Thermal analysis method and system for high-pressure turbine blade made of ceramic matrix composite

Abstract

The invention provides a thermal analysis method and system for a ceramic matrix composite high-pressure turbine blade. The method comprises the steps that S1, a grid is generated based on a turbine blade profile; s2, calculating and assigning a heat conductivity coefficient tensor according to the generated grid; the heat conductivity coefficient tensor comprises the heat conductivity coefficient tensor of the blade surface, the heat conductivity coefficient tensor of the interior of the blade body and the heat conductivity coefficient tensor of the rib plate; and S3, carrying out heat conductivity coefficient tensor assignment, carrying out final heat conduction or gas-solid-heat coupling calculation, and outputting a calculation result. According to the invention, a set of assignment method for the anisotropic heat conductivity coefficient of the CMC material is established, an automatic assignment system for the anisotropic heat conductivity coefficient is established by adopting MATLAB and Fluent UDF, the problem of rapid assignment of the anisotropic heat conductivity coefficient of the CMC high-pressure turbine guide vane is solved, and technical support is provided for coupling thermal analysis and research of the CMC high-pressure turbine guide vane.

Description

Technical Field

[0001] The present invention relates to the field of engineering thermophysics technology, and in particular to a thermal analysis method and system for a ceramic-based composite high-pressure turbine blade. Background Art

[0002] Conventional metal blades have isotropic thermal conductivity, meaning their thermal conductivity is uniform across the entire blade. However, ceramic matrix composites (CMCs) exhibit anisotropic thermal conductivity, meaning their thermal conductivity varies across different coordinate directions. Traditional numerical simulations, based on the thermal conductivity of isotropic solids, are no longer suitable for the anisotropic thermal conductivity of CMC materials and their application in high-pressure turbine blades. New thermal analysis methods are needed to address this issue.

[0003] The present invention aims to establish a method for quickly assigning the anisotropic thermal conductivity of CMC materials based on Fluent User Define Function (UDF), providing technical support for the gas-solid-thermal coupling analysis of CMC high-pressure turbine guide vanes.

[0004] Patent document CN117574527A discloses a method for anisotropic thermal analysis of CMC material turbine blades based on Fluent UDF. The patent document first solves the thermal conductivity tensor of three profile lines. However, when the bending and torsion differences of the blade profile along the blade height direction are large, the thermal conductivity assignment error of the patent document is large. The method proposed in this application is completely different. The present application adopts a method of first solving the thermal conductivity tensor of the entire outer surface of the blade, and then solving the thermal conductivity tensor of the internal grid points. When the blade profile has large differences along the blade height direction, the calculation and assignment accuracy of the thermal conductivity is guaranteed.

[0005] Furthermore, the patent document fails to consider the thermal conductivity of the blade's central ribs. The ribs' thermal conductivity is assigned values based on the proximity of the three profile lines, which is not rational. This application, however, considers the fiber orientation of the ribs and assigns values based on this orientation, improving both the rationality and accuracy of the thermal conductivity assignment.

[0006] In addition, the operation process provided by the patent document requires entering many commands in the console to implement the assignment method when operating UDF. When using UDF to calculate the thermal conductivity tensor, it is necessary to reserve memory space for the thermal conductivity tensor component of each grid node in advance to store specific data; and there are many files that need to be prepared before using UDF, and three blade profile coordinates need to be prepared separately. The anisotropic thermal conductivity automatic assignment system provided by this application uses MATLAB to calculate the thermal conductivity tensor. It only needs to prepare a file of the coordinate data of all points on the outer surface of the blade for MATLAB. The input file of UDF will be automatically generated by MATLAB. After mounting with compiled UDF, there is no need to allocate memory separately for the calculation grid points. The mounted UDF will automatically read the thermal conductivity tensor corresponding to the current grid calculation point. The operation is simple, and the mounting process does not require any console instructions. The process is clear, fast and convenient. Summary of the Invention

[0007] In view of the defects in the prior art, the purpose of the present invention is to provide a thermal analysis method and system for ceramic matrix composite high-pressure turbine blades.

[0008] According to the present invention, a thermal analysis method for a ceramic matrix composite high-pressure turbine blade is provided, comprising:

[0009] Step S1: generating a grid based on the turbine blade profile;

[0010] Step S2: Calculate and assign the thermal conductivity tensor based on the generated grid;

[0011] The thermal conductivity tensor includes the thermal conductivity tensor of the blade surface, the thermal conductivity tensor inside the blade body, and the thermal conductivity tensor of the ribs;

[0012] Step S3: Assign the thermal conductivity tensor and perform the final thermal conductivity or gas-solid-thermal coupling calculation, and output the calculation results.

[0013] Preferably, the step S2 includes outputting the overall three-dimensional grid coordinate data of the outer surface of the blade through grid software as input for solving the thermal conductivity tensor.

[0014] Preferably, the blade surface grid is obtained according to the grid points, and it is assumed that there are m layers of grid along the blade height direction, and the thermal conductivity tensor is solved for each layer of grid;

[0015] Solve for the thermal conductivity tensor at any mesh level:

[0016] Select the grid points P0, P1, P2 to P of the jth (j = 1, 2, 3, ..., m) layer blade surface grid n ; For point P i (i=1,2,3,……,n-1), use Pi-1 and P i+1 Solve for the slope and angle θ at two points;

[0017]

[0018] θ=arctan(slope)

[0019] Among them, P0 and P n Point connection, for point P0, P i-1 =P n , P i+1 =P1; for point P n , P i-1 =P n-1 , P i+1 = P0; Assume that the CMC fibers constituting the guide vanes are geometrically consistent with the outer contour of the blade section, and the rib fibers are parallel to the ribs, that is, the tensor K rotates around the z-axis only in the xOy plane;

[0020] According to the coordinate transformation principle of scalar tensor, solve point P i Thermal conductivity tensor K ij ';

[0021]

[0022] K′=Q T ·K·Q

[0023]

[0024] Among them, the tensor K is the thermal conductivity tensor along the fiber direction, K ξ is the thermal conductivity along the fiber direction, K η and K ζ It is the thermal conductivity of the other two coordinate directions perpendicular to the fiber direction, and the tensor Q is the coordinate transformation matrix;

[0025] The thermal conductivity tensor of all grid points on the entire blade surface is obtained by solving this problem.

[0026] Preferably, the calculation process of the thermal conductivity tensor inside the blade body includes:

[0027] Assuming the current calculation point P, find the point S closest to point P in the blade surface grid point coordinates. At this time, the PS connecting line is the normal direction of the outer contour line at point S, then the thermal conductivity tensor of point P is equal to the thermal conductivity tensor of point S.

[0028] Preferably, the rib surface grid is obtained according to the grid points. The rib surface is a structured grid. It is assumed that there are m layers of grid along the blade height direction. The thermal conductivity tensor is solved for each layer of grid.

[0029] Preferably, after the thermal conductivity tensor of all blade surface and rib surface grid points is solved, the component data of the thermal conductivity tensor are directly used as input for the numerical simulation calculation.

[0030] Preferably, step S3 includes using Fluent UDF to assign a thermal conductivity tensor and perform a final thermal conductivity or gas-solid-thermal coupling calculation; any grid type is applicable to the model mesh division during the numerical solution of this step.

[0031] When using a UDF, a compiled UDF is used, and all operations are performed using the DEFINE_EXECUTE_ON_LOADING macro function. During Fluent calculations, the specific anisotropic thermal conductivity component data is automatically loaded into the calculation grid points using DEFINE_ANISOTROPIC_CONDUCTIVITY. The thermal conductivity tensor calculation and assignment for the blade airfoil are performed within the UDF, and data is exchanged for each grid point during the numerical simulation.

[0032] A thermal analysis system for a ceramic matrix composite high-pressure turbine blade provided by the present invention comprises:

[0033] Module M1: Generate mesh based on turbine blade profile;

[0034] Module M2: Calculate and assign the thermal conductivity tensor based on the generated grid;

[0035] The thermal conductivity tensor includes the thermal conductivity tensor of the blade surface, the thermal conductivity tensor inside the blade body, and the thermal conductivity tensor of the ribs;

[0036] Module M3: Assign thermal conductivity tensor and perform final heat conduction or gas-solid-thermal coupling calculation, and output the calculation results.

[0037] Preferably, the module M2 includes outputting the overall three-dimensional grid coordinate data of the blade outer surface through grid software as input for solving the thermal conductivity tensor.

[0038] Preferably, the blade surface grid is obtained according to the grid points, and it is assumed that there are m layers of grid along the blade height direction, and the thermal conductivity tensor is solved for each layer of grid;

[0039] Solve for the thermal conductivity tensor at any mesh level:

[0040] Select the grid points P0, P1, P2 to P of the jth (j = 1, 2, 3, ..., m) layer blade surface grid n ; For point P i (i=1,2,3,……,n-1), use P i-1 and P i+1 Solve for the slope and angle θ at two points;

[0041]

[0042] θ=arctan(slope)

[0043] Among them, P0 and P n Point connection, for point P0, P i-1 =P n , P i+1 =P1; for point P n , P i-1 =P n-1 , P i+1 = P0; Assume that the CMC fibers constituting the guide vanes are geometrically consistent with the outer contour of the blade section, and the rib fibers are parallel to the ribs, that is, the tensor K rotates around the z-axis only in the xOy plane;

[0044] According to the coordinate transformation principle of scalar tensor, solve point P i Thermal conductivity tensor K ij ';

[0045]

[0046] K′=Q T ·K·Q

[0047]

[0048] Among them, the tensor K is the thermal conductivity tensor along the fiber direction, K ξ is the thermal conductivity along the fiber direction, K η and K ζ It is the thermal conductivity of the other two coordinate directions perpendicular to the fiber direction, and the tensor Q is the coordinate transformation matrix;

[0049] The thermal conductivity tensor of all grid points on the entire blade surface is obtained by solving this problem.

[0050] Preferably, the calculation process of the thermal conductivity tensor inside the blade body includes:

[0051] Assuming the current calculation point P, find the point S closest to point P in the blade surface grid point coordinates. At this time, the PS connecting line is the normal direction of the outer contour line at point S, then the thermal conductivity tensor of point P is equal to the thermal conductivity tensor of point S.

[0052] Preferably, the rib surface grid is obtained according to the grid points. The rib surface is a structured grid. It is assumed that there are m layers of grid along the blade height direction. The thermal conductivity tensor is solved for each layer of grid.

[0053] Preferably, after the thermal conductivity tensor of all blade surface and rib surface grid points is solved, the component data of the thermal conductivity tensor are directly used as input for the numerical simulation calculation.

[0054] Preferably, the module M3 includes using Fluent UDF to assign thermal conductivity tensor and perform final thermal conductivity or gas-solid-thermal coupling calculation; when this module is numerically solved, the model mesh division is applicable to any mesh type.

[0055] When using a UDF, a compiled UDF is used, and all operations are performed using the DEFINE_EXECUTE_ON_LOADING macro function. During Fluent calculations, the specific anisotropic thermal conductivity component data is automatically loaded into the calculation grid points using DEFINE_ANISOTROPIC_CONDUCTIVITY. The thermal conductivity tensor calculation and assignment for the blade airfoil are performed within the UDF, and data is exchanged for each grid point during the numerical simulation.

[0056] Compared with the prior art, the present invention has the following beneficial effects:

[0057] 1. This paper establishes a method for assigning the anisotropic thermal conductivity of CMC materials, and uses MATLAB and Fluent UDF to establish an automated anisotropic thermal conductivity assignment system, which solves the problem of quickly assigning the anisotropic thermal conductivity of CMC high-pressure turbine guide vanes and provides technical support for the coupled thermal analysis research of CMC high-pressure turbine guide vanes.

[0058] 2. The present invention adopts a method of first solving the thermal conductivity tensor of the entire outer surface of the blade and then solving the thermal conductivity tensor of the internal grid points. When the blade profile varies greatly along the blade height direction, the calculation and assignment accuracy of the thermal conductivity is guaranteed.

[0059] 3. The present invention takes the fiber orientation of the rib into consideration and assigns values separately according to the fiber orientation, thereby improving the rationality of the assignment of the thermal conductivity coefficient and the calculation accuracy.

[0060] 4. The anisotropic thermal conductivity automatic assignment system provided by the present invention uses MATLAB to calculate the thermal conductivity tensor. It is only necessary to prepare a file for MATLAB with the coordinate data of all points on the outer surface of the blade. The UDF input file will be automatically generated by MATLAB. After the compiled UDF is mounted, there is no need to allocate memory separately for the calculation grid points. The mounted UDF will automatically read the thermal conductivity tensor corresponding to the current grid calculation point. The operation is simple, and the mounting process does not require any console commands. The process is clear, fast and convenient.

[0061] Other beneficial effects of the present invention will be explained through the introduction of specific technical features and technical solutions in the specific implementation methods. Those skilled in the art should be able to understand the beneficial technical effects brought about by the introduction of these technical features and technical solutions. BRIEF DESCRIPTION OF THE DRAWINGS

[0062] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0063] Figure 1 Schematic diagram of the turbine blade of the present invention.

[0064] Figure 2 Flow chart of the method of the present invention.

[0065] Figure 3 This is a flow chart of assigning thermal conductivity tensor according to the grid in the present invention.

[0066] Figure 4 This is the blade surface grid diagram of the present invention.

[0067] Figure 5 This is the solution diagram for the thermal conductivity tensor of the blade outer profile in the present invention.

[0068] Figure 6 Schematic diagram of the rib surface grid of the present invention.

[0069] Figure 7 Schematic diagram of solving the thermal conductivity tensor of the rib in the present invention.

[0070] Figure 8 This is a flow chart of the automatic assignment system for anisotropic thermal conductivity of the present invention. DETAILED DESCRIPTION

[0071] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0072] Reference Figure 1 and Figure 2 As shown, a thermal analysis method for a ceramic matrix composite high-pressure turbine blade comprises:

[0073] Step 1: Generate a mesh based on the turbine blade profile. Commercial software such as Pointwise or ANSYS ICEM can be used to generate the mesh.

[0074] Step 2: Calculate and assign the thermal conductivity tensor according to the grid. This step is the core content, and the main steps are divided into the following Figure 3 As shown:

[0075] Step 2.1: Get the grid. The grid is as follows Figure 1 As shown in the figure, the mesh software outputs the three-dimensional mesh coordinate data of the blade's outer surface as input for solving the thermal conductivity tensor. This also facilitates the use of a user-defined function (UDF) to obtain the coordinates of each mesh node.

[0076] Step 2.2: Solve the thermal conductivity tensor of the blade surface. Obtain the blade surface mesh according to the grid points. The blade surface mesh is as follows: Figure 4 As shown in Figure 2, the blade surface is a structured grid. Assume that there are m layers of grid along the blade height. The thermal conductivity tensor is solved for each layer of grid.

[0077] Here the thermal conductivity tensor of any layer of mesh is solved.

[0078] like Figure 5 As shown, the grid points P0, P1, P2 to P n , where P0 and P n Point connection. For point P i (i=1,2,3,……,n-1), use P i-1 and P i+1 The slope and angle θ are solved by two points. The solution formulas are shown in equations (1) and (2). n Point connection, for point P0, P i-1 =P n , P i+1 =P1; for point P n , P i-1 =P n-1 , P i+1 =P0.

[0079]

[0080] θ=arctan(slope) (2)

[0081] According to the current process method, it is assumed that the orientation of the CMC fibers constituting the guide vane is geometrically consistent with the outer contour of the blade section, and the orientation of the rib fibers is parallel to the ribs, that is, the tensor K rotates around the z-axis only in the xOy plane.

[0082] According to the coordinate transformation principle of scalar tensor, the thermal conductivity tensor K of point Pi is solved by formulas (3), (4), and (5): ij '. Among them, the tensor K is the thermal conductivity tensor along the fiber direction, K ξis the thermal conductivity along the fiber direction, K η and K ζ It is the thermal conductivity of the other two coordinate directions perpendicular to the fiber direction, and the tensor Q is the coordinate transformation matrix.

[0083]

[0084]

[0085]

[0086] According to the above steps, the thermal conductivity tensor of all grid points on the entire blade surface can be obtained.

[0087] Step 2.3: Solve for the thermal conductivity tensor inside the blade.

[0088] After solving the thermal conductivity tensor of the blade surface, the remaining points inside the blade (except the ribs) are assigned values using the "nearest consistency" method, as follows: assuming the current calculation point P, find the point S closest to point P in the grid point coordinates of the blade surface. It is approximately assumed that the PS line is the normal direction of the outer contour line at point S, then the thermal conductivity tensor of point P is equal to the thermal conductivity tensor of point S, and so on.

[0089] Step 2.4: Solve for the thermal conductivity tensor of the ribs.

[0090] Get the rib surface mesh according to the mesh points, such as Figure 6 As shown in Figure 2, the rib surface is a structured grid, assuming that there are m layers of grid along the blade height. The thermal conductivity tensor is calculated for each layer of grid.

[0091] Here we solve the thermal conductivity tensor of any layer of grid, such as Figure 7 As shown, the same method as that for the blade can be used to obtain the grid point coordinates (p0, p1, p2, ..., pn) of the edge line, and solve the slope and rotation angle of each point respectively through equations (1) and (2), and then solve the thermal conductivity tensor through equations (3), (4), and (5).

[0092] Because rib structures are often simple, curve fitting is relatively easy. Therefore, mathematical methods or the polyfit function in MATLAB can be used to fit the curve formula using each grid point (p0, p1, p2, ..., pn). Assuming the fitted curve is f(x), equation (6) can be used instead of equation (1).

[0093] slope=f′(x) (6)

[0094] After the thermal conductivity tensor of all blade surface and rib surface grid points is solved, the data of each component of the thermal conductivity tensor is directly used as the input of the numerical simulation calculation.

[0095] Step 3: Perform numerical simulation. Use Fluent UDF to assign the thermal conductivity tensor and perform the final thermal conductivity or gas-solid-thermal coupling calculation. Any mesh type can be used for the model meshing during this numerical solution.

[0096] When using a UDF, a compiled UDF is used, and all operations are executed using the DEFINE_EXECUTE_ON_LOADING macro function. During Fluent calculations, the specific anisotropic thermal conductivity component data is automatically loaded into the calculation grid points using DEFINE_ANISOTROPIC_CONDUCTIVITY, eliminating the need for other operations such as the console. The thermal conductivity tensor calculation and assignment for the blade airfoil are performed within the UDF, and data is exchanged for each grid point during the numerical simulation.

[0097] The division of the blade surface mesh requires structured blade surface mesh data in the thermal conductivity tensor solution stage (i.e., step S2), but the thermal conductivity assignment in the numerical simulation stage (i.e., step S3) is applicable to any mesh type, that is, it can be a structured mesh or an unstructured mesh.

[0098] Based on the above method, an automatic assignment system for anisotropic thermal conductivity is implemented. The system uses MATLAB to calculate the thermal conductivity tensor and assigns the thermal conductivity tensor based on Fluent User Define Function. The program is designed as follows Figure 8 The basic framework is shown in the figure. CAE pre-processing requires the user to prepare the grid data points for calculation and the corresponding grid coordinate data file. MATLAB solves the thermal conductivity tensor for all blade surface grid points and automatically outputs the results to a text file as input for the user-defined function (UDF). This file contains the coordinate information of all blade surface grid points and the components of the corresponding thermal conductivity tensor. Fluent automatically executes and reads the thermal conductivity tensor data through the UDF and automatically assigns the values to all grid points requiring calculation using pre-programmed macro commands.

[0099] This method can also be used to assign anisotropic thermal conductivity to turbine blades with film holes. For blades with film holes, the thermal conductivity tensor can be calculated using the same blades without film holes in steps 1 and 2, and the turbine blades with film holes can be used for simulation calculations in step 3.

[0100] Those skilled in the art will appreciate that, in addition to implementing the system and its various devices, modules, and units provided by the present invention in purely computer-readable program code, it is entirely possible to implement the same functions of the system and its various devices, modules, and units provided by the present invention in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system and its various devices, modules, and units provided by the present invention can be considered a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; the devices, modules, and units for implementing various functions can also be considered as both software modules implementing the method and structures within the hardware component.

[0101] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A thermal analysis method for a ceramic matrix composite high-pressure turbine blade, characterized in that: include: Step S1: generating a mesh based on the turbine blade profile; Step S2: Calculate and assign the thermal conductivity tensor based on the generated grid; The thermal conductivity tensor includes the thermal conductivity tensor of the blade surface, the thermal conductivity tensor inside the blade body, and the thermal conductivity tensor of the ribs; Step S3: Assign the thermal conductivity tensor and perform the final thermal conductivity or gas-solid-thermal coupling calculation, and output the calculation results.

2. The thermal analysis method of a ceramic matrix composite high-pressure turbine blade according to claim 1, characterized in that: The step S2 includes outputting the overall three-dimensional grid coordinate data of the blade outer surface through grid software as input for solving the thermal conductivity tensor.

3. The thermal analysis method of a ceramic matrix composite high-pressure turbine blade according to claim 2, characterized in that: Obtain the blade surface grid based on the grid points. Assuming that there are m layers of grid along the blade height, solve the thermal conductivity tensor for each layer of grid. Solve for the thermal conductivity tensor at any mesh level: Select the grid points P0, P1, P2 to P of the jth (j = 1, 2, 3, ..., m) layer blade surface grid n ; For point P i (i=1,2,3,……,n-1), use P i-1 and P i+1 Solve for the slope and angle θ at two points; θ=arctan(slope) Among them, P0 and P n Point connection, for point P0, P i-1 =P n , P i+1 =P1; for point P n , P i-1 =P n-1 , P i+1 = P0; Assume that the CMC fibers constituting the guide vanes are geometrically consistent with the outer contour of the blade section, and the rib fibers are parallel to the ribs, that is, the tensor K rotates only around the z-axis in the xOy plane; According to the coordinate transformation principle of scalar tensor, solve point P i Thermal conductivity tensor K ij '; K′=Q T ·K·Q Among them, the tensor K is the thermal conductivity tensor along the fiber direction, K ξ is the thermal conductivity along the fiber direction, K η and K ζ It is the thermal conductivity of the other two coordinate directions perpendicular to the fiber direction, and the tensor Q is the coordinate transformation matrix; The thermal conductivity tensor of all grid points on the entire blade surface is obtained by solving this problem.

4. The thermal analysis method of a ceramic matrix composite high-pressure turbine blade according to claim 3, characterized in that: The calculation process of the thermal conductivity tensor inside the blade body includes: Assuming the current calculation point P, find the point S closest to point P in the blade surface grid point coordinates. At this time, the PS connecting line is the normal direction of the outer contour line at point S, then the thermal conductivity tensor of point P is equal to the thermal conductivity tensor of point S.

5. The thermal analysis method of a ceramic matrix composite high-pressure turbine blade according to claim 4, characterized in that: The rib surface mesh is obtained based on the grid points. The rib surface is a structured mesh. Assuming that there are m layers of mesh along the blade height direction, the thermal conductivity tensor is solved for each layer of mesh.

6. The thermal analysis method of a ceramic matrix composite high-pressure turbine blade according to claim 5, characterized in that: After the thermal conductivity tensor of all grid points is solved, the data of each component of the thermal conductivity tensor are directly used as the input of the numerical simulation calculation.

7. The thermal analysis method of a ceramic matrix composite high-pressure turbine blade according to claim 1, characterized in that: The step S3 includes using Fluent UDF to assign a thermal conductivity tensor and perform a final heat conduction or gas-solid-thermal coupling calculation; When using UDF, a compiled UDF is used, and all operations are performed using the DEFINE_EXECUTE_ON_LOADING macro function. During Fluent calculations, the specific anisotropic thermal conductivity component data is automatically read into the calculation grid points through DEFINE_ANISOTROPIC_CONDUCTIVITY.

8. A thermal analysis system for ceramic matrix composite high-pressure turbine blades, characterized in that: include: Module M1: Generate mesh based on turbine blade profile; Module M2: Calculate and assign the thermal conductivity tensor based on the generated grid; The thermal conductivity tensor includes the thermal conductivity tensor of the blade surface, the thermal conductivity tensor inside the blade body, and the thermal conductivity tensor of the ribs; Module M3: Assign thermal conductivity tensor and perform final heat conduction or gas-solid-thermal coupling calculation, and output the calculation results.

9. The thermal analysis system for ceramic matrix composite high-pressure turbine blades according to claim 8, characterized in that: The module M2 includes outputting the overall three-dimensional grid coordinate data of the blade outer surface through grid software as input for solving the thermal conductivity tensor.

10. The thermal analysis system for ceramic matrix composite high-pressure turbine blades according to claim 9, characterized in that: Obtain the blade surface grid based on the grid points. Assuming that there are m layers of grid along the blade height, solve the thermal conductivity tensor for each layer of grid. Solve for the thermal conductivity tensor at any mesh level: Select the grid points P0, P1, P2 to P of the jth (j = 1, 2, 3, ..., m) layer blade surface grid n ; For point P i (i=1,2,3,……,n-1), use P i-1 and P i+1 Solve for the slope and angle θ at two points; θ=arctan(slope) Among them, P0 and P n Point connection, for point P0, P i-1 =P n , P i+1 =P1; for point P n , P i-1 =P n-1 , P i+1 = P0; Assume that the CMC fibers constituting the guide vanes are geometrically consistent with the outer contour of the blade section, and the rib fibers are parallel to the ribs, that is, the tensor K rotates only around the z-axis in the xOy plane; According to the coordinate transformation principle of scalar tensor, solve point P i Thermal conductivity tensor K ij '; K′=Q T ·K·Q Among them, the tensor K is the thermal conductivity tensor along the fiber direction, K ξ is the thermal conductivity along the fiber direction, K η and K ζ It is the thermal conductivity of the other two coordinate directions perpendicular to the fiber direction, and the tensor Q is the coordinate transformation matrix; The thermal conductivity tensor of all grid points on the entire blade surface is obtained by solving this problem.

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