Blade performance determination method and device, storage medium and electronic equipment

Abstract

The invention provides a blade performance determination method and device, a storage medium and electronic equipment, and the method comprises the steps: determining a plurality of primitives, the primitives are blade profiles after a plane where a blade intersects with the side surface of a corresponding target cylinder is unfolded, and the cross section of the target cylinder is a target circle; two-dimensional blade profile parameters of all the primitives are determined, the mean camber line and thickness distribution of the primitives are determined according to the two-dimensional blade profile parameters, and the two-dimensional blade profile parameters at least comprise structure parameters of part of blades corresponding to the primitives; and according to the mean camber line and thickness distribution of the primitives, stacking all the primitives in a stacking manner to obtain a blade simulation model of the blade, and performing simulation analysis on the blade based on fluid dynamics and the blade simulation model to obtain performance parameters of the blade. According to the method, the modeling efficiency of the axial flow fan blade of the air conditioner outdoor unit can be improved, the blade performance can be accurately obtained, the three-dimensional blade design is optimized through the three-dimensional parametric modeling method, and the workload of blade analysis is greatly reduced.

Description

Technical Field

[0001] This application relates to the field of simulation modeling, and more specifically, to a method for determining blade performance, a device for determining blade performance, a computer-readable storage medium, and an electronic device. Background Technology

[0002] In the air conditioning industry, three-dimensional complex curved and twisted composite blades are widely used in the outdoor fans of air conditioning systems. These blades have complex shapes and exhibit high spatial bending and twisting characteristics. The design of the blades directly affects the performance and noise level of the entire system, making it one of the core elements for improving air conditioning system performance. However, existing modeling methods for air conditioning blades mainly rely on traditional design experience and reverse engineering, making it difficult to achieve rapid and accurate parametric modeling.

[0003] Existing methods for fabricating complex 3D curved and twisted blades suffer from problems such as low modeling efficiency, long design cycles, insufficient parametric capabilities, and poor adaptability to complex geometric features. In particular, existing technologies struggle to meet the practical requirements of air conditioning systems for low power consumption, low noise, and high heat transfer performance in areas such as parametric representation of bending and twisting of air conditioning blades, aerodynamic performance optimization, and smoothness control of complex surfaces. Summary of the Invention

[0004] The main objective of this application is to provide a method, apparatus, computer-readable storage medium, and electronic device for determining blade performance, so as to at least solve the problem that the construction of wind turbine blade simulation models in the prior art is inaccurate and inefficient, which leads to the inability to effectively optimize the performance of real blades.

[0005] To achieve the above objectives, according to one aspect of this application, a method for determining blade performance is provided, comprising: determining a plurality of basic elements, wherein each basic element is an airfoil formed by unfolding a plane from the intersection of the blade and the side surface of a corresponding target cylinder, the cross section of the target cylinder is a target circle, the center of the target circle is the hub center of the blade, the radius of the target circle is less than the distance from the hub center of the blade to the blade tip, and the radii of the target circles corresponding to any two basic elements are different; determining two-dimensional airfoil parameters for each basic element, and determining the mid-curve line and thickness distribution of the basic element based on the two-dimensional airfoil parameters, wherein the two-dimensional airfoil parameters include at least some structural parameters of the blade corresponding to the basic element; stacking all the basic elements using an accumulation method based on the mid-curve line and thickness distribution of the basic element to obtain a blade simulation model of the blade, and performing simulation analysis on the blade based on fluid dynamics and the blade simulation model to obtain the performance parameters of the blade.

[0006] Optionally, determining multiple primitives includes: acquiring the number of primitives, the tip radius of the blade, and the hub radius of the blade, and sequentially labeling the multiple primitives; determining the difference between the tip radius of the blade and the hub radius of the blade as a first calculated value; determining the ratio of the label of the current primitive to the number of primitives as a second calculated value; if the radii of the target circles corresponding to the multiple primitives are determined to be an arithmetic sequence, determining the radius of the current primitive based on the first calculated value and the second calculated value; if the radii of the target circles corresponding to the multiple primitives are determined to be a non-arithmetic sequence, determining the radius of the current primitive based on the first calculated value, the second calculated value, and the hub radius of the blade, thereby determining the multiple primitives.

[0007] Optionally, when the radii of the target circles corresponding to the plurality of primitives are determined to be an arithmetic sequence, the radius of the current primitive is determined based on the first calculated value and the second calculated value, including: multiplying the first calculated value and the second calculated value to determine the radius of the target circle corresponding to the current primitive; and / or, when the radii of the target circles corresponding to the plurality of primitives are determined to be a non-arithmetic sequence, the radius of the current primitive is determined based on the first calculated value, the second calculated value and the hub radius of the blade, including: multiplying the square of the first calculated value and the second calculated value to determine a third calculated value, and taking the square root of the sum of the third calculated value and the square of the hub radius to obtain the radius of the target circle corresponding to the current primitive.

[0008] Optionally, the two-dimensional airfoil parameters include the trailing edge direction angle, chord length, installation angle, and leading edge direction angle of the blade. Determining the mid-arc line of the primitive element based on the two-dimensional airfoil parameters includes: determining the order of the Bézier curve; determining the number and coordinates of control points based on the order of the Bézier curve, and sequentially labeling the control points; determining the Bernstein polynomial corresponding to each control point based on the factorial of the control point's label, the factorial of the order of the Bézier curve, and the curve parameters of the Bézier curve; determining the Bézier curve based on the Bernstein polynomial corresponding to each control point and the coordinates of each control point, and defining the Bézier curve as the mid-arc line of the primitive element.

[0009] Optionally, determining the number and coordinates of control points based on the order of the Bézier curve includes: adding one to the order of the Bézier curve to obtain the number of control points; determining the starting control point as the origin of a two-dimensional Cartesian coordinate system; determining the product of the cosine of the mounting angle and the chord length as the abscissa of the ending control point, and determining the product of the sine of the mounting angle and the chord length as the ordinate of the ending control point, thus obtaining the coordinates of the ending control point; determining the relative curvature of the blade, and determining the curvature of the blade based on the relative curvature and the chord length; determining a first set of intermediate control points based on the starting control point, the leading edge direction angle, and the curvature, wherein the angle between the line connecting the starting control point and the first set of intermediate control points and the first coordinate axis is the leading edge direction angle; determining a second set of intermediate control points based on the ending control point, the trailing edge direction angle, and the curvature, wherein the angle between the line connecting the ending control point and the second set of intermediate control points and the first coordinate axis is the trailing edge direction angle.

[0010] Optionally, the blade thickness has an unequal distribution. The two-dimensional blade profile parameters include the chord length, root thickness, and tip thickness of the blade. Determining the thickness distribution of the primitive based on the two-dimensional blade profile parameters includes: normalizing the chord length of the blade to obtain a normalized chord length; determining the root thickness and tip thickness of the blade, where the root thickness is the thickness at the closest point between the blade and the hub, and the tip thickness is the thickness at the farthest point between the blade and the hub; performing a first exponential operation on the difference between 1 and the normalized chord length to obtain a first parameter term, and performing a second exponential operation on the normalized chord length to obtain a second parameter term, where the first exponent of the first exponential operation is an exponential parameter controlling the rate of thickness change, and the second exponent of the second exponential operation is another exponential parameter controlling the rate of thickness change; determining the product of the root thickness and the first parameter term as a first term, and determining the product of the tip thickness and the second parameter term as a second term; and determining the sum of the first term and the second term as the thickness at the current position of the primitive.

[0011] Optionally, the stacking method includes one of leading edge stacking, trailing edge stacking, and centroid stacking.

[0012] According to another aspect of this application, a blade performance determination apparatus is provided, comprising: a first determining unit, configured to determine a plurality of basic elements, wherein each basic element is an airfoil formed by unfolding a plane from which the blade intersects with the side surface of a corresponding target cylinder, the cross section of the target cylinder is a target circle, the center of the target circle is the hub center of the blade, the radius of the target circle is less than the distance from the hub center of the blade to the blade tip, and the radii of the target circles corresponding to any two basic elements are different; a second determining unit, configured to determine two-dimensional airfoil parameters of each basic element, and determine the mid-curve line and thickness distribution of the basic element based on the two-dimensional airfoil parameters, wherein the two-dimensional airfoil parameters include at least some structural parameters of the blade corresponding to the basic element; and a simulation unit, configured to stack all the basic elements in a stacking manner according to the mid-curve line and thickness distribution of the basic elements to obtain a blade simulation model of the blade, and perform simulation analysis on the blade based on fluid dynamics and the blade simulation model to obtain the performance parameters of the blade.

[0013] According to another aspect of this application, a computer-readable storage medium is provided, the computer-readable storage medium including a stored program, wherein, when the program is executed, it controls the device where the computer-readable storage medium is located to perform any of the blade performance determination methods described above.

[0014] According to another aspect of this application, an electronic device is provided, comprising: one or more processors, a memory, and one or more programs, wherein the one or more programs are stored in the memory and configured to be executed by the one or more processors, the one or more programs including a method for performing any of the blade performance determination methods described above.

[0015] Applying the technical solution of this application, the method for determining the blade performance first determines multiple primitives. Each primitive is the blade profile formed by unfolding the plane where the blade intersects with the side of the corresponding target cylinder, and the cross-section of the target cylinder is the target circle. Then, the two-dimensional blade profile parameters of each primitive are determined, and based on these parameters, the mid-curve and thickness distribution of the primitive are determined. These parameters include at least some structural parameters of the blade corresponding to the primitive. Finally, based on the mid-curve and thickness distribution, all primitives are stacked to obtain a blade simulation model. The blade is then simulated and analyzed based on fluid dynamics and the simulation model to obtain its performance parameters. This method improves the efficiency of modeling axial flow fan blades in air conditioning outdoor units through rapid parametric modeling of complex three-dimensional curved and twisted composite blades. By extracting relevant characteristic parameters of the fan blades using this method, blade performance can be accurately obtained. Furthermore, the three-dimensional parametric modeling method optimizes the three-dimensional blade design, significantly reducing the workload of blade analysis, thereby more scientifically improving the aerodynamic performance of axial flow fan blades. This solves the problem in existing technologies where the construction of fan blade simulation models is inaccurate and inefficient, leading to an inability to effectively optimize the performance of real blades. Attached Figure Description

[0016] The accompanying drawings, which form part of this application, are used to provide a further understanding of this application. The illustrative embodiments and descriptions of this application are used to explain this application and do not constitute an undue limitation of this application. In the drawings:

[0017] Figure 1 A hardware structure block diagram of a mobile terminal for performing a method for determining blade performance according to an embodiment of this application is shown.

[0018] Figure 2 A flowchart illustrating a method for determining blade performance according to an embodiment of this application is shown.

[0019] Figure 3 A schematic diagram of a parametric fan blade provided according to an embodiment of this application is shown;

[0020] Figure 4 A two-dimensional leaf shape schematic diagram of a basic element provided according to an embodiment of this application is shown;

[0021] Figure 5 A schematic diagram of a mid-arc superimposed thickness distribution is shown according to an embodiment of this application;

[0022] Figure 6 A schematic diagram of a parameterized blade Z-plane projection according to an embodiment of this application is shown;

[0023] Figure 7 A schematic diagram of the axial projection of a parameterized blade according to an embodiment of this application is shown;

[0024] Figure 8 A schematic diagram of a parameterized blade provided according to an embodiment of this application is shown;

[0025] Figure 9 A flowchart illustrating another method for determining blade performance according to an embodiment of this application is shown.

[0026] Figure 10 A structural block diagram of a blade performance determination device provided according to an embodiment of this application is shown.

[0027] The above figures include the following reference numerals:

[0028] 1. First primitive; 2. Nth primitive; 3. Intermediate primitive; 4. Trailing edge direction angle; 5. Mid-arc line; 6. Chord length; 7. Mounting angle; 8. Leading edge direction angle; 9. Curve angle; 10. Leading edge overlap line; 11. Sweep angle; 102. Processor; 104. Memory; 106. Transmission device; 108. Input / output device. Detailed Implementation

[0029] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0030] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort should fall within the scope of protection of the present application.

[0031] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate for the embodiments of this application described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0032] As described in the background section, existing methods for handling complex three-dimensional curved and twisted blades suffer from problems such as low modeling efficiency, long design cycles, insufficient parameterization, and poor adaptability to complex geometric features. In particular, existing technologies struggle to meet the actual requirements of air conditioning systems for low power, low noise, and high heat transfer performance in areas such as the parameterized expression of bending and twisting of air conditioning blades, aerodynamic performance optimization, and smoothness control of complex surfaces. To address the problem of inaccurate and inefficient construction of existing wind turbine blade simulation models, which prevents effective optimization of real blade performance, embodiments of this application provide a method for determining blade performance, a device for determining blade performance, a computer-readable storage medium, and an electronic device.

[0033] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.

[0034] The methods and embodiments provided in this application can be executed on a mobile terminal, computer terminal, or similar computing device. Taking running on a mobile terminal as an example, Figure 1 This is a hardware structure block diagram of a mobile terminal for a method of determining blade performance according to an embodiment of the present invention. (See diagram below.) Figure 1 As shown, a mobile terminal may include one or more ( Figure 1 Only one is shown in the diagram. A processor 102 (which may include, but is not limited to, a microprocessor MCU or a programmable logic device FPGA, etc.) and a memory 104 for storing data are also shown. The mobile terminal may further include a transmission device 106 for communication functions and an input / output device 108. Those skilled in the art will understand that... Figure 1 The structure shown is for illustrative purposes only and does not limit the structure of the mobile terminal described above. For example, the mobile terminal may also include components that are more... Figure 1 The more or fewer components shown, or having the same Figure 1 The different configurations shown.

[0035] The memory 104 can be used to store computer programs, such as application software programs and modules, like the computer program corresponding to the blade performance determination method in this embodiment of the invention. The processor 102 executes various functional applications and data processing by running the computer program stored in the memory 104, thereby implementing the above-described method. The memory 104 may include high-speed random access memory and non-volatile memory, such as one or more magnetic storage devices, flash memory, or other non-volatile solid-state memory. In some instances, the memory 104 may further include memory remotely located relative to the processor 102, and these remote memories can be connected to the mobile terminal via a network. Examples of the aforementioned networks include, but are not limited to, the Internet, corporate intranets, local area networks, mobile communication networks, and combinations thereof. The transmission device 106 is used to receive or send data via a network. Specific examples of the aforementioned networks may include wireless networks provided by the mobile terminal's communication provider. In one example, the transmission device 106 includes a network interface controller (NIC), which can be connected to other network devices via a base station to communicate with the Internet. In one example, the transmission device 106 may be a radio frequency (RF) module, which is used to communicate with the Internet wirelessly.

[0036] This embodiment provides a method for determining the performance of a blade running on a mobile terminal, computer terminal, or similar computing device. It should be noted that the steps shown in the flowchart in the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions. Furthermore, although a logical order is shown in the flowchart, in some cases, the steps shown or described may be executed in a different order than that shown here.

[0037] Figure 2 This is a flowchart of a method for determining blade performance according to an embodiment of this application. Figure 2 As shown, the method includes the following steps:

[0038] Step S201: Determine multiple basic elements. The basic element is the blade shape after unfolding the plane of the intersection of the blade and the side of the corresponding target cylinder. The cross section of the target cylinder is the target circle. The center of the target circle is the hub center of the blade. The radius of the target circle is less than the distance from the hub center of the blade to the blade tip. The radii of the target circles corresponding to any two basic elements are different.

[0039] Specifically, in blade design, a primitive refers to a segment of the entire blade that is divided into several independent, planar blade profile segments according to different radii. Each primitive represents the blade profile at a specific radius position, that is, the planar blade profile that unfolds after the blade intersects with the side of the target cylinder perpendicular to the axis of rotation (Z-axis in this example). By combining multiple primitives, the shape of a three-dimensional blade can be constructed.

[0040] The target cylinder is an auxiliary geometry introduced in blade design to define the airfoil at different radial positions. Each primitive is associated with a specific target cylinder, the cross-section of which is a target circle. The center of the target circle is located precisely at the hub center of the blade, where the blade connects to the shaft. The radius of the target circle is smaller than the radial distance from the hub center to the blade tip, ensuring that the target cylinder intersects the blade accurately and is used for airfoil definition.

[0041] Multiple primitives are distributed radially along the blade, each with a different radius. This typically means that from the hub to the tip, each primitive represents a local shape of the blade at different radial positions. This distribution allows for finer control of the blade's geometry, facilitating the parameterization and optimization of complex blade shapes. The airfoil parameters (such as chord length, bend angle, and angle of attack) of each primitive may vary with the radius, allowing designers to personalize the blade at different radial positions to meet the aerodynamic requirements at varying radii. For example, primitives near the hub may require smaller chord lengths and different bend angles, while primitives near the tip may require larger chord lengths and different bend angles to optimize the overall performance of the blade.

[0042] Step S202: Determine the two-dimensional blade profile parameters of each of the above basic elements, and determine the mid-arc line and thickness distribution of the above basic elements based on the above two-dimensional blade profile parameters. The above two-dimensional blade profile parameters include at least the structural parameters of the blade corresponding to the above basic elements.

[0043] Specifically, in designing axial fan blades, to precisely control the blade's shape and performance, the blade can be divided radially into a series of basic elements. Each basic element can be viewed as a planar airfoil formed by the blade intersecting with a target cylinder at a specific radius. For each basic element, a set of two-dimensional airfoil parameters needs to be determined. These parameters describe the geometry and characteristics of the airfoil, and typically include, but are not limited to, the following:

[0044] Chord length: This is the straight-line distance between the leading and trailing edges of the leaf, reflecting the width of the leaf.

[0045] Bending angle: This refers to the rotation angle of the blade, which determines the degree of blade twisting. This is crucial for controlling the airflow direction and improving the aerodynamic efficiency of the blade.

[0046] Installation angle: The angle between the blade chord and the radial direction of the rotation axis, which affects the blade's response to airflow and the thrust it generates.

[0047] Once the two-dimensional airfoil parameters of the basic unit are determined, the next step is to calculate the mid-curve of that airfoil using these parameters. The mid-curve is the skeleton of the airfoil, and its basic outline can be determined. Third-order Bézier curves are often used in design to parameterize the mid-curve because they offer good continuity and adjustability, facilitating adjustments to the curve shape according to design requirements. Given the airfoil parameters, the designer calculates the control points of the Bézier curve, thereby obtaining a precise description of the mid-curve.

[0048] Determining the thickness distribution is a crucial step in constructing the blade body. The thickness distribution is typically along the chord length, based on the mid-curve, with the blade thickness superimposed on the mid-curve in both positive and negative directions. The thickness distribution can be uniform or tailored to specific design requirements, such as increasing the thickness at the blade root to improve structural strength or decreasing the thickness at the blade tip to reduce air resistance and noise. Various functions may be used to describe the thickness distribution in the design, including simple linear distributions or more complex nonlinear distributions, such as the exponential parameter-based distribution function mentioned in the technical disclosure.

[0049] The entire process begins by determining the number and location of primitives, then refining the blade profile parameters of each primitive. Next, based on these parameters, mathematical methods (such as Bézier curves) are used to calculate and determine the mid-curve of each primitive, as well as the thickness distribution of the blade at that primitive location. In this way, starting from two-dimensional parameters, the complete geometry of the three-dimensional blade is gradually constructed, ensuring both design flexibility and accuracy while making the design process more efficient and scientific. This series of steps is the core component of the rapid parametric modeling method for blades, facilitating the rapid design and optimization of complex axial flow wind turbine blades.

[0050] Step S203: Based on the above-mentioned arc line and thickness distribution of the above-mentioned basic elements, all the above-mentioned basic elements are stacked in a stacking manner to obtain the blade simulation model of the above-mentioned blade. Based on fluid dynamics and the above-mentioned blade simulation model, the blade is simulated and analyzed to obtain the performance parameters of the above-mentioned blade.

[0051] Specifically, firstly, for each element, we have determined its two-dimensional airfoil parameters, including the centerline and thickness distribution. The centerline is the blade's centerline, which determines the blade's basic geometry. The thickness distribution defines the variation in blade thickness from the root to the tip, which is crucial for the blade's aerodynamic performance and structural strength.

[0052] Next, by combining these basic airfoil shapes in three-dimensional space according to a specific stacking method (such as leading edge stacking, trailing edge stacking, or centroid stacking), a three-dimensional model of the blade can be constructed. The stacking method refers to how the two-dimensional airfoil shapes are combined into a three-dimensional blade along the radial direction of the blade (i.e., the direction from the hub center to the blade tip). For example, leading edge stacking connects the leading edge points of all the basic elements along the leading edge line of the blade, trailing edge stacking connects the trailing edge points of all the basic elements, and so on.

[0053] During the stacking process, the sweep characteristics (i.e. the changes in the blade's bend and sweep angles) need to be considered. This is usually achieved by adjusting the shape of the stacking lines (such as the bend stacking line and the sweep stacking line) to ensure that the three-dimensional blade has the required complex spatial bending and twisting characteristics.

[0054] After the stacking is completed, we obtain a three-dimensional simulation model of the blade, which forms the basis for the next step of fluid dynamics simulation. The three-dimensional simulation model includes not only the outer surface of the blade, but also the internal structure and material properties of the blade, in order to comprehensively reflect the physical properties of the blade.

[0055] Based on a 3D blade simulation model, designers can use CFD (Computational Fluid Dynamics) software for simulation analysis. CFD simulation can model the airflow around the blade, including airflow velocity, pressure distribution, and vortex structure, thereby evaluating the blade's aerodynamic performance. Specifically, simulation analysis can predict blade efficiency, thrust, pressure loss, noise, fluid separation, and vortices.

[0056] Through CFD simulation analysis, designers can obtain a series of performance parameters that reflect the aerodynamic efficiency and acoustic characteristics of the blades under specific design conditions. Detailed analysis and optimization of these performance parameters are crucial steps in the design iteration process. Designers can adjust the blade geometry based on these parameters, such as changing the chord length, installation angle, bend angle, and sweep angle, or optimizing the blade stacking method, to achieve the goals of optimizing aerodynamic performance and reducing noise.

[0057] The entire process begins with two-dimensional parametric modeling, builds a three-dimensional model through stacking, and finally uses fluid dynamics simulation to analyze blade performance, forming a systematic method for axial fan blade design, which greatly improves design efficiency and optimization accuracy.

[0058] The method for determining the blade performance described in this application first defines multiple primitives, where each primitive is the unfolded blade profile of the plane where the blade intersects with the side of the corresponding target cylinder, and the cross-section of the target cylinder is the target circle. Next, the two-dimensional blade profile parameters of each primitive are determined, and based on these parameters, the mid-curve and thickness distribution of the primitive are determined. These parameters include at least some structural parameters of the blade corresponding to the primitive. Finally, based on the mid-curve and thickness distribution, all primitives are stacked using an accumulation method to obtain a blade simulation model. The blade is then simulated and analyzed based on fluid dynamics and the blade simulation model to obtain its performance parameters. This method improves the efficiency of modeling axial flow fan blades in air conditioning outdoor units through rapid parametric modeling of complex three-dimensional curved and twisted composite blades. By extracting relevant characteristic parameters of the fan blades using this method, blade performance can be accurately obtained. Furthermore, the three-dimensional parametric modeling method optimizes the three-dimensional blade design, significantly reducing the workload of blade analysis, thereby more scientifically improving the aerodynamic performance of axial flow fan blades. This solves the problem in existing technologies where the construction of fan blade simulation models is inaccurate and inefficient, leading to an inability to effectively optimize the performance of real blades.

[0059] In some embodiments, determining multiple primitives includes the following steps:

[0060] Step S2011: Obtain the number of the above-mentioned basic elements, the tip radius of the above-mentioned blades, and the hub radius of the above-mentioned blades, and label the multiple above-mentioned basic elements in sequence;

[0061] Step S2012: The difference between the blade tip radius and the blade hub radius is determined as the first calculated value.

[0062] Step S2013: Determine the ratio of the current primitive's label to the quantity of the aforementioned primitives as the second calculated value;

[0063] Step S2014: When it is determined that the radii of the target circles corresponding to the multiple basic elements are an arithmetic sequence, the radius of the current basic element is determined according to the first calculated value and the second calculated value.

[0064] Step S2015: If the radius of the target circle corresponding to the plurality of the above-mentioned basic elements is determined to be a non-arithmetic sequence, the radius of the current basic element is determined according to the first calculated value, the second calculated value and the hub radius of the blade, so as to determine the plurality of the above-mentioned basic elements.

[0065] In this context, a primitive element refers to the blade shape formed by the intersection of cylinders of different diameters along the z-axis with a three-dimensional wind turbine blade. The resulting surface, when flattened into a two-dimensional plane, represents the primitive elements of the three-dimensional wind turbine blade. The number of primitive elements is defined as follows: Figure 3As shown, the hub is defined as the first basic element 1, the blade tip as the Nth basic element 2, and the rest as intermediate basic elements 3. The total number of basic elements is N. The number of basic elements will affect the final forming effect of the axial flow blade. The value of N is in the range of [4, 10]. The recommended implementation scheme is 6. The distribution of the basic element radii can be equidistant or unequal.

[0066] When the radii of cylinders corresponding to multiple basic elements form an arithmetic sequence, the radial positions of the elements on the blade can be evenly distributed according to the rules of an arithmetic sequence. An arithmetic sequence means that the difference between adjacent terms is constant, which in blade design means that the radius increment between basic elements is fixed.

[0067] First, determine the total number N of primitives to be divided on the blade, as well as the radii of the outermost (tip) and innermost (hub) layers of the blade. Calculate the difference between the tip radius and the hub radius; this difference is used as the total span of the arithmetic sequence. The relative position of the current primitive (i) within the radial range of the blade is determined by the ratio between the current primitive's label (i) and the total number of primitives (N). The radius corresponding to the current primitive is obtained by multiplying the first calculated value (the difference between the tip radius and the hub radius) by the second calculated value (the ratio of the relative positions of the primitives), and then adding the hub radius.

[0068] This method, through the rule of an arithmetic sequence, ensures that the blades are evenly divided radially, and the radial positions of each element are linearly distributed, thus simplifying the radial position determination step in the design process.

[0069] In some complex blade designs, the radius increments between elements may not be fixed but vary according to certain rules or design requirements, resulting in a non-arithmetic sequence distribution of element radii. Similar to the arithmetic sequence case, the total number of elements N, the blade tip radius, and the hub radius are first obtained. The difference between the blade tip radius and the hub radius is calculated as the first calculated value, and the ratio of the current element's label to the total number is used as the second calculated value. At this point, in addition to using the first and second calculated values, the hub radius needs to be introduced as one of the parameters to determine the radius of the current element through a more complex mathematical function or formula. This function or formula can reflect the nonlinear radial distribution and may include exponential, logarithmic functions, or other nonlinear relationships to adapt to specific aerodynamic performance or structural strength requirements.

[0070] By choosing either an arithmetic or non-arithmetic sequence radius distribution method, designers can flexibly control the radial distribution of primitives on the blade according to different design requirements, further optimizing the blade's aerodynamic performance, such as improving efficiency, reducing noise, or enhancing structural stability. Both arithmetic and non-arithmetic sequence methods for determining the radial position of primitives aim to simplify the designer's operation through mathematical formulas, reducing manual calculations and trial-and-error processes, thereby improving design efficiency. Decomposing the complex three-dimensional blade design problem into a series of parametric designs of two-dimensional primitive airfoils allows for more precise control of the blade's geometry, improving model accuracy and ensuring that the final designed blade meets both aerodynamic performance and structural strength requirements.

[0071] In some embodiments, when the radii of the target circles corresponding to multiple primitives are determined to be an arithmetic sequence, the radius of the current primitive is determined based on the first calculated value and the second calculated value, including: multiplying the first calculated value and the second calculated value to determine the radius of the target circle corresponding to the current primitive; the specific equidistant distribution formula is shown in Formula 1:

[0072]

[0073] Where Ri is the radius of the target circle corresponding to the current primitive, Hub is the hub radius, Tip is the blade tip radius, N1 is the total number of primitives, and i is the label of the current primitive.

[0074] When the radii of the target circles corresponding to multiple basic elements are determined to be non-arithmetic sequences, the radius of the current basic element is determined based on the first calculated value, the second calculated value, and the hub radius of the blade. This includes: multiplying the square of the first calculated value by the second calculated value to obtain the third calculated value, and taking the square root of the sum of the third calculated value and the square of the hub radius to obtain the radius of the target circle corresponding to the current basic element. The specific equidistant distribution formula is shown in Formula 2:

[0075]

[0076] Where Ri is the radius of the target circle corresponding to the current primitive, Hub is the hub radius, Tip is the blade tip radius, N1 is the total number of primitives, and i is the label of the current primitive.

[0077] In the case of an arithmetic progression, the radius distribution of the elements follows a linear law, meaning that the increase in element radius from hub radius to blade tip radius is constant. In the case of a non-arithmetic progression, the distribution of element radius follows a non-linear law. This is usually to adapt to the specific aerodynamic performance requirements of the blade. For example, it may be necessary to have a denser element distribution at certain radial locations on the blade to optimize local aerodynamic characteristics.

[0078] The arithmetic and non-arithmetic distributions of the element radius each have their own application scenarios and advantages, and their selection depends on the specific axial fan blade design requirements and objectives.

[0079] If the element radii are distributed in an arithmetic progression, it means that the element radii increase in a fixed increment from the hub to the blade tip. This distribution simplifies the mathematical model and calculation process, making it easy to calculate the exact position of each element and reducing the complexity in the initial design phase. An arithmetic progression distribution helps achieve uniform control across the entire radial direction of the blade. This means that the aerodynamic characteristics of the blade can be parametrically designed with the same spacing, ensuring consistent blade performance across the entire radial direction. Since the relationship between the positions of the elements is fixed, it is easier to identify which parameter adjustments will affect the overall performance, thereby accelerating the design iteration and optimization process.

[0080] If the element radii are distributed unequally, more elements can be placed at specific radial locations to meet the aerodynamic performance requirements of the blade. For example, at the blade root or tip, densely packed elements can finely adjust the aerodynamic characteristics of these areas to optimize overall performance. Complex blades often have specific geometric requirements at certain radial locations, such as significant bending or twisting. Unequal distributions can flexibly adapt to these complex geometric features, ensuring the accuracy of the design model. In areas requiring additional structural strength, such as the blade root, increased element density can enhance control, which helps improve the overall structural safety of the blade without compromising aerodynamic performance.

[0081] Since the above embodiments are for accurately establishing a simulation model of the blade, the actual blade requirements can be determined first, deciding whether to establish arithmetic progression (or unequal arithmetic progression) primitives. Then, the radius of each primitive can be determined using the above formula to establish the blade simulation model. An arithmetic progression distribution is suitable for situations requiring simplified design processes or pursuing uniform performance control, and is particularly suitable for preliminary designs or standardized products. An unequal arithmetic progression distribution, on the other hand, is more suitable for situations pursuing high performance and customized designs. It allows designers to precisely control and optimize for specific performance targets or complex geometric features. Although it may be more computationally complex, it is particularly important in high-performance product design. The choice between arithmetic progression and unequal arithmetic progression distributions can be made based on specific circumstances and objectives.

[0082] In some embodiments, the two-dimensional airfoil parameters include the trailing edge direction angle, chord length, mounting angle, and leading edge direction angle of the blade. Determining the mid-arc line of the basic element based on these two-dimensional airfoil parameters includes the following steps:

[0083] Step S301: Determine the order of the Bézier curve;

[0084] Step S302: Determine the number and coordinates of control points based on the order of the Bézier curve, and label the control points sequentially.

[0085] Step S303: Determine the Bernstein polynomial corresponding to each of the above control points based on the factorial of the label of each control point, the factorial of the order of the above Bézier curve, and the curve parameter of the above Bézier curve.

[0086] Step S304: Determine the Bézier curve based on the Bernstein polynomial corresponding to each of the control points and the coordinates of each of the control points, and define the Bézier curve as the mid-arc of the primitive.

[0087] Bézier curves are smooth curves widely used in computer graphics. They can be defined using control points and are well-suited for parametrically defining the contours of complex shapes. For two-dimensional airfoil parameters, including trailing edge direction angle, chord length, mounting angle, and leading edge direction angle, designers can use these parameters to determine the control points of the Bézier curve, thereby constructing the mid-curve of the blade.

[0088] The order of a Bézier curve determines its complexity. Higher-order Bézier curves can represent more complex shapes, but they also increase computational complexity. In most applications, third- or fourth-order Bézier curves are sufficient. The number of control points required depends on the chosen order of the Bézier curve. For example, a third-order Bézier curve requires four control points (two endpoints and two intermediate control points). The coordinates of the control points can be determined by analyzing the blade's two-dimensional airfoil parameters, particularly the chord length, installation angle, and leading and trailing edge orientation angles, which provide crucial geometric information for constructing the curve.

[0089] Each control point has an associated Bernstein polynomial, which is part of the parametric representation of the Bézier curve. The coefficients of the Bernstein polynomial are related to the order and label of the control point, as well as the curve parameter t (t belongs to the interval [0,1]), and are used to calculate the points on the Bézier curve.

[0090] By combining the Bernstein polynomials corresponding to each control point with the coordinates of the control points, the position of each point on the Bézier curve can be calculated, and a smooth curve representing the arc of the airfoil can be constructed.

[0091] By using Bézier curves, a precise and smooth mid-curve representation can be obtained, which helps to more accurately simulate the true geometry of the blade, especially when dealing with blades with complex bending and twisting characteristics. This method ensures that the geometric details of the blade design are fully considered, improving the accuracy and reliability of the model.

[0092] The parametric nature of Bézier curves allows for easy modification of blade shape by adjusting the position of control points, without recreating the entire model. This means that parameters can be fine-tuned in simulations to optimize blade aerodynamic performance, such as improving efficiency, reducing noise, or decreasing drag, without significantly increasing design time and computational resource consumption. The mid-curve constructed using Bézier curves allows for more effective optimization of blade design. For example, by adjusting the trailing edge direction angle or chord length, desired bends and twists can be introduced into different parts of the blade to better adapt to airflow conditions. Furthermore, accurate mid-curve representation makes subsequent fluid dynamics simulations more precise, providing more reliable performance parameters to guide design optimization.

[0093] The two-dimensional airfoil is described using a combination of a mid-curve and an airfoil thickness distribution curve. The mid-curve is parametrically described using a third-order Bezier curve. Bezier curves have excellent continuity and have been widely used in parametric modeling in multiple fields. The expression for the Bezier curve is shown in Equation 3, and the expression for the Bernstein polynomial is shown in Equation 4.

[0094]

[0095] Among them, P j B is the control point of the curve. j,n (t) is the Bernstein polynomial of the j-th control point, where t is the curve parameter of the Bezier curve, ranging from [0, 1]. In this embodiment, n is 3, where n is the order of the Bezier curve, typically third order is sufficient. The number of control points is the order plus 1. Higher orders result in more flexible and complex line segment shapes; first order represents a straight line, second order a parabola, and third order and above curves. Higher orders mean more control points and greater computational complexity. The value of t ranges from 0 to 1, and the sampling interval can be 0.01 or 0.05. Taking 0.01 as an example, t = [0, 0.01, 0.02...]. Since the control point p in the two-dimensional plane is expressed as (x, y), the coordinates on the corresponding axes can be solved by substituting the x or y values ​​into the calculation formula.

[0096] In some embodiments, determining the number and coordinates of control points based on the order of the Bézier curve includes the following steps:

[0097] Step S3021: Add one to the order of the above Bézier curve to obtain the number of control points;

[0098] Step S3022: Determine the starting control point as the origin of the two-dimensional Cartesian coordinate system;

[0099] Step S3023: The product of the cosine of the installation angle and the chord length is determined as the abscissa of the termination control point, and the product of the sine of the installation angle and the chord length is determined as the ordinate of the termination control point, thus obtaining the coordinates of the termination control point.

[0100] Step S3024: Determine the relative curvature of the blade, and determine the curvature of the blade based on the relative curvature and the chord length.

[0101] Step S3025: Based on the above-mentioned starting control point, the above-mentioned leading edge direction angle and the above-mentioned curvature, determine the first part of intermediate control point, and the angle between the line connecting the above-mentioned starting control point and the above-mentioned first part of intermediate control point and the first coordinate axis is the above-mentioned leading edge direction angle.

[0102] Step S3026: Based on the above-mentioned termination control point, the above-mentioned trailing edge direction angle and the above-mentioned curvature, determine the second part intermediate control point, and the angle between the line connecting the above-mentioned termination control point and the above-mentioned second part intermediate control point and the first coordinate axis is the above-mentioned trailing edge direction angle.

[0103] Bézier curves are defined by control points, the positions of which directly determine the shape of the curve. For a given order of Bézier curve, the number of control points is always one more than the order of the curve. For example, a third-order Bézier curve has four control points, and a fourth-order Bézier curve has five control points. Control points include the two endpoints of the curve and one or more intermediate control points.

[0104] First, based on the order n of the Bézier curve, the number of control points is determined as m = n + 1. The simplest starting control point can be set as the origin (0,0) of a two-dimensional Cartesian coordinate system, which is the starting point of the mid-curve. The position of the ending control point is determined by the installation angle θ1 and the chord length s. The x-coordinate of the ending control point is determined by calculating the product of the cosine of the installation angle and the chord length s, and the y-coordinate is determined by calculating the product of the sine of the installation angle and the chord length s. In this way, the coordinates of the ending control point are (x, y), ensuring that the endpoint of the curve meets specific geometric and aerodynamic requirements.

[0105] The location of the intermediate control point is determined by the relative camber of the blade (i.e., the ratio of the blade's curvature to the chord length), the chord length s, the leading-edge direction angle α, and the trailing-edge direction angle β1. Designers need to determine the specific location of the intermediate control point based on these parameters to control the shape of the Bézier curve.

[0106] The first set of intermediate control points is determined based on the starting control point, the leading edge direction angle α, and the relative camber. Here, camber refers to the curvature of the curve, which determines the degree of curvature as the curve approaches the starting point. Similarly, the second set of intermediate control points is determined based on the ending control point, the trailing edge direction angle β1, and the relative camber. This camber determines the shape of the curve as it approaches the ending point.

[0107] After determining all control points through the above steps, any point on the Bézier curve can be calculated using Bernstein polynomials. Bernstein polynomials are associated with the coordinates of the control points, the curve parameter t (t belongs to the interval [0,1]), and the order of the Bézier curve, helping to construct a complete Bézier curve.

[0108] The mid-curve constructed using Bézier curves can accurately describe the geometry of blade elements, especially when dealing with complex blades with bending and twisting characteristics. This method ensures the smoothness and continuity of the mid-curve, avoiding abrupt changes or unnatural transitions that may occur when using simple lines or circular segments, thus improving the accuracy of blade design.

[0109] By carefully adjusting the position of control points, parametric design of the curvature in the blade elements can be achieved. Designers can fine-tune the control points according to aerodynamic performance requirements (such as improving efficiency, reducing noise, or improving airflow distribution). In particular, by adjusting the leading and trailing edge azimuth angles and the relative camber of the intermediate control points, the blade shape can be optimized, thereby improving its performance. This method provides designers with a powerful and flexible tool that enables performance prediction and optimization during the design phase, reducing later adjustments and testing.

[0110] Once the coordinates of the control points are determined, constructing a Bézier curve is a rapid and deterministic process. This means that designers can quickly iterate on the design, trying different curve shapes until the optimal design is found. Compared to traditional manual drafting or trial-and-error methods, this approach significantly accelerates the design process, saving time and costs.

[0111] In one specific embodiment, the parameter description diagram of the basic airfoil is as follows: Figure 4 As shown, the parameters include trailing edge direction angle 4, mid-curve 5, chord length 6, installation angle 7, and leading edge direction angle 8. Blade elements (or cascade elements, blade elements) are a fundamental concept in fluid dynamics and turbomachinery design. They refer to simplifying complex blade structures into a series of representative, smaller geometric units for analysis and design. Blade element theory (or cascade theory) is widely used in the blade design of rotating machinery such as axial fans, turbines, and propellers to understand and optimize blade aerodynamic performance. Correlating the physical quantities of blade elements with mid-curve control points enables the mutual conversion between blade characteristics, parameters, and geometry. A third-order Bezier curve is used to describe the mid-curve. The initial two control points are determined by the chord length and installation angle. The remaining control points are then obtained based on parameters such as the inlet and outlet direction angles. Finally, all control points are substituted into the above formula to obtain the Bezier curve of the mid-curve.

[0112] Taking a third-order Bézier curve as an example, there are four control points. The starting control point is designated as control point 0, which is also the origin on the two-dimensional plane coordinate system. The ending control point is designated as control point 3. The x-coordinate of control point 3 is the product of the chord length and the cosine of the installation angle, and the y-coordinate is the product of the chord length and the sine of the installation angle. The two intermediate control points are control point 1 and control point 2, which are positioned on the same horizontal line. The tangent between the line connecting control point 1 and control point 0 and the middle arc is the inlet direction angle. The camber of the blade can be calculated based on the relative curvature and chord length, where the curvature is the product of the relative curvature and chord length. Based on the ratio, the relative height position of the control point can be determined at three-quarters of its height, i.e., the ratio of the curvature to the ordinate of control point 1 is three-quarters. Therefore, the y-axis height of control point 1 can be calculated, and the x-axis coordinate of control point 1 can be deduced from the height combined with the angle. Similarly, the coordinates of another control point, 2, can be derived from the outlet direction angle.

[0113] If the mid-arc is drawn using a fourth-order Bézier curve, there are 5 control points. The advantage of using a fourth-order Bézier curve is that it can more accurately control the relative camber position of the two-dimensional airfoil. Similar to finding the mid-arc using a third-order curve, the starting control point 0 and the ending control point 4 are obtained through the chord length and the installation angle. The intermediate control points are control point 1, control point 2, and control point 3. The coordinates of control points 1 and 3 are solved in a similar way to those of the third-order curve. For control point 2, the first derivative extremum of the fourth-order curve needs to be obtained first. The extremum and the coordinates of the other four control points are substituted into the curve equation to obtain the right-hand side of the equation. The left-hand side is the set relative camber position. The coordinates of control point 2 are solved by solving the equations of both, thereby achieving precise control of the relative camber position and thus better adjusting the aerodynamic performance of the airfoil.

[0114] The thickness normal is superimposed onto the mid-arc line from the thickness distribution curve. Finally, the coordinates of the upper and lower edges of the airfoil are determined based on the thickness and the mid-arc line. The thickness distribution can be obtained from the thickness distribution function, and the coordinates of the mid-arc line are obtained from the aforementioned Bezier curve. That is, N2 data points are distributed on a curve, and N2 is determined by the sampling interval t (the curve parameter of the Bezier curve) in the above formula. N2 = 1 / t, therefore, the value of t is generally set to an integer for N2. When the sampling interval is small and the number of sampling points is sufficient, the middle arc segment can be approximated as a continuous combination of N² sufficiently short straight lines. Let the angle between the straight line between two points and the horizontal X-axis be β², the length of the straight line be b, the normal thickness perpendicular to the straight line be d, and the coordinates on the middle arc be (x, y). Then, the x-axis coordinate of the point on the suction surface, which corresponds to the lower edge of the airfoil, is x + d × sin(β²), and the y-axis coordinate is y - b × sin(β²). Similarly, the corresponding coordinates on the other side can be calculated. The thickness coordinates corresponding to each straight line segment can be calculated, and connecting these points yields the complete airfoil. (Partial enlarged image shown) Figure 5 (As shown).

[0115] In some embodiments, the thickness of the blade is unevenly distributed, and the two-dimensional leaf shape parameters include the chord length, root thickness, and tip thickness of the blade. Determining the thickness distribution of the basic element based on these two-dimensional leaf shape parameters includes the following steps:

[0116] Step S401: Normalize the chord length of the blades to obtain the normalized chord length.

[0117] Step S402: Determine the root thickness and tip thickness of the blade. The root thickness is the thickness of the blade at the closest point to the hub, and the tip thickness is the thickness of the blade at the farthest point from the hub.

[0118] Step S403: Perform a first exponential operation on the difference between 1 and the normalized chord length to obtain a first parameter term, and perform a second exponential operation on the normalized chord length to obtain a second parameter term. The first exponent of the first exponential operation is an exponential parameter that controls the thickness change rate, and the second exponent of the second exponential operation is another exponential parameter that controls the thickness change rate.

[0119] Step S404: The product of the above-mentioned leaf root thickness and the above-mentioned first parameter item is determined as the first item, and the product of the above-mentioned leaf tip thickness and the above-mentioned second parameter item is determined as the second item;

[0120] Step S405: The sum of the first term and the second term is determined as the thickness at the current position of the basic element.

[0121] Normalization makes blade profile parameters comparable across blades of different sizes, facilitating the application of a uniform thickness distribution rule across different primitives. First, the blade chord length needs to be measured and normalized. The normalized chord length value will be between 0 and 1, with 0 corresponding to the hub (blade root) and 1 corresponding to the blade tip (blade apex).

[0122] The basic parameters are blade root thickness (the thickest part where the blade contacts the hub) and blade tip thickness (the thickness of the blade furthest from the hub). Two exponential parameters are designed, with the first exponential operation performed using the normalized chord length (1-x) and the second exponential operation using x, where x is the normalized chord length position. These two exponential parameters control the rate of thickness change from the blade root to the blade tip, respectively. The first parameter controls the thickness change near the blade root, and the second parameter controls the thickness change near the blade tip. The first and second parameter terms obtained from the above calculations are multiplied by the blade root thickness and the blade tip thickness, and then the sum of the two is used to determine the thickness of the current primitive at a specific radial position.

[0123] The thickness distribution of blades has a significant impact on their aerodynamic performance. Using an unequal thickness distribution can optimize the lift-to-drag ratio, reduce noise, and improve efficiency. For example, designing a thicker blade root can enhance structural strength and prevent vibration; while designing a thinner section near the blade tip helps reduce frictional drag and improve aerodynamic efficiency.

[0124] The root of a blade typically bears significant centrifugal force and aerodynamic loads; therefore, thickening the blade root increases its structural strength, ensuring stability and safety during high-speed rotation. Conversely, thickening the blade tip may lead to uneven weight distribution, increasing inertial forces and thus affecting overall performance and energy consumption. Uneven thickness distribution helps achieve a balance between structural strength and lightweight design.

[0125] By adjusting the blade root thickness, blade tip thickness, and exponent parameters, designers can flexibly control the variation trend of blade thickness at different radial positions, achieving a high degree of customization of blade shape and performance. This method improves design flexibility and controllability, enabling designers to optimize for specific aerodynamic and structural requirements.

[0126] Unequal thickness distribution allows designers to adjust the thickness according to the aerodynamic and structural requirements of different areas of the blade. For example, thickening the blade in areas with a high tendency for airflow separation can improve local aerodynamic performance; thinning the blade in areas subjected to smaller aerodynamic loads can reduce overall weight and improve efficiency.

[0127] Thickness distribution can be divided into uniform thickness distribution and unequal thickness distribution. The functional equation for unequal thickness distribution is shown in Equation 5, but the design is not limited to this equation:

[0128] A(x)=A root ×(1-x) j1 +A tip ×x j2 (Formula 5)

[0129] Where A(x) is the thickness at the current position, x is the normalized chord length, and A root A represents the thickness of the leaf root. tip Let j1 be the thickness at the leaf tip, and j2 be the exponential parameters that control the rate of change of thickness, namely the first exponent and the second exponent, which are used to adjust the trend of thickness change from the root to the tip. j1∈(0.05, 0.95), with an optimal value of 0.5, and j2∈(0.05, 0.9), with an optimal value of 0.5.

[0130] In some embodiments, the above-described stacking method includes one of leading edge stacking, trailing edge stacking, and centroid stacking.

[0131] Stacking method is one of the key technologies in axial fan blade design. It determines the arrangement of the blades in three-dimensional space and directly affects the aerodynamic performance, noise characteristics, and structural strength of the blades. Leading edge stacking, trailing edge stacking, and center-of-gravity stacking are three common stacking methods, each with its specific application scenarios and effects. Below is an analysis of the effects of these three stacking methods:

[0132] Leading edge overlap refers to the way blades are arranged in a rotating pattern around their leading edge (the tip of the windward side). This alters the angular distribution of the blades along the axial direction, especially changing the position of the leading edge along the flow direction, thus affecting the relative angle between the blades and the airflow.

[0133] Leading edge accumulation helps guide airflow more smoothly into the blades, reducing inlet airflow disturbance and separation, thereby improving the blade's aerodynamic efficiency and stability. By optimizing the contact between the leading edge and the airflow, leading edge accumulation can reduce noise generated by airflow impacting the blades, especially under high speed and high airflow conditions, where it has a significant effect on noise reduction. Leading edge accumulation also improves the structural stability of the blades, especially in the case of longer blades, effectively resisting torsional and bending stresses.

[0134] Trailing edge stacking is similar to leading edge stacking, but it involves a rotating arrangement around the trailing edge of the blade (i.e., the end of the leeward side). This method adjusts the angle of the blade exit, affecting the airflow distribution behind the blade.

[0135] Trailing edge accumulation helps smooth the airflow exiting the blades, reducing turbulence and vortices, thereby improving the quality of downstream airflow and overall engine performance. By optimizing the trailing edge accumulation angle, airflow losses at the blade trailing edge can be reduced, improving the blade's aerodynamic efficiency. Trailing edge accumulation also reduces airflow recirculation, especially in the blade trailing region, helping to maintain high airflow velocity and directional consistency.

[0136] Center-of-gravity stacking is a rotational arrangement based on the center-of-gravity position of the blades. This method takes into account the overall balance of the blades, ensuring their dynamic stability during rotation.

[0137] Center-of-gravity stacking helps maintain good dynamic balance of the blades during rotation, reducing vibration and unbalanced forces, and extending blade life. By precisely controlling the position of the blade's center of gravity, stacking can also optimize the blade's structural layout, making it more robust under aerodynamic and centrifugal loads. Improved dynamic balance indirectly reduces mechanical losses during wind turbine operation, thereby helping to reduce energy consumption and improve the overall efficiency of the machine.

[0138] The choice of stacking method directly affects the aerodynamic performance, noise level, and structural stability of axial fan blades, making it a crucial aspect of blade design. Leading-edge stacking focuses on improving inlet airflow conditions and reducing noise; trailing-edge stacking focuses on optimizing outlet airflow and improving aerodynamic efficiency; while center-of-gravity stacking emphasizes the dynamic balance and structural strength of the blade. Designers should comprehensively consider and select the appropriate stacking method based on specific application scenarios and performance requirements to achieve the best blade design results.

[0139] Currently, commonly used stacking methods for 3D wind turbine blades include leading-edge stacking, trailing-edge stacking, and centroid stacking. The stacking line is a spatial curve, and the curve obtained by projecting it onto the Z-plane (assuming the rotation axis is the Z-axis) is the bending stacking curve, such as... Figure 6 As shown, it includes a bend angle 9 and a leading edge overlap line 10; projecting it circumferentially and flattening it yields the sweep overlap line, and the sweep angle 11 is as follows. Figure 7 As shown. Taking leading-edge stacking as an example, the blade generated after stacking the two-dimensional blade shape of each primitive through leading-edge stacking is as follows. Figure 8 As shown. The overlapping curves of the curves and sweeps can be expressed, but are not limited to, using polar coordinate equations. Figure 6 For example, the expression for the overlapping curve at the starting point of the circle is shown in Formula 6:

[0140] r(θ2)=Hub+h1×θ2 (Formula 6)

[0141] Where r(θ2) is the radius of the bend product line, Hub is the hub radius, θ2 is the bend angle, and the value range is [20°, 60°]. In the calculation, θ2 will start from 0; the coefficient h1 can control the shape of the bend product line. When θ2 is at its maximum value, h1 = (Tip - Hub) / θ2.

[0142] by Figure 7 For example, the origin is located on the axis, and its height is the same as the stacking point of the primitives on the hub. The height expressions for the other primitives are shown in Formula 7:

[0143] h2=tanβ2×r (Formula 7)

[0144] Where β2 is the sweep angle of the current primitive and r is the radius of the current primitive.

[0145] To enable those skilled in the art to better understand the technical solution of this application, the implementation process of the method for determining blade performance of this application will be described in detail below with reference to specific embodiments.

[0146] This embodiment relates to a specific method for determining blade performance, such as... Figure 9As shown, the process includes: first, determining the number of basic elements, as the number of basic elements affects the final axial flow blade forming effect; second, determining the two-dimensional blade profile parameters on each basic element; calculating the control points of the third-order Bézier curve using these parameters; drawing the mid-arc line of each basic element blade profile using the third-order Bézier curve; then using the third-order Bézier curve to control the sweep and installation angle of the blades respectively; and finally, stacking them to generate a three-dimensional composite axial flow blade.

[0147] This application also provides a blade performance determination apparatus. It should be noted that the blade performance determination apparatus of this application can be used to execute the blade performance determination method provided in this application. This apparatus is used to implement the above embodiments and preferred embodiments; details already described will not be repeated. As used below, the term "module" can refer to a combination of software and / or hardware that implements a predetermined function. Although the apparatus described in the following embodiments is preferably implemented in software, hardware implementation, or a combination of software and hardware, is also possible and contemplated.

[0148] The following describes the blade performance determination device provided in the embodiments of this application.

[0149] Figure 10 This is a schematic diagram of a blade performance determination device according to an embodiment of this application. Figure 10 As shown, the device includes a first determining unit 20, a second determining unit 30, and a simulation unit 40. The first determining unit 20 is used to determine multiple primitives, which are the airfoils of the planes where the blade intersects with the side of the corresponding target cylinder. The cross-section of the target cylinder is a target circle, the center of the target circle is the hub center of the blade, and the radius of the target circle is less than the distance from the hub center of the blade to the blade tip. The radii of the target circles corresponding to any two primitives are different. The second determining unit 30 is used to determine the two-dimensional airfoil parameters of each primitive, and determine the mid-arc line and thickness distribution of the primitive based on the two-dimensional airfoil parameters. The two-dimensional airfoil parameters include at least some of the structural parameters of the blade corresponding to the primitive. The simulation unit 40 is used to stack all the primitives in a stacking manner according to the mid-arc line and thickness distribution of the primitive to obtain a blade simulation model of the blade, and perform simulation analysis on the blade based on fluid dynamics and the blade simulation model to obtain the performance parameters of the blade.

[0150] The blade performance determination device of this application includes a first determination unit, a second determination unit, and a simulation unit. The first determination unit is used to determine multiple primitives, where each primitive is the blade profile after unfolding the plane where the blade intersects with the side of the corresponding target cylinder, and the cross-section of the target cylinder is the target circle. The second determination unit is used to determine the two-dimensional blade profile parameters of each primitive and, based on the two-dimensional blade profile parameters, to determine the mid-curve and thickness distribution of the primitive. The two-dimensional blade profile parameters include at least some structural parameters of the blade corresponding to the primitive. The simulation unit is used to stack all primitives using a stacking method based on the mid-curve and thickness distribution of the primitive to obtain a blade simulation model. Based on fluid dynamics and the blade simulation model, the blade is simulated and analyzed to obtain the blade's performance parameters. This device improves the modeling efficiency of axial flow fan blades in air conditioning outdoor units by rapidly parametrically modeling complex three-dimensional curved and twisted composite blades. Using this method to extract relevant characteristic parameters of the fan blades, the blade performance can be accurately obtained. Furthermore, by employing a three-dimensional parametric modeling method, the three-dimensional blade design is optimized, significantly reducing the workload of blade analysis. This allows for a more scientific improvement in the aerodynamic performance of axial fan blades, addressing the problem that existing technologies suffer from inaccurate and inefficient construction of fan blade simulation models, which prevents effective optimization of the performance of real blades.

[0151] In some embodiments, the first determining unit includes a first acquiring module, a first determining module, a second determining module, a third determining module, and a fourth determining module. The first acquiring module is used to acquire the number of the aforementioned primitives, the tip radius of the aforementioned blades, and the hub radius of the aforementioned blades, and to sequentially label the plurality of aforementioned primitives. The first determining module is used to determine the difference between the tip radius of the aforementioned blades and the hub radius of the aforementioned blades as a first calculated value. The second determining module is used to determine the ratio of the label of the current primitive to the number of the aforementioned primitives as a second calculated value. The third determining module is used to determine the radius of the current primitive based on the first calculated value and the second calculated value when the radii of the target circles corresponding to the plurality of aforementioned primitives are determined to be an arithmetic sequence. The fourth determining module is used to determine the radius of the current primitive based on the first calculated value, the second calculated value, and the hub radius of the aforementioned blades when the radii of the target circles corresponding to the plurality of aforementioned primitives are determined to be a non-arithmetic sequence, thereby determining the plurality of aforementioned primitives. By using the rules of an arithmetic sequence, it can be ensured that the blades are evenly divided in the radial direction, and the radial position of each element is linearly distributed, thus simplifying the radial position determination step in the design process.

[0152] In some embodiments, the third determining module includes a first determining submodule, which is used to determine the radius of the target circle corresponding to the current primitive by multiplying the first calculated value and the second calculated value; the fourth determining module includes a second determining submodule, which is used to determine the third calculated value by multiplying the square of the first calculated value and the second calculated value, and to take the square root of the sum of the third calculated value and the square of the hub radius to obtain the radius of the target circle corresponding to the current primitive. Arithmetic progression is suitable for situations requiring simplified design processes or pursuit of uniform performance control, and is particularly suitable for preliminary designs or standardized products.

[0153] In some embodiments, the two-dimensional airfoil parameters include the trailing edge direction angle, chord length, installation angle, and leading edge direction angle of the blade. The second determining unit includes a fifth determining module, a sixth determining module, a seventh determining module, and an eighth determining module. The fifth determining module is used to determine the order of the Bézier curve; the sixth determining module is used to determine the number and coordinates of control points based on the order of the Bézier curve, and to sequentially label the control points; the seventh determining module is used to determine the Bernstein polynomial corresponding to each control point based on the factorial of the label of each control point, the factorial of the order of the Bézier curve, and the curve parameters of the Bézier curve; the eighth determining module is used to determine the Bézier curve based on the Bernstein polynomial corresponding to each control point and the coordinates of each control point, and to determine the Bézier curve as the mid-arc of the primitive. By using the Bézier curve, an accurate and smooth mid-arc representation can be obtained, which helps to more accurately simulate the true geometry of the blade, especially when dealing with blades with complex bending and twisting characteristics.

[0154] In some embodiments, the sixth determining module includes a first calculation module, a ninth determining module, a second calculation module, a tenth determining module, an eleventh determining module, and a twelfth determining module. The first calculation module is used to add one to the order of the Bézier curve to obtain the number of control points. The ninth determining module is used to determine the starting control point as the origin of a two-dimensional Cartesian coordinate system. The second calculation module is used to determine the product of the cosine of the installation angle and the chord length as the abscissa of the termination control point, and to determine the product of the sine of the installation angle and the chord length as the ordinate of the termination control point, thus obtaining the coordinates of the termination control point. The tenth determining module... The first module determines the relative camber of the blade and, based on the relative camber and chord length, the blade's camber. The eleventh module determines the first intermediate control point based on the starting control point, the leading edge direction angle, and the camber; the angle between the line connecting the starting control point and the first intermediate control point and the first coordinate axis is the leading edge direction angle. The twelfth module determines the second intermediate control point based on the ending control point, the trailing edge direction angle, and the camber; the angle between the line connecting the ending control point and the second intermediate control point and the first coordinate axis is the trailing edge direction angle. This ensures the smoothness and continuity of the mid-curve, avoiding abrupt changes or unnatural transitions that may occur when using simple lines or circular segments, thus improving the accuracy of blade design.

[0155] In some embodiments, the thickness of the blades is of unequal distribution. The two-dimensional blade profile parameters include the chord length, root thickness, and tip thickness of the blades. The second determining unit includes a third calculation module, a thirteenth determining module, a fourth calculation module, a fifth calculation module, and a sixth calculation module. The third calculation module is used to normalize the chord length of the blades to obtain a normalized chord length. The thirteenth determining module is used to determine the root thickness and tip thickness of the blades. The root thickness is the thickness of the blade at the closest position to the hub, and the tip thickness is the thickness of the blade at the farthest position from the hub. The fourth calculation module is used to calculate the thickness of the blade at the root thickness and tip thickness of the blades. The difference in normalized chord lengths is subjected to a first exponential operation to obtain a first parameter term, and the normalized chord lengths are subjected to a second exponential operation to obtain a second parameter term. The first exponent of the first exponential operation is an exponential parameter that controls the rate of thickness change, and the second exponent of the second exponential operation is another exponential parameter that controls the rate of thickness change. The fifth calculation module is used to determine the first term by multiplying the blade root thickness by the first parameter term, and to determine the second term by multiplying the blade tip thickness by the second parameter term. The sixth calculation module is used to determine the thickness at the current position of the basic element by summing the first term and the second term. Normalization processing makes the blade shape parameters comparable on blades of different sizes, facilitating the application of a uniform thickness distribution rule across different basic elements.

[0156] In some embodiments, the aforementioned stacking method includes one of leading-edge stacking, trailing-edge stacking, and center-of-gravity stacking. The stacking method is one of the key technologies in axial fan blade design, determining the arrangement of the blades in three-dimensional space and directly affecting the blade's aerodynamic performance, noise characteristics, and structural strength.

[0157] The aforementioned blade performance determination device includes a processor and a memory. The first determination unit and other components are stored as program units in the memory, and the processor executes these program units to achieve the corresponding functions. All of the aforementioned modules reside in the same processor; alternatively, the modules may be located in different processors in any combination.

[0158] The processor contains a kernel, which retrieves the corresponding program units from memory. One or more kernels can be configured, and adjusting kernel parameters can address the problems in existing wind turbine blade simulation models that are inaccurate and inefficient, hindering effective optimization of real blade performance.

[0159] The memory may include non-permanent memory in computer-readable media, such as random access memory (RAM) and / or non-volatile memory, such as read-only memory (ROM) or flash RAM, and the memory includes at least one memory chip.

[0160] This invention provides a computer-readable storage medium including a stored program, wherein, when the program is executed, it controls the device containing the computer-readable storage medium to perform the method for determining blade performance.

[0161] This invention provides a processor for running a program, wherein the program executes the method for determining blade performance.

[0162] This invention provides an apparatus including a processor, a memory, and a program stored in the memory and executable on the processor. When the processor executes the program, it implements at least the steps of the above-described method.

[0163] The devices mentioned in this article can be servers, PCs, tablets, mobile phones, etc.

[0164] This application also provides a computer program product that, when executed on a data processing device, is suitable for executing an initialization program having at least the above-described method steps.

[0165] It is obvious to those skilled in the art that the modules or steps of the present invention described above can be implemented using general-purpose computing devices. They can be centralized on a single computing device or distributed across a network of multiple computing devices. They can be implemented using computer-executable program code, and thus can be stored in a storage device for execution by a computing device. In some cases, the steps shown or described can be performed in a different order than those described herein, or they can be fabricated as separate integrated circuit modules, or multiple modules or steps can be fabricated as a single integrated circuit module. Thus, the present invention is not limited to any particular combination of hardware and software.

[0166] Those skilled in the art will understand that embodiments of this application can be provided as methods, systems, or computer program products. Therefore, this application can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this application can take the form of a computer program product embodied on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0167] This application is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of this application. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart... Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0168] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0169] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0170] In a typical configuration, a computing device includes one or more processors (CPU), input / output interfaces, network interfaces, and memory.

[0171] Memory may include non-persistent memory in computer-readable media, such as random access memory (RAM) and / or non-volatile memory, such as read-only memory (ROM) or flash RAM. Memory is an example of computer-readable media.

[0172] Computer-readable media includes both permanent and non-permanent, removable and non-removable media that can store information using any method or technology. Information can be computer-readable instructions, data structures, modules of programs, or other data. Examples of computer storage media include, but are not limited to, phase-change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technologies, CD-ROM, digital versatile optical disc (DVD) or other optical storage, magnetic tape, disk storage or other magnetic storage devices, or any other non-transferable medium that can be used to store information accessible by a computing device. As defined herein, computer-readable media does not include transient computer-readable media, such as modulated data signals and carrier waves.

[0173] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0174] It should also be noted that the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus. Unless otherwise specified, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes that element.

[0175] As can be seen from the above description, the embodiments of this application achieve the following technical effects:

[0176] 1) The method for determining the blade performance described in this application first determines multiple primitives. Each primitive is the blade profile formed by unfolding the plane where the blade intersects with the side of the corresponding target cylinder, and the cross-section of the target cylinder is the target circle. Then, the two-dimensional blade profile parameters of each primitive are determined. Based on these parameters, the mid-curve and thickness distribution of the primitive are determined. These parameters include at least some structural parameters of the blade corresponding to the primitive. Finally, based on the mid-curve and thickness distribution, all primitives are stacked to obtain a blade simulation model. The blade is then simulated and analyzed based on fluid dynamics and the simulation model to obtain its performance parameters. This method improves the efficiency of modeling axial flow fan blades in air conditioning outdoor units through rapid parametric modeling of complex three-dimensional curved and twisted composite blades. By extracting relevant characteristic parameters of the fan blades using this method, blade performance can be accurately obtained. Furthermore, the three-dimensional parametric modeling method optimizes the three-dimensional blade design, significantly reducing the workload of blade analysis, thereby more scientifically improving the aerodynamic performance of axial flow fan blades. This solves the problem in existing technologies where the construction of fan blade simulation models is inaccurate and inefficient, leading to an inability to effectively optimize the performance of real blades.

[0177] 2) The blade performance determination device of this application includes a first determination unit, a second determination unit, and a simulation unit. The first determination unit is used to determine multiple primitives, where each primitive is the blade profile after unfolding the plane where the blade intersects with the side of the corresponding target cylinder, and the cross-section of the target cylinder is the target circle. The second determination unit is used to determine the two-dimensional blade profile parameters of each primitive and, based on the two-dimensional blade profile parameters, to determine the mid-curve and thickness distribution of the primitive. The two-dimensional blade profile parameters include at least some structural parameters of the blade corresponding to the primitive. The simulation unit is used to stack all primitives using an accumulation method based on the mid-curve and thickness distribution of the primitive to obtain a blade simulation model. Based on fluid dynamics and the blade simulation model, the blade is simulated and analyzed to obtain the blade performance parameters. This device improves the modeling efficiency of axial flow fan blades in air conditioning outdoor units by rapidly parametrically modeling complex three-dimensional curved and twisted composite blades. By using this method to extract relevant characteristic parameters of the fan blades, the blade performance can be accurately obtained. Furthermore, by employing a three-dimensional parametric modeling method, the three-dimensional blade design is optimized, significantly reducing the workload of blade analysis. This allows for a more scientific improvement in the aerodynamic performance of axial fan blades, addressing the problem that existing technologies suffer from inaccurate and inefficient construction of fan blade simulation models, which prevents effective optimization of the performance of real blades.

[0178] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A method for determining blade performance, characterized in that, include: Multiple primitives are defined. Each primitive is the blade shape after unfolding the plane of the intersection of the blade and the side of the corresponding target cylinder. The cross section of the target cylinder is the target circle. The center of the target circle is the hub center of the blade. The radius of the target circle is smaller than the distance from the hub center of the blade to the blade tip. The radii of the target circles corresponding to any two primitives are different. Determine the two-dimensional blade profile parameters of each of the basic elements, and determine the mid-arc line and thickness distribution of the basic elements based on the two-dimensional blade profile parameters. The two-dimensional blade profile parameters include at least some of the structural parameters of the blade corresponding to the basic element. Based on the arc line and thickness distribution of the basic element, all the basic elements are stacked in a stacking manner to obtain the blade simulation model. The blade is then simulated and analyzed based on fluid dynamics and the blade simulation model to obtain the performance parameters of the blade.

2. The method according to claim 1, characterized in that, Define multiple primitives, including: Obtain the number of the primitives, the tip radius of the blade, and the hub radius of the blade, and then label the primitives sequentially. The difference between the blade tip radius and the blade hub radius is determined as the first calculated value; The ratio of the current primitive's label to the quantity of the primitives is determined as the second calculated value; When the radii of the target circles corresponding to the multiple primitives are determined to be an arithmetic sequence, the radius of the current primitive is determined based on the first calculated value and the second calculated value. When the radius of the target circle corresponding to the plurality of primitives is determined to be a non-arithmetic sequence, the radius of the current primitive is determined based on the first calculated value, the second calculated value, and the hub radius of the blade, thereby determining the plurality of primitives.

3. The method according to claim 2, characterized in that, When the radii of the target circles corresponding to multiple primitives are determined to be an arithmetic sequence, the radius of the current primitive is determined based on the first calculated value and the second calculated value, including: determining the radius of the target circle corresponding to the current primitive as the product of the first calculated value and the second calculated value; and / or, When the radii of the target circles corresponding to the multiple primitives are determined to be non-arithmetic sequences, the radius of the current primitive is determined based on the first calculated value, the second calculated value, and the hub radius of the blade. This includes: determining the product of the square of the first calculated value and the second calculated value as a third calculated value, and taking the square root of the sum of the third calculated value and the square of the hub radius to obtain the radius of the target circle corresponding to the current primitive.

4. The method according to claim 1, characterized in that, The two-dimensional airfoil parameters include the trailing edge direction angle, chord length, installation angle, and leading edge direction angle of the blade. Based on these two-dimensional airfoil parameters, the mid-arc line of the basic element is determined, including: Determine the order of the Bézier curve; The number and coordinates of the control points are determined according to the order of the Bézier curve, and the control points are numbered sequentially. The Bernstein polynomial corresponding to each control point is determined based on the factorial of the label of each control point, the factorial of the order of the Bézier curve, and the curve parameter of the Bézier curve. Based on the Bernstein polynomial corresponding to each control point and the coordinates of each control point, the Bézier curve is determined, and the Bézier curve is defined as the mid-arc of the primitive.

5. The method according to claim 4, characterized in that, The number and coordinates of control points are determined based on the order of the Bézier curve, including: The number of control points is obtained by adding one to the order of the Bézier curve. The initial control point is determined to be the origin of a two-dimensional Cartesian coordinate system; The product of the cosine of the installation angle and the chord length is determined as the x-coordinate of the termination control point, and the product of the sine of the installation angle and the chord length is determined as the y-coordinate of the termination control point, thus obtaining the coordinates of the termination control point; Determine the relative curvature of the blade, and determine the curvature of the blade based on the relative curvature and the chord length; Based on the starting control point, the leading edge direction angle, and the curvature, a first set of intermediate control points is determined, and the angle between the line connecting the starting control point and the first set of intermediate control points and the first coordinate axis is the leading edge direction angle. Based on the termination control point, the trailing edge direction angle, and the curvature, a second intermediate control point is determined, and the angle between the line connecting the termination control point and the second intermediate control point and the first coordinate axis is the trailing edge direction angle.

6. The method according to claim 1, characterized in that, The blade has a non-uniform thickness distribution. The two-dimensional leaf shape parameters include the chord length, root thickness, and tip thickness of the blade. The thickness distribution of the basic element is determined based on these two-dimensional leaf shape parameters, including: The chord length of the blade is normalized to obtain the normalized chord length; The root thickness and tip thickness of the blade are determined, wherein the root thickness is the thickness of the blade at the closest point to the hub, and the tip thickness is the thickness of the blade at the farthest point from the hub. A first exponential operation is performed on the difference between 1 and the normalized chord length to obtain a first parameter term, and a second exponential operation is performed on the normalized chord length to obtain a second parameter term. The first exponent of the first exponential operation is an exponential parameter that controls the rate of thickness change, and the second exponent of the second exponential operation is another exponential parameter that controls the rate of thickness change. The product of the leaf root thickness and the first parameter is determined as the first term, and the product of the leaf tip thickness and the second parameter is determined as the second term; The sum of the first and second terms is determined as the thickness at the current position of the primitive.

7. The method according to any one of claims 1 to 6, characterized in that, The stacking method includes one of leading edge stacking, trailing edge stacking, and centroid stacking.

8. A device for determining blade performance, characterized in that, include: The first determining unit is used to determine multiple basic elements. The basic element is the blade shape after unfolding the plane of the intersection of the blade and the side of the corresponding target cylinder. The cross section of the target cylinder is the target circle. The center of the target circle is the hub center of the blade. The radius of the target circle is smaller than the distance from the hub center of the blade to the blade tip. The radii of the target circles corresponding to any two basic elements are different. The second determining unit is used to determine the two-dimensional blade profile parameters of each of the basic elements, and to determine the mid-arc line and thickness distribution of the basic elements based on the two-dimensional blade profile parameters. The two-dimensional blade profile parameters include at least some of the structural parameters of the blades corresponding to the basic elements. The simulation unit is used to stack all the basic elements according to the mid-arc line and the thickness distribution of the basic elements to obtain the blade simulation model, and to perform simulation analysis on the blade based on fluid dynamics and the blade simulation model to obtain the performance parameters of the blade.

9. A computer-readable storage medium, characterized in that, The computer-readable storage medium includes a stored program, wherein, when the program is executed, it controls the device containing the computer-readable storage medium to perform the method for determining blade performance as described in any one of claims 1 to 7.

10. An electronic device, characterized in that, include: One or more processors, a memory, and one or more programs, wherein the one or more programs are stored in the memory and configured to be executed by the one or more processors, the one or more programs including a method for performing the determination of blade performance according to any one of claims 1 to 7.

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