Design method and device of compressor blade, electronic equipment and storage medium

Abstract

The application discloses a compressor blade design method and device, electronic equipment and storage medium, including the following steps: S1: determining the boundary condition in the blade span direction and the boundary condition in the blade flow direction, wherein the boundary condition in the blade flow direction includes the root section angle distribution, the tip section angle distribution, the root section thickness distribution and the tip section thickness distribution; S2: closing the convection diffusion equation based on the boundary condition, giving the determined value of the control coefficient in the convection diffusion equation, solving the convection diffusion equation to obtain the angle distribution and thickness distribution of each section of the blade; compared with the prior art, the convection diffusion equation with clear physical meaning is reasonably borrowed, so that the performance upper limit of the compressor blade is improved, and the performance of the compressor blade is avoided from being reduced, the practicality is high, and the application is suitable for wide promotion and application.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engine, in particular, to a compressor blade design method and device, electronic equipment and storage medium. BACKGROUND

[0002] The compressor is one of the core components of the aero-engine, and its performance largely determines the performance of the aero-engine, and the blade design is the core content of the compressor design, which often determines the performance of the compressor. The compressor blade design is affected by many factors, among which the weight of the inlet Mach number is the largest. The compressor blade needs to adapt to the complex and variable inlet conditions, and the inlet Mach number of the compressor changes from the inlet to the outlet, from the root to the tip, and each specific position has the best blade shape that adapts to the inlet Mach number. In recent years, with the increase of the compression ratio and efficiency of the compressor, the range of the aerodynamic parameters of the blade from the root to the tip is further expanded, which increases the difficulty of the aerodynamic design of the compressor.

[0003] At present, the design of the compressor blade mainly adopts a quasi-three-dimensional design method, which divides the blade into several sections from the root to the tip, designs the shape of each section separately, connects all the sections into a curve group through a space curve, and finally forms a complete blade surface through the curve group. The blade profile of the compressor blade is usually composed of a series of sections, and one of the main construction methods of the blade profile is to draw a series of circles along a curve, and the intersection of the vertical lines of the centers of the circles and the circles forms the upper and lower surfaces of the blade profile, the curve is the middle camber line, and the radius of the circle is the maximum thickness of the section, and the thickness distribution is the change rule of the thickness from the inlet to the outlet.

[0004] In the design process of the compressor blade, if a suitable blade profile is selected according to the inlet and outlet conditions of each section, the performance of the compressor blade can be ensured to be optimal; however, although there are various blade profiles for selection in the design process of the compressor blade, such as NACA65 blade profile, cubic polynomial blade profile and multi-arc blade profile, each blade profile has its applicable Mach number range; in the existing design method of the compressor blade, the same blade profile is basically selected from the root to the tip, but this method limits the upper limit of the performance of the compressor blade; some design methods allow different blade profiles to be selected for the root and tip sections, but due to the large difference between different blade profiles, smooth transition cannot be achieved between different sections from the root to the tip, which greatly reduces the performance of the compressor blade.

[0005] It should be noted that the disclosure of the above background art content is only used to assist in understanding the inventive concept and technical solutions of the present application, and it does not necessarily belong to the prior art of the present application. In the absence of explicit evidence that the above content has been disclosed on the filing date of the present application, the above background art should not be used to evaluate the novelty and inventiveness of the present application. SUMMARY

[0006] The application provides a design method, device, electronic equipment and storage medium of a compressor blade, to solve the technical problem that the existing design method of the compressor blade limits the upper limit of the performance of the compressor blade or reduces the performance of the compressor blade.

[0007] According to one aspect of the application, a design method of a compressor blade is provided, comprising the following steps: S1: determining boundary conditions in a blade spanwise direction and boundary conditions in a blade streamwise direction, wherein the boundary conditions in the blade streamwise direction comprise a root section angle distribution, a tip section angle distribution, a root section thickness distribution and a tip section thickness distribution; S2: solving a convection-diffusion equation based on the boundary conditions, giving a determined value of a control coefficient in the convection-diffusion equation, to obtain an angle distribution and a thickness distribution of each section of the blade by solving the convection-diffusion equation, wherein the convection-diffusion equation is:

[0008] ;

[0009] In the equation, is an angle or thickness, x is a streamwise coordinate, y is a spanwise coordinate, and is a streamwise control coefficient, and is a spanwise control coefficient.

[0010] Further, the boundary conditions in the blade spanwise direction comprise an inlet spanwise angle distribution, an outlet spanwise angle distribution, an inlet spanwise thickness distribution and an outlet spanwise thickness distribution, and the determination of the boundary conditions in the blade spanwise direction specifically comprises the following steps: based on the design requirements of rotational speed, pressure and flow rate, the inlet spanwise angle distribution and the outlet spanwise angle distribution are determined by using element level analysis; based on the design requirements of aerodynamic performance and structural strength, the inlet spanwise thickness distribution and the outlet spanwise thickness distribution are determined.

[0011] Further, the determination of the boundary conditions in the blade streamwise direction specifically comprises the following steps: according to the design requirements of aerodynamic performance and structural strength, the maximum thickness of the root section and the maximum thickness of the tip section are determined; according to the root inlet Mach number and the tip inlet Mach number, the root section angle distribution and the tip section angle distribution are determined, and the root section thickness distribution type and the tip section thickness distribution type are determined; according to the root section thickness distribution type, a root section thickness distribution analytical formula is selected, according to the tip section thickness distribution type, a tip section thickness distribution analytical formula is selected, and based on the inlet spanwise thickness distribution, the outlet spanwise thickness distribution, the maximum thickness of the root section and the maximum thickness of the tip section, the root section thickness distribution and the tip section thickness distribution are respectively determined according to the root section thickness distribution analytical formula and the tip section thickness distribution analytical formula.

[0012] Furthermore, step S2 is followed by step S3: iteratively optimize the control coefficients to obtain the blade geometry that meets the design requirements.

[0013] Furthermore, step S3 specifically includes the following steps: generating the blade geometry based on the angle and thickness distribution of each cross section of the blade; performing fluid dynamics simulation analysis based on the blade geometry; outputting the design results when the simulation results meet the design requirements; and repeating steps S2-S3 until the simulation results meet the design requirements when the simulation results do not meet the design requirements.

[0014] Furthermore, the control coefficient is 0-10.

[0015] Furthermore, in step S3, a numerical optimizer is used for iterative optimization.

[0016] According to another aspect of the present invention, a design apparatus for a compressor blade is also provided, characterized in that it comprises: a determining module for determining boundary conditions in the spanwise direction and the flowwise direction of the blade, wherein the boundary conditions in the flowwise direction include the root section angle distribution, the tip section angle distribution, the root section thickness distribution, and the tip section thickness distribution; and a calculation module for solving the convection-diffusion equation based on the boundary conditions and given initial values ​​of the control coefficients in the convection-diffusion equation to obtain the angle distribution and thickness distribution of each section of the blade, wherein the convection-diffusion equation is:

[0017] ;

[0018] In the equation, Let x represent the angle or thickness, x be the flow direction coordinate, and y be the spanwise coordinate. , This is the flow direction control coefficient. , This is the span control coefficient.

[0019] According to another aspect of the present invention, an electronic device is also provided, comprising: a processor; a memory for storing processor-executable instructions; wherein the processor is configured to implement the above-described compressor blade design method when executing the instructions stored in the memory.

[0020] According to another aspect of the present invention, a computer-readable storage medium is also provided, which stores computer program instructions that, when executed by a processor, implement the above-described compressor blade design method.

[0021] The present invention has the following beneficial effects:

[0022] The compressor blade design method of this invention first determines the boundary conditions in the spanwise direction and the flowwise direction of the blade. Since the boundary conditions in the flowwise direction include the root section angle distribution, tip section angle distribution, root section thickness distribution, and tip section thickness distribution, determining the boundary conditions in the flowwise direction determines the root section airfoil and the tip section airfoil, allowing different airfoils to be used at the root and tip of the compressor blade to improve the upper limit of compressor blade performance. Then, based on the boundary conditions, a convection-diffusion equation is closed to specifically apply the convection-diffusion equation to the design of the compressor blade and to serve as the benchmark for the solution. Finally, the control coefficients in the given convection-diffusion equation are determined... This method uses a fixed value and solves the convection-diffusion equation to obtain the angular and thickness distributions of each cross section of the blade. Due to the presence of the diffusion term in the convection-diffusion equation, the angular and thickness distributions of each cross section of the blade are necessarily smooth, meaning that there is a smooth transition between each cross section from the root to the tip of the blade, thus ensuring the performance of the compressor blade. This method breaks through the traditional design theory. Compared with existing technologies, it reasonably borrows the physically meaningful convection-diffusion equation to couple the physical flow field characteristics with the compressor blade design, completing the thickness / angle distribution design adapted to the incoming flow. This improves the upper limit of compressor blade performance while avoiding the reduction of compressor blade performance. It is highly practical and suitable for widespread promotion and application.

[0023] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0024] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0025] Figure 1 This is a flowchart illustrating the steps of a compressor blade design method according to a preferred embodiment of the present invention.

[0026] Figure 2 This is a schematic diagram of the compressor blade design device module according to a preferred embodiment of the present invention;

[0027] Figure 3 This is a schematic block diagram of an electronic device according to a preferred embodiment of the present invention. Detailed Implementation

[0028] The following description provides specific application scenarios and requirements for this specification, intended to enable those skilled in the art to make and use the contents of this specification. Various partial modifications to the disclosed embodiments will be apparent to those skilled in the art, and the general principles defined herein can be applied to other embodiments and applications without departing from the spirit and scope of this specification.

[0029] The terminology used herein is for the purpose of describing particular exemplary embodiments only and is not restrictive. For example, unless the context clearly indicates otherwise, the singular forms “a,” “an,” and “the” used herein may also include the plural forms. When used in this specification, the terms “comprising,” “including,” and / or “containing” mean that the associated integers, steps, operations, elements, and / or components are present, but do not exclude the presence of one or more other features, integers, steps, operations, elements, components, and / or groups, or that other features, integers, steps, operations, elements, components, and / or groups may be added to the system / method.

[0030] Considering the following description, these and other features of this specification, as well as the operation and function of the related components of the structure, and the economy of assembly and manufacture of the parts, can be significantly improved. All of these form part of this specification with reference to the accompanying drawings. However, it should be clearly understood that the drawings are for illustrative and descriptive purposes only and are not intended to limit the scope of this specification. It should also be understood that the drawings are not drawn to scale.

[0031] like Figure 1 As shown, the compressor blade design method of this embodiment is characterized by the following steps: S1: Determining the boundary conditions in the spanwise direction and the flowwise direction of the blade, wherein the boundary conditions in the flowwise direction include the root section angle distribution, the tip section angle distribution, the root section thickness distribution, and the tip section thickness distribution; S2: Based on the boundary conditions, closing the convection-diffusion equation, and given the determined values ​​of the control coefficients in the convection-diffusion equation, solving the convection-diffusion equation to obtain the angle distribution and thickness distribution of each section of the blade, wherein the convection-diffusion equation is:

[0032] ;

[0033] In the equation, Let x represent the angle or thickness, x be the flow direction coordinate, and y be the spanwise coordinate. and This is the flow direction control coefficient. and This is the span control coefficient.

[0034] Specifically, the compressor blade design method of the present invention first determines the boundary conditions in the spanwise direction and the flowwise direction of the blade. Since the boundary conditions in the flowwise direction include the root section angle distribution, the tip section angle distribution, the root section thickness distribution, and the tip section thickness distribution, determining the boundary conditions in the flowwise direction determines the root section airfoil and the tip section airfoil, allowing the root and tip sections of the compressor blade to adopt different airfoils to improve the performance upper limit of the compressor blade. Then, based on the boundary conditions, the convection-diffusion equation is closed to apply the convection-diffusion equation to the design of the compressor blade and to serve as the benchmark for solving the problem. Finally, the control coefficients in the convection-diffusion equation are given. The angular and thickness distributions of each blade cross-section are obtained by solving the convection-diffusion equation. Due to the presence of the diffusion term in the convection-diffusion equation, the angular and thickness distributions of each blade cross-section are necessarily smooth, meaning that there is a smooth transition between the cross-sections from the root to the tip of the blade, thus ensuring the performance of the compressor blade. This scheme breaks through the traditional design theory. Compared with the existing technology, by reasonably borrowing the convection-diffusion equation with clear physical meaning, it realizes the coupling of the physical flow field characteristics with the compressor blade design, and completes the thickness / angle distribution design adapted to the incoming flow. This improves the upper limit of compressor blade performance while avoiding the reduction of compressor blade performance. It is highly practical and suitable for widespread promotion and application.

[0035] It should be understood that the root section angle distribution and the tip section angle distribution can have completely different characteristics, and the root section thickness distribution type and the tip section thickness distribution type can be completely different. Therefore, the performance limit of the compressor blade can be maximized, and the performance limit of the compressor blade can be avoided by the blade shape.

[0036] It should be understood that control coefficients include flow direction control coefficients and extension direction control coefficients.

[0037] It should be understood that the flow direction refers to the flow from the blade inlet to the blade outlet.

[0038] It should be understood that span refers to the direction from the base of the leaf to the tip of the leaf.

[0039] In this embodiment, the boundary conditions in the blade spanwise direction include the inlet spanwise angle distribution, the outlet spanwise angle distribution, the inlet spanwise thickness distribution, and the outlet spanwise thickness distribution. Determining the boundary conditions in the blade spanwise direction specifically includes the following steps: based on design requirements for rotational speed, pressure, and flow rate, the inlet and outlet spanwise angle distributions are determined using elementary-level analysis; based on design requirements for aerodynamic performance and structural strength, the inlet and outlet spanwise thickness distributions are determined. Specifically, the boundary conditions in the blade spanwise direction are determined through the above steps to serve as the solution benchmark for the convection-diffusion equation.

[0040] It should be understood that the specific steps of primitive-level analysis are well-known techniques to those skilled in the art, and will not be elaborated upon here.

[0041] In this embodiment, determining the boundary conditions in the blade flow direction specifically includes the following steps: Based on the design requirements for aerodynamic performance and structural strength, determine the maximum thickness of the root section and the maximum thickness of the tip section; based on the Mach number at the root inlet and the Mach number at the tip inlet, determine the angle distribution of the root section and the angle distribution of the tip section, and determine the thickness distribution types of the root section and the tip section; select the analytical formula for the root section thickness distribution based on the thickness distribution type of the root section, and select the analytical formula for the thickness distribution of the tip section based on the thickness distribution type of the tip section; based on the spanwise thickness distribution at the inlet, the spanwise thickness distribution at the outlet, the maximum thickness of the root section, and the maximum thickness of the tip section, calculate and determine the thickness distribution of the root section and the thickness distribution of the tip section respectively using the analytical formulas for the thickness distribution of the root section and the thickness distribution of the tip section. Specifically, through the above steps, the boundary conditions in the blade flow direction are determined as the solution benchmark for the convection-diffusion equation, ensuring that the root section and the tip section are matched with the inlet Mach number, ensuring that the root section and the tip section are in the optimal design state, and maximizing the performance limit of the compressor blade. Optionally, the thickness distribution types include C4, NACA65, quadratic polynomial thickness, and cubic polynomial thickness.

[0042] In this embodiment, step S2 is followed by step S3: iterative optimization of the control coefficients to obtain a blade geometry that meets the design requirements. Specifically, iterative optimization is used to maximize the performance of the compressor blades.

[0043] In this embodiment, step S3 specifically includes the following steps: generating the blade geometry based on the angle and thickness distributions of each cross-section of the blade; performing fluid dynamics simulation analysis based on the blade geometry; outputting the design results when the simulation results meet the design requirements; and repeating steps S2-S3 until the simulation results meet the design requirements when the simulation results do not meet the design requirements. Specifically, by reasonably associating the flow direction control coefficient and the manifestation control coefficient with the flow field state, and combining numerical optimization algorithms, the blade angle and thickness distributions most suitable for the flow field characteristics are obtained, thereby maximizing the performance of the compressor blades.

[0044] Optionally, in one embodiment, simulation results show that the blade inlet Mach number is relatively high, ranging from 0.9 to 1.5 from root to tip, indicating poor initial blade performance. , It transforms into a linear distribution from 2 to 1, making , The distribution is changed to a linear distribution from 1 to 2, which gives the blade more ultrasonic characteristics, reduces aerodynamic losses, and after multiple iterations of optimization, the blade geometry that meets the design requirements is obtained.

[0045] In this embodiment, in step S3, a numerical optimizer is used for iterative optimization to quickly output design results, maximize the performance of the compressor blades, shorten the iteration cycle, and further improve design efficiency.

[0046] In this embodiment, the control coefficient is between 0 and 10. Specifically, when the control coefficient is selected between 0 and 10, the number of iterations is small and the design efficiency is high; when the control coefficient is greater than 10, the number of iterations is large and the design efficiency is low.

[0047] The compressor blades in this embodiment employ the compressor blade design method described above. Specifically, by using the compressor blade design method described above, the compressor blades are designed to achieve optimal performance.

[0048] The compressor in this embodiment includes the compressor blades described above. Specifically, by employing the compressor blades described above in the compressor, and by ensuring the optimal performance of the compressor blades, the performance of the compressor is maximized.

[0049] The aero-engine of this embodiment includes the compressor blades or the compressor described above. Specifically, by employing the compressor blades or compressor described above in the aero-engine, the overall performance of the engine is improved by enhancing the performance of the components.

[0050] like Figure 2 As shown, the compressor blade design device of this embodiment is characterized by comprising: a determination module for determining the boundary conditions in the spanwise direction and the flowwise direction of the blade, wherein the boundary conditions in the flowwise direction include the root section angle distribution, the tip section angle distribution, the root section thickness distribution, and the tip section thickness distribution; and a calculation module for solving the convection-diffusion equation based on the boundary conditions, given initial values ​​of the control coefficients in the convection-diffusion equation, to obtain the angle distribution and thickness distribution of each section of the blade, wherein the convection-diffusion equation is:

[0051] ;

[0052] In the equation, Let x represent the angle or thickness, x be the flow direction coordinate, and y be the spanwise coordinate. , This is the flow direction control coefficient. , This is the span control coefficient.

[0053] like Figure 3As shown, the electronic device of this embodiment includes: a processor; a memory for storing processor-executable instructions; wherein the processor is configured to implement the above-described compressor blade design method when executing the instructions stored in the memory.

[0054] The computer-readable storage medium of this embodiment stores computer program instructions, which, when executed by a processor, implement the above-described compressor blade design method.

[0055] Optionally, the computer-readable storage medium is a non-volatile storage medium.

[0056] If the functions described in this embodiment are implemented as software functional units and sold or used as independent products, they can be stored in one or more electronically readable storage media. Based on this understanding, the parts of this application's embodiments that contribute to the prior art or the technical solutions can be embodied in the form of software products. These software products are stored in a storage medium and include several instructions to cause an electronic device (which may be a personal computer, server, mobile electronic device, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this application. The aforementioned storage media include various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0057] 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 implemented 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. The solutions in the embodiments of this application can be implemented in various computer languages, such as the object-oriented programming language Java and the interpreted scripting language JavaScript.

[0058] 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.

[0059] 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.

[0060] 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.

[0061] In summary, after reading the detailed disclosure of this specification, those skilled in the art will understand that the foregoing detailed disclosure is presented by way of example only and is not restrictive. Although not explicitly stated herein, those skilled in the art will understand that this specification requires various reasonable changes, improvements, and modifications to the embodiments. These changes, improvements, and modifications are intended to be made by this specification and are within the spirit and scope of the exemplary embodiments described herein.

[0062] Furthermore, certain terms in this specification have been used to describe embodiments of this specification. For example, "an embodiment," "an embodiment," and / or "some embodiments" mean that a particular feature, structure, or characteristic described in connection with that embodiment may be included in at least one embodiment of this specification. Therefore, it is to be emphasized and understood that two or more references to "an embodiment" or "an embodiment" or "alternative embodiment" in various parts of this specification do not necessarily refer to the same embodiment. Moreover, specific features, structures, or characteristics may be suitably combined in one or more embodiments of this specification.

[0063] It should be understood that in the foregoing description of the embodiments in this specification, various features are combined in a single embodiment, drawing, or description for the purpose of simplifying the description and aiding in the understanding of a feature. However, this does not mean that the combination of these features is necessary, and those skilled in the art may readily identify some of the devices as separate embodiments when reading this specification. That is, the embodiments in this specification can also be understood as an integration of multiple secondary embodiments. It is also valid when each secondary embodiment contains fewer than all the features of a single foregoing disclosed embodiment.

Claims

1. A method for designing compressor blades, characterized in that, Includes the following steps: S1: Determine the boundary conditions in the spanwise direction and the flowwise direction of the blade. The boundary conditions in the flowwise direction include the root section angle distribution, the tip section angle distribution, the root section thickness distribution, and the tip section thickness distribution. S2: Based on the boundary condition closed convection-diffusion equation, given the definite values ​​of the control coefficients in the convection-diffusion equation, solve the convection-diffusion equation to obtain the angular distribution and thickness distribution of each section of the blade. The convection-diffusion equation is: ； In the equation, ∅ represents the angle or thickness, x is the flow direction coordinate, and y is the spanwise coordinate. and This is the flow direction control coefficient. and For span control coefficients; The boundary conditions in the blade spanwise direction include the inlet spanwise angle distribution, the outlet spanwise angle distribution, the inlet spanwise thickness distribution, and the outlet spanwise thickness distribution. Determining the boundary conditions in the blade spanwise direction specifically includes the following steps: Based on the design requirements of rotational speed, pressure, and flow rate, the inlet spanwise angle distribution and outlet spanwise angle distribution are determined using elementary-level analysis. Based on the design requirements of aerodynamic performance and structural strength, the spanwise thickness distribution at the inlet and outlet was determined. Determining the boundary conditions in the direction of blade flow specifically includes the following steps: Based on the design requirements for aerodynamic performance and structural strength, determine the maximum thickness of the root section and the maximum thickness of the tip section; Based on the Mach number at the root inlet and the Mach number at the tip inlet, determine the angle distribution of the root section and the angle distribution of the tip section, and determine the thickness distribution type of the root section and the thickness distribution type of the tip section; The root section thickness distribution analytical formula is selected based on the root section thickness distribution type, and the tip section thickness distribution analytical formula is selected based on the tip section thickness distribution type. Based on the inlet spanwise thickness distribution, the outlet spanwise thickness distribution, the maximum thickness of the root section, and the maximum thickness of the tip section, the root section thickness distribution and the tip section thickness distribution are calculated and determined respectively using the root section thickness distribution analytical formula and the tip section thickness distribution analytical formula. Step S2 is followed by the following steps: S3: Iteratively optimize the control coefficients to obtain the blade geometry that meets the design requirements.

2. The compressor blade design method according to claim 1, characterized in that, Step S3 specifically includes the following steps: The blade's geometric shape is generated based on the angular and thickness distributions of each cross section. Fluid dynamics simulation analysis is performed based on the blade geometry. When the simulation results meet the design requirements, the design results are output. When the simulation results do not meet the design requirements, steps S2-S3 are repeated until the simulation results meet the design requirements.

3. The compressor blade design method according to claim 2, characterized in that, The control factor is 0-10.

4. The compressor blade design method according to claim 2, characterized in that, In step S3, a numerical optimizer is used for iterative optimization.

5. A design device for compressor blades, characterized in that, The method for designing compressor blades according to claim 1 includes: Determining module: Used to determine the boundary conditions in the spanwise direction and the flow direction of the blade. The boundary conditions in the flow direction include the root section angle distribution, the tip section angle distribution, the root section thickness distribution, and the tip section thickness distribution. The calculation module is used to solve the convection-diffusion equation based on boundary conditions and given initial values ​​for the control coefficients in the equation, to obtain the angular and thickness distributions of various blade sections. The convection-diffusion equation is as follows: ； In the equation, ∅ represents the angle or thickness, x is the flow direction coordinate, and y is the spanwise coordinate. , This is the flow direction control coefficient. , This is the span control coefficient.

6. An electronic device, characterized in that, include: processor; Memory used to store processor-executable instructions; The processor is configured to implement the compressor blade design method according to any one of claims 1 to 4 when executing instructions stored in the memory.

7. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer program instructions that, when executed by a processor, implement the compressor blade design method according to any one of claims 1 to 4.

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