Turbine cooling blade integrated design and analysis platform

Abstract

The invention relates to a turbine cooling blade integrated design and analysis platform, an external heat exchange module, an external heat exchange correction module, an internal heat exchange module and a temperature field module are deployed at a server side, the external heat exchange module is used for calculating a gas heat exchange coefficient and a gas recovery temperature by using an external heat exchange solver according to original data of a turbine cooling blade, and the internal heat exchange module is used for calculating a gas recovery temperature by using an internal heat exchange solver according to the original data of the turbine cooling blade; obtaining external heat exchange boundary conditions; the outer heat exchange correction module is used for combining the outer heat exchange boundary conditions and the air film hole parameters, and solving air film parameter information by utilizing an air film cooling program solver to obtain outer wall surface heat exchange boundary conditions; the inner heat exchange module is used for constructing a network topological graph of cold air flowing in the blade and calculating the pressure, temperature and heat exchange coefficient of each element in the network topological graph to obtain a temperature field boundary condition; and the temperature field module is used for calculating the temperature distribution of the turbine cooling blade by utilizing a temperature field solver. According to the embodiment, the design efficiency of the turbine cooling blade is improved, the design quality is improved, and meanwhile the design cost is reduced.

Description

Technical Field

[0001] The invention belongs to the field of aeroengines, and in particular relates to an integrated design and analysis platform for turbine cooling blades. Background Art

[0002] In high-tech fields such as aerospace, energy and power, turbines are core power devices, and their performance directly determines the efficiency and reliability of the entire system. Turbine cooling blades, as key components in turbines, are subjected to high temperatures, high pressures and complex stress environments, and their design quality is crucial to the overall performance of the turbine.

[0003] The design of aircraft engine turbine cooling blades is a very complex multi-physics coupling problem involving many disciplines. During the analysis and design process, it usually requires the collaborative work of personnel from multiple departments, involving numerous computing software and codes, complex and diverse data transmission modes, etc. In addition, the design process of turbine cooling blades often involves multiple independent software tools, including CAD modeling, CFD simulation, thermal analysis, structural optimization, etc. The data exchange between these tools is complex, the design cycle is long, and it is difficult to achieve global optimization design.

[0004] In past design practices, due to the lack of unified processing standards, the analysis methods were quite arbitrary, involving a lot of manual processing, and the process was cumbersome and inefficient, making it difficult to design turbine cooling blades efficiently. Summary of the invention

[0005] In order to solve the above problems existing in the prior art, the present invention provides an integrated design and analysis platform for turbine cooling blades. The technical problem to be solved by the present invention is achieved through the following technical solutions:

[0006] The embodiment of the present invention provides an integrated design and analysis platform for turbine cooling blades, including: a server end and a browser end, wherein the server end is equipped with an external heat exchange module, an external heat exchange correction module, an internal heat exchange module and a temperature field module, and the browser end provides an operation access interface for the external heat exchange module, the external heat exchange correction module, the internal heat exchange module and the temperature field module, wherein:

[0007] The external heat exchange module is used to calculate the gas heat transfer coefficient and the gas recovery temperature by numerically solving the viscosity differential equation in the profile using the external heat exchange solver according to the S1 flow surface data, S2 flow surface data of the turbine cooling blade and the performance parameters of all sections of the blade, and obtain the external heat exchange boundary conditions;

[0008] The external heat exchange correction module is used to combine the external heat exchange boundary conditions and the air film hole parameters, and use the air film cooling program solver to solve the air film parameter information to obtain the external wall heat exchange boundary conditions;

[0009] The internal heat exchange module is used to construct a network topology diagram of the flow of cold air inside the blade using elements, nodes inside the elements and boundary points of the elements, calculate the pressure, temperature and heat transfer coefficient of each element in the network topology diagram according to the flow balance and energy balance to obtain the temperature field boundary conditions, and add the pressure, temperature and heat transfer coefficient to the element parameters to form a complete element library;

[0010] The temperature field module is used to calculate the temperature distribution of the turbine cooling blades using a temperature field solver according to the external heat exchange boundary conditions, the external wall heat exchange boundary conditions, the temperature field boundary conditions and the network topology diagram.

[0011] In one embodiment of the present invention, the external heat exchange module comprises:

[0012] A first data receiving module is used to receive the S1 flow surface data, S2 flow surface data and performance parameters of all sections of the turbine cooling blade according to user instructions, and obtain the original data of several sections in the three-dimensional model of the turbine cooling blade;

[0013] A parameter modification module, used to modify the target parameters in the original data under different first working conditions according to user instructions to obtain modified data;

[0014] The external heat exchange solving module is used to calculate the gas heat transfer coefficient and the gas recovery temperature by numerically solving the viscosity differential equation in the surface according to user instructions and based on the modified data, convert the gas heat transfer coefficient and the gas recovery temperature into a two-dimensional thermal boundary condition, and use a three-dimensional thermal boundary reconstruction technology to output the three-dimensional thermal boundary condition of the outer surface of the cooling blade to obtain the external heat exchange boundary condition.

[0015] In one embodiment of the present invention, when the first operating condition is a cooling efficiency test condition, modifying the target parameter in the original data includes:

[0016] Modify the total temperature of the incoming gas flow, the total pressure of the incoming gas flow and the outlet static pressure parameters, the pressure surface data and the suction surface data of different cross sections in the S1 flow surface data.

[0017] In one embodiment of the present invention, the external heat exchange correction module comprises:

[0018] A second data receiving module, used for receiving the external heat exchange boundary condition according to a user instruction;

[0019] A mode selection module, configured to select a target computing mode from a computing mode list and select a target correction mode from a correction mode list under the target computing mode according to a user instruction;

[0020] The working condition parameter setting module is used to set different custom variables and the value of each custom variable according to user instructions to form a plurality of second working conditions;

[0021] An air film hole adding module, used for adding air film holes on a plurality of cross sections in the cross section model according to a user instruction and based on the target correction mode;

[0022] A parameter setting module, used to set the cross-sectional parameters and film hole parameters of the turbine cooling blade according to user instructions;

[0023] The external heat exchange correction solution module is used to solve the air film parameters using the air film cooling program solver according to the user's instructions and under different second working conditions according to the external heat exchange boundary conditions, the cross-sectional parameters and the air film hole parameters to obtain the outer wall heat exchange boundary conditions.

[0024] In one embodiment of the present invention, the calculation modes in the calculation mode list include: default correction mode, mixing model, air film superposition, blades near broken walls, front wake cooling efficiency, front wake heat transfer coefficient and thermal barrier coating;

[0025] In each calculation mode, the correction modes in the correction mode list include: film hole correction, OTDF correction and temperature margin correction;

[0026] The cross-sectional parameters include any one of the total temperature of the incoming gas flow, the total pressure of the incoming gas flow, the Mach number of the incoming gas flow, and the adiabatic index;

[0027] The air film parameters include the relative position of the air film holes from the leading edge stagnation point, hole type control parameters, air film hole diameter, lateral spacing of air film holes, number of lateral air film holes in the hole row, cold air flow rate of the air film holes, cold air temperature, hole inclination angle, hole yaw angle, ratio of hole outlet area to cylindrical section area, hole length and length of the cylindrical section of the hole.

[0028] In one embodiment of the present invention, a grid partitioning module is further deployed on the server side, wherein the grid partitioning module is used to discretize the calculation area into a number of grid units.

[0029] In one embodiment of the present invention, the internal heat exchange module comprises:

[0030] A third data receiving module, used for receiving the outer wall heat exchange boundary condition according to a user instruction;

[0031] An internal flow network building module is used to connect several components according to the number of nodes and boundary points within the components according to user instructions, and set the input parameters of each component, or import an already created internal flow network including all input parameters to obtain a network topology diagram of the cooling air flow inside the blade;

[0032] An internal flow coupling creation module, used for mapping the plurality of elements and the plurality of grid cells one by one according to a user instruction to obtain an internal flow coupling mapping relationship;

[0033] An air film hole coupling creation module is used to map the plurality of elements and the plurality of air film holes one by one according to a user instruction to obtain an air film hole coupling mapping relationship;

[0034] The internal heat exchange solution module is used to calculate the pressure, temperature and heat transfer coefficient of each element of the network topology diagram according to user instructions, based on the internal flow coupling mapping relationship and the air film hole coupling mapping relationship, according to flow balance and energy balance, and obtain the temperature field boundary conditions.

[0035] In one embodiment of the present invention, the server side is also deployed with a material library, wherein the material library is used to provide material data required for the design process.

[0036] In one embodiment of the present invention, the temperature field module comprises:

[0037] a fourth data receiving module, configured to receive the external heat exchange boundary condition, the external wall heat exchange boundary condition, the temperature field boundary condition and the network topology diagram according to a user instruction, so as to form a turbine cooling blade geometric model;

[0038] A material selection module, for selecting a material for the turbine cooling blade geometric model in the material library according to a user instruction;

[0039] A convection adding module, used for adding boundary conditions to the model surface of the turbine cooling blade geometric model by setting parameters according to user instructions; the boundary includes any one of convection, temperature, heat flow, surface radiation, and environmental radiation;

[0040] The temperature field solving module is used to calculate the temperature distribution of the turbine cooling blade using the temperature field calculation module solver according to user instructions, based on the turbine cooling blade geometric model, the material of the turbine cooling blade geometric model and the boundary conditions.

[0041] In one embodiment of the present invention, the server side is also deployed with a post-processing module, wherein the post-processing module is used to visualize and analyze any simulation result of the external heat exchange boundary condition, the external wall heat exchange boundary condition, the temperature field boundary condition, and the blade temperature field, and present the simulation result in the form of a three-dimensional image; the visualization processing and analysis includes one or more of cloud map display, vector control, streamline control, and profile control.

[0042] Compared with the prior art, the present invention has the following beneficial effects:

[0043] The integrated design and analysis platform for turbine cooling blades of the present invention deploys an external heat exchange module, an external heat exchange correction module, an internal heat exchange module and a temperature field module, and the modules are connected accordingly, thereby realizing data transmission links between different calculation methods of each module. It can perform coupled thermal analysis on the internal and external flows of the turbine cooling blades, thereby realizing a full-chain automated design process for the turbine cooling blades from preliminary design to final optimization, providing accurate thermal analysis capabilities, multi-physical field coupling capabilities, and efficient calculation algorithms, thereby improving the design efficiency of turbine cooling blades, reducing human errors, improving design quality, and reducing design costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] Figure 1 A schematic diagram of the structure of a turbine cooling blade integrated design and analysis platform provided by an embodiment of the present invention;

[0045] Figure 2 A deployment diagram of a turbine cooling blade integrated design and analysis platform provided by an embodiment of the present invention;

[0046] Figure 3 A flow chart of a turbine cooling blade design provided by an embodiment of the present invention;

[0047] Figure 4 A cross-sectional schematic diagram of an external heat exchange module provided in an embodiment of the present invention;

[0048] Figure 5 A cross-sectional schematic diagram of an external heat exchange correction module provided in an embodiment of the present invention;

[0049] Figure 6 A schematic diagram of operating condition parameter settings provided by an embodiment of the present invention;

[0050] Figure 7 A schematic diagram of adding air film holes provided in an embodiment of the present invention;

[0051] Figure 8 A schematic diagram of air film hole parameter settings provided in an embodiment of the present invention;

[0052] Fig. 9 A partial schematic diagram of a network topology diagram provided by an embodiment of the present invention;

[0053] Fig.10 A schematic diagram of a geometric model provided by an embodiment of the present invention;

[0054] Figure 11a-Figure 11b A schematic diagram showing the temperature field distribution of a turbine cooling blade provided in an embodiment of the present invention. DETAILED DESCRIPTION

[0055] The present invention is further described in detail below with reference to specific embodiments, but the embodiments of the present invention are not limited thereto.

[0056] Embodiment 1

[0057] See also Figure 1 , Figure 1 A schematic diagram of the structure of a turbine cooling blade integrated design and analysis platform provided in an embodiment of the present invention. The turbine cooling blade integrated design and analysis platform adopts a B / S architecture mode, is implemented based on the "cloud + distributed" SOA architecture system, and uses real-time collaborative technology based on CAP theory and Stomp technology to build a new generation of distributed cloud-based computer-aided engineering (CAE) platform to achieve cross-regional, cross-platform, and cross-time multi-person and multi-team collaborative simulation design and analysis.

[0058] The platform specifically includes: a server side and a browser side. The server side is deployed with an external heat exchange module, an external heat exchange correction module, an internal heat exchange module and a temperature field module, and the browser side is used to provide an operation access interface for the external heat exchange module, the external heat exchange correction module, the internal heat exchange module and the temperature field module.

[0059] Specifically, the platform needs to uniformly install, publish and centrally manage all application software on the server side. The terminal client can access it through the browser. Each module can be deployed on different servers and adapted to different operating systems to make effective use of resources and reduce maintenance and management costs. Some component operations of the same project can be updated collaboratively, and the various modules of the entire project can be carried out simultaneously and collaboratively developed to save developers' time.

[0060] An external heat exchange module, an external heat exchange correction module, an internal heat exchange module and a temperature field module are deployed on the server side, and an operation access interface of the external heat exchange module, the external heat exchange correction module, the internal heat exchange module and the temperature field module is provided on the browser side.

[0061] The external heat exchange module is used to calculate the gas heat transfer coefficient and gas recovery temperature by numerically solving the viscosity differential equation in the profile according to the S1 flow surface data, S2 flow surface data and performance parameters of all sections of the turbine cooling blades, and obtain the external heat exchange boundary conditions. Among them, the calculation process using the external heat exchange solver needs to consider the airflow turbulence in the S1 flow surface data, the distribution characteristics of the Mach number along the S1 section, and the influence of the local curvature of the blade surface on the heat exchange.

[0062] Specifically, the main function of the external heat exchange module is to perform external gas flow and heat exchange calculations on the blades. The S1 flow surface data, S2 flow surface data and performance parameters of all sections of the blades are provided by the turbine aerodynamic calculations.

[0063] The S1 stream surface data stores different blade cross-section data under different working conditions. There is no limit on the number of cross-sections. If the temperature field composite material is generated later, the number of cross-sections is three. Each blade cross-section data includes several groups of data, each group of data forms a row, including X coordinate, Y coordinate, Z coordinate, relative arc length, Mach number, gamma number, pressure, and temperature; among them, the data row with Mach number tending to 0 is regarded as the leading edge, and the data row with relative arc length starting from 1 is regarded as the trailing edge. In addition, the group with fewer data after the leading edge and the trailing edge are divided as the pressure PS surface, and the group with more data is regarded as the suction SS surface.

[0064] The working conditions of S2 flow surface data are the same as those of S1 flow surface data. S2 flow surface data mainly describes parameters such as inlet and outlet total temperature and total pressure, including inlet section height, inlet static pressure, inlet total pressure, inlet total temperature, inlet static temperature, average value of various inlet parameters, and outlet section height, outlet static pressure, outlet total pressure, outlet total temperature, and outlet static temperature.

[0065] The performance parameters of all sections of the blade include the number of blades in a circle, the total number of sections, the number of suction surface coordinate points and pressure surface coordinate points of each section, the X and Y coordinates of each point on the suction surface, the X and Y coordinates of each point on the pressure surface, the XY coordinates of the leading edge center point, the XY coordinates of the trailing edge center point, the leading edge diameter, the trailing edge diameter, the aerodynamic translation distance and the section radius.

[0066] The external heat exchange solver includes NPUSATAN7.exe, which is an existing program. It calculates the gas heat transfer coefficient and gas recovery temperature by numerically solving the viscosity differential equation in the profile, and considers the distribution characteristics of the airflow turbulence and Mach number along the S1 section in the S1 flow surface data and the influence of the local curvature of the blade surface on the heat transfer. Furthermore, the external heat exchange module converts the format of the gas heat transfer coefficient and the gas recovery temperature, converts the calculation results into a file in a unified format that the platform can recognize, and forms the corresponding two-dimensional thermal boundary conditions; then, the three-dimensional thermal boundary reconstruction technology is used to reconstruct the two-dimensional thermal boundary conditions, and the collected temperature values ​​are associated with the corresponding positions on the three-dimensional geometric model to generate an intuitive three-dimensional temperature distribution view. The obtained three-dimensional thermal boundary condition data of the outer surface of the turbine cooling blade is used as the external heat exchange boundary condition, and the command stream file is automatically loaded for the output boundary condition of the three-dimensional blade structure thermal analysis software. The external heat exchange solution module can also compare and analyze the calculation results of S1 flow surface data and S2 flow surface data under different working conditions, and display the results in various modes such as comb charts, line charts, cloud charts, tables, etc., to achieve formatted output of processing results.

[0067] The external heat exchange correction module is connected to the external heat exchange module, and is used to combine the external heat exchange boundary conditions and the air film hole parameters, and use the air film cooling program solver to solve the air film parameter information to obtain the external wall heat exchange boundary conditions.

[0068] Specifically, the data of the external heat exchange correction module comes from the calculation results of the external heat exchange module. The external heat exchange correction module obtains the corresponding blade shape (coordinates of each point of each section), heat transfer coefficient, temperature and Mach number from the external heat exchange boundary conditions as the input parameter file of the film cooling program, and converts these parameter files into a format file that can be read by the film cooling program. The film cooling program uses the existing FILMCG.exe. The film-related parameters can be modified in the FILMCG.exe interface; after running, FILMCG.exe outputs the film parameter information, and the film parameters include film temperature, film heat transfer coefficient, film efficiency, film pressure, etc.; according to the FILMCG.exe output format, the interface program can read the results, parse the result file, obtain the corresponding data and generate relevant graphs and tables.

[0069] Furthermore, after obtaining the air film parameter information, the air model correction module further converts the obtained air film parameter information into a format, converts the calculation results into a file in a unified format that can be recognized by the platform, and obtains the corresponding two-dimensional thermal boundary conditions. The air film correction method is used to correct the two-dimensional thermal boundary conditions to correct the air film hole parameter information and geometric information; the air film correction method can adopt the correction method in the prior art, such as the curve-based parameterized air film correction method. Then, the three-dimensional thermal boundary reconstruction technology is used to reconstruct the two-dimensional thermal boundary conditions, and the collected temperature values ​​are associated with the corresponding positions on the three-dimensional geometric model to generate an intuitive three-dimensional temperature distribution view. The obtained three-dimensional thermal boundary condition data of the outer surface of the turbine cooling blade is used as the outer wall heat exchange boundary condition, and the command stream file is automatically loaded for the output boundary condition of the three-dimensional blade structure thermal analysis software. The air model correction module can also change the air film hole parameters to realize dynamic real-time refresh of the calculation, and observe the influence of the air film hole on the blade in real time, which is accurate and controllable. Furthermore, the gas model correction module can compare and analyze the calculation results of S1 flow surface data and S2 flow surface data under different working conditions, and display the results in various modes such as comb charts, line charts, cloud charts, tables, etc., to achieve formatted output of processing results.

[0070] The internal heat exchange module is connected to the external heat exchange module and the external heat exchange correction module, and is used to construct a network topology diagram of the cold air flow inside the blade using components, nodes inside the components and boundary points of the components. The pressure, temperature and heat transfer coefficient of the cold air flow inside the network topology diagram are calculated according to the flow balance and energy balance to obtain the temperature field boundary conditions, and the pressure, temperature and heat transfer coefficient are added to the component parameters to form a complete component library.

[0071] Specifically, the internal heat exchange module obtains a one-dimensional parameterized model of the cooling scheme by determining the internal cooling structure form, cooling structure parameters, etc. according to the design indicators. Specifically, the internal heat exchange module abstracts the airflow inside the blade into a network diagram consisting of elements, nodes inside the element, and element boundary nodes, constructs a network topology diagram of the cold air flow inside the blade, and generates a data file for the internal flow and heat exchange calculation module solver. Among them, the nodes inside the element and the boundary points of the element are determined according to the airflow inlet and outlet of the element, and each element is connected according to the nodes inside the element and the boundary points of the element. Among them, the nodes inside the element are located inside each unit in the finite element grid and do not directly contact the external boundary of the model. Through these internal nodes, the changes inside the unit can be captured more accurately. The boundary points of the element are located on the boundary of the finite element grid and are in direct contact with the external environment of the model. Boundary nodes can be used to set temperature boundary conditions or convective heat transfer coefficients; internal nodes are used to calculate the temperature field inside the material.

[0072] The main function of the internal heat exchange module is to calculate the flow and heat exchange of the internal cooling airflow for the one-dimensional model composed of the network topology diagram. According to the fluid network algorithm theory, the internal flow of the blade is regarded as a network composed of components with different flow and heat transfer characteristics. The internal heat exchange solver is used, and the LGSAS air system is used as the main carrier to obtain the pressure, temperature, heat transfer coefficient and other parameters of the internal cooling air flow according to the flow balance and energy balance. Among them, the internal heat exchange solver can use the existing LGSAS.exe. The calculation models of this program include: Flowmaster, FLOWENX, Flow Simulator, Amesim and other secondary air system component calculation models used for fluid system solving. The internal heat exchange solver can also use Python programs, other existing solvers or solvers developed by users themselves.

[0073] Furthermore, the internal heat exchange module can add the calculated parameters such as pressure, temperature, heat transfer coefficient, etc. to the elements related to blade cooling in the network topology diagram to form a complete component library, thereby improving the calculation accuracy, optimizing the program algorithm, improving the convergence of the calculation, and forming a visual post-processing platform to facilitate the comparison of multiple schemes in the one-dimensional design stage.

[0074] In addition, the internal heat exchange module supports multi-person collaborative work mode, which can display the components and parameter changes on the canvas in real time; supports multiple projects online, supports intelligent storage and protection of projects, and achieves the functions of real-time storage and power off and network protection; supports multi-mode solver calculation, switching to cloud maps, charts and animation modes, displays post-processing data, and realizes formatted output of processing results.

[0075] The temperature field module is connected with the external heat exchange module, the external heat exchange correction module and the internal heat exchange module, and is used to calculate the blade temperature distribution using the temperature field calculation module solver according to the external heat exchange boundary conditions, the external wall heat exchange boundary conditions, the temperature field boundary conditions and the network topology diagram.

[0076] Specifically, the blade surface temperature field can be obtained through the external heat exchange boundary conditions of the external heat exchange module and the outer wall heat exchange boundary conditions of the external heat exchange correction module. The temperature field boundary conditions are obtained through the internal heat exchange module. The blade surface temperature field and the temperature field boundary conditions are input into the temperature field solver to calculate the temperature field of the turbine cooling blade. The temperature field calculation results can be opened using the post-processing module to analyze the final cloud map results. The temperature field solver can be Ansys, or it can be switched to a user-developed solver. For example, the temperature field solver supports Ansys Mechanical APDL, Fluent, or the open source finite element structural solver Calculix.

[0077] Furthermore, the temperature field module supports multi-state calculations, wherein the multi-states are realized by changing the values ​​of airflow parameters.

[0078] In a specific embodiment, the server side is also deployed with the following auxiliary modules: main platform, material library, parametric modeling module, meshing module, formula library, post-processing module, intensity field module, curve and surface library, optimization design module and fluid-solid coupling module. Correspondingly, the browser side is deployed with the operation access interface of these modules, such as Figure 2 As shown, Figure 2 A deployment diagram of a turbine cooling blade integrated design and analysis platform provided in an embodiment of the present invention.

[0079] Specifically, the main platform is mainly used for the management of platform users and their permissions, user project task management, module solver management, project task template management, project task team management and system operation monitoring.

[0080] The material library is the starting point of the blade design analysis process. Its main function is to provide the material data required for the temperature field during the design process. Its functions mainly include: providing commonly used material data, supporting user-defined materials, and transferring selected materials to the required modules.

[0081] The parametric modeling module is used to provide data for grid division, and mainly realizes the following functions: clearly define and describe various variables and parameters in the problem so that the model can adapt to different situations and conditions, and analyze and solve different problems by setting different parameter values, thereby improving the adaptability and universality of the model; through parametric modeling, the complexity in the problem is simplified and abstracted, and converted into a mathematical model. By setting different parameter values, different situations and conditions can be analyzed and solved, thereby simplifying the complexity of the model; through parametric modeling, the model can be continuously optimized and improved. By setting different parameter values, the model can be subjected to sensitivity analysis and parameter optimization, thereby improving the performance and effect of the model; through parametric modeling, the problem can be converted into a mathematical model, and then analyzed and solved using mathematical methods. By setting different parameter values, the model can be analyzed and solved, thereby improving the efficiency and effect of problem solving.

[0082] The meshing module is used to discretize the calculation area into several mesh units. This process can divide the calculation area into smaller geometric units and provide a three-dimensional mesh model for the temperature field to facilitate flow field calculation and heat transfer analysis. This embodiment divides the mesh units in a structural network manner. The structural network includes unit types such as triangles, quadrilaterals, tetrahedrons, and hexahedrons. Meshing directly affects the accuracy and efficiency of the calculation results. It is the basis for flow field calculations and heat transfer analysis, and provides a mesh model for subsequent three-dimensional modules. It is crucial for optimizing the design and improving the cooling effect of the turbine. The mesh .msh file generated by meshing in this embodiment can be used for three-dimensional modules such as internal heat exchange, temperature field, and intensity field.

[0083] The formula library is used to provide the mathematical formulas required for the turbine blade design process. It is used to describe and calculate physical phenomena and engineering problems in different fields. It brings together various mathematical formulas and users can add custom formulas.

[0084] The post-processing module is used to visualize and analyze the simulation results of the external heat exchange module, external heat exchange correction module, internal heat exchange module and temperature field module, and present the simulation results in the form of three-dimensional images. Visualization and analysis include one or more of cloud map display, vector control, streamline control and profile control. Cloud map display is used to display the distribution of physical quantities such as pressure and temperature in the flow field; vector control is used to display the magnitude and direction of the velocity in the flow field; streamline control is used to display streamlines in the flow field, thereby helping engineers better understand the flow situation; profile control visualizes the physical quantities of the flow field along a certain plane section.

[0085] The strength field module is used to calculate the blade strength. The solvers used for strength field calculation include Ansys MechanicalAPDL or the open source finite element structural solver Calculix. The boundary conditions that can be solved include: displacement, force, pressure, speed, etc.

[0086] The main function of the curve and surface library is to call the curves and surfaces of material properties in the material library, generate and manage geometric models such as curves and surfaces. The curve and surface library includes various basic curves, surfaces and other geometric models. Through curves and surfaces, engineers can quickly generate and compile complex geometric models and use them for simulation analysis or product design. Users can add custom curves or surfaces in the curve and surface library, and modify their x, y, z axis names, units, scales, orders, etc.

[0087] The optimization design module is used to optimize the result data of two-dimensional modules such as the external heat exchange module, the outer ring thermal correction module, and the inner ring thermal module. It adopts the MOEA framework, which supports genetic algorithms, differential evolution, particle swarm optimization, genetic programming, grammar evolution, etc., and uses experimental design (Design of Experiments, abbreviated as DOE) to simulate and optimize key factors.

[0088] The fluid-solid coupling module is used to calculate the interaction between the fluid model and the solid model. It uses canvas dynamic drawing technology to restore the display of different three-dimensional models and realize geometric modeling functions such as calculation, verification, display, hiding, and solving of the model. The fluid-solid coupling calculation adopts finite element calculation and solution, and the solver adopts Ansys, which can also be switched to the solver developed by the user.

[0089] Furthermore, the server also has databases, file libraries, and solver libraries deployed, such as Figure 2 The file library includes a unified file access API module, a file sharing server, and a file storage system; the solver library includes a unified operation access API module and several solvers, including Flent_Host, Tec360, PREANSYS, and so on.

[0090] The integrated design and analysis platform for turbine cooling blades in this embodiment deploys an external heat exchange module, an external heat exchange correction module, an internal heat exchange module and a temperature field module, and the modules are connected accordingly, thereby realizing data transmission links between different calculation methods of each module. It can perform coupled thermal analysis on the internal and external flows of the turbine cooling blades, and can accurately simulate the temperature distribution, cooling effect and other physical properties of the turbine cooling blades under different working conditions, thereby realizing a full-chain automated design process for the turbine cooling blades from preliminary design to final optimization, providing accurate thermal analysis capabilities, multi-physical field coupling capabilities, and efficient calculation algorithms, thereby improving the design efficiency of the turbine cooling blades, reducing human errors, improving the design quality, and reducing the design cost.

[0091] Embodiment 2

[0092] Based on the first embodiment, this embodiment further illustrates the external heat exchange module, the external heat exchange correction module, the internal heat exchange module and the temperature field module.

[0093] When designing turbine cooling blades, drag the external heat exchange module, external heat exchange correction module, internal heat exchange module, and temperature field module displayed on the browser operation access interface to the canvas, connect them, and use lines to represent data updates, such as Figure 3 As shown, Figure 3 A flow chart of a turbine cooling blade design provided in an embodiment of the present invention.

[0094] In a specific embodiment, the external heat exchange module includes a first data receiving module, a parameter modification module and an external heat exchange solving module.

[0095] The first data receiving module is used to receive the S1 flow surface data, S2 flow surface data and performance parameters of all sections of the turbine cooling blade according to user instructions, and obtain the original data of several sections in the three-dimensional model of the turbine cooling blade.

[0096] Specifically, the original data of the turbine cooling blade three-dimensional model is the original data corresponding to a number of cross sections extracted from the three-dimensional model by the simulation personnel, and the number of cross sections may be 3. After the first data receiving module receives the original data, the viewing area loads the display model and displays the tree list of the model, and controls the display and hiding of the cross sections in the tree list, such as Figure 4 As shown, Figure 4 A cross-sectional schematic diagram of an external heat exchange module provided in an embodiment of the present invention, Figure 4 The number of cross sections shown is 2.

[0097] The parameter modification module is used to modify the target parameters in the original data under different first working conditions according to user instructions to obtain the modified data. When the working condition is the cooling efficiency test condition, modifying the target parameters in the original data includes: modifying the total temperature of the gas flow, the total pressure of the gas flow, and the static pressure parameters of the outlet in different sections of the S1 flow surface data 、 Pressure side data and suction side data.

[0098] Taking the cooling efficiency test condition as an example, the target parameters that need to be modified in the parameter modification module include two aspects: on the one hand, modify the parameters such as the total temperature of the gas flow, the total pressure of the gas flow and the outlet static pressure of different sections in the S1 flow surface data. On the other hand, for some sections, the isentropic Ma number distribution in the S1 input data may produce a large adverse pressure gradient, causing boundary layer separation, resulting in the program being unable to complete the calculation. Therefore, in order to complete the calculation, the trailing edge velocity correction method is generally used; specifically in this case, select the condition to be calculated and the corresponding S2 flow surface data, and modify the following sections and input parameters in the S1 flow surface data:

[0099] Section S1_j1_ps, input parameters: NKVR=1, KVR=3, IX1=145, IX2=150,

[0100] Section S1_j1_ss, input parameters: NKVR=1, KVR=3, IX1=80, IX2=150,

[0101] Section S1_j2_ps, input parameters: NKVR=1, KVR=3, IX1=145, IX2=150,

[0102] Section S1_j3_ps, input parameters: NKVR=1, KVR=3, IX1=145, IX2=150,

[0103] Wherein, S1 represents the blade number, j1, j2, and j3 represent the section names, ps represents the pressure surface, ss represents the suction surface, NKVR represents the number of groups of modified surface Mach number distribution (up to three groups), and NKVR=0 when not modified; KVR represents the method of modifying the surface Mach number; if KVR=1, it means that the air film hole is located near the stagnation point and the heat transfer coefficient is not corrected; if KVR=2, it means that the calculation will correct the heat transfer coefficient of the pressure surface and the suction surface; if KVR=3, it means that any point on the pressure surface or the suction surface is selected as the starting point, and the gas flow velocity remains unchanged to the end point of the surface; IX1 represents the modification starting point number, and IX2 represents the modification end point number.

[0104] The external heat exchange solution module is used to calculate the gas heat transfer coefficient and the gas recovery temperature by numerically solving the viscosity differential equation within the surface according to user instructions and based on the modified data using the external heat exchange solver, convert the format of the gas heat transfer coefficient and the gas recovery temperature, and convert the calculation results into a file in a unified format that can be recognized by the platform to form a two-dimensional thermal boundary condition, and use three-dimensional thermal boundary reconstruction technology to associate the collected two-dimensional temperature values ​​with the corresponding positions on the three-dimensional geometric model to generate an intuitive three-dimensional temperature distribution view, output the three-dimensional thermal boundary conditions of the outer surface of the cooling blade, and obtain the external heat exchange boundary conditions.

[0105] Specifically, the external heat exchange solution module uses NPUSATAN7.exe to solve according to the solution command input by the user, and the log output of the solution will be displayed in the log area. After the solver solves and converts the format, the heat exchange boundary conditions are obtained. Through the result analysis, the canvas area displays the comb diagram and line diagram of the input data calculated by external heat exchange, and the physical quantity can be switched to view the corresponding analysis graphics.

[0106] In addition, the calculation results of the external heat exchange solution module can be generated into a ***.doc file through the report generation module and downloaded to the local computer, and the calculation results of the external heat exchange solution module can be generated into a ***.out file through the export module and exported to the local computer.

[0107] The process of external heat exchange correction is: passing the result file of the external heat exchange module to the external heat exchange correction module through updating data, performing air film hole calculation in the external heat exchange correction module, and outputting the air film temperature and heat transfer coefficient with air film holes. In a specific embodiment, the external heat exchange correction module includes a second data receiving module, a mode selection module, a working condition parameter setting module, an air film hole adding module, a parameter setting module and an external heat exchange correction solving module.

[0108] The second data receiving module is used to receive external heat exchange boundary conditions according to user instructions.

[0109] Specifically, first update the data on the main platform of the project, and transfer the calculated .out file to the external heat exchange correction module through the connection update between the external heat exchange module and the external heat exchange correction module. The second data receiving module of the external heat exchange correction module receives the .out file; you can also import the saved .out file from the outside. Enter the external heat exchange correction module page. Since the data has been updated, the blade section is displayed in the canvas of the external heat exchange correction module, such as Figure 5 As shown, Figure 5 A cross-sectional schematic diagram of an external heat exchange correction module provided in an embodiment of the present invention, Figure 5 The number of cross sections shown is 3.

[0110] The mode selection module is used to select a target calculation mode in the calculation mode list and select a target correction mode in the correction mode list under the target calculation mode according to a user instruction.

[0111] Specifically, the calculation modes in the calculation mode list include: default correction mode, mixing model, air film superposition, blades near the broken wall, front wake cooling efficiency, front wake heat transfer coefficient and thermal barrier coating. In each calculation mode, the correction modes in the correction mode list include: air film hole correction, outlet temperature distribution factor (OTDF) correction and temperature margin correction.

[0112] Exemplarily, the target calculation mode selects the default correction mode, and the target correction mode selects the film hole correction.

[0113] The operating condition parameter setting module is used to set different custom variables and their corresponding values ​​according to user instructions to form a number of second operating conditions.

[0114] For example, the custom variable names are set to P1, P2, TJ2, and TJ3, and a set of P1, P2, TJ2, and TJ3 values ​​are set under the working condition state1, and another set of P1, P2, TJ2, and TJ3 values ​​are set under the working condition state2 to form two sets of second working conditions, such as Figure 6 As shown, Figure 6 A schematic diagram of operating parameter settings provided in an embodiment of the present invention.

[0115] The air film hole adding module is used to add air film holes on several sections in the cross-section model according to user instructions and based on the target correction mode.

[0116] Specifically, an air film hole is added to the cross-sectional line displayed in the external heat exchange correction module. After the air film hole is added, the air film hole is displayed on the cross-sectional line of the external heat exchange correction module, such as Figure 7 As shown, Figure 7 A schematic diagram of adding air film holes provided in an embodiment of the present invention.

[0117] The parameter setting module is used to set the cross-sectional parameters and film hole parameters of the turbine cooling blade according to user instructions.

[0118] Section parameters include any one of the total temperature of the incoming gas flow, the total pressure of the incoming gas flow, the Mach number of the incoming gas flow, and the adiabatic index. Exemplarily, setting the section parameters includes: setting the total temperature of the incoming gas flow TTO of the IsenMa_S1_j1 section to P2, setting the total temperature of the incoming gas flow TTO of the IsenMa_S1_j2 section to TJ2, and setting the total temperature of the incoming gas flow TTO of the IsenMa_S1_j3 section to 1226. Among them, IsenMa is the blade name, S1 is the blade number, j1, j2, and j3 represent the section name, and P2 and TJ2 are both custom variable names, which can be named in the working condition form as needed. Setting the total temperature of the incoming gas flow TTO to P2 means that TTO references the variable P2, and setting the total temperature of the incoming gas flow TTO to TJ2 means that TTO references TJ2.

[0119] like Figure 8 As shown, Figure 8 A schematic diagram of the film hole parameter setting provided in an embodiment of the present invention, wherein j1 and j2 represent the section name, ps represents the pressure surface, ss represents the suction surface, qmk represents the film hole, and qmk0 represents the film hole number 0. The film parameters include the relative position XR (mm) of the film hole from the leading edge stagnation point, the hole type control parameter KCOR (mm, referring to the diameter of the cylindrical part of the expansion hole), the film hole diameter DH (mm), the transverse spacing PITCH (mm) of the film holes, the number of transverse film holes in the hole row NHC, the film hole cold air flow GC (kg / s, corresponding to the number of holes NHC), the cold air temperature TC (K), the hole inclination angle GAMA (deg), the hole yaw angle BETA (deg), the hole outlet area to the cylindrical section area ratio AR (AR = 1 is a cylindrical hole, AR = 0 is the calculated expansion hole area ratio), the hole length HL (mm) and the hole cylindrical section length HLM (mm). Among them, the air film hole cooling air flow GC is an arbitrary given value, the GAMA and BETA angles are empirical estimates, and the cooling air temperature TC is the operating value.

[0120] The external heat exchange correction solution module is used to solve the air film parameters using the air film cooling program solver according to the user's instructions and under different second working conditions according to the external heat exchange boundary conditions, cross-sectional parameters and air film hole parameters to obtain the external wall heat exchange boundary conditions.

[0121] Specifically, the external heat exchange correction solution module uses FILMCG.exe to solve according to the solution command input by the user, and the log output of the solution will be displayed in the log area. After the solver solves and the format conversion, the heat exchange boundary conditions of the external wall are obtained. Through the result analysis, click to modify the physical quantity to the air film efficiency, and the canvas area displays the comb chart and line chart calculated by the input data after the external heat exchange correction.

[0122] In addition, you can also use the report generation module to generate a ***.doc file with the calculation results of the external heat exchange correction module and download it locally, and use the export module to export the film hole file (**.qmk), external surface file (**.map), and external heat exchange correction file (**.out) locally.

[0123] The internal heat exchange calculation includes the construction of the internal flow network, the setting of component parameters, and the debugging of the internal flow rate and heat transfer coefficient. The internal heat exchange module supports the import of external heat exchange correction data to associate the air film holes and outlet components, supports the import of temperature field grids to associate the internal flow components and grid boundaries, and supports the association of the air film temperature and external heat transfer coefficient calculated by the external heat exchange correction with the inner cavity components. The internal heat exchange module calculates and gives the corresponding internal heat exchange calculation results, including the total pressure, static pressure, flow rate and heat transfer coefficient of each component. In a specific embodiment, the internal heat exchange module includes a third data receiving module, an internal flow network construction module, an internal flow coupling creation module, an air film hole coupling creation module and an internal heat exchange solution module.

[0124] The third data receiving module is used to receive the outer wall heat exchange boundary conditions according to the user instruction.

[0125] Specifically, firstly, data is updated on the main platform of the project, and the calculated external heat exchange correction result file .out is transferred to the internal heat exchange module, and the third data receiving module of the internal heat exchange module receives the result file .out.

[0126] The internal flow network building module is used to connect several components according to the number of nodes and boundary points in the components according to user instructions, and set the input parameters of each component, or import the internal flow network that has been created and includes all input parameters to obtain the network topology diagram of the cooling air flow inside the blade. Among them, the components and their input parameters can be customized as needed.

[0127] Specifically, according to user instructions, move the components in the component library to the canvas, and connect the components in the canvas according to the internal nodes and boundary points of the components. The internal nodes and boundary points of the components represent the number of airflow inlets and outlets. For example, if the component has 1 internal node and 2 boundary points, it has 1 airflow inlet and 2 airflow outlets. For another example, if the component has only 1 internal node, it only has an airflow inlet and no airflow outlet. Then set the input parameters of each component one by one, or import the internal flow network that has been created and includes all input parameters to obtain the network topology diagram of the cold air flow inside the blade, such as Fig. 9 As shown, Fig. 9 A partial schematic diagram of a network topology diagram provided by an embodiment of the present invention, Fig. 9There are 5 elements in it, and the arrows connecting the lines indicate the airflow direction. For example, the cavity_34 element has 1 airflow inlet and 11 airflow outlets, and accordingly it has 1 internal node and 11 boundary points.

[0128] In addition, if the air system network is not prepared in advance, it is necessary to manually create the air system network and set the required parameters of all air system components. It can be understood that the original data of the external heat exchange module, the air system network topology diagram of the internal heat exchange module, and the temperature field using the three-dimensional model grid file can be a file prepared in advance or a file created through the platform. After the file is created through the platform, the required parameters of each file must be set so that the designed cooling blades match the imported data.

[0129] The internal flow coupling creation module is used to map a number of elements and a number of grid cells one by one according to user instructions to obtain an internal flow coupling mapping relationship.

[0130] Specifically, by decoupling, the inlet temperature, pressure or flow rate of the specified fluid of each element is mapped to the grid cells of the three-dimensional grid model surface to form the thermal boundary conditions of the model surface, realize the association between the element and the three-dimensional grid model surface, and create an internal flow coupling mapping relationship.

[0131] The air film hole coupling creation module is used to map a number of components and a number of air film holes one by one according to user instructions to obtain an air film hole coupling mapping relationship.

[0132] Specifically, through decoupling, the attribute parameters of each air film hole are mapped to the corresponding internal flow element as the input parameter of the corresponding element, that is, part of the parameters of the air film hole are passed to the corresponding element, so as to realize the association between the air film hole of external heat exchange correction and the elements of the network topology diagram, and create the air film hole coupling mapping relationship.

[0133] The internal heat transfer solution module is used to calculate the pressure, temperature and heat transfer coefficient of each element in the network topology diagram according to user instructions, based on the internal flow coupling mapping relationship and the air film hole coupling mapping relationship, according to the flow balance and energy balance, and obtain the temperature field boundary conditions.

[0134] Specifically, the internal heat exchange solution module uses LGSAS.exe to calculate the pressure (including static pressure and total pressure), temperature and heat transfer coefficient of each component according to the calculation and solution instructions input by the user, and the flow balance and energy balance are calculated. After the solution is completed, the parameters can be output in the parameter setting area through any component on the canvas, and the air system network***.lgsas file can also be exported through the export module.

[0135] Furthermore, the animation of the internal heat exchange system and the set component parameters can be displayed through the post-processing module.

[0136] In a specific embodiment, the temperature field module includes: a fourth data receiving module, a material selection module, a convection adding module and a temperature field solving module.

[0137] The fourth data receiving module is used to receive external heat exchange boundary conditions, external wall heat exchange boundary conditions, temperature field boundary conditions and network topology diagram according to user instructions to form a turbine cooling blade geometric model.

[0138] Specifically, first update the data on the main platform of the project, and transfer the calculated external heat exchange boundary conditions, external wall heat exchange boundary conditions, temperature field boundary conditions and network topology diagram to the temperature field module. The fourth data of the temperature field module receives these data, and the canvas area of ​​the temperature field module displays the geometric model after these data are loaded, such as Fig.10 As shown, Fig.10 A schematic diagram of a geometric model provided for an embodiment of the present invention.

[0139] The material selection module is used to select the material of the turbine cooling blade geometric model in the material library according to the user instruction. For example, steel material is selected as the material of the turbine cooling blade geometric model in the material library.

[0140] The convection adding module is used to add boundary conditions to the model surface of the turbine cooling blade geometric model by setting parameters according to user instructions; the boundary conditions include any one of convection, temperature, heat flow, surface radiation, and environmental radiation.

[0141] Specifically, by setting the relevant parameters of any boundary among convection, temperature, heat flow, surface radiation, and environmental radiation, the boundary conditions of the model surface of the turbine cooling blade geometric model are added. The set parameters can be a set of data or a single data.

[0142] For example, the temperature is set to 30°C to implement the addition of temperature boundaries on the geometric model surface of the turbine cooling blade. For another example, the convection temperature is changed to TableT and the heat transfer coefficient is changed to TableH to implement the addition of convection boundaries on the geometric model surface of the turbine cooling blade, wherein TableT represents a set of convection temperature data and TableH represents a set of heat transfer coefficient data.

[0143] The temperature field solving module is used to calculate the temperature field distribution of the turbine cooling blade using the temperature field calculation module solver according to user instructions, based on the turbine cooling blade geometry model, the material and boundary conditions of the turbine cooling blade geometry model.

[0144] Specifically, based on the turbine cooling blade geometry model, the material and boundary conditions of the turbine cooling blade geometry model, the Fluent solver is used to solve the temperature field distribution of the turbine cooling blade under the state 1 working condition.

[0145] In addition, the calculation results can be exported to the local computer through the export module, and the post-processing results of the calculation results can be displayed through the post-processing module, and the result data can be displayed in cloud diagrams and cross-sectional diagrams, such as Figure 11a-Figure 11b As shown, Figure 11a-Figure 11b A schematic diagram showing the temperature field distribution of a turbine cooling blade provided by an embodiment of the present invention. Fig.11a is the result cloud map, Fig.11b It is a cross-sectional view.

[0146] In this embodiment, the external heat exchange boundary conditions are calculated by the external heat exchange module under the guide vane cooling effect test conditions, and the cold air temperature and flow rate of the cooling effect test, the outer wall heat exchange boundary conditions (air film temperature and heat transfer coefficient) calculated by the external heat exchange correction module, and the heat exchange boundaries (internal flow pressure, temperature and heat transfer coefficient) of the inner cavity and the air film hole element calculated by the internal heat exchange module are transmitted to the temperature field module to calculate the temperature distribution of the turbine blade.

[0147] After analyzing the calculation results of temperature distribution, the average wall temperature calculation results of the guide vane surface of this embodiment are compared with the actual test results. The relative deviation of the average wall temperature calculation results of this embodiment is: -6.42%, and the relative deviation of the guide vane cooling effect calculated according to the average wall temperature and the test results is: 6.67%. At the same time, compared with the existing design method, the design cycle of the platform of this embodiment is shortened by about 30%, and the design cost is reduced by about 20%, which verifies the effectiveness and practicality of this platform.

[0148] The above contents are further detailed descriptions of the present invention in combination with specific preferred embodiments, and it cannot be determined that the specific implementation of the present invention is limited to these descriptions. For ordinary technicians in the technical field to which the present invention belongs, several simple deductions or substitutions can be made without departing from the concept of the present invention, which should be regarded as falling within the protection scope of the present invention.

Claims

1. A turbine cooling blade integrated design and analysis platform, characterized in that: include: The server side and the browser side, the server side is deployed with an external heat exchange module, an external heat exchange correction module, an internal heat exchange module and a temperature field module, and the browser side provides an operation access interface for the external heat exchange module, the external heat exchange correction module, the internal heat exchange module and the temperature field module, wherein: The external heat exchange module is used to calculate the gas heat transfer coefficient and the gas recovery temperature by numerically solving the viscosity differential equation in the profile using the external heat exchange solver according to the S1 flow surface data, S2 flow surface data of the turbine cooling blade and the performance parameters of all sections of the blade, so as to obtain the external heat exchange boundary conditions; The external heat exchange correction module is used to combine the external heat exchange boundary conditions and the air film hole parameters, and use the air film cooling program solver to solve the air film parameter information to obtain the external wall heat exchange boundary conditions; The internal heat exchange module is used to construct a network topology diagram of the flow of cold air inside the blade using elements, nodes inside the elements and boundary points of the elements, calculate the pressure, temperature and heat transfer coefficient of each element in the network topology diagram according to the flow balance and energy balance to obtain the temperature field boundary conditions, and add the pressure, temperature and heat transfer coefficient to the element parameters to form a complete element library; The temperature field module is used to calculate the temperature distribution of the turbine cooling blades using a temperature field solver according to the external heat exchange boundary conditions, the external wall heat exchange boundary conditions, the temperature field boundary conditions and the network topology diagram.

2. The integrated design and analysis platform for turbine cooling blades according to claim 1, characterized in that: The external heat exchange module comprises: A first data receiving module is used to receive the S1 flow surface data, S2 flow surface data and performance parameters of all sections of the turbine cooling blade according to user instructions, and obtain the original data of several sections in the three-dimensional model of the turbine cooling blade; A parameter modification module, used to modify the target parameters in the original data under different first working conditions according to user instructions to obtain modified data; The external heat exchange solving module is used to calculate the gas heat transfer coefficient and the gas recovery temperature by numerically solving the viscosity differential equation in the surface according to user instructions and based on the modified data, convert the gas heat transfer coefficient and the gas recovery temperature into a two-dimensional thermal boundary condition, and use a three-dimensional thermal boundary reconstruction technology to output the three-dimensional thermal boundary condition of the outer surface of the cooling blade to obtain the external heat exchange boundary condition.

3. The integrated design and analysis platform for turbine cooling blades according to claim 2, characterized in that: When the first operating condition is a cooling efficiency test operating condition, modifying the target parameter in the original data includes: Modify the total temperature of the gas flow, the total pressure of the gas flow, and the static pressure parameters of the outlet in different sections of the S1 flow surface data 、 Pressure side data and suction side data.

4. The integrated design and analysis platform for turbine cooling blades according to claim 1, characterized in that: The external heat exchange correction module comprises: A second data receiving module, used for receiving the external heat exchange boundary condition according to a user instruction; A mode selection module, configured to select a target computing mode from a computing mode list and select a target correction mode from a correction mode list under the target computing mode according to a user instruction; The working condition parameter setting module is used to set different custom variables and the value of each custom variable according to user instructions to form a plurality of second working conditions; An air film hole adding module, used for adding air film holes on a plurality of cross sections in the cross section model according to a user instruction and based on the target correction mode; A parameter setting module, used to set the cross-sectional parameters and film hole parameters of the turbine cooling blade according to user instructions; The external heat exchange correction solution module is used to solve the air film parameters using the air film cooling program solver according to the user's instructions and under different second working conditions according to the external heat exchange boundary conditions, the cross-sectional parameters and the air film hole parameters to obtain the outer wall heat exchange boundary conditions.

5. The integrated design and analysis platform for turbine cooling blades according to claim 4, characterized in that: The calculation modes in the calculation mode list include: default correction mode, mixing model, air film superposition, blades near broken walls, front wake cooling efficiency, front wake heat transfer coefficient and thermal barrier coating; In each calculation mode, the correction modes in the correction mode list include: film hole correction, OTDF correction and temperature margin correction; The cross-sectional parameters include any one of the total temperature of the incoming gas flow, the total pressure of the incoming gas flow, the Mach number of the incoming gas flow, and the adiabatic index; The air film parameters include the relative position of the air film holes from the leading edge stagnation point, hole type control parameters, air film hole diameter, lateral spacing of air film holes, number of lateral air film holes in the hole row, cold air flow rate of the air film holes, cold air temperature, hole inclination angle, hole yaw angle, ratio of hole outlet area to cylindrical section area, hole length and length of the cylindrical section of the hole.

6. The integrated design and analysis platform for turbine cooling blades according to claim 1, characterized in that: The server side is also deployed with a grid division module, wherein the grid division module is used to discretize the calculation area into a number of grid units.

7. The integrated design and analysis platform for turbine cooling blades according to claim 6, characterized in that: The internal heat exchange module comprises: A third data receiving module, used for receiving the outer wall heat exchange boundary condition according to a user instruction; An internal flow network building module is used to connect several components according to the number of nodes and boundary points within the components according to user instructions, and set the input parameters of each component, or import an already created internal flow network including all input parameters to obtain a network topology diagram of the cooling air flow inside the blade; An internal flow coupling creation module, used for mapping the plurality of elements and the plurality of grid cells one by one according to a user instruction to obtain an internal flow coupling mapping relationship; An air film hole coupling creation module is used to map the plurality of elements and the plurality of air film holes one by one according to user instructions to obtain an air film hole coupling mapping relationship; The internal heat exchange solution module is used to calculate the pressure, temperature and heat transfer coefficient of each element of the network topology diagram according to user instructions, based on the internal flow coupling mapping relationship and the air film hole coupling mapping relationship, according to flow balance and energy balance, and obtain the temperature field boundary conditions.

8. The integrated design and analysis platform for turbine cooling blades according to claim 1, characterized in that: The server side is also deployed with a material library, wherein the material library is used to provide material data required for the design process.

9. The integrated design and analysis platform for turbine cooling blades according to claim 8, characterized in that: The temperature field module comprises: a fourth data receiving module, configured to receive the external heat exchange boundary condition, the external wall heat exchange boundary condition, the temperature field boundary condition and the network topology diagram according to a user instruction, so as to form a turbine cooling blade geometric model; A material selection module, for selecting a material for the turbine cooling blade geometric model in the material library according to a user instruction; A convection adding module, used for adding boundary conditions to the model surface of the turbine cooling blade geometric model by setting parameters according to user instructions; the boundary conditions include any one of convection, temperature, heat flow, surface radiation, and environmental radiation; The temperature field solving module is used to calculate the temperature distribution of the turbine cooling blade using the temperature field calculation module solver according to user instructions, based on the turbine cooling blade geometric model, the material of the turbine cooling blade geometric model and the boundary conditions.

10. The integrated design and analysis platform for turbine cooling blades according to claim 1, characterized in that: The server side is also deployed with a post-processing module, wherein the post-processing module is used to visualize and analyze any simulation result of the external heat exchange boundary condition, the external wall heat exchange boundary condition, the temperature field boundary condition, and the blade temperature field, and present the simulation result in the form of a three-dimensional image; the visualization processing and analysis includes one or more of cloud map display, vector control, streamline control, and profile control.

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