Power system blade structure optimization design method and application thereof

Abstract

The invention discloses a power system blade structure optimization design method which comprises the following steps: acquiring a digital model of a blade, and dividing the digital model into a non-design domain shell and a design domain space; performing section taking processing on the design domain space of the digital model to obtain a plurality of sections of the design domain space; performing triangulation on the layered boundary of the design domain space again to obtain a lofting surface corresponding to each section; reducing the plurality of lofting surfaces obtained by triangulation into an optimized design domain space; and filling the optimized design domain space by adopting a microstructure filling method to obtain a blade structure subjected to optimization design. The functional metamaterial can be effectively used in the structure of a complex curved surface structure, and the integrated design of the impact resistance function and the bearing performance is achieved.

Description

Technical Field

[0001] This application relates to the field of structural optimization design technology, and in particular to a method for optimizing the structure of a power system blade, a device for optimizing the structure of a power system blade, an electronic device, and a computer-readable storage medium. Background Technology

[0002] Power system blades serve as the core "skeleton" of equipment in aviation, aerospace, and marine industries, playing a decisive role in the stable and efficient operation of such equipment under varying air and airflow environments. Taking aero-engine fan blades as an example, their operating conditions are harsh. They not only withstand enormous centrifugal and alternating loads in complex environments but also face the threat of impact from foreign objects. This necessitates that the design of aero-engine blades consider both structural load-bearing requirements and impact resistance. Therefore, these large, integrated, and complex curved surface components are increasingly employing multi-scale lattice / metamaterial infill configurations to achieve integrated functional-structural design.

[0003] Hollow fan blades represent an important development direction in the structural design of turbofan engine fan blades. A hollow fan blade is a complex thin-walled component composed of a wall panel and a filling structure system. The outer wall panel is a solid plate with varying curvature, while the inner filling is a lightweight, porous structure with a high void ratio. The wall panel and the filling structure exhibit significant dimensional differences. Compared to traditional narrow-chord solid blades, wide-chord hollow blades offer advantages such as higher airflow, lighter weight, and lower noise.

[0004] Meanwhile, hollow fan blades operate under harsh conditions, enduring not only enormous centrifugal and alternating loads in complex environments, but also facing threats from foreign object impacts (such as sand, metal particles, and birds) and blade vibration. Statistics show that the vast majority of foreign object impact accidents involving civilian aircraft are caused by birds, with engine fan blades and windshields being the two most frequently struck locations. When birds are ingested by low-altitude, high-speed aircraft engines, it can cause localized edge curling, denting, or even blade breakage of the fan blades, severely impacting aircraft safety.

[0005] Hollow blades can be constructed by combining wall panels and cavity structures. However, due to the constraints of traditional design methods and manufacturing processes, the overall performance of current hollow fan blade structures is difficult to guarantee: (1) the filling structure is uniform and singular, and the structural potential of gradient configuration design in terms of weight reduction, vibration reduction and load bearing has not been fully explored; (2) simple honeycomb, I-beam or triangular corrugated fillings are widely used, and specific functional porous metamaterials (such as tensile metamaterials with significant impact resistance and fatigue durability) have not been adopted, making it difficult to effectively achieve the structural-functional integration of load bearing and vibration reduction. In recent years, the complex configuration integral manufacturing process represented by additive manufacturing can realize the integrated molding of hollow blade wall panels and gradient metamaterial fillings, which is becoming a powerful guarantee for the development of lightweight, integrated and multifunctional aero-engine structures. Conducting research on the integrated design of wall panels and gradient metamaterial fillings for hollow blades is of great significance for further improving their overall performance. Summary of the Invention

[0006] To overcome the shortcomings of the prior art, this invention provides a method for optimizing the design of power system blade structures and its application, which can effectively use functional metamaterials in the construction of complex curved surface structures to achieve integrated design of impact resistance and load-bearing performance.

[0007] On one hand, this invention proposes a method for optimizing the design of a power system blade structure, comprising: acquiring a digital model of the blade; dividing the digital model into a non-design domain shell and a design domain space; performing cross-sectional processing on the design domain space of the digital model to obtain multiple cross-sections of the design domain space; re-triangulating the layered boundaries of the design domain space to obtain a lofting surface corresponding to each cross-section; restoring the multiple lofting surfaces to an optimized design domain space; and filling the optimized design domain space using a microstructure filling method to obtain an optimized blade structure.

[0008] In one embodiment, the power system blade structure optimization design method further includes: rounding the corners of each of the multiple lofting surfaces; or rounding the corners of the entire design domain space.

[0009] In one embodiment, after rounding the corners of each of the multiple lofting surfaces, the method further includes: taking four counterclockwise points on each lofting surface after rounding as the four fixed points of a topological quadrilateral, and constructing the topological quadrilateral corresponding to each lofting surface by combining the Jordan domain of that layer.

[0010] In one embodiment, the step of using a microstructure filling method to fill the optimized design domain space to obtain an optimized blade structure includes: mapping the design domain space of the blade in a first coordinate system to an initial cubic unit in a second coordinate system; uniformly filling the initial cubic unit with microstructure units in the second coordinate system to obtain filled cubic units; mapping the filled cubic units in the second coordinate system back to the first coordinate system to obtain an optimized design domain space; and thus obtaining an optimized blade structure.

[0011] In one embodiment, the process of taking cross sections of the design domain space of the digital model specifically includes taking cross sections of the design domain space of the digital model at intervals not greater than 10 mm.

[0012] In one embodiment, the blade structure includes a distal end and a proximal end, the proximal end being close to the rotation center of the blade and the distal end being far from the rotation center of the blade. The method further includes taking cross-sections of the digital model of the blade at fixed intervals, using the proximal end as the end face.

[0013] On the other hand, this invention also proposes a method for optimizing the design of a power system blade structure, comprising: obtaining a power system blade structure to be optimized, wherein the type of the blade structure includes a thin-shell curved surface structure, a swept curved surface structure, and a lofted curved surface structure; performing triangulation processing on the blade structure according to the type of the blade structure, and obtaining the design domain space corresponding to the blade structure; and filling the design domain space with microstructures to be filled according to the constraints of the power system blade structure and the constraints including operating conditions and iteration conditions, thereby completing the optimization design of the power system blade structure.

[0014] In one embodiment, the material of the microstructure to be filled includes at least one of BCC, FCC, and tensile metamaterials.

[0015] In another aspect, embodiments of the present invention also propose an electronic device, comprising: a memory and one or more processors connected to the memory, the memory storing a computer program, and the processors being used to execute the computer program to implement the power system blade structure optimization design method as described in any of the above embodiments.

[0016] In another aspect, embodiments of the present invention also provide a computer-readable storage medium storing computer-executable commands for executing the power system blade structure optimization design method as described in any of the above embodiments.

[0017] As can be seen from the above, the embodiments of the present invention, compared with the prior art, can have at least one or more of the following beneficial effects: By dividing the digital model of the blade into a non-design domain shell and a design domain space, the design domain space is processed by taking sections, and the layered boundaries of the design domain space are re-triangulated to obtain the lofting surface corresponding to each section. The lofting surface is restored to the optimized design domain space, and then the optimized design domain space is filled by the microstructure filling method to obtain the optimized blade structure. In this way, functional metamaterials are effectively used in the construction of complex curved surface structures to achieve the integrated design of impact resistance and load-bearing performance. Attached Figure Description

[0018] The accompanying drawings, which are included to provide a further understanding of the invention and form part of this invention, illustrate exemplary embodiments of the invention and are used to explain the invention, but do not constitute an undue limitation of the invention. In the drawings: Figure 1 A flowchart of a power system blade structure optimization design method provided in an embodiment of the present invention; Figure 2 This is a schematic diagram of a digital model of a solid fan blade provided in an embodiment of the present invention; Figure 3 This is a schematic diagram of the outer contour of the fan blade and the shell layer boundary provided in an embodiment of the present invention; Figure 4 This is a schematic diagram of the fillet treatment of the blade section provided in an embodiment of the present invention; Figure 5 This is a schematic diagram of the topological quadrilateral of the blade cross-section design domain provided in an embodiment of the present invention; Figure 6 A schematic diagram of the axial side and bottom of a fan blade wall panel provided in an embodiment of the present invention; Figure 7 A schematic diagram of the blade optimization design results provided in an embodiment of the present invention; Figure 8 This is a schematic diagram of the structure of an electronic device provided in an embodiment of the present invention; Figure 9 This is a schematic diagram of the structure of a computer-readable storage medium provided in an embodiment of the present invention. Detailed Implementation

[0019] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other. The present invention will now be described with reference to the accompanying drawings and embodiments.

[0020] To enable those skilled in the art to better understand the technical solutions of the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments, and should all fall within the protection scope of the present invention.

[0021] It should be noted that the terms "first," "second," etc., used in the specification, claims, and accompanying drawings of this invention are applicable in distinguishing similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such terms can be used interchangeably where appropriate so that the embodiments of the invention described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover a 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 applicable to such processes, methods, products, or apparatus.

[0022] It should also be noted that the division of multiple embodiments in this invention is only for the convenience of description and should not constitute a special limitation. Features in various embodiments can be combined and referenced in each other without contradiction.

[0023] like Figure 1 As shown, the first embodiment of the present invention proposes a method for optimizing the design of a power system blade structure, including: step S1, obtaining a digital model of the blade, and dividing the digital model into a non-design domain shell and a design domain space; step S2, performing cross-sectional processing on the design domain space of the digital model to obtain multiple cross-sections of the design domain space; step S3, re-triangulating the layered boundaries of the design domain space to obtain a lofting surface corresponding to each cross-section; step S4, restoring the multiple lofting surfaces obtained by triangulation into an optimized design domain space; step S5, using a microstructure filling method to fill the optimized design domain space to obtain an optimized blade structure.

[0024] The technical solution of this application will be further described below using a hollow fan blade of an aero-turbofan engine as a specific embodiment. The blade profile is a spatial curved surface formed according to certain rules based on the airfoil shape. It is characterized by complex shape, numerous dimensions, and strict tolerance requirements. Furthermore, the parameters of the profile are not fixed, the surface is complexly twisted, and the geometric dimensions and curvature vary greatly. In this embodiment, when performing multi-scale optimization design on the fan blade, the outer contour shape of the blade is not changed; only the filled area is studied.

[0025] In one specific embodiment, the fan blades are made of titanium alloy Ti6Al4V, with the following material properties: substrate density 4430 kg / m³. 3 The substrate has a Young's modulus of 110 GPa, a Poisson's ratio of 0.31, and a yield strength of 1030 MPa. This application analyzes only the centrifugal and aerodynamic loads on the blade. According to the current load spectrum of a certain aero-engine, the fan blade speed is 3350 rpm at low-pressure rotor speed (idle state), 9980 rpm at cruise state, and 11200 rpm at maximum speed. Blade mechanical analysis typically applies the centrifugal load to the finite element model of the fan blade through the fan shaft's rotational speed. The center of rotation is the coordinate axis containing the fan shaft's axis, and its rotational speed is the fan shaft's rotational speed, with the blade back facing the airflow direction in a clockwise direction. Simultaneously, aerodynamic calculation formulas show that the aerodynamic force at a point on the fan blade increases with the increase of the blade's radial height and is applied to the blade surface through pressure. The stress caused by centrifugal load is significantly greater than the stress generated by aerodynamic load alone. In other words, during flight, the effect of centrifugal load on the fan blades is greater than that of aerodynamic load.

[0026] Based on the above fundamental conditions, this application will provide a specific description of a preferred embodiment.

[0027] First, the original digital model of the blade is processed. The original digital model of the blade is as follows: Figure 2 As shown, taking the bottom plane of the blade as the end face, for example, after taking cross-sections every 10.0 mm from the original blade model, a 2.0 mm shell is extracted from each cross-section using SDF. The blade cross-section mainly consists of four parts: the blade basin curve, the blade back curve, the leading edge arc (intake edge), and the trailing edge arc (exhaust edge). Figure 3 As shown, the layers after shelling have sharp points at the boundaries. Since the blade thickness gradually changes, uniform rounding might drastically reduce the design domain; therefore, sharp points need to be rounded individually. The blade wall obtained after shelling, i.e., the non-design domain in the optimization design, is as follows: Figure 6 As shown, by re-triangulating the layered boundaries of the blade filling area (design domain), the lofting surface of each layer is obtained.

[0028] Take the four counter-clockwise points near the intake and exhaust edges of each layer's lofted surface after rounding the corners as the four vertices of a topological quadrilateral, and construct the topological quadrilateral by combining it with the Jordan domain of that layer. place (i.e.) Figure 3 Taking the tenth floor position as an example, the design domain without rounded corners is as follows: Figure 4 As shown on the left, the design domain after rounding the corners is as follows: Figure 4As shown on the right, the point of origin is located near the exhaust edge in the blade design domain. and The blade design area is located near the exhaust edge. and Together with Forming a topological quadrilateral ,like Figure 5 As shown.

[0029] Each layer of the lofting surface is constructed into a topological quadrilateral using the method described above. After obtaining the blade design domain using the general translational lofting method, the non-design domain of the blade can be obtained through Boolean operations, such as... Figure 6 As shown.

[0030] The blade's infill structure was optimized using a multi-scale surface structure optimization method. The optimization objective was to minimize the blade's compliance under load, while ensuring the design domain volume fraction was less than 28%. The optimization objective was also to minimize structural compliance under centrifugal loads and aerodynamic loads generated by the fan blades in the airflow at a cruise speed of 9980 rpm and zero angular acceleration. Fixed constraints were applied at the blade root to simulate the boundary conditions of the blade clamped onto the tenon. Considering optimization efficiency, all finite element analyses and calculations in this section were linear. The optimized blade design results are shown below. Figure 7 As shown, the sectional view of the optimized design result is shown below. Figure 7 Part (b) of the text.

[0031] In a preferred embodiment, the operation steps of this application are as follows: (1) First step: Create a new project / open an existing project and define the type of surface in the design. Choose the type of multi-scale optimization design, with options including thin-shell surface structure, swept surface structure, and lofted surface structure.

[0032] (2) Second step: Initial model input For different optimization design problems, different discrete triangular mesh models are uploaded. In one embodiment, for multi-scale optimization design of thin-shell curved surface structures, the discrete triangulation form of the surface in the design domain needs to be uploaded; for swept and lofted surfaces, a single swept surface or multiple lofted surfaces and their corresponding traces need to be uploaded. Preferably, after uploading the discrete triangulated surface model, the conformal mapping result of the surface and the corresponding angular distortion contour map will be displayed in the display area.

[0033] (3) Third step: Select microstructure type Next, select the desired type of infill microstructure; options include BCC, FCC, and dilatational metamaterials. After selecting the configuration of the infill microstructure, the volume fraction range of the microstructure in the optimization design can be further restricted.

[0034] (4) Fourth step: Define working conditions Preferably, for the definition of loads in the optimization design, load points can be directly selected within the real-world region, and the load magnitude and direction can be numerically defined; for the definition of constraints in the optimization design, constraint points can be directly selected within the real-world region, and the degrees of freedom of the constraints can be selected. Preferably, the selection of load points and constraint points can be done either within the parameter space or on the surface, and the camera view and mouse point selection display are completely synchronized. Preferably, the design domain and non-design domain can be directly selected within the parameter domain or solid domain.

[0035] (5) Fifth step: Define optimization parameters and start optimization design. Choose the iteration stopping condition for the optimization design and set the corresponding value: you can set the iteration step number and convergence condition at the same time, and end the loop when either one is reached during the iteration process, or you can set the iteration stopping condition separately.

[0036] (6) Step Six: Results Display After the optimization design is completed, the results of the optimization are displayed.

[0037] In a preferred embodiment, the specific steps of filling the design domain space with microstructures in this application include: First, the design domain space of the blade in the first coordinate system is mapped to an initial cubic unit in the second coordinate system; that is, the irregular blade structure is mapped to a regular cubic structure, preferably a 1*1*1 cubic unit, to facilitate the filling of the structure. Secondly, microstructure units are uniformly filled into the initial cubic unit in the second coordinate system to obtain a filled cubic unit; the optional material form of the microstructure units includes one or more of BCC, FCC, tensile metamaterials, etc. At this time, the microstructures filled into the cubic unit are regular shapes of uniform size, and the structural and mechanical characteristics they exhibit in each dimension of the cube are also uniform. Finally, the filled cubic units in the second coordinate system are mapped back to the first coordinate system to obtain the optimized design domain space; thus, the optimized blade structure is obtained. The aforementioned cubes filled with microstructure units still need to be restored to an irregular blade shape to obtain the final optimized blade structure.

[0038] In summary, the first embodiment of this invention proposes a method for optimizing the design of a power system blade structure. This method divides the digital model of the blade into a non-design domain shell and a design domain space. The design domain space is then processed by taking cross sections, and the layered boundaries of the design domain space are re-triangulated to obtain a lofting surface corresponding to each cross section. The lofting surface is then restored to the optimized design domain space, and the optimized design domain space is filled using a microstructure filling method to obtain the optimized blade structure. This effectively utilizes functional metamaterials in the construction of complex curved surface structures, achieving an integrated design of impact resistance and load-bearing performance.

[0039] like Figure 8 As shown, the second embodiment of the present invention also proposes an electronic device 30, which includes, for example, at least one processor 31 and at least one memory 32, wherein the memory 32 stores a computer program, and when the computer program is executed by the processor 31, the processor 31 executes the power system blade structure optimization design method as described in the first embodiment, and the beneficial effects of the electronic device 30 provided in this embodiment are the same as the beneficial effects of the power system blade structure optimization design method provided in the first embodiment.

[0040] like Figure 9 As shown, the third embodiment of the present invention also provides a computer-readable storage medium 40, on which a computer program is stored. When the program is executed by a processor, it implements the steps of the above-described method. The beneficial effects of the computer-readable storage medium 40 provided in this embodiment are the same as the beneficial effects of the power system blade structure optimization design method provided in the first embodiment.

[0041] The computer-readable storage medium may include, but is not limited to, any type of disk, including floppy disks, optical disks, DVDs, CD-ROMs, microdrives, as well as magneto-optical disks, ROMs, RAMs, EPROMs, EEPROMs, DRAMs, VRAMs, flash memory devices, magnetic cards or optical cards, nanosystems (including molecular memory ICs), or any type of medium or device suitable for storing instructions and / or data.

[0042] It should be noted that, for the sake of simplicity, the foregoing method embodiments are all described as a series of actions. However, those skilled in the art should understand that this application is not limited to the described order of actions, as some steps may be performed in other orders or simultaneously according to this application. Furthermore, those skilled in the art should also understand that the embodiments described in the specification are preferred embodiments, and the actions and modules involved are not necessarily essential to this application.

[0043] In the above embodiments, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions in other embodiments.

[0044] In the several embodiments provided in this application, it should be understood that the disclosed apparatus can be implemented in other ways. For example, the apparatus embodiments described above are merely illustrative; for instance, the division of units is only a logical functional division, and in actual implementation, there may be other division methods. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the coupling or direct coupling or communication connection shown or discussed may be through some service interface; the indirect coupling or communication connection between devices or units may be electrical or other forms.

[0045] The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the units can be selected to achieve the purpose of this embodiment according to actual needs.

[0046] Furthermore, the functional units in the various embodiments of this application can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated unit can be implemented in hardware or as a software functional unit.

[0047] If the integrated unit is implemented as a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage device (CMD). Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or all or part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a memory and includes several instructions to cause a computer device (which may be a personal computer, server, 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 memory includes various media capable of storing program code, such as USB flash drives, read-only memory (ROM), random access memory (RAM), portable hard drives, magnetic disks, or optical disks.

[0048] Those skilled in the art will understand that all or part of the steps in the various methods of the above embodiments can be implemented by a program instructing related hardware. The program can be stored in a computer-readable storage medium, which may include: a flash drive, a read-only memory (ROM), a random access memory (RAM), a magnetic disk, or an optical disk, etc.

[0049] The foregoing description is merely an exemplary embodiment of this disclosure and should not be construed as limiting the scope of this disclosure. Any equivalent changes and modifications made in accordance with the teachings of this disclosure shall still fall within the scope of this disclosure. Those skilled in the art will readily conceive of embodiments of this disclosure upon considering the specification and practicing the disclosure herein. This application is intended to cover any variations, uses, or adaptations of this disclosure that follow the general principles of this disclosure and include common knowledge or customary techniques in the art not described herein. The specification and embodiments are to be considered exemplary only, and the scope and spirit of this disclosure are defined by the claims.

[0050] 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.

[0051] Those skilled in the art will readily understand that the above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A method for optimizing the design of blade structure in a power system, characterized in that, include: Obtain a digital model of the blade, and divide the digital model into a non-design domain shell and a design domain space; The design domain space of the digital model is subjected to cross-sectional processing to obtain multiple cross-sections of the design domain space; By re-triangulating the layered boundaries of the design domain space, a lofting surface corresponding to each of the cross sections is obtained; The multiple lofted surfaces obtained by triangulation are restored to the optimized design domain space; The optimized design domain space is filled using a microstructure filling method to obtain the optimized blade structure.

2. The method for optimizing the design of power system blade structure according to claim 1, characterized in that, Also includes: Each of the aforementioned lofted surfaces is rounded. or The entire design domain space is rounded.

3. The method for optimizing the design of power system blade structure according to claim 2, characterized in that, After rounding the corners of each of the lofted surfaces, the process also includes: After rounding the corners, take the four counterclockwise points on each layer of the lofting surface as the four fixed points of the topological quadrilateral, and construct the topological quadrilateral corresponding to each layer of the lofting surface by combining the Jordan domain of that layer.

4. The method for optimizing the design of power system blade structure according to claim 3, characterized in that, The method of filling the optimized design domain space with a microstructure filling method to obtain the optimized blade structure includes: The design domain space of the blade in the first coordinate system is mapped to an initial cubic unit in the second coordinate system; In the second coordinate system, microstructure units are uniformly filled into the initial cubic unit to obtain a filled cubic unit; The filled cubic unit in the second coordinate system is mapped back to the first coordinate system to obtain the optimized design domain space; thus, the optimized blade structure is obtained.

5. The method for optimizing the design of power system blade structure according to any one of claims 1 to 4, characterized in that, The process of taking a section from the design domain space of the digital model specifically includes: The design domain space of the digital model is subjected to cross-sectional processing at intervals not exceeding 10mm.

6. The method for optimizing the design of power system blade structure according to any one of claims 1 to 4, characterized in that, The blade structure includes a distal end and a proximal end, the proximal end being close to the rotation center of the blade, and the distal end being far from the rotation center of the blade. The method further includes: Using the proximal end as the end face, cross sections are taken from the digital model of the blade at fixed intervals.

7. A method for optimizing the design of blade structure in a power system, characterized in that, include: Obtain the blade structure of the power system to be optimized, wherein the blade structure types include thin shell curved surface structure, swept curved surface structure and lofted curved surface structure; Based on the type of blade structure, the blade structure is triangulated, and the corresponding design domain space is obtained. Based on the constraints of the power system blade structure, including operating conditions and iteration conditions, the microstructures to be filled are filled into the design domain space to complete the optimized design of the power system blade structure.

8. The method for optimizing the design of power system blade structure according to claim 7, characterized in that, include: The material of the microstructure to be filled includes at least one of BCC, FCC, and tensile metamaterials.

9. An electronic device, characterized in that, include: A memory and one or more processors connected to the memory, the memory storing a computer program, the processors executing the computer program to implement the power system blade structure optimization design method as described in any one of claims 1-8.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer-executable commands for performing the power system blade structure optimization design method as described in any one of claims 1-8.

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