A multi-physical field coupling calculation and matching optimization method and system for low stress design of turbine blades

Abstract

A kind of multi-physical field response calculation and matching optimization method and system for low stress design of turbine blade, it is related to the field of aero-engine and gas turbine structure design and matching optimization, solve how the complex multi-physical field calculation is landed in the aero-engine structure design in the existing turbine blade design method, and under the strong coupling of multi-physical field, it is difficult to accurately reveal the internal relationship between temperature distribution characteristics, structural constraint conditions and stress formation, lack of unified calculation evaluation index and system matching optimization process and other problems, the method described in the application is calculated by the aerodynamic load, temperature load and structural response of turbine blade under complex service conditions, and the multi-physical field response is comprehensively evaluated based on engineering calculation model, the matching optimization design of turbine blade structure characteristics and cooling characteristics is realized.

Description

Technical Field

[0001] This invention relates to the field of structural design and matching optimization of aero-engines and gas turbines, and specifically to a multi-physics coupling calculation and matching optimization method and system for low-stress design of turbine blades. Background Technology

[0002] As aero-engine technology advances towards higher thrust-to-weight ratios, higher turbine inlet temperatures, and longer lifespans, the operating environment of turbine blades within engines is becoming increasingly demanding. In actual service, turbine blades not only bear aerodynamic loads from high-speed gas flow but also experience significant thermal loads from high-temperature gas flow and centrifugal loads from high-speed rotation.

[0003] Under the combined action of the aforementioned loads, a complex multi-physics coupling state forms inside the turbine blade, leading to high thermo-mechanical coupling stress in localized areas. These stress concentration areas often become the main cause of fatigue damage, creep damage, and even fracture failure in turbine blades.

[0004] Existing turbine blade design methods typically employ a phased analysis strategy, where aerodynamic performance, cooling performance, and structural strength are designed and verified separately. While this approach has some practicality in engineering applications, it struggles to accurately reveal the intrinsic relationships between temperature distribution characteristics, structural constraints, and stress formation under strong multi-physics coupling. This is especially problematic when structural and cooling parameters change simultaneously, as there is a lack of unified computational evaluation indicators and a systematic matching optimization process.

[0005] Furthermore, the traditional structural design of aero-engines and gas turbines relies on linear superposition, empirical formulas, or single-physics simulation, and multi-physics coupled calculations are too complex, computationally intensive, and have difficulty converging boundary conditions. Therefore, there is an urgent need for a multi-physics response calculation and matching optimization method for low-stress turbine blade design, which can efficiently and accurately apply multi-physics coupled calculation methods, such as fluid-thermal-solid and thermo-acoustic-vibration, directly to the structural design iteration. Summary of the Invention

[0006] This invention addresses the challenges of applying complex multiphysics calculations to aero-engine structural design in existing turbine blade design methods. Specifically, it simplifies the application of these calculations to the design of aero-engines, particularly when strong multiphysics coupling makes it difficult to accurately reveal the intrinsic relationships between temperature distribution characteristics, structural constraints, and stress formation. Furthermore, it addresses the lack of unified computational evaluation metrics and a systematic matching optimization process when structural and cooling parameters change simultaneously. To resolve these technical problems, this invention employs the following technical solution: Option 1: This invention proposes a multiphysics coupling calculation method for low-stress design of turbine blades, the method comprising the following steps: Step 1: Establish a complete geometric model of the turbine blade, which includes the external outline of the turbine blade, the blade root structure, and the internal cooling structure features. Step 2: Import the complete geometric model of the turbine blade established in Step 1 into the aerodynamic calculation software as a unified geometric source to obtain the aerodynamic load calculation results. Based on the aerodynamic load calculation results, establish the flow field calculation model of the turbine blade. Through numerical simulation of the flow state around the turbine blade, calculate the pressure distribution on the surface of the turbine blade. Step 3: Import the complete geometric model of the turbine blade into thermal analysis or conjugate heat transfer calculation software to obtain the heat transfer results. Based on the heat transfer results, establish a temperature field analysis model of the turbine blade to obtain the temperature field calculation results, which are used to obtain the temperature distribution function of the turbine blade under service conditions. Step 4: Use finite element structural analysis software to establish a structural analysis model of the turbine blade, and apply the aerodynamic load calculation results calculated in Step 2 and the temperature field calculation results calculated in Step 3 as load conditions to the structural analysis model. At the same time, consider the centrifugal load generated by the turbine blade in the rotating state to realize the structural response calculation under multiple load conditions. Step 5: Based on the structural response calculation results under multiple load conditions in Step 4, evaluate the stress state of the turbine blade to obtain the equivalent stress distribution of the turbine blade as a whole and in local areas, and display it in the form of cloud map or data to intuitively reflect the location and degree of stress concentration areas.

[0007] Furthermore, a preferred embodiment is provided, in which step 1 further includes defining the chord length, spanwise height, thickness distribution, and spatial positional relationship of the cooling structure of the turbine blade in a parametric manner, so as to enable the complete geometric model of the turbine blade to support subsequent structural and cooling scheme adjustments.

[0008] Furthermore, a preferred embodiment is provided in which step 2 further includes the step of importing a unified geometric source into thermal analysis or conjugate heat transfer calculation software and finite element structural analysis software for simulation analysis of different physical fields.

[0009] Furthermore, a preferred embodiment is provided, wherein the method for importing the complete geometric model into the aerodynamic calculation software in step 2 to obtain the aerodynamic load calculation results is as follows:

[0010] in, Let n be the local pressure on the blade surface and n be the surface normal vector.

[0011] Furthermore, a preferred embodiment is provided, wherein the method for evaluating the stress state of the turbine blade in step 5 based on the structural response calculation results under multiple load conditions in step 4 is as follows:

[0012] in, , , These are the principal stresses obtained from the structural model analysis.

[0013] Option 2: A multiphysics matching optimization method for low-stress turbine blade design, wherein the matching optimization method is based on the multiphysics coupling calculation method for low-stress turbine blade design described in Option 1, and the matching optimization method includes the following steps: Step 1: Construct a multi-physics stress response evaluation index system based on the obtained equivalent stress distribution of the turbine blade as a whole and in local areas; Step 2: While keeping the aerodynamic shape basically unchanged, adjust the local structural features of the turbine blade using 3D modeling software, and re-execute the multiphysics calculation steps. Compare and analyze the stress response evaluation index under different structural schemes. Step 3: Based on the structural feature analysis in Step 2, the temperature field calculation and structural response calculation are re-executed by adjusting the arrangement of the turbine blade cooling structure. By comparing the temperature gradient distribution and stress response evaluation index under different cooling structure schemes, the influence mechanism of cooling structure changes on stress formation is analyzed. Step 4: Based on the analysis results of changes in comprehensive structural features and changes in cooling structure, perform structure-cooling matching optimization calculations to complete the multiphysics matching optimization for low-stress design of turbine blades.

[0014] Furthermore, a preferred embodiment is provided, wherein the multiphysics stress response evaluation index system described in step 1 includes at least one of the following: maximum equivalent stress index, stress distribution uniformity index, and thermal stress contribution ratio index.

[0015] Option 3: A multiphysics matching optimization system for low-stress turbine blade design, wherein the matching optimization system is based on the multiphysics matching optimization method for low-stress turbine blade design described in Option 2, and the matching optimization system includes: The module for constructing a multi-physics stress response evaluation index system is used to construct a multi-physics stress response evaluation index system based on the obtained equivalent stress distribution of the overall and local areas of the turbine blade. The comparative analysis module is used to adjust the local structural features of turbine blades using 3D modeling software while keeping the aerodynamic shape basically unchanged, and to re-execute the multiphysics calculation steps to compare and analyze the stress response evaluation index under different structural schemes. The calculation module is used for structural feature analysis based on the comparative analysis module. By adjusting the arrangement of the turbine blade cooling structure, the temperature field calculation and structural response calculation are re-executed. By comparing the temperature gradient distribution and stress response evaluation index under different cooling structure schemes, the influence mechanism of cooling structure changes on stress formation is analyzed. The matching optimization module is used to perform structure-cooling matching optimization calculations based on the results of comprehensive structural feature change analysis and cooling structure change analysis, and to complete multi-physics response matching optimization for low-stress design of turbine blades.

[0016] Option 4: A computer-readable storage medium storing a computer program that, when executed by a processor, implements the steps of the method described in Option 1.

[0017] Option 5: A computer device, including a memory and a processor, wherein the memory stores a computer program, and when the processor runs the computer program stored in the memory, the processor executes the method described in Option 1.

[0018] The advantages of this invention are: The multiphysics coupling calculation and matching optimization method and system for low-stress design of turbine blades described in this invention realizes for the first time the direct application of multiphysics coupling calculation method in the front end of aero-engine structural design. It changes the existing serial mode of design-verification-redesign and provides a brand-new technical path for aero-engine structural design. By systematically calculating the aerodynamic load, temperature load and structural response of turbine blades under complex service conditions, and comprehensively evaluating the multiphysics response based on the engineering calculation model, the matching optimization design of turbine blade structural characteristics and cooling characteristics is realized.

[0019] The present invention discloses a multi-physics coupling calculation and matching optimization method for low-stress design of turbine blades. By obtaining the multi-load response of turbine blades under service conditions and constructing a stress response evaluation model in combination with engineering calculation formulas, the method realizes the matching optimization design of turbine blade structural features and cooling features, thereby effectively reducing the stress level of turbine blades and improving their structural reliability and service life.

[0020] This invention is also applicable to engineering implementation schemes for low-stress design of turbine blades, and can be used in subsequent product design and verification. Attached Figure Description

[0021] Figure 1 This is a flowchart illustrating the multiphysics coupling calculation method for low-stress turbine blade design described in Implementation Method 1.

[0022] Figure 2 This is a flowchart illustrating the multiphysics matching optimization method for low-stress turbine blade design described in Implementation Method 1.

[0023] Figure 3 This is a schematic diagram of the three-dimensional structural model of the turbine blade described in Embodiment 1.

[0024] (a) is a schematic diagram of the surface structure of the turbine blade, and (b) is a schematic diagram of the internal cooling structure.

[0025] Figure 4 This is a schematic diagram of the temperature distribution calculated by gas-heat coupling as described in Implementation Method 1.

[0026] Among them, (a) is a schematic diagram of the temperature distribution calculated by gas-thermal coupling on the pressure surface, and (b) is a schematic diagram of the temperature distribution calculated by gas-thermal coupling on the suction surface.

[0027] Figure 5 This is a schematic diagram of the equivalent stress distribution of the blade under multi-physics coupling.

[0028] (a) is a schematic diagram of stress distribution on the pressure surface, and (b) is a schematic diagram of equivalent stress distribution on the suction surface. Detailed Implementation

[0029] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them.

[0030] Implementation Method 1, see [link] Figure 1 and Figure 2 This embodiment describes a multiphysics response calculation and matching optimization method for low-stress design of turbine blades. The method specifically includes the following steps: S1: Establishment of a unified geometric model and management of data consistency In this step, a complete geometric model of the turbine blade is first established using 3D modeling software. This geometric model includes not only the blade's external outline but also the blade root structure and internal cooling structure features. During the modeling process, the continuity and integrity of the geometric model must be ensured to meet the modeling requirements of subsequent multiphysics analysis software.

[0031] The established geometric model serves as a unified data source for multiple analysis stages, including aerodynamic calculations, temperature field calculations, and structural analysis. By managing the geometric model uniformly, load mapping errors caused by geometric inconsistencies across different analysis phases can be avoided, thus ensuring the comparability and reliability of multiphysics calculation results.

[0032] In this embodiment, a three-dimensional geometric model of the turbine blade is first established using 3D modeling software (such as UG, CATIA, or SolidWorks). The geometric model includes the basic configuration of the blade's aerodynamic shape, root structure, and internal cooling channels. During the geometric modeling process, the spatial relationships of the turbine blade's chord length, spanwise height, thickness distribution, and cooling structure are defined parametrically, enabling the geometric model to support subsequent adjustments to the structure and cooling scheme.

[0033] After completing the geometric modeling, the model undergoes geometric checks and repairs to ensure the absence of geometric defects such as gaps, overlaps, or non-manifolds. Subsequently, the geometric model is used as a unified geometric source and imported into aerodynamic calculation software (ANSYS CFX), thermal analysis or conjugate heat transfer calculation software, and finite element structural analysis software for simulation analysis in different physical fields.

[0034] During the aerodynamic analysis phase, flow field simulation calculations were performed on the turbine blades using aerodynamic calculation software to obtain the pressure distribution results on the blade surface. This pressure distribution was output as surface pressure variables and then integrated using pressure to form an aerodynamic load data file, providing input for subsequent structural analysis.

[0035] After completing the aerodynamic analysis, thermal analysis or conjugate heat transfer calculation software is used to simulate the temperature field of the turbine blade, calculating the temperature distribution of the blade under the influence of high-temperature combustion gas environment and cooling structure. The temperature field results are output as temperature variables and input as thermal loads into the structural analysis model.

[0036] This embodiment describes the process of calculating the structural response under multiphysics coupling.

[0037] In this embodiment, a structural analysis model of the turbine blade is established using finite element structural analysis software. The structural model is generated based on a unified geometric model, and meshing is performed according to the blade's structural characteristics to ensure the calculation accuracy of key areas.

[0038] Subsequently, the aerodynamic load files obtained from the aerodynamic analysis are imported into the structural analysis model, and the temperature distribution results obtained from the temperature field analysis are mapped to the corresponding nodes or elements of the structural model. Simultaneously, a rotating reference frame is introduced into the structural analysis model to consider the centrifugal loads generated by blade rotation, thus reflecting the stress state under actual operating conditions.

[0039] The above-mentioned multi-load conditions were solved using finite element structural analysis software to obtain the displacement and stress field distributions of the turbine blade under multi-physics coupling. The stress field includes anisotropic stress components and equivalent stress variables automatically calculated by the software, which are used for subsequent stress evaluation and analysis.

[0040] S2: Aerodynamic Load Calculation and Aerodynamic Response Acquisition After establishing the unified geometric model, it is imported into aerodynamic calculation software to create a flow field calculation model for the turbine blade. The pressure distribution on the blade surface is then calculated through numerical simulation of the flow state around the blade.

[0041] The aerodynamic load is obtained based on the integral calculation of the pressure on the blade surface, and its expression is:

[0042] in denoted by , where n represents the local pressure on the blade surface and n represents the surface normal vector.

[0043] Essentially, it reflects the effect of aerodynamic forces on the blade structure. Aerodynamic loads can be expressed as the integral result of the pressure on the blade surface along the normal direction. The calculation results are output in the form of a data file, providing direct input for subsequent structural analysis.

[0044] This step allows us to obtain load information that reflects the aerodynamic characteristics of turbine blades under actual operating conditions.

[0045] S3: Temperature Field Calculation and Thermal Environment Response Acquisition After the aerodynamic analysis is completed, the unified geometric model is imported into thermal analysis or conjugate heat transfer calculation software to establish a turbine blade temperature field analysis model. This model comprehensively considers the high-temperature combustion gas environment and the effects of the cooling structure to calculate the temperature distribution inside and on the surface of the blade.

[0046] Numerical solutions can be used to obtain the temperature distribution function of the blade under service conditions. This temperature distribution result not only reflects the overall thermal environment of the blade, but also reveals the temperature differences and temperature gradient characteristics between different structural regions, providing basic data for subsequent thermal stress analysis.

[0047] S4: Structural Response Calculation and Multi-Load Coupling Analysis In this step, a structural analysis model of the turbine blade is established using finite element method (FEM) software, and the aforementioned aerodynamic load calculation results and temperature field calculation results are applied to the structural model as load conditions. Simultaneously, the centrifugal load generated by the blade during rotation is considered to achieve structural response calculation under multiple load conditions.

[0048] By solving the problem using structural analysis software, the structural response results of the blade under the coupling of multiple physics fields can be obtained, including displacement and stress. This step realizes the engineering coupling between the aerodynamic field, temperature field, and structural field, laying the foundation for subsequent stress evaluation.

[0049] S5: Equivalent stress calculation and stress field distribution acquisition Based on the structural analysis results, the stress state of the turbine blade is evaluated. In this invention, the von Mises equivalent stress is used as the main stress evaluation index, and its calculation formula is as follows:

[0050] Wherein, σ1, σ2, and σ3 are the principal stresses obtained from structural analysis. The equivalent stress is automatically calculated by the structural analysis software based on the principal stress components, and its calculation formula is based on the yield criterion in mechanics of materials.

[0051] This step allows us to obtain the equivalent stress distribution of the turbine blade as a whole and in local areas, and display it in the form of cloud maps or data, thereby intuitively reflecting the location and degree of stress concentration areas.

[0052] S6: Temperature Gradient Calculation and Thermal Stress Mechanism Analysis After obtaining the temperature field distribution, the temperature variation characteristics of local areas of the turbine blade are further analyzed. By taking the spatial derivative of the temperature distribution function, the temperature gradient distribution inside the blade can be obtained.

[0053] Based on thermoelasticity theory, temperature gradients cause uneven thermal expansion of materials, thus creating thermal stress components in the structure. By comparing the results of temperature gradient analysis with those of structural analysis, the mechanism by which the thermal environment affects the formation of structural stress can be clarified, providing a physical basis for subsequent low-stress design.

[0054] This embodiment describes the evaluation method and key variable analysis process for multiphysics stress response.

[0055] After obtaining the structural analysis results, a systematic evaluation of the stress state of the turbine blade is conducted. In this embodiment, the equivalent stress variable is used as the main evaluation index to characterize the comprehensive stress level of the blade under multi-directional stress conditions.

[0056] The post-processing function of the structural analysis software was used to analyze the equivalent stress distribution cloud map and identify areas of stress concentration in the blade. Simultaneously, combined with the temperature field analysis results, the temperature variables inside and on the surface of the blade were analyzed, with a focus on the temperature gradient distribution in areas of drastic temperature changes.

[0057] By calculating the spatial variation of temperature, the temperature gradient variable is obtained. Then, using thermoelastic theory, the influence of the temperature gradient on stress formation is analyzed. By comparing the temperature gradient distribution results with the equivalent stress distribution results, the main influencing factors of stress formation under multi-physics coupling can be identified.

[0058] S7: Construction of Multiphysics Stress Response Evaluation Indicators To enable quantitative comparison between different design schemes, a multiphysics stress response evaluation index system is constructed in this step. This index system includes at least the maximum equivalent stress index, the stress distribution uniformity index, and the thermal stress contribution ratio index.

[0059] By transforming complex stress distribution results into quantifiable evaluation indicators, the comparability between different design schemes can be significantly improved, providing clear evaluation criteria for matching optimization.

[0060] S8: Calculation and analysis of stress response to changes in structural characteristics While maintaining the basic aerodynamic shape, the local structural features of the turbine blade were adjusted using 3D modeling software, and the multiphysics calculation process was re-executed. By comparing and analyzing the stress response evaluation indicators under different structural schemes, the influence of structural feature changes on stress response can be summarized. This step helps to identify structural features sensitive to structural stress, providing key adjustment directions for subsequent matching optimization.

[0061] This embodiment describes the process of optimizing the matching of turbine blade structural features with cooling structure.

[0062] In this embodiment, based on the initial multiphysics analysis, the local structural features of the turbine blade are adjusted using 3D modeling software. This adjustment is achieved by modifying structural variables in the geometric model, such as changing the local thickness distribution or the spatial location of the cooling structure, without altering the overall aerodynamic shape of the blade.

[0063] After the structural adjustment is completed, the updated geometric model is re-imported into the aerodynamic calculation software, thermal analysis software, and structural analysis software. The aerodynamic analysis, temperature field analysis, and structural response calculation process are repeated to obtain new multiphysics response results.

[0064] Based on the structural adjustment analysis, the internal cooling structure of the turbine blade was adjusted accordingly, and the impact of the cooling structure changes on temperature and temperature gradient variables was analyzed through temperature field simulation calculations. Through multiple rounds of structural and cooling structure adjustments and simulation calculations, the synergistic matching optimization between structural features and cooling structure was achieved.

[0065] S9: Calculation and Analysis of Stress Response to Changes in Cooling Structure Based on the structural feature analysis, the temperature field and structural response calculations were re-executed by adjusting the arrangement of the turbine blade cooling structure. By comparing the temperature gradient distribution and stress response evaluation indicators under different cooling structure schemes, the influence mechanism of cooling structure changes on stress formation can be analyzed.

[0066] This step is used to reveal the coupling relationship between cooling design and structural stress.

[0067] S10: Structural-Cooling Matching Optimization and Solution Selection Based on the analysis results of changes in comprehensive structural features and cooling structure, structural-cooling matching optimization calculations were performed. Through multiple rounds of calculations and comparisons, the design scheme with the optimal stress response evaluation index was gradually selected. The final determined design scheme can serve as the engineering implementation plan for low-stress design of turbine blades and can be used for subsequent product design and verification.

[0068] This implementation method describes the comparative analysis of multiphysics simulation results and their engineering application effects.

[0069] In this embodiment, based on the multiphysics simulation results obtained from the aforementioned embodiments, the stress distribution characteristics under different structural and cooling schemes are compared and analyzed. By comparing the equivalent stress variables, stress concentration region locations, and distribution characteristics under different schemes, the effectiveness of the multiphysics response calculation and matching optimization method in reducing the stress level of turbine blades can be verified. The final determined structure-cooling matching design scheme can serve as an engineering implementation scheme for low-stress turbine blade design and can be used in subsequent structural verification and product design stages.

[0070] Those skilled in the art will understand that the above description is merely a preferred embodiment of the present invention, and the features described in the various embodiments and / or claims of this disclosure can be combined or combined in various ways, even if such combinations or combinations are not explicitly described in this disclosure. This is not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

[0071] Although preferred embodiments of the invention have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including both the preferred embodiments and all changes and modifications falling within the scope of the invention. Clearly, those skilled in the art can make various alterations and modifications to the invention without departing from its spirit and scope. Thus, if these modifications and modifications of the invention fall within the scope of the claims and their equivalents, the invention is also intended to include these modifications and modifications.

Claims

1. A multiphysics coupling calculation method for low-stress design of turbine blades, characterized in that, The method includes the following steps: Step 1: Establish a complete geometric model of the turbine blade, which includes the external outline of the turbine blade, the blade root structure, and the internal cooling structure features. Step 2: Import the complete geometric model of the turbine blade established in Step 1 into the aerodynamic calculation software as a unified geometric source to obtain the aerodynamic load calculation results. Based on the aerodynamic load calculation results, establish the flow field calculation model of the turbine blade. Through numerical simulation of the flow state around the turbine blade, calculate the pressure distribution on the surface of the turbine blade. Step 3: Import the complete geometric model of the turbine blade into thermal analysis or conjugate heat transfer calculation software to obtain the heat transfer results. Based on the heat transfer results, establish a temperature field analysis model of the turbine blade to obtain the temperature field calculation results, which are used to obtain the temperature distribution function of the turbine blade under service conditions. Step 4: Use finite element structural analysis software to establish a structural analysis model of the turbine blade, and apply the aerodynamic load calculation results calculated in Step 2 and the temperature field calculation results calculated in Step 3 as load conditions to the structural analysis model. At the same time, consider the centrifugal load generated by the turbine blade in the rotating state to realize the structural response calculation under multiple load conditions. Step 5: Based on the structural response calculation results under multiple load conditions in Step 4, evaluate the stress state of the turbine blade to obtain the equivalent stress distribution of the turbine blade as a whole and in local areas, and display it in the form of cloud map or data to intuitively reflect the location and degree of stress concentration areas.

2. The multiphysics coupling calculation method for low-stress design of turbine blades according to claim 1, characterized in that, Step 1 also includes defining the chord length, spanwise height, thickness distribution, and spatial relationship of the cooling structure of the turbine blade through parametric methods, so that the complete geometric model of the turbine blade can support the adjustment of the structure and cooling scheme.

3. The multiphysics coupling calculation method for low-stress design of turbine blades according to claim 1, characterized in that, Step 2 also includes importing a unified geometric source into thermal analysis or conjugate heat transfer calculation software and finite element structural analysis software for simulation analysis of different physical fields.

4. The multiphysics coupling calculation method for low-stress design of turbine blades according to claim 1, characterized in that, The method for importing the complete geometric model into the aerodynamic calculation software in step 2 to obtain the aerodynamic load calculation results is as follows: in, Let n be the local pressure on the blade surface and n be the surface normal vector.

5. The multiphysics coupling calculation method for low-stress design of turbine blades according to claim 1, characterized in that, In step 5, based on the structural response calculation results under multiple load conditions in step 4, the method for evaluating the stress state of the turbine blade is as follows: in, , , These are the principal stresses obtained from the structural model analysis.

6. A multiphysics matching optimization method for low-stress design of turbine blades, characterized in that, The matching optimization method is based on the multiphysics coupling calculation method for low-stress design of turbine blades as described in claim 1, and the matching optimization method includes the following steps: Step 1: Construct a multi-physics stress response evaluation index system based on the obtained equivalent stress distribution of the turbine blade as a whole and in local areas; Step 2: While keeping the aerodynamic shape basically unchanged, adjust the local structural features of the turbine blade using 3D modeling software, and re-execute the multiphysics calculation steps. Compare and analyze the stress response evaluation index under different structural schemes. Step 3: Based on the structural feature analysis in Step 2, the temperature field calculation and structural response calculation are re-executed by adjusting the arrangement of the turbine blade cooling structure. By comparing the temperature gradient distribution and stress response evaluation index under different cooling structure schemes, the influence mechanism of cooling structure changes on stress formation is analyzed. Step 4: Based on the analysis results of changes in comprehensive structural features and changes in cooling structure, perform structure-cooling matching optimization calculations to complete the multiphysics matching optimization for low-stress design of turbine blades.

7. The multiphysics matching optimization method for low-stress design of turbine blades according to claim 4, characterized in that, The multiphysics stress response evaluation index system mentioned in step 1 includes at least one of the following: maximum equivalent stress index, stress distribution uniformity index, and thermal stress contribution ratio index.

8. A multiphysics matching optimization system for low-stress design of turbine blades, characterized in that, The matching optimization system is implemented based on the multiphysics matching optimization method for low-stress design of turbine blades as described in claim 6. The matching optimization system includes: The module for constructing a multi-physics stress response evaluation index system is used to construct a multi-physics stress response evaluation index system based on the obtained equivalent stress distribution of the overall and local areas of the turbine blade. The comparative analysis module is used to adjust the local structural features of turbine blades using 3D modeling software while keeping the aerodynamic shape basically unchanged, and to re-execute the multiphysics calculation steps to compare and analyze the stress response evaluation index under different structural schemes. The calculation module is used for structural feature analysis based on the comparative analysis module. By adjusting the arrangement of the turbine blade cooling structure, the temperature field calculation and structural response calculation are re-executed. By comparing the temperature gradient distribution and stress response evaluation index under different cooling structure schemes, the influence mechanism of cooling structure changes on stress formation is analyzed. The matching optimization module is used to perform structure-cooling matching optimization calculations based on the results of comprehensive structural feature change analysis and cooling structure change analysis, and to complete multi-physics response matching optimization for low-stress design of turbine blades.

9. A computer storage medium storing a computer program, characterized in that, When the computer program is executed by a processor, it implements the method of claim 6.

10. A computer device, characterized in that, include: A memory, a processor, and a computer program stored in the memory and executable on the processor, the processor executing the program to implement the method of claim 6.

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