Thermal-mechanical coupled peridynamics method for failure prediction of thermal barrier coatings

Abstract

The present invention discloses a thermomechanical coupling peridynamic method for predicting the damage of thermal barrier coating materials. The method first discretizes the structure of the thermal barrier coating material into a series of material points containing physical information, obtains various basic parameters according to the peridynamic linearization theory, and performs calculation and solution on this basis; the dynamic failure process of the thermal barrier coating material structure is divided into several time steps for calculation, and the Verlet integration method is used for iterative calculation for each incremental step; the thermomechanical coupling equation in the form of peridynamic integral is combined to determine the heat and force iteration time step that meets the convergence, and calculates the temperature, force and displacement of the material point, selects the critical elongation criterion to determine whether the material point pair is broken, and the fracture of the material point pair within the near field range is statistically analyzed to obtain the damage value, and the failure and damage of the structure are displayed based on the damage value. The present invention can realize the use of peridynamics to solve complex crack initiation and expansion problems of thermal barrier coating materials.

Description

Technical Field

[0001] The present invention relates to the technical field of failure prediction and mechanical numerical simulation of thermal barrier coating materials, and in particular to a numerical simulation method for the dynamic failure process of thermal barrier coating materials under the framework of peridynamics, specifically a thermomechanically coupled peridynamic method for predicting the damage of thermal barrier coating materials. Background Art

[0002] Thermal barrier coatings (TBCs) refer to ceramic coating structures covering the surface of metal substrates. They use the high heat resistance, corrosion resistance and low thermal conductivity of ceramic materials to protect the substrate materials in high-temperature working environments, allowing components with the coating to work in relatively extreme high-temperature environments. Therefore, they are widely used in aerospace and other fields. Studying the destruction mechanism of thermal barrier coating materials in high-temperature difference working environments is of great significance to effectively improve the service life and safety performance of the coatings. Compared with using complex experimental equipment to study the destruction of thermal barrier coatings with complex structures in high-temperature environments, the use of numerical simulation methods to study the destruction process of thermal barrier coating materials has the advantages of being economical and efficient, while traditional theories have certain difficulties in simulating discontinuities such as crack propagation. Peri-field dynamics theory (SASilling. Reformulation of elasticity theory for discontinuities and long-range forces [J]. Journal of the Mechanics and Physics of Solids, 2000. 48 (1): 175-209) is a meshless method based on the idea of ​​non-local action. It uses integral equations instead of differential equations to model, avoiding the singularity problem faced when solving the crack tip. The constitutive force function of the model includes a description of fracture damage, which can naturally simulate the process of crack initiation and propagation. It has certain advantages in studying fracture failure problems.

[0003] After searching, there are documents on the simulation and prediction of material structure spalling using peri-field dynamics theory, such as the Chinese patent with publication number CN112116128A published on December 22, 2020, which discloses a method for simulating and predicting structural spalling and multiple spalling under impact loads, but the application does not solve the simulation and prediction of the thermal shock damage process of thermal barrier coating materials. There are documents on the destruction mechanism of thermal barrier coating materials in high-temperature service environments, such as the Chinese patent with publication number CN105046023B published on April 24, 2018, which discloses a method for simulating working conditions during the period of coating with thermal barrier coatings, but the application fails to reflect the mutual influence between force and heat, and cannot correct the temperature field and deformation.

[0004] Therefore, the present invention studies the thermal shock damage process of thermal barrier coating materials based on peridynamics (PD) theory to solve the problems existing in the simulation and prediction of the failure process of existing thermal barrier coating materials. Summary of the invention

[0005] In order to overcome the above-mentioned deficiencies of the prior art, the present invention provides a thermomechanically coupled peridynamic method for predicting the damage of thermal barrier coating materials, thereby realizing the simulation prediction of the crack initiation and propagation process of thermal barrier coating materials.

[0006] The present invention is achieved through the following technical solutions:

[0007] Thermo-mechanical coupled peridynamics method for thermal barrier coating material failure prediction includes:

[0008] Step 1, establishing a thermal barrier coating material structure entity model;

[0009] Step 2: discretize the established entity model to obtain a series of material points containing physical information;

[0010] Step 3: Initialize the information of the material points and read the initial boundary conditions;

[0011] Step 4: Obtain the heat contribution of other material points within the near field to the current material point and update the temperature field value;

[0012] Step 5: Based on the thermal-mechanical coupling term, the deformation between material point pairs is corrected and the mechanical variables of the material points are updated;

[0013] Step 6, determine the fracture damage of the material point and update the damage value;

[0014] Step 7: introduce force-heat coupling term and correct the temperature field value according to deformation and damage;

[0015] Step 8: Repeat steps 4 to 7 until all material points are calculated, and determine the failure and damage of the thermal barrier coating material based on the final damage statistics.

[0016] In the above technical solution, the thermal barrier coating material structure is first discretized into a series of material points containing physical information, and various basic parameters are obtained according to the peridynamic linearization theory, and then the calculation and solution are performed on this basis; the dynamic failure process of the thermal barrier coating material structure is divided into several time steps for calculation, and the Verlet integration method is used for iterative calculation for each incremental step; the thermal and force iteration time steps that meet the convergence are determined by combining the thermomechanical coupling equation in the form of peridynamic integrals, and the temperature, force and displacement of the material points are calculated, and the critical elongation criterion is used to determine whether the material point pairs are broken or not, and the fracture of the material point pairs within the near field range is statistically calculated to obtain the damage value, and the failure and damage of the structure are displayed based on the damage value. This technical solution can realize the use of peridynamics to solve complex crack initiation and expansion problems of thermal barrier coating materials.

[0017] As a further technical solution, step 2 further includes: meshing the solid model, using hexahedral units to generate a discretized three-dimensional mesh model, adjusting the discrete spacing according to the calculation accuracy requirements, and defining each unit block as a near-field dynamic material point.

[0018] Furthermore, the geometric model is meshed according to the standard finite element method, and the three-dimensional mesh model is generated using hexahedral units. The unit division is required to be as uniform and consistent as possible, and the discrete spacing is usually about 1 / 100 of the maximum edge length of the solid geometric model, which is adjusted according to the calculation accuracy requirements.

[0019] Specifically, the grid is divided to meet the calculation accuracy requirements, a discretized model is generated, and the material parameters of each region of the model are input, including elastic modulus, Poisson's ratio, density, thermal expansion coefficient, thermal conductivity coefficient, etc.

[0020] Furthermore, the initial boundary condition application area is divided into blocks, and the structural parts with different material components are numbered in blocks. Boundary condition values ​​such as velocity, displacement and temperature are assigned to the material points of the corresponding blocks.

[0021] As a further technical solution, step three further includes: displacement boundary conditions and velocity boundary conditions are given by directly assigning the position information of the material point, and the force boundary conditions are converted into force density conditions for application;

[0022] The temperature boundary conditions include: the initial temperature condition is set to T t＝0 =T(x, y, z), the first type of temperature boundary condition is the known boundary temperature, which is applied by directly assigning the temperature of the material point in the specified area to T = T(t), and the second type of temperature boundary condition is the known heat flux density on the boundary The third type of temperature boundary condition is the convective heat transfer condition q n =h(TT ∞), where T is temperature, k is the thermal conductivity, q n is the normal heat flux density, h is the thermal convection coefficient, T ∞ is the convective ambient temperature, n represents the normal direction, and x, y, z represent the coordinates of the material point.

[0023] As a further technical solution, the method further includes: using the Verlet integration method to iteratively update the thermal and mechanical calculation results of steps four to seven.

[0024] Specifically, the Verlet integration method is used to solve the displacement and acceleration in the following iterative manner:

[0025]

[0026] Among them, u n is the displacement of the material point at the nth step, is the velocity of the material point at the nth step, is the acceleration of the material point at the n+1th step, and Δt is the time step.

[0027] The temperature is iterated as follows:

[0028]

[0029] Among them, T n is the temperature of the material point at the nth step, Δt is the time step of the temperature field iteration, Indicates the temperature change rate of the material point at the nth step. Considering the difference in the time step convergence conditions, different iterative time steps Δt are usually taken ME (displacement, acceleration iteration) and Δt TH (Temperature Iteration).

[0030] As a further technical solution, in step 4,

[0031] The heat contribution of other material points in the near field to the current material point is obtained through the Lagrangian integral form equation. The integral equation of heat conduction in the peridynamics framework is as follows:

[0032]

[0033] Where ρ is the material density, c v is the specific heat capacity of the material, H is the near field range, h (x, t) is the heat flow scalar state of the material point, Sb represents the heat source generated by the volume heat per unit mass, represents the temperature change rate, X represents the current material point, X′ represents the adjacent material point that interacts with it, V x′ Represents the volume of neighboring material points.

[0034] As a further technical solution, in step 5, the basic equation of motion of peridynamics considering the temperature effect is as follows:

[0035]

[0036] in, T s is the force vector state that only includes the structural deformation part, b is the body force density, T s In the peridynamic constitutive model, it is expressed as K is the bulk modulus, G is the shear modulus, θ is the expansion scalar function, m is the volume weight function, x is the distance between material points in the initial configuration, e d To describe the deviation from the elongation state of shear deformation, M To describe the unit direction vector state of the deformation of a material point pair, ω represents the influence function, represents acceleration, H represents the near field range, T represents temperature, B Represents the thermal modulus vector state, V x′ Represents the volume of neighboring material points.

[0037] As a further technical solution, in step six, the fracture damage of the material point is judged according to the critical elongation criterion:

[0038]

[0039]

[0040] Among them, ξ is the relative position between the two material points in the reference configuration; η is the relative displacement between the two material points, s is the relative elongation of the material point pair, and μ is a discontinuous function. The above formula indicates that when the relative elongation of the distance between the material point pair reaches S0, the material point pair will break, and there will be no connection and deformation between the material point pairs after the break. S0 is selected according to the following formula:

[0041]

[0042] Among them, G0 is the critical fracture energy density, which depends on the fracture toughness and elastic modulus of the material, K represents the bulk modulus, and δ is the radius of the near field range.

[0043] Count the number of fractures of material point pairs before and after destruction to describe the local damage of material points The definition is as follows

[0044]

[0045] As a further technical solution, in step seven, a force-heat coupling term is introduced to correct the temperature field value according to the deformation and damage conditions;

[0046]

[0047] in, B is the thermal modulus vector state, is the material point pair elongation.

[0048] According to one aspect of the present invention, there is provided a system for implementing the thermomechanical coupling near-field dynamics method for predicting the damage of thermal barrier coating materials, comprising a construction module for establishing a structural entity model of the thermal barrier coating material; a discretization module for generating a discretization model to obtain a series of material points containing physical information; an initialization module for initializing material point information and reading initial boundary conditions; an iteration module for iteratively updating thermal and mechanical calculation results; and a prediction module for statistically judging the failure and damage of the thermal barrier coating material according to the final damage situation after the calculation of all material points is completed.

[0049] Furthermore, the iteration module also includes: a temperature field calculation module, which is used to obtain the heat contribution of other material points in the near field to the current material point and update the temperature field value; a mechanical variable calculation module, which corrects the deformation between material point pairs based on the thermal-mechanical coupling term and updates the mechanical variables of the material points; a damage calculation module, which is used to determine the fracture and damage conditions of the material point pairs and update the damage values; a temperature field correction module, which is used to introduce the force-heat coupling term and correct the temperature field value according to the deformation and damage conditions.

[0050] Compared with the prior art, the beneficial effects of the present invention include:

[0051] (1) The present invention provides a method, which first discretizes the structure of thermal barrier coating materials into a series of material points containing physical information, obtains various basic parameters according to the peridynamic linearization theory, and performs calculation and solution on this basis; divides the dynamic failure process of the thermal barrier coating material structure into several time steps for calculation, and uses the Verlet integration method for iterative calculation for each incremental step; combines the thermomechanical coupling equation in the form of peridynamic integral to determine the thermal and force iteration time steps that meet the convergence, and calculates the temperature, force and displacement of the material points, selects the critical elongation criterion to determine whether the material point pairs are broken or not, and statistically calculates the fracture conditions of the material point pairs within the near field range to obtain the damage value, and displays the failure and damage of the structure based on the damage value. This method can solve the deformation and damage of thermal barrier coating materials under temperature load, simulate the conduction of temperature and the crack initiation and expansion process, thereby realizing the use of peridynamics to solve complex crack initiation and expansion problems of thermal barrier coating materials.

[0052] (2) The present invention adopts a constitutive model that takes thermal-mechanical coupling into consideration, which can reflect the mutual influence between force and heat and correct the temperature field and deformation.

[0053] (3) Based on the integral form of the peridynamic thermomechanical coupling equation in the above theory, the present invention can directly solve the transient temperature field including discontinuity problems and reflect the influence of cracks on temperature conduction. BRIEF DESCRIPTION OF THE DRAWINGS

[0054] Figure 1 Schematic diagram of a method flow according to an embodiment of the present invention.

[0055] Figure 2 Schematic diagram of mesh division for model pre-processing according to an embodiment of the present invention.

[0056] Figure 3 Schematic diagram of an implementation of a multi-rate coupled integration method according to an embodiment of the present invention.

[0057] Figure 4 FIG. 4 is a temperature distribution cloud diagram of a plate affected by crack propagation according to an embodiment of the present invention.

[0058] Figure 5 FIG. 4 is a schematic diagram of damage of a plate according to an embodiment of the present invention. DETAILED DESCRIPTION

[0059] The following will clearly and completely describe the technical solutions of various embodiments of the present invention in conjunction with the accompanying drawings. 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 making creative work are within the scope of protection of the present invention.

[0060] The present invention provides a thermomechanical coupling peridynamic method for predicting the damage of thermal barrier coating materials. The method first discretizes the thermal barrier coating material structure into a series of material points containing physical information, obtains various basic parameters according to the peridynamic linearization theory, and performs calculation and solution on this basis; divides the dynamic failure process of the thermal barrier coating material structure into a number of time steps for calculation, and adopts the Verlet integration method for iterative calculation for each incremental step; combines the thermomechanical coupling equation in the integral form of peridynamics to determine the heat and force iteration time step that meets the convergence, calculates the temperature, force and displacement of the material point, selects the critical elongation criterion to determine whether the material point pair is broken, counts the fracture situation of the material point pair within the near field range to obtain the damage value, and displays the failure and damage situation of the structure based on the damage value.

[0061] The present invention comprises the following steps:

[0062] Step 1: Establish a solid model of the thermal barrier coating material structure. The area where the initial boundary conditions are applied is divided into blocks separately, and the structural parts with different material components are numbered in blocks.

[0063] Step 2: Divide the grid to meet the calculation accuracy requirements, generate a discretized model, and input the material parameters of each area of ​​the model, including elastic modulus, Poisson's ratio, density, thermal expansion coefficient, thermal conductivity coefficient, etc. Divide the geometric model into grids according to the standard finite element method, and use hexahedral units to generate a three-dimensional grid model. The unit division is required to be as uniform as possible. The discrete spacing is usually about 1 / 100 of the maximum edge length of the solid geometric model. It is adjusted according to the calculation accuracy requirements. Define each unit block as a near-field dynamic material point and generate a .g format grid model file. Assign initial material parameters to the material points belonging to different blocks.

[0064] Step 3: Based on the mesh model files generated in steps 1 and 2, initialize the material point information, read the initial boundary conditions, and assign boundary condition values ​​such as velocity, displacement, and temperature to the material points of the corresponding block. Displacement boundary conditions (including velocity boundary conditions) can be given by directly assigning values ​​to the material point position information, and force boundary conditions are all converted into force density conditions; the initial temperature condition is set to T t＝0 =T(x, y, z), the first type of temperature boundary condition is the known boundary temperature, which is applied by directly assigning the temperature of the material point in the specified area to T = T(t), and the second type of temperature boundary condition is the known heat flux density on the boundary The third type of temperature boundary condition is the convective heat transfer condition q n =h(TT ∞ ), where T is temperature, k is the thermal conductivity, q n is the normal heat flux density, h is the thermal convection coefficient, T ∞ is the convection ambient temperature.

[0065] Step 4: Use the Verlet integration method to iteratively update the thermal and mechanical calculation results. For example, when solving displacement and acceleration, iterate as follows:

[0066]

[0067] Among them, u n is the displacement of the material point at the nth step, is the velocity of the material point at the nth step, is the acceleration of the material point at the n+1th step, and Δt is the time step.

[0068] The temperature is iterated as follows:

[0069]

[0070] Among them, T n is the temperature of the material point at the nth step, Δt is the time step of the temperature field iteration, Indicates the temperature change rate of the material point at the nth step. Considering the difference in the time step convergence conditions, different iterative time steps Δt are usually taken ME (displacement, acceleration iteration) and Δt TH (Temperature Iteration) uses the multi-rate coupled integration method to iteratively solve the thermomechanical coupling equations.

[0071] Step 5: Obtain the heat contribution of other material points in the near field to the current material point through the Lagrange integral form equation, and update the temperature field value;

[0072] The integral equation of heat conduction in the peridynamics framework is as follows:

[0073]

[0074] Where ρ is the material density, c v is the specific heat capacity of the material, H is the near field range, h (x, t) is the heat flux scalar state of the material point, and Sb represents the heat source generated by the volume heat per unit mass.

[0075] Step 6: Based on the thermal-mechanical coupling term, the deformation between material point pairs is corrected, and mechanical variables such as the material point force state and displacement are updated;

[0076] The basic equation of motion for peridynamics considering the effect of temperature is as follows:

[0077]

[0078] in, T s is the force vector state that only includes the structural deformation part, b is the body force density, T s In the peridynamic constitutive model, it is expressed as K is the bulk modulus, G is the shear modulus, θ is the expansion scalar function, m is the volume weight function, x is the distance between material points in the initial configuration, e d To describe the deviation from the elongation state of shear deformation, M To describe the unit direction vector state of the deformation of a material point pair, ω represents the influence function, represents acceleration, H represents the near field range, T represents temperature, B Represents the thermal modulus vector state, V x′ Represents the volume of neighboring material points.

[0079] Step 7: According to the critical elongation criterion, the fracture damage of the material point pair is judged and the damage value is updated; the fracture of the material point pair is judged according to the following criteria:

[0080]

[0081]

[0082] Among them, ξ is the relative position between the two material points in the reference configuration; η is the relative displacement between the two material points, s is the relative elongation of the material point pair, and μ is a discontinuous function. The above formula indicates that when the relative elongation of the distance between the material point pair reaches s0, the material point pair will break, and the material point pair after the break will no longer be connected and deformed. s0 is selected according to the following formula:

[0083]

[0084] Among them, G0 is the critical fracture energy density, which depends on the fracture toughness and elastic modulus of the material.

[0085] Step 8: Introduce force-heat coupling term and correct the temperature field value according to deformation and damage conditions;

[0086]

[0087] in, B is the thermal modulus vector state, is the material point pair elongation.

[0088] Step nine, iterate until the calculation is completed, and the failure and damage of the thermal barrier coating material are statistically determined based on the final damage situation, and the whole process of crack initiation and propagation of the structure under thermal shock load is obtained.

[0089] Example

[0090] This embodiment provides a peridynamic method for predicting failure of thermal barrier coating materials.

[0091] like Figure 1 As shown, the peridynamic method for predicting failure of thermal barrier coating materials provided in this embodiment includes the following steps:

[0092] a) Establish a solid model of the thermal barrier coating material structure

[0093] This example simulates the damage of a plate made of Al2O3 ceramic, a surface material of a thermal barrier coating, under a thermal shock load. The size of the plate is 50 mm × 5 mm × 0.3 mm, the elastic modulus of Al2O3 is 370 GPa, the Poisson's ratio is 0.3, and the density is 3980 kg / m 3 , the thermal expansion coefficient is 7.5×10 -6 / ℃, fracture toughness is 3.0MPa·m 1 / 2

[0094] b) Divide the grid and generate a discretized model

[0095] In this embodiment, 500 material points are divided along the length direction, 50 material points are divided along the width direction, and 3 material points are divided along the thickness direction. The material point size is 0.1mm×0.1mm×0.1mm, the total number of material points is 75,000, and the near field range is set to about three times the discrete spacing of the material points 0.3001mm. The division results are shown in Figure 2 shown.

[0096] c) Initialization information, read initial boundary conditions

[0097] This example simulates a ceramic plate quenching test. The plate is surrounded by a fluid with a constant water temperature of 0°C, which exchanges heat with the ceramic plate heated to 300°C at the boundary. The temperature boundary condition is set to T t＝0 =300℃, T 下边界 =0℃.

[0098] d) Use Verlet integration method to iteratively update thermal and mechanical calculation results

[0099] Considering the convergence of the calculation results, the mechanical iteration time step is set to 1.5×10 -8 s, and the temperature field iteration time step is 7.5×10 -4 s. The multi-rate coupled integration method is implemented as follows Figure 3 shown.

[0100] e) The time step counter increases by one

[0101] The total calculation time is set to 250ms to simulate the temperature field diffusion, and the total number of time steps is 333 steps.

[0102] f) Obtain the heat contribution of other material points in the near field to the current material point through the Lagrange integral form equation, and update the temperature field value

[0103] g) Introduce thermal-mechanical coupling terms to correct the deformation between material point pairs and update mechanical variables such as material point force state and displacement

[0104] h) Determine the fracture damage of the material point according to the critical elongation criterion and update the damage value

[0105] i) Introduce force-heat coupling term, modify the temperature field value according to the deformation and damage conditions, and the temperature distribution cloud diagram of the plate affected by crack extension is as follows: Figure 4 shown.

[0106] j) Enter the next time step and repeat the update iteration until the calculation is completed

[0107] k) According to the final damage situation, the failure and damage of the thermal barrier coating material are statistically judged. The damage cloud map of the simulated plate is as follows: Figure 5 shown.

[0108] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the technical solutions of the embodiments of the present invention.

Claims

1. A thermomechanical coupled peridynamic method for predicting the damage of thermal barrier coating materials, characterized in that: include: Step 1, establishing a thermal barrier coating material structure entity model; Step 2: discretize the established entity model to obtain a series of material points containing physical information; Step 3: Initialize the information of the material points and read the initial boundary conditions; Step 4: Obtain the heat contribution of other material points in the near field to the current material point and update the temperature field value; obtain the heat contribution of other material points in the near field to the current material point through the Lagrangian integral form equation, where the heat conduction integral equation under the perifield dynamics framework is as follows: Where ρ is the material density, c v is the specific heat capacity of the material, H is the near field range, h (x, t) is the heat flow scalar state of the material point, s b The heat source that represents the volumetric heat generated per unit mass, represents the temperature change rate, x represents the current material point, x′ represents the adjacent material point that interacts with it, V x′ Represents the volume of neighboring material points; Step 5: Based on the thermal-mechanical coupling term, the deformation between material point pairs is corrected and the mechanical variables of the material points are updated. The basic equation of motion of peridynamics considering the influence of temperature is as follows: in, T s is the force vector state that only includes the structural deformation part, b is the body force density, T s In the peridynamic constitutive model, it is expressed as K is the bulk modulus, G is the shear modulus, θ is the expansion scalar function, m is the volume weight function, x is the distance between material points in the initial configuration, e d To describe the deviation from the elongation state of shear deformation, M To describe the unit direction vector state of the deformation of a material point pair, ω represents the influence function, represents acceleration, H represents the near field range, T represents temperature, B Represents the thermal modulus vector state, V x′ Represents the volume of neighboring material points; Step 6: Determine the damage of the material point to the fracture and update the damage value; determine the damage of the material point to the fracture according to the critical elongation criterion: Among them, ξ is the relative position between the two material points in the reference configuration; η is the relative displacement between the two material points, s is the relative elongation of the material point pair, and μ is a discontinuous function. The above formula indicates that when the relative elongation of the distance between the material point pair reaches s0, the material point pair will break, and the material point pair after the break will no longer be connected and deformed. s0 is selected according to the following formula: Where G0 is the critical fracture energy density, which depends on the fracture toughness and elastic modulus of the material, K represents the bulk modulus, and δ is the radius of the near field range; Step 7: introduce force-heat coupling term and correct the temperature field value according to deformation and damage; in, B is the thermal modulus vector state, is the material point pair elongation; Step 8: Repeat steps 4 to 7 until all material points are calculated, and determine the failure and damage of the thermal barrier coating material based on the final damage statistics.

2. The thermomechanical coupled peridynamic method for predicting thermal barrier coating material damage according to claim 1, characterized in that: Step 2 further includes: meshing the solid model, using hexahedral units to generate a discretized three-dimensional mesh model, adjusting the discrete spacing according to the calculation accuracy requirements, and defining each unit block as a peridynamic material point.

3. The thermomechanical coupled peridynamic method for predicting thermal barrier coating material damage according to claim 2, characterized in that: Step three further includes: displacement boundary conditions and velocity boundary conditions are given by directly assigning the position information of material points, and force boundary conditions are converted into force density conditions for application; The temperature boundary conditions include: the initial temperature condition is set to T t＝0 =T(x,y,z), the first type of temperature boundary condition is the known boundary temperature, which is applied by directly assigning the temperature of the material point in the specified area to T = T(t), and the second type of temperature boundary condition is the known heat flux density on the boundary The third type of temperature boundary condition is the convective heat transfer condition q n =h(TT ∞ ), where T is temperature, k is the thermal conductivity, q n is the normal heat flux density, h is the thermal convection coefficient, T ∞ is the convective ambient temperature, n represents the normal direction, and x, y, z represent the coordinates of the material point.

4. The thermomechanical coupled peridynamic method for predicting thermal barrier coating material damage according to claim 1, characterized in that: The method further comprises: using the Verlet integration method to iteratively update the thermal and mechanical calculation results of steps four to seven.

5. A system for implementing the thermomechanical coupling peridynamic method for predicting the damage of thermal barrier coating materials according to any one of claims 1 to 4, characterized in that: It includes a construction module for establishing a physical model of the thermal barrier coating material structure; a discretization module for generating a discretization model to obtain a series of material points containing physical information; Initialization module, used to initialize material point information and read initial boundary conditions; The iteration module is used to iteratively update the thermal and mechanical calculation results; the prediction module is used to statistically judge the failure and damage of the thermal barrier coating material based on the final damage situation after the calculation of all material points is completed.

6. The system of the thermomechanical coupling peridynamic method for predicting the damage of thermal barrier coating materials according to claim 5, characterized in that: The iteration module also includes: a temperature field calculation module, which is used to obtain the heat contribution of other material points in the near field to the current material point and update the temperature field value; a mechanical variable calculation module, which corrects the deformation between material point pairs based on the thermal-mechanical coupling term and updates the mechanical variables of the material points; a damage calculation module, which is used to determine the fracture and damage of the material point pairs and update the damage value; a temperature field correction module, which is used to introduce the force-heat coupling term and correct the temperature field value according to the deformation and damage conditions.

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