Multidisciplinary integrated experimental analysis methods, equipment and media for air-cooled turbine blade simulation components

Abstract

The multidisciplinary fusion test analysis method, equipment and medium for air-cooled turbine blade simulation disclosed in the present invention relate to the field of turbine blade design. The design of the present invention also covers multidisciplinary scientific integrated tests, combines finite element analysis methods with material tests, conducts multidisciplinary fusion tests and analysis methods, examines the similarities and differences of finite element analysis thermal-force field results, completes multidisciplinary "internal circulation" tests, and further provides a technical path for multidisciplinary training in the field of research and development of hot end components such as gas turbine blades, supports troubleshooting and performance evaluation, accelerates the iteration of multidisciplinary optimization design of blade structures, and improves the efficiency of advanced blade design.

Description

Technical Field

[0001] The invention relates to the field of turbine blade design, and in particular to a multidisciplinary fusion test analysis method, equipment and medium for an air-cooled turbine blade simulation part. Background Art

[0002] In traditional turbine blade design, the following process is generally followed: the overall performance department first determines the performance indicators that the blades are to achieve, and then the structural design department carries out the design. After the blades that meet the aerodynamic performance requirements are designed, they are handed over to the strength calculation department for strength verification. If they pass, the blade design comes to an end. If they fail, the design department will redesign them, and then the strength department will perform calculations. This cycle continues until the requirements are met.

[0003] It can be seen that the existing research method is to complete the work in multiple disciplines step by step, and there is no communication platform at the same level between disciplines. In the actual blade test experiment, the entire blade is often used as the experimental object, which has high test costs and long cycles, and it is difficult to achieve the optimal performance solution at the source of the design. This not only takes a long cycle, but also makes it difficult to find the optimal design shape of the blade, and it is impossible to locally optimize the locations where the blades are prone to failure, which does not meet the requirements of modern aircraft engine research and development. An experimental plan that covers the multidisciplinary propositions of heat transfer-strength-materials-manufacturing in a single test process has not yet been established, and it is impossible to carry out high-throughput turbine blade structure design and performance evaluation work.

[0004] Multidisciplinary integration is a new hot spot and growth point, but materials science is a typical experimental discipline, which is difficult to integrate with traditional design disciplines such as structural strength, heat transfer and other digital simulations. Multidisciplinary integration has key difficulties such as unclear research objects and unspecific research methods, and lacks a training model for multidisciplinary talents. Summary of the invention

[0005] In order to solve the above problems existing in the prior art, the present invention provides a multidisciplinary fusion test and analysis method, equipment and medium for an air-cooled turbine blade simulation.

[0006] To achieve the above object, the present invention provides the following solutions:

[0007] A multidisciplinary fusion test and analysis method for an air-cooled turbine blade simulation, the method comprising:

[0008] Identify the structural features and service conditions of target locations of air-cooled turbine blade specimens;

[0009] The identified structural features of the target position of the air-cooled turbine blade are used as characteristic structural units with multidisciplinary scientific attributes, and the service conditions are used as characteristic structural parameters; the multidisciplinary attributes include heat transfer, structural strength and materials science;

[0010] Constructing a three-dimensional model of the characteristic structural unit;

[0011] Taking the characteristic structure parameters as independent variables, a finite element simulation analysis of the solid-fluid-heat-force coupling behavior is performed on the three-dimensional model of the characteristic structure unit to obtain a finite element simulation analysis result; the finite element simulation analysis result includes: a temperature field calculation result and a stress-strain distribution diagram;

[0012] Based on the finite element simulation analysis results, a characteristic structural unit with the best comprehensive performance from a multidisciplinary perspective is obtained, and the characteristic structural unit is used as a typical simulation component structure;

[0013] Using single crystal directional growth technology, a typical simulation component structure is prepared into an entity, and the characteristic structural parameters are used as test parameters to conduct a simulated service damage test under set thermal field and load conditions, and the entity is subjected to material science microstructure observation to obtain material science microstructure observation results; the material science microstructure observation results include backscattered electron imaging results and scanning electron microscope imaging results;

[0014] The thermal / mechanical load conditions are obtained by analyzing the material microstructure observation results, and the thermal / mechanical load conditions are used as material theory to explain the microscopic mechanism of the failure site, examine the similarities and differences with the finite element analysis thermal-mechanical field results, and complete the multidisciplinary fusion test and analysis of the air-cooled turbine blade simulation.

[0015] Optionally, in the process of conducting a simulated service damage test under set thermal field and load conditions with the characteristic structural parameters as test parameters, performing material science microstructural observation on the entity, and obtaining material science microstructural observation results, the test environment of the entity is determined based on the service conditions, and experimental equipment for conducting the simulated service damage test is selected based on the test environment.

[0016] Optionally, the experimental equipment is used to provide a testing environment for non-steady-state heat flow and thermal field.

[0017] Optionally, the identified target position of the air-cooled turbine blade specimen includes a stress concentration point of the air-cooled turbine blade specimen.

[0018] Optionally, taking the characteristic structure parameters as independent variables, a finite element simulation analysis of the solid-fluid-thermal-mechanical coupling behavior is performed on the three-dimensional model of the characteristic structure unit to obtain a finite element simulation analysis result, which specifically includes:

[0019] The three-dimensional model of the characteristic structural unit is imported into Fluent software, the solid domain and the fluid domain are planned, the grid that meets the simulation accuracy requirements is divided, the heat transfer boundary conditions are set, and the temperature field distribution is solved by CFX software to obtain the temperature field calculation results;

[0020] The temperature field calculation results are input into the workbench software, the mechanical grid is divided, the load boundary conditions are set, the stress-strain distribution diagram is calculated, the position most likely to fail is predicted and iteratively optimized; the position most likely to fail is the position corresponding to the minimum stress-strain value.

[0021] Optionally, ansys finite element analysis software is used to construct a three-dimensional model of the characteristic structural unit.

[0022] A computer device comprises: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the steps of the multidisciplinary fusion test and analysis method for air-cooled turbine blade simulation parts as described in any one of the above items.

[0023] A computer-readable storage medium stores a computer program, which, when executed by a processor, implements the steps of the multidisciplinary fusion test and analysis method for an air-cooled turbine blade simulation component as described in any one of the above.

[0024] According to the specific embodiments provided by the present invention, the present invention discloses the following technical effects:

[0025] The design of the present invention simultaneously covers integrated tests of several scientific disciplines such as heat transfer, structural strength, and materials science. It combines finite element analysis methods with material tests, conducts multidisciplinary fusion tests and analysis methods, implements testing of integrated test units, and conducts multidisciplinary fusion research. It provides a technical path for multidisciplinary training in the research and development of hot end components such as gas turbine blades, supports troubleshooting and performance evaluation, accelerates multidisciplinary optimization design iterations of blade structures, and thereby improves the efficiency of advanced blade design. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0027] Figure 1 A flow chart of a multidisciplinary fusion test and analysis method for an air-cooled turbine blade simulation provided by an embodiment of the present invention;

[0028] Figure 2 A schematic diagram of modeling results provided by an embodiment of the present invention;

[0029] Figure 3 A schematic diagram of a first grid result provided by an embodiment of the present invention;

[0030] Figure 4 A schematic diagram of a first simulation result provided by an embodiment of the present invention;

[0031] Figure 5 A schematic diagram of a second simulation result provided by an embodiment of the present invention;

[0032] Figure 6 A schematic diagram of a second grid result provided by an embodiment of the present invention;

[0033] Figure 7 A schematic diagram of calculation results provided by an embodiment of the present invention;

[0034] Figure 8 A schematic diagram of backscattered electron imaging results provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0035] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0036] The purpose of the present invention is to provide a multidisciplinary fusion test and analysis method, equipment and medium for an air-cooled turbine blade simulation, aiming to provide a technical path for multidisciplinary training in the research and development of hot end components such as gas turbine blades, support troubleshooting and performance evaluation, accelerate the iteration of multidisciplinary optimization design of blade structures, and thereby improve the efficiency of advanced blade design.

[0037] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0038] Example 1

[0039] This embodiment provides a multidisciplinary fusion test and analysis method for air-cooled turbine blade simulation. The method design covers integrated tests of several disciplines such as heat transfer, structural strength, and materials science. It combines finite element analysis methods with material tests to carry out multidisciplinary fusion tests and analysis. Figure 1 As shown, the method includes:

[0040] Step 100: Identify the structural features and service conditions of the target location of the air-cooled turbine blade specimen.

[0041] In the test of simulating service damage of real turbine blades (referred to as blades), the local maximum temperature of the leading edge of the blade can reach 2100K, and there are obvious failure modes such as thermal stress, creep, and fatigue. Through scanning electron microscope imaging, obvious dislocation entanglement can be observed, indicating that this is a stress concentration point, so it is often the first location to be damaged. This area can be selected as a local optimization object to carry out integrated multidisciplinary experiments and analysis.

[0042] The above-mentioned local units (i.e., the areas corresponding to the local optimization objects) are simplified into characteristic structural units with multidisciplinary scientific attributes. The traditional material testing units are plate-shaped or rod-shaped specimens, which do not have the subject attributes of structural strength and heat transfer, and the obtained performance parameters cannot reflect the damage and failure of real blades with complex structures in service. Therefore, in this embodiment, it is necessary to design an integrated test unit with multidisciplinary attributes. The designed test unit includes shapes and structures such as rotation, elliptical symmetry, semi-rotating cylinder, semi-rotating hollow shell, and coupled air film holes (reflecting heat transfer), so that the material test results can better represent the performance and damage and failure behavior of the blades under service conditions.

[0043] Step 101: The identified structural features of the target position of the air-cooled turbine blade are used as characteristic structural units with multidisciplinary scientific attributes, and the service conditions are used as characteristic structural parameters. Multidisciplinary refers to several disciplines such as heat transfer, structural strength and materials science. Among them, the heat source power, compressed cold air pressure / flow, the inclination angle θ of the heat flow scouring sample surface, the double wall thickness, the aperture and distribution of the air film holes, etc. are used as characteristic structural parameters of the integrated unit.

[0044] Step 102: construct a three-dimensional model of the characteristic structural unit.

[0045] In practical application, ANSYS finite element analysis software can be used to construct a three-dimensional model of the characteristic structural unit.

[0046] Step 103: Using the characteristic structural parameters as independent variables, a finite element simulation analysis of the solid-fluid-thermal-mechanical coupling behavior of the three-dimensional model of the characteristic structural unit is performed to obtain a finite element simulation analysis result. The finite element simulation analysis result includes: temperature field calculation results and stress-strain distribution diagrams.

[0047] In actual application, the implementation process of this step can be as follows: construct a three-dimensional model of the test unit, import the Fluent software, plan the solid domain and the fluid domain, divide the grid that meets the simulation accuracy requirements, set the heat transfer boundary conditions, and use the CFX software to solve the temperature field distribution. Generate the temperature field calculation results to the workbench software, divide the mechanical grid, set the load boundary conditions, calculate the stress-strain distribution diagram, predict the most likely location for failure, and iterate and optimize. Based on the standard of achieving the best comprehensive performance from a multidisciplinary perspective, select typical simulation component structures.

[0048] Step 104: Based on the finite element simulation analysis results, a characteristic structural unit with the best comprehensive performance from a multidisciplinary perspective is obtained, and the characteristic structural unit is used as a typical simulation component structure.

[0049] Step 105: Using single crystal directional growth technology, a typical simulation component structure is prepared into an entity, and characteristic structural parameters are used as test parameters to perform a simulated service damage test under set thermal field and load conditions, and a material science microstructure observation is performed on the entity to obtain a material science microstructure observation result. The material science microstructure observation result includes backscattered electron imaging (BSE) results and scanning electron microscope imaging (SEM) results.

[0050] During the test, it is necessary to first determine the service performance of the specimen under the actual test conditions based on the service environment of the specimen, and the selected experimental equipment needs to allow for the provision of a non-steady-state heat flow and thermal field test environment. Among them, the selected test conditions should be close to the actual service environment of the blade, including non-steady-state heat transfer conditions such as cold air convection and local heating. Therefore, it is not possible to use instruments such as traditional steady-state thermal field tube furnaces, and the selected experimental equipment should allow for the provision of non-steady-state heat flow and thermal field test environments, such as high-power infrared heating, gun-type combustion, plasma heat source, compressed high-temperature gas source, etc.

[0051] Step 106: Analyze the observation results of material science microstructure to obtain thermal / mechanical load conditions, and use the thermal / mechanical load conditions as material science theory to explain the microscopic mechanism of the failure site, examine the similarities and differences with the finite element analysis thermal-mechanical field results, and complete the multidisciplinary "internal cycle" test and analysis. Among them, the thermal / mechanical load conditions include the distribution ratio of the high temperature resistant phase and other items, dislocation entanglement and accumulation, etc.

[0052] Based on the above description, the multidisciplinary fusion test and analysis method for air-cooled turbine blade simulation provided by the present invention has the properties of interdisciplinary, small-scale, integrated multidisciplinary fusion "anchor point", which can provide a technical path for multidisciplinary training in the research and development of hot end components such as gas turbine blades, and provide technical support for promoting discipline development and cultivating new interdisciplinary talents. Among them, cultivating new interdisciplinary talents includes carrying out academic training and test simulation under multidisciplinary integration.

[0053] Example 2

[0054] This embodiment describes the specific implementation process of the multidisciplinary fusion test analysis method for air-cooled turbine blade simulation provided in the above-mentioned embodiment 1 of the present invention. Specifically, the implementation process includes:

[0055] Step 1: Identify the structural characteristics and service conditions of the target position of the air-cooled turbine blade, and simplify the test specimen into characteristic structural units with multidisciplinary scientific attributes.

[0056] Step 2: Use 3D modeling software to realize 3D modeling of the characteristic structural unit under study (i.e., characteristic structural unit) and divide the solid domain and the fluid domain.

[0057] Step 3: Start the Fluent software in meshing mode, divide the mesh used to simulate and calculate the heat transfer field in the model obtained by 3D modeling, check the mesh accuracy, and save the mesh file.

[0058] Step 4: Open the CFX-Pre software in general mode, import the grid file saved in step 3, and solve after giving the boundary conditions to obtain the temperature field distribution results.

[0059] Step 5: Start the workbench platform and import the solid model and heat transfer calculation results (i.e. temperature field distribution results).

[0060] Step 6: Edit the geometry in DesignModeler and segment the edited geometry to facilitate meshing. The hexahedral mesh is used as the main mesh to divide the mesh used to calculate the stress field.

[0061] Step 7: Select the geometry to be imported, match the corresponding temperature data source, set the import as free expansion, select three nodes according to the spatial coordinate system, set their XYZ displacement to zero, XZ displacement to zero, and Y displacement to zero, and calculate the stress and strain distribution under the thermal field. The setting of this spatial coordinate system can be carried out according to actual needs, and its origin and XYZ axis are not specifically limited here.

[0062] Step 8: Select simulation parts (i.e. test specimens) with typical structures and prepare them into entities, conduct simulated service damage tests under specific thermal fields and load conditions, and conduct material microstructure observations.

[0063] Step 9: Analyze the thermal / mechanical load conditions reflected by the material microstructure based on the materials science microstructure observation results, examine the similarities and differences with the finite element analysis thermal-mechanical field results, and complete the multidisciplinary "inner loop" verification.

[0064] Based on the above description, compared with the traditional turbine blade design and test process, the present invention sets up integrated test schemes such as simulation parts and service environment for testing, completes the fusion experiment and result analysis under the multidisciplinary fusion of heat transfer-strength-material-manufacturing, and the obtained microscopic morphology of the real test piece is consistent with the simulated prediction result; a rotating cylindrical shell with a smaller scale than the real blade is found as a smaller test unit, with lower experimental cost and short iteration cycle; by designing simulation parts with different structural characteristics and heat transfer conditions, a high-throughput local structure optimization and performance evaluation process is achieved; and a multidisciplinary talent training model with turbine blades as the object can be provided. It can be seen that the present invention achieves the interdisciplinary, small-scale, integrated multidisciplinary fusion "anchor" effect through a single test.

[0065] Example 3

[0066] This embodiment uses a group of single crystal alloy DD406 hollow rectangular tubes as samples to illustrate the implementation process of the multidisciplinary fusion test and analysis method for air-cooled turbine blade simulation parts provided in the above embodiment 1 of the present invention. Specifically:

[0067] Step 1: Identify the structural characteristics and service conditions of the target position of the air-cooled turbine blades, and simplify the test specimens into characteristic structural units with multidisciplinary scientific attributes.

[0068] A set of single crystal alloy DD406 hollow rectangular tubes were designed, with outer dimensions of 6X4mm, wall thickness of 1mm, regular air film holes with a diameter of 0.3mm, vertical holes, room temperature compressed air entering the hollow and one side closed, cold air flows out from the air film holes, inlet pressure of 17bar, temperature of 1300K, cooling pressure of 1.76Mpa, cooling temperature of 25℃, no uniaxial tensile load applied. The heat source is one-side gas flushing, the sample is placed in a parallel thermal field with an inclination angle θ of 30° to the gas direction, and the maximum temperature load on the outer surface of the sample is 1100℃.

[0069] Step 2: Use 3D modeling software to realize 3D modeling of the characteristic structural unit under study (i.e., a group of single crystal alloy DD406 hollow rectangular tubes) and divide the solid domain and the fluid domain.

[0070] Among them, solid domain modeling: according to the size of the physical model, a solid 1:1 model is established, which is the solid domain.

[0071] Fluid domain modeling: Based on the solid domain, a fluid domain is established. The fluid domain is the area where the "fluid" part passes in the finite element simulation. Generally, the fluid domain should be larger than the solid domain, and the shape should be planned in advance according to the actual situation of the actual experiment, including gas inlet, gas outlet, fluid-solid interface, and adiabatic wall. The modeling results are as follows: Figure 2 shown.

[0072] Step 3: Start Fluent software in meshing mode, divide the mesh used to simulate and calculate the heat transfer field, check the mesh accuracy, and save the mesh file. For example, start Fluent and choose to start in meshing mode; import the solid / fluid model into Fluent, divide the surface mesh when importing, check "CFD surface mesh", and when dividing the mesh, the empirical size is the minimum size of the mesh, which is 1 / 5 of the minimum size of the model; check the mesh quality, if skewed-faces (>0.85) is 0, the mesh quality is qualified; if the mesh quality is not up to standard, check the unqualified mesh, and repeatedly click "Smooth All" and "Collapse All" until the mesh is qualified; save the drawn mesh file, the mesh result is as follows: Figure 3 shown.

[0073] Step 4. Open the CFX-Pre software in general mode, import the mesh file in step 4, solve the model after given boundary conditions, and obtain the temperature field distribution results. For example, open CFX-Pre in general mode; right-click "Mesh"-"Import Mesh"-"FLUENT", import the drawn mesh file; select "Domain", select the domain type as solid / fluid respectively, define the solid domain and fluid domain, set the solid domain material, fluid domain parameters, fluid domain / solid domain / fluid-solid interface boundary conditions, etc. according to the parameters in step 1; select "Solver Control", change the residual to 0.0000001, and it is considered converged when the residual is less than this number; click the "SM" icon on the toolbar to generate and save the solver, click "start run" to start solving, and after the solution is completed, the solution result file is automatically generated and saved to the same folder as the solver. The simulation results are as follows: Figure 4 and Figure 5 As shown. Among them, Figure 4 The English meaning of the upper left corner is the temperature cloud map. Figure 5 The English meaning of the upper left corner is flow rate line.

[0074] Step 5: Start the workbench platform and import the solid model and heat transfer calculation results. For example, start the workbench platform, create a new CFX module and a static structure module, right-click CFX\Solve, select Import Solution, select CFX result file, right-click CFX\Result after successful import, select Update, and complete the result import.

[0075] Step 6: Edit the geometry in Design Modeler to get the geometry, split the geometry to facilitate meshing, and use hexahedral meshes as the main mesh to divide the mesh used to calculate the stress field. For example: select Edit the geometry in Design Modeler, split the geometry to facilitate meshing; click Create in the upper toolbar, select New Plane, select Base Plane and Offset Distance, and click Generate; select Slice in the upper toolbar, select Cut by Plane for Cutting Type, and repeat the above steps based on the newly created plane until the cutting is completed.

[0076] Meshing: Double-click the static structure\model to open the Mechanical interface, right-click the mesh option in the left toolbar, select the insertion method and size adjustment, click the method, select all geometric bodies, and select the hexahedron dominant; select the edges that may have stress concentration, adjust the geometric size according to the part size, and generate the mesh. The mesh result is as follows Figure 6 shown.

[0077] Step 7. Select the geometry to be imported, match the corresponding temperature data source, set the import as free expansion, select three nodes according to the coordinate system, set their XYZ displacement to zero, XZ displacement to zero, and Y displacement to zero, and calculate the stress and strain distribution under the thermal field. The calculation results are as follows: Figure 7 shown.

[0078] Step 8: Screen and prepare simulation parts with typical structures, conduct simulated service damage tests under specific thermal fields and load conditions, observe the material microstructure, and obtain backscattered electron imaging (BSE) results. Figure 8 shown.

[0079] Step nine: Analyze the thermal / mechanical load conditions reflected by the material microstructure and examine the similarities and differences with the thermal-mechanical field results of finite element analysis. Figure 8 The dark-colored part is the high-temperature resistant phase. It can be observed that under 1300°C conditions, the proportion of the high-temperature resistant phase decreases, indicating that the structural strength performance of the structure here degrades under high temperature, which is consistent with the location of the maximum thermal stress obtained by simulation. The thermal-mechanical coupling results obtained from the actual test and the simulation results confirm each other, completing the multidisciplinary "internal cycle" verification.

[0080] Example 4

[0081] A computer device includes: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the steps of the multidisciplinary fusion test and analysis method for air-cooled turbine blade simulation parts in Example 1.

[0082] Example 5

[0083] A computer-readable storage medium stores a computer program, which, when executed by a processor, implements the steps of the multidisciplinary fusion test and analysis method for an air-cooled turbine blade simulation component in Example 1.

[0084] Example 6

[0085] A computer device, which may be a database. The computer device includes a processor, a memory, an input / output interface (Input / Output, referred to as I / O) and a communication interface. The processor, the memory and the input / output interface are connected via a system bus, and the communication interface is connected to the system bus via the input / output interface. The processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program and a database. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The database of the computer device is used to store pending transactions. The input / output interface of the computer device is used to exchange information between the processor and an external device. The communication interface of the computer device is used to communicate with an external terminal via a network connection. When the computer program is executed by the processor, the multidisciplinary fusion test analysis method of the air-cooled turbine blade simulation component in Example 1 is implemented.

[0086] It should be noted that the object information (including but not limited to object device information, object personal information, etc.) and data (including but not limited to data used for analysis, stored data, displayed data, etc.) involved in the present invention are all information and data authorized by the object or fully authorized by all parties, and the collection, use and processing of relevant data need to comply with relevant laws, regulations and standards of relevant countries and regions.

[0087] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiments can be completed by instructing the relevant hardware through a computer program, and the computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to the memory, database or other medium used in the embodiments provided by the present invention can include at least one of non-volatile and volatile memory. Non-volatile memory can include read-only memory (ROM), magnetic tape, floppy disk, flash memory, optical memory, high-density embedded non-volatile memory, resistive random access memory (ReRAM), magnetoresistive random access memory (MRAM), ferroelectric random access memory (FRAM), phase change memory (PCM), graphene memory, etc. Volatile memory can include random access memory (RAM) or external cache memory, etc. As an illustration and not limitation, RAM can be in various forms, such as static random access memory (SRAM) or dynamic random access memory (DRAM). The database involved in each embodiment provided by the present invention may include at least one of a relational database and a non-relational database. Non-relational databases may include distributed databases based on blockchains, etc., but are not limited thereto. The processor involved in each embodiment provided by the present invention may be a general-purpose processor, a central processing unit, a graphics processor, a digital signal processor, a programmable logic device, a data processing logic device based on quantum computing, etc., but are not limited thereto.

[0088] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, 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.

[0089] The principles and implementation methods of the present invention are described in this article using specific examples. The description of the above embodiments is only used to help understand the method and core ideas of the present invention. The same and similar parts between the embodiments can be referred to each other. At the same time, for those skilled in the art, according to the ideas of the present invention, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as limiting the present invention.

Claims

1. A multidisciplinary fusion test and analysis method for air-cooled turbine blade simulation, characterized in that: The method comprises: Identify the structural features and service conditions of target locations of air-cooled turbine blade specimens; The identified structural features of the target position of the air-cooled turbine blade are used as characteristic structural units with multidisciplinary scientific attributes, and the service conditions are used as characteristic structural parameters; the multidisciplinary attributes include heat transfer, structural strength and materials science; Constructing a three-dimensional model of the characteristic structural unit; Taking the characteristic structure parameters as independent variables, a finite element simulation analysis of the solid-fluid-heat-force coupling behavior is performed on the three-dimensional model of the characteristic structure unit to obtain a finite element simulation analysis result; the finite element simulation analysis result includes: a temperature field calculation result and a stress-strain distribution diagram; Based on the finite element simulation analysis results, a characteristic structural unit with the best comprehensive performance from a multidisciplinary perspective is obtained, and the characteristic structural unit is used as a typical simulation component structure; Using single crystal directional growth technology, a typical simulation component structure is prepared into an entity, and the characteristic structural parameters are used as test parameters to conduct a simulated service damage test under set thermal field and load conditions, and the entity is subjected to material science microstructure observation to obtain material science microstructure observation results; the material science microstructure observation results include backscattered electron imaging results and scanning electron microscope imaging results; Analyze the material microstructure observation results to obtain thermal / mechanical load conditions, and use the thermal / mechanical load conditions as material theory to explain the microscopic mechanism of the failure site, examine the similarities and differences with the finite element analysis thermal-mechanical field results, and complete the multidisciplinary fusion test and analysis of the air-cooled turbine blade simulation parts; Among them, taking the characteristic structure parameters as independent variables, a finite element simulation analysis of the solid-fluid-thermal-mechanical coupling behavior is performed on the three-dimensional model of the characteristic structure unit to obtain a finite element simulation analysis result, which specifically includes: The three-dimensional model of the characteristic structural unit is imported into Fluent software, the solid domain and the fluid domain are planned, the grid that meets the simulation accuracy requirements is divided, the heat transfer boundary conditions are set, and the temperature field distribution is solved by CFX software to obtain the temperature field calculation results; The temperature field calculation results are input into the workbench software, the mechanical grid is divided, the load boundary conditions are set, the stress-strain distribution diagram is calculated, the position most likely to fail is predicted and iteratively optimized; the position most likely to fail is the position corresponding to the minimum stress-strain value.

2. The multidisciplinary fusion test and analysis method for air-cooled turbine blade simulation according to claim 1 is characterized in that: In the process of conducting a simulated service damage test under set thermal field and load conditions with the characteristic structural parameters as test parameters, performing material science microstructural observation on the entity, and obtaining material science microstructural observation results, the test environment of the entity is determined based on the service conditions, and experimental equipment for conducting the simulated service damage test is selected based on the test environment.

3. The multidisciplinary fusion test and analysis method for air-cooled turbine blade simulation according to claim 2 is characterized in that: The experimental equipment is used to provide a testing environment for non-steady-state heat flow and thermal field.

4. The multidisciplinary fusion test and analysis method for air-cooled turbine blade simulation according to claim 1 is characterized in that: The identified target position of the air-cooled turbine blade specimen includes a stress concentration point of the air-cooled turbine blade specimen.

5. The multidisciplinary fusion test and analysis method for air-cooled turbine blade simulation according to claim 1 is characterized in that: The three-dimensional model of the characteristic structural unit is constructed using ANSYS finite element analysis software.

6. A computer device comprising: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the steps of the multidisciplinary fusion test and analysis method for air-cooled turbine blade simulation parts as described in any one of claims 1 to 5.

7. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the multidisciplinary fusion test and analysis method for air-cooled turbine blade simulation parts described in any one of claims 1 to 5 are implemented.

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