generation function of related design files, specifically including: generating a Focus software file through format output according to blade section airfoil (chord length normalization) and profile distribution data (chord length, torsion angle, relative thickness, variable pitch shaft, pre-bending, forward / backward sweep), which is used for blade structure design; calculating a 3D space point cloud of the blade according to the blade section airfoil and the blade profile database, and generating a CATIA file through format output, which is used for blade 3D profile modeling; generating a Bladed software file through format output according to standard airfoil aerodynamic parameters (lift, drag, torsion coefficient) and the blade profile database, which is used for detailed load analysis of the blade.

[0059] Figure 2 is a display interface of the profile output module provided by the embodiment of the present application, from Figure 2 It can be seen that the interface includes a difference method and correction interface, an output setting interface and a file self-defined generation interface below, and the specific interface functions have been described in the embodiment and will not be described in detail.

[0060] Further, on the basis of the above embodiment, the profile expansion module is further included in the embodiment, if the data loading module determines that the input file is a profile design scheme to be expanded, the input file is transmitted to the profile expansion module to obtain an expanded profile design scheme, and the profile expansion module transmits the expanded profile design scheme to the profile output module as a profile scheme of a blade that has been finalized.

[0061] The profile expansion module is used to receive the input file transmitted by the data loading module, and then interactively adjusts and smooths the profile design scheme to be expanded, and outputs a final expansion scheme and expansion scheme performance after solving the blade element momentum theory, as the expanded profile design scheme.

[0062] Specifically, the profile expansion module reads the data of the profile design scheme to be expanded, and performs local fine tuning and smoothing processing on the profile design scheme to be expanded through an interactive adjustment function, and outputs a final design scheme and performance analysis result after solving the blade element momentum theory.

[0063] The working process of the blade aerodynamic profile design system including the data loading module, the profile expansion module and the profile output module is described from the overall logic, mainly as follows:

[0064] (1) The data loading module reads the input file and transmits the data to the profile expansion module;

[0065] (2) Based on the input original blade data, i.e., the shape design scheme to be expanded, the blade expansion method (root expansion, tip expansion, and mid-leaf expansion) and the length change of the expansion area (length extension or shortening) are defined in the shape expansion module, and a new extended shape is generated by scaling along the blade span direction;

[0066] (3) Discretize the shape of the expansion area and use the interactive adjustment function of the shape expansion module to adjust the discrete shape distribution line segments. After the adjustment is completed, smooth the curve and perform blade element momentum theory analysis and calculation to determine the aerodynamic performance of the expansion scheme.

[0067] (4) Realize the design iteration of blade series expansion through the cyclic action of shape adjustment, shape smoothing and blade element momentum theory solution analysis and evaluation;

[0068] (5) Finally, the function of the shape output module is executed in the same manner as in the above embodiment to complete the expansion and output of the shape design scheme to be expanded.

[0069] The shape expansion module is specifically used for the serialized design of blades. It can realize automatic scaling, smoothing, interactive shape adjustment of the expansion area, and rapid analysis using the boundary element method (BEM).

[0070] Among them, the shape expansion module includes three shape expansion methods: root segment expansion, tip segment expansion and mid-blade segment expansion. After defining the starting / ending positions of the expansion area (corresponding to the original blade mold) and the change amount of the expansion area (the scaled length of the new mold), the shape expansion module automatically scales in the span direction to generate a new shape; in addition, the blade root parameters (blade root twist angle, blade root diameter and length) can be customized during automatic expansion.

[0071] After generating the automatically expanded shape, the shape distribution curve of the expanded area is discretized. Graphical interaction is used to move the discrete points to their new positions. A smoothing curve is generated based on the coordinates of the discrete points, and the aerodynamic shape data is then updated. Shape parameters that can be adjusted through graphical interaction include chord length, twist angle, relative thickness, leading edge distribution curve (the pitch axis and trailing edge distribution curves are automatically calculated using the chord length data), and pre-bend.

[0072] The shape expansion module can directly perform BEM analysis on the current solution and quickly provide the Cp-tip speed ratio curve and thrust-wind speed curve, thereby significantly shortening the operation time of shape adjustment and performance analysis and providing shape expansion solutions more quickly.

[0073] Figure 3 This is the display interface of the appearance expansion module provided by the embodiment of the present invention, such as Figure 3 As shown, the functional area of ​​the appearance expansion module includes the following:

[0074] (1) Extension parameters: define the extension area, length variation and root parameters of the blade;

[0075] (2) Basic operations: switching the displayed shape parameters, generating, discretizing, calculating and saving extended shapes;

[0076] (3) Performance prediction: Displays the BEM calculation results of the current expansion scheme, including: Cp peak, thrust peak, optimal tip speed ratio, thrust coefficient, rated wind speed and fixed wind speed (wind speed corresponding to rated wind speed);

[0077] (4) Display window: Display and interactive adjustment window of shape parameters, which can also display the Cp-tip speed ratio and thrust-wind speed curve of BEM analysis results.

[0078] Furthermore, based on the above embodiment, the blade aerodynamic shape design system in this embodiment also includes a shape design module; if it is necessary to perform initial design of the aerodynamic shape of the blade, the data loading module transmits the input file to the shape design module, and after obtaining the automatically designed shape scheme, the shape design module transmits the automatically designed shape scheme to the shape expansion module.

[0079] Among them, the shape design module is used to receive the input file transmitted by the data loading module, determine the shape generation algorithm based on the shape control parameters, design algorithm parameters and performance index constraints, and automatically design the initial aerodynamic shape design scheme based on the shape generation algorithm to obtain the initial shape design scheme.

[0080] Specifically, the shape design module is used for the automated design of the blade's aerodynamic shape, enabling global / local optimization of the blade's shape and rapid traversal of the aerodynamic shape. For a blade aerodynamic shape design system comprising a data loading module, a shape design module, a shape expansion module, and a shape output module, the overall workflow can be as follows: the data loading module reads the input file and passes the data to the shape design module; the shape design module defines blade shape control parameters (such as chord length, twist angle, and relative thickness distribution range), design algorithm parameters (such as the number of initial solutions, number of iterations, optimization criteria, etc.), and performance indicator constraints (such as Cp peak, thrust peak, tip speed ratio, etc.), and then randomly generates aerodynamic shape solutions through a shape generation algorithm. These solutions are then input into the shape expansion module as the shape design solutions to be expanded. The working process of the shape expansion module is described in the above embodiment and will not be explained in detail.

[0081] Automatic aerodynamic shape design methods include optimization algorithm design and random scheme screening:

[0082] (1) Optimization algorithm design: Randomly generate a population of blade shapes, calculate the performance indicators of each shape (such as Cp peak, thrust peak, tip speed ratio, thrust coefficient, etc.) through the platform's BEM solver kernel, and optimize the blade's aerodynamic shape parameters based on a genetic algorithm;

[0083] (2) Random scheme screening: By constraining the shape parameters, randomly generate shape schemes, perform BEM analysis and calculation, and determine the performance indicators to determine whether the performance indicators meet the design requirements; repeat the above steps to generate a large number of random schemes that meet the requirements, and then manually screen out the optimal scheme.

[0084] Figure 4 This is the display interface of the appearance design module provided by the embodiment of the present invention. Figure 5 yes Figure 4 The fitness display interface in Figure 6 yes Figure 4 The optimization algorithm display interface in Figure 7 yes Figure 4 The optimization result display interface, Figure 8 yes Figure 4 The random result display interface.

[0085] like Figure 4 As shown in the figure, the functional area of ​​the appearance design module includes the following:

[0086] (1) Design objectives: performance indicators and appearance indicators used to control the design scheme;

[0087] (2) Adaptability: used to define the optimization criteria of the optimization design method (including maximizing wind energy utilization, minimizing ultimate thrust, minimizing tip speed ratio), as well as the calculation parameters of performance evaluation indicators. The specific interface is as follows: Figure 5 As shown;

[0088] (3) Optimization algorithm: used to define the selection operator, crossover operator and mutation operator model of the genetic algorithm. The specific interface is as follows: Figure 6 As shown;

[0089] (4) Shape control parameters: define the range of chord length, twist angle and relative thickness distribution parameters to control the randomly generated aerodynamic shape scheme;

[0090] (5) Process monitor: used for real-time monitoring of the shape distribution and aerodynamic performance indicators of the solution set during the optimization design process;

[0091] (6) Optimization results: Output the main performance indicators of the final optimized design solution, the shape distribution data and the graphical display of the steady-state power analysis, specifically displayed as follows Figure 7 As shown;

[0092] (7) Random results: used for real-time monitoring and graphical display of the aerodynamic performance of random schemes, specifically displayed as follows Figure 8 shown.

[0093] Figure 9 This is the display interface of the aerodynamic performance analysis module provided by the embodiment of the present invention. Figure 10 This is the display interface of the stall performance analysis module provided by the embodiment of the present invention. Figure 11 This is the display interface of the solution comparison module provided in the embodiment of the present invention.

[0094] Furthermore, based on the above embodiment, this embodiment also includes an aerodynamic performance analysis module, a stall performance analysis module, and a scheme comparison module. The aerodynamic performance analysis module is used to output the basic operating parameters, aerodynamic performance parameters, and steady-state operating loads of the blade based on the blade element momentum theory solver. The stall performance analysis module is used to output the operating angle of attack distribution, Reynolds number distribution, and circulation distribution of the blade under different incoming wind speeds based on the blade element momentum theory solver. The scheme comparison module is used to graphically compare different aerodynamic design schemes and output aerodynamic shape distribution, basic operating parameters, aerodynamic performance parameters, and steady-state operating load parameters.

[0095] The aerodynamic performance analysis module and the stall performance analysis module implement related analysis and calculation functions based on the BEM solver kernel of the platform. The aerodynamic performance analysis module calculates and outputs the basic operating parameters of the blade (such as: wind speed-rotation curve, power generation / aerodynamic power curve, pitch angle change curve); aerodynamic performance parameters (such as: Cp-tip speed ratio curve, wind rotor thrust curve, tip speed ratio curve, thrust coefficient curve and power coefficient curve); steady-state operating load (such as: blade element thrust / torque distribution, axial / tangential induction coefficient distribution, lift / drag coefficient distribution). The aerodynamic performance analysis module includes 4 graphical windows that can display 4 variable data at the same time, such as Figure 9 shown.

[0096] like Figure 10 As shown, the stall performance analysis module calculates and outputs the blade's operating angle of attack distribution, Reynolds number distribution, and circulation distribution under different incoming wind speeds; the angle of attack distribution display window can display the stall angle of attack of the standard airfoil to help determine the blade's stall margin; the Reynolds number distribution display window can display the Reynolds number corresponding to the standard airfoil to help determine whether the airfoil parameters need to be corrected for the Reynolds number effect.

[0097] The scheme comparison module is used for graphical comparison of aerodynamic design schemes. It has 6 data output channels. The output variables include aerodynamic shape distribution, basic operating parameters, aerodynamic performance parameters and steady-state operating load parameters, such as Figure 11 shown.

[0098] Among them, the workflow of the blade aerodynamic shape design system, which includes the data loading module, shape design module, shape expansion module, aerodynamic performance analysis module, stall performance analysis module, scheme comparison module and shape output module, is explained from the overall logic, mainly as follows:

[0099] (1) The data loading module reads the input file and passes the data to the shape design module;

[0100] (2) The shape design module defines the blade shape control parameters (such as chord length, twist angle, and relative thickness distribution range), design algorithm parameters (such as the number of initial solutions, number of iterations, and optimization criteria), and performance index constraints (such as Cp peak, thrust peak, and tip speed ratio).

[0101] (3) The shape design module randomly generates an aerodynamic shape scheme through a shape generation algorithm. The calculation kernel of the aerodynamic performance analysis module and the stall performance analysis module (BEM algorithm based on blade element momentum theory) calculates the aerodynamic performance (such as Cp peak, thrust peak, Cp-tip speed ratio curve, etc.), power characteristics (such as power curve, speed curve, rated wind speed, etc.) and stall characteristics (such as angle of attack distribution, stall margin, etc.) of the shape scheme.

[0102] (4) The scheme comparison module uses an optimization algorithm to evaluate the shape scheme based on the BEM calculation results, and adjusts the shape generation parameters according to the optimization criteria (such as maximizing wind energy utilization, minimizing peak thrust, minimizing thrust coefficient, etc.), and then feeds back to the shape generation algorithm to regenerate the shape scheme. It iterates repeatedly until the constraints of the performance indicators are met, and caches the automatic design scheme as the shape design scheme to be expanded;

[0103] (5) The shape expansion module reads the shape design scheme to be expanded, and through the interactive adjustment function, performs local fine-tuning and smoothing processing on the automatically designed shape scheme. After performing BEM analysis, it outputs the final design scheme and performance analysis results, and outputs the value shape output module;

[0104] (6) The shape expansion module loads the data of the final design scheme (including: chord length, twist angle, relative thickness, pitch axis, pre-bend, forward / backward sweep) into the shape output module, defines the standard airfoil, shape difference algorithm and correction algorithm, generates the execution script file of the X-foil software, calculates the point cloud coordinates of the airfoil with different relative thicknesses by calling the X-foil software, and further combines the aerodynamic shape data to perform spatial point cloud computing to obtain the 3D shape of the blade and related model files (blade model of Bladed software, STP file of spatial point cloud, Focus model of blade structure design).

[0105] The blade aerodynamic shape design system of the present invention aims to achieve automation and rapidity in all aspects of blade aerodynamic design work. Specifically, it can realize the main functions such as automatic optimization design of blade aerodynamic shape, traversal and screening of shape schemes, automatic expansion of serialized blades, aerodynamic performance and stall analysis and calculation, and automatic calculation and output of 3D shape.

[0106] Figure 12 This is the display interface of the appearance design module provided by the embodiment of the present invention. Figure 13 yes Figure 12 The display interface of the airfoil parameter panel in Figure 14 yes Figure 12 The display interface of the whole machine parameter panel, Figure 15 yes Figure 12 The display interface of the solver settings panel in .

[0107] like Figure 12 As shown, the graphical interface includes: airfoil parameter panel, whole machine parameter panel, solver setting panel, graphic tool panel, module tab and main function area.

[0108] Among them, such as Figure 13 As shown, the airfoil parameter panel is used to define the aerodynamic parameters (lift, drag, torsion coefficient) and airfoil point cloud coordinates of the standard airfoil; the above data can be directly selected from the platform's blade shape database, or a custom file path can be used.

[0109] like Figure 14 As shown, the whole machine parameter panel is used for the environmental parameters and state parameters of the wind turbine operation, which is the basic data for BEM (Blade Element Momentum Theory) analysis; including: air density, air viscosity, wind turbine cut-in / out wind speed, minimum / rated speed of the wind rotor, maximum / minimum value of the tip speed ratio, blade installation angle, wind rotor cone angle, generator rated torque / speed, and gearbox speed ratio (automatically calculated by the rated speed of the wind rotor and generator).

[0110] like Figure 15 As shown, the solver setting panel is used to control the input parameters and correction models of the BEM calculation process. The input parameters include: BEM convergence accuracy, BEM iteration step, tip speed ratio / wind speed and pitch angle discrete scale; the correction model includes: mechanical loss correction, electrical loss correction, three-dimensional rotation effect correction, and induction factor correction.

[0111] Graphics tool panel: used for interactive operations of graphically displaying data, including zooming in, moving, rotating, adding data labels, etc.

[0112] Main function area: used to display the operation interface of the current function module.

[0113] Module tab: used to switch the operation interface of different modules.

[0114] Figure 16 It is a schematic diagram of the principle of the aerodynamic shape design system provided by an embodiment of the present invention.

[0115] like Figure 16 As shown, the custom import is the data loading module 1, and from left to right are the shape design module 3, the shape expansion module 4 and the shape output module 2. The arrows shown above are the corresponding three situations. Therefore, the corresponding module can be selected according to the processing results of the data loading module 1. The specific process has been introduced in detail in the above embodiment, and the detailed process of each module is no longer described. When the data loading module 1 determines that the input file is the initial aerodynamic shape design scheme of the blade, the data flow is data loading module 1-shape design module 3-shape expansion module 4-shape output module 2; when the data loading module 1 determines that the input file is a shape design scheme that needs to be expanded, the data flow is data loading module 1-shape expansion module 4-shape output module 2. When the data loading module 1 determines that the input file is a shape design scheme that has been finalized, the data flow is data loading module 1-shape output module 4.

[0116] The aerodynamic shape design system of the present invention includes optimization design, extended design, analysis and calculation, and modeling output modules, which integrate and cover all functional requirements of the initial aerodynamic design of the blade; it can realize the automatic optimization design function of the blade aerodynamic shape; through an interactive extended design method, it can quickly carry out serial design and aerodynamic performance comparison; call X-foil software to perform shape difference calculation to improve the shape generation accuracy, and effectively improve the work efficiency of the initial design, extended design, aerodynamic analysis and shape output of the blade aerodynamic shape.

[0117] Based on the same general inventive concept, the present invention also protects a method for designing a blade aerodynamic shape, comprising:

[0118] Reading an input file, wherein the input file includes a standard airfoil coordinate point cloud, a standard airfoil aerodynamic parameters, a blade shape database, mechanical and electrical loss curves, an airfoil trailing edge thickness correction curve, and a data extraction section;

[0119] If it is determined that the input file is a finalized blade shape solution, the input file is transmitted to the shape output module, and the shape output module generates a blade cross-section airfoil, a three-dimensional space point cloud, and a model file for a downstream application.

[0120] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate, and the components shown as units may or may not be physical units, i.e., they may be located in one location or distributed across multiple network units. Some or all of the modules may be selected based on actual needs to achieve the objectives of the present embodiment. Persons of ordinary skill in the art will be able to understand and implement the present invention without inventive effort.

[0121] Through the description of the above embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus the necessary general hardware system, or of course, by hardware. Based on this understanding, the above technical solution, in essence, or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a magnetic disk, an optical disk, etc., and includes a number of instructions for enabling a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or certain parts of the embodiments.

[0122] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A blade aerodynamic shape design system, characterized in that: include: Data loading module and shape output module; The data loading module is used to read input files, which include standard airfoil coordinate point clouds, standard airfoil aerodynamic parameters, blade shape database, mechanical and electrical loss curves, airfoil trailing edge thickness correction curves and data extraction sections; If the data loading module determines that the input file is a finalized blade shape scheme, the input file is transmitted to the shape output module, and the shape output module generates a blade cross-section airfoil, a three-dimensional space point cloud, and a model file for a downstream application; The system also includes an appearance expansion module; If the data loading module determines that the input file is an appearance design scheme that needs to be expanded, the input file is transmitted to the appearance expansion module to obtain the expanded appearance design scheme. The appearance expansion module transmits the expanded appearance design scheme as the finalized blade appearance scheme to the appearance output module.

2. The blade aerodynamic shape design system according to claim 1, characterized in that: The model files include: Focus file, CATIA file and Bladed file; The generation of blade cross-section airfoil, 3D point cloud and model files for downstream applications includes: Based on the input file, a standard airfoil, a shape difference algorithm and a correction algorithm are defined, an execution script file of a target software is generated, and the target software is called to calculate the blade cross-section airfoil; Based on the blade cross-section airfoil and the blade shape database, generating a Focus file by formatting output; Based on the blade cross-section airfoil and the blade shape database, determining a three-dimensional point cloud of the blade, and generating a CATIA file by formatting output; Based on the standard airfoil aerodynamic parameters and the blade shape database, a Bladed file is output through formatting.

3. The blade aerodynamic shape design system according to claim 1, characterized in that: The shape expansion module is used to receive the input file transmitted by the data loading module, interactively adjust and smooth the shape design scheme to be expanded, solve the blade element momentum theory, and output the final expansion scheme and the performance of the expansion scheme as the expanded shape design scheme.

4. The blade aerodynamic shape design system according to claim 1, characterized in that: Also includes appearance design module; If it is necessary to perform an initial design on the aerodynamic shape of the blade, the data loading module transmits the input file to the shape design module. After obtaining the automatically designed shape scheme, the shape design module transmits the automatically designed shape scheme to the shape expansion module.

5. The blade aerodynamic shape design system according to claim 4, characterized in that: The shape design module is used to receive the input file transmitted by the data loading module, determine the shape generation algorithm based on the shape control parameters, design algorithm parameters and performance index constraints, and automatically design the initial aerodynamic shape design scheme based on the shape generation algorithm to obtain the initial shape design scheme.

6. The blade aerodynamic shape design system according to any one of claims 1 to 5, characterized in that: Also includes aerodynamic performance analysis module; The aerodynamic performance analysis module is used to output basic operating parameters, aerodynamic performance parameters and steady-state operating loads of the blade based on a blade element momentum theory solver.

7. The blade aerodynamic shape design system according to any one of claims 1 to 5, characterized in that: Also included is a stall performance analysis module; The stall performance analysis module is used to output the blade's operating angle of attack distribution, Reynolds number distribution, and circulation distribution under different incoming wind speeds based on a blade element momentum theory solver.

8. The blade aerodynamic shape design system according to any one of claims 1 to 5, characterized in that: It also includes a plan comparison module; The scheme comparison module is used for graphical comparison of different aerodynamic design schemes and outputs aerodynamic shape distribution, basic operating parameters, aerodynamic performance parameters and steady-state operating load parameters.

9. A method for designing aerodynamic shape of a blade, characterized in that: The method is executed in the blade aerodynamic shape design system according to any one of claims 1 to 8, and the method comprises: Reading an input file, wherein the input file includes a standard airfoil coordinate point cloud, a standard airfoil aerodynamic parameters, a blade shape database, mechanical and electrical loss curves, an airfoil trailing edge thickness correction curve, and a data extraction section; If it is determined that the input file is a finalized blade shape solution, the input file is transmitted to a shape output module, and the shape output module generates a blade cross-section airfoil, a three-dimensional space point cloud, and a model file for a downstream application.

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