A method for analyzing the thermal shock resistance of ceramic matrix composite turbine guide blades

Abstract

The present invention discloses a method for analyzing the thermal shock resistance of ceramic-based composite (CMC) turbine guide blades. The method comprises the following steps: first, establishing a geometric model reflecting the process characteristics of CMC turbine guide blades; second, performing transient flow-thermal coupling calculations on the CMC turbine guide blades under given operating conditions to obtain the temperature variation of the blades over time; third, defining the material properties and principal unit directions of the CMC turbine guide blades and performing meshing; fourth, performing quasi-static stress calculations on the CMC turbine guide blades using the node temperature at a certain moment as the thermal load; and fifth, performing progressive damage analysis at a typical moment to determine the damage location and failure mode of the CMC turbine guide blades. This method fills a gap in the existing thermal shock resistance analysis methods for CMC turbine guide blades, taking into account the influence of anisotropy on the thermal, mechanical, and nonlinear mechanical properties of CMCs, and accurately predicting the thermal shock damage location and failure mode of CMC turbine guide blades.

Description

Technical Field

[0001] The present invention relates to the field of composite material strength calculation, and in particular to a method for analyzing the thermal shock resistance of a ceramic-based composite material turbine guide blade. Background Art

[0002] Turbine guide vanes are subject to the harshest operating environment among engine hot-end components, requiring them to withstand a range of harsh environments, including high temperatures, oxidation, corrosion, thermal fatigue, and thermal shock. Their reliability and durability directly impact the service life of the entire aircraft engine. However, high-temperature alloy guide vanes have currently reached their operating temperature limits. Ceramic matrix composites (CMCs), particularly those reinforced with silicon carbide fibers, offer advantages such as high-temperature resistance, lightweight, and resistance to oxidation and ablation, making them the preferred materials for advanced aircraft engine hot-end components.

[0003] During engine startup and shutdown, the rapid changes in temperature and speed cause the temperature distribution of turbine blades to exhibit strong transient characteristics, resulting in transient high-stress areas and thermal shock damage to the blades. During engine cyclic operation, thermal shock cycles can easily cause cracks in the blades, leading to the risk of blade fracture and failure. Ceramic-based composite turbine guide vanes have low thermal conductivity, which can easily lead to large transient temperature differences. Thermal shock strength analysis and failure modes are complex, and there is a lack of transient thermal shock analysis methods that consider the anisotropy of CMC thermal, mechanical, and nonlinear mechanical properties.

[0004] Therefore, it is urgent to explore a simulation analysis method for the thermal shock resistance of ceramic matrix composite turbine guide blades to accurately predict the thermal shock damage location and failure mode of turbine guide blades, and promote the improvement of the design and analysis technology of ceramic matrix composite turbine guide blades. Summary of the Invention

[0005] The purpose of the present invention is to provide a method for analyzing the thermal shock resistance of ceramic-based composite turbine guide blades. Based on the characteristics of parameter anisotropy and diversity of damage forms of ceramic-based composite materials, the transient temperature and thermal stress distribution of the turbine guide blades are calculated based on the fluid-thermal-solid coupling simulation method, and the damage location and failure mode of the blades are solved using the progressive damage method.

[0006] In order to achieve the above technical objectives, the technical solution adopted by the present invention is:

[0007] A method for analyzing the thermal shock resistance of a ceramic matrix composite turbine guide blade comprises the following steps:

[0008] Step 1: Establish a blade geometry model that reflects the process characteristics of ceramic matrix composite turbine guide blades, and establish the fluid and solid computational domains based on actual operating conditions;

[0009] Step 2: Define the principal element directions of the blade geometry model based on the fiber weaving direction of the ceramic matrix composite turbine guide blade, assign equivalent anisotropic thermal performance parameters to the blade geometry model, and perform transient flow-heat bidirectional coupling calculations in the fluid and solid computational domains under given boundary conditions to solve the temperature change data of the ceramic matrix composite turbine guide blade at any time during the process from startup to steady state.

[0010] Step 3: Establish a finite element model of the ceramic matrix composite turbine guide blade, assign equivalent anisotropic thermal performance parameters and elastic mechanical parameters to the finite element model, and define the unit main direction of the finite element model according to the fiber orientation of the ceramic matrix composite turbine guide blade;

[0011] Step 4: Import the node temperatures at different times in the temperature change data obtained in Step 2 as thermal loads into the finite element model, and impose constraints on the finite element model to perform finite element analysis of the ceramic matrix composite turbine guide blade. Simplify the blade transient thermal stress analysis into a quasi-static stress analysis at different times, thereby obtaining the anisotropic thermal stress distribution of the ceramic matrix composite turbine guide blade at the corresponding time.

[0012] Step 5: According to the anisotropic thermal stress distribution of the ceramic matrix composite turbine guide blade at the corresponding moment, the high stress area of ​​the ceramic matrix composite turbine guide blade at each moment can be known. The high stress area is the easily damaged part of the blade after thermal shock. The node coordinates of the easily damaged part and the temperature data corresponding to the node coordinates are extracted. The typical moment is selected for progressive damage analysis to obtain the damage position and failure mode of the blade after thermal shock, and the thermal shock resistance analysis of the ceramic matrix composite turbine guide blade is completed.

[0013] To optimize the technical solution, the present invention is further improved as follows:

[0014] The ceramic-based composite material turbine guide blade is a two-dimensional plain-woven double-cold air cavity structure. The ceramic-based composite material turbine guide blade includes a hollow blade body. A rib extending in the span direction is provided in the middle of the blade body. The upper end of the rib is connected to the upper edge surface of the blade body, and the lower end of the rib is connected to the lower edge surface of the blade body. The rib separates the front cold air cavity and the rear cold air cavity in the blade body. An air film hole connecting the outside of the blade body and the corresponding cold air cavity is provided on the blade body. The trailing edge of the blade body is an open trailing edge.

[0015] The ceramic matrix composite turbine guide blade is periodic in the span direction. A periodic region is selected as the fluid and solid calculation domains. The fluid calculation domain includes the external fluid calculation domain and the internal fluid calculation domain. The external fluid calculation domain is the gas region outside the ceramic matrix composite turbine guide blade, the solid region is the ceramic matrix composite turbine guide blade itself, and the internal fluid calculation domain is the gas region of the front cooling air cavity and the rear cooling air cavity.

[0016] In step 2, the unit main direction of the blade geometric model is defined according to the fiber weaving direction of the ceramic matrix composite turbine guide blade: the coordinate direction is defined according to the warp yarn, weft yarn and layer thickness direction of the ceramic matrix composite turbine guide blade.

[0017] In step 2, the equivalent anisotropic thermal performance parameters specifically include the density, thermal conductivity and specific heat capacity of the material; the given boundary conditions are the working conditions of high-temperature gas impact and cold air cooling under the actual service of the ceramic matrix composite turbine guide blades, and the flow-heat bidirectional coupling is the process of mutual influence between fluid flow and solid heat conduction. The specific process of transient flow-heat bidirectional coupling calculation is to first mesh the fluid calculation domain and the solid calculation domain, and the coupling surface of the fluid calculation domain and the solid calculation domain share the topology, and use CFD software to perform transient calculation of the blade flow-heat coupling to obtain the temperature change data of the ceramic matrix composite turbine guide blade at any time from startup to stability.

[0018] In step 3, after establishing the finite element model of the ceramic matrix composite turbine guide blade, the ceramic matrix composite turbine guide blade in the finite element model is meshed. The meshing of the finite element model is consistent with the meshing of the solid calculation domain. The equivalent anisotropic thermal performance parameters and elastic mechanical parameters of the finite element model specifically include the material's density, thermal conductivity, thermal expansion coefficient, specific heat capacity, elastic modulus, Poisson's ratio and shear modulus.

[0019] In step 4, the node temperatures obtained in step 2 are imported into the finite element model as thermal loads by inputting the node temperatures of the solid computational domain mesh into the mesh of the finite element model one by one.

[0020] In step 4, the constraint condition refers to limiting the degree of freedom of the ceramic matrix composite material turbine guide blade according to the constraint condition of the ceramic matrix composite material turbine guide blade in the engine, and the constraint condition includes displacement constraint, fixation constraint and friction constraint.

[0021] In step 5, the typical moment refers to the moment with a transient high stress change in the transient stress change of the vulnerable part.

[0022] In step 5, typical moments include the moments of fiber tensile failure, compression failure, in-plane shear failure, and air film hole edge failure at vulnerable locations.

[0023] The present invention has the following beneficial effects: Currently available turbine blade thermal shock simulation and analysis methods are primarily targeted at metal blades. Due to the anisotropic thermal / mechanical properties of CMCs, nonlinear mechanical properties, and complex damage and failure modes, existing research on thermal shock of CMC blades has primarily relied on experimental thermal shock cycle performance testing and damage characterization, and no thermal shock simulation and analysis methods applicable to CMC blades exist. The present invention provides a method for simulating the thermal shock resistance of ceramic matrix composite (CMC) turbine guide blades. First, utilizing a bidirectional fluid-thermal coupling calculation that considers anisotropic thermal conductivity, the fluid and solid computational domains are simultaneously solved and data is transferred in real time, accurately calculating the transient temperature distribution of CMC blades subjected to thermal shock. Furthermore, using the thermal-solid coupling solution, the transient thermal stress dynamic simulation is simplified into a quasi-static thermal stress simulation at different moments during the thermal shock process, enabling the determination of typical transient high stress moments and their corresponding anisotropic stress distributions. Finally, a progressive damage algorithm is used to further analyze the damage location and failure mode of the blades at these typical high thermal stress moments. The present invention provides an effective means for strength prediction and failure mode assessment of CMC turbine guide blades subjected to thermal shock. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 This is a schematic diagram of the thermal shock simulation calculation process of ceramic matrix composite turbine guide blades;

[0025] Figure 2 is a blade geometric model of an embodiment of the present invention;

[0026] Figure 3 1 and 2 are the fluid computational domain and solid computational domain meshes of an embodiment of the present invention; wherein (a) is the fluid computational domain mesh, and (b) is the solid computational domain mesh;

[0027] Figure 4 : is the blade temperature field calculation result of the embodiment of the present invention; wherein (a) is the blade pressure surface temperature at 2s; (b) is the blade suction surface temperature at 2s; (c) is the blade pressure surface temperature at steady state; (d) is the blade suction surface temperature at steady state;

[0028] Figure 5 Calculation results of warp direction stress of the blade in the embodiment of the present invention after reaching steady state; wherein (a) is the warp direction stress of the pressure side, and (b) is the warp direction stress of the suction side;

[0029] Figure 6 This is the calculation result of thermal shock damage of the blade in the embodiment of the present invention at 2s;

[0030] Figure 7 This is a schematic diagram of the camber line of the blade profile of a ceramic matrix composite turbine guide blade;

[0031] Figure 8 This is a schematic diagram of the periodic surface in the fluid calculation domain of the ceramic matrix composite turbine guide blade;

[0032] Figure 9 It is a schematic diagram of the axis of the ceramic matrix composite turbine guide blade.

[0033] The reference numerals in the figure are: blade body 1, rib 2, front cooling air cavity 3, rear cooling air cavity 4, air film hole 5, spoiler column array 6, open trailing edge 7. DETAILED DESCRIPTION

[0034] In order to make the purpose, technical solutions and advantages of this application more clearly understood, the present application is described and illustrated below in conjunction with the accompanying drawings and examples. It should be understood that the specific embodiments described herein are merely used to explain this application and are not intended to limit this application. Based on the embodiments provided in this application, all other embodiments obtained by those of ordinary skill in the art without making any creative efforts are within the scope of protection of this application.

[0035] Obviously, the drawings described below are merely examples or embodiments of the present application. Those skilled in the art can, without inventive effort, apply the present application to other similar scenarios based on these drawings. Furthermore, it is also understood that, although the effort involved in such a development process may be complex and lengthy, for those skilled in the art related to the content disclosed in this application, changes in design, manufacturing, or production based on the technical content disclosed in this application are merely conventional technical means and should not be construed as an insufficiency of the content disclosed in this application.

[0036] References to "embodiments" in this application mean that a particular feature, structure, or characteristic described in connection with the embodiment may be included in at least one embodiment of the application. The appearance of this phrase in various places in the specification does not necessarily refer to the same embodiment, nor does it refer to independent or alternative embodiments that are mutually exclusive of other embodiments. It is understood, both explicitly and implicitly, by those skilled in the art that the embodiments described in this application may be combined with other embodiments unless there is a conflict.

[0037] Unless otherwise defined, the technical or scientific terms used in this application should have the ordinary meaning understood by a person of ordinary skill in the technical field to which this application belongs. The words "a", "an", "a", "the" and the like used in this application do not indicate a limit on quantity and may indicate the singular or plural. The terms "include", "comprise", "have" and any variations thereof used in this application are intended to cover non-exclusive inclusions; for example, a process, method, system, product or device that includes a series of steps or units (units) is not limited to the listed steps or units, but may also include steps or units that are not listed, or may also include other steps or units that are inherent to these processes, methods, products or devices. The words "connect", "connected", "coupled" and the like used in this application are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. The words "multiple" / "several" used in this application refer to two or more. "And / or" describes the association relationship between associated objects, indicating that three relationships can exist. For example, "A and / or B" can mean: A exists alone, A and B exist at the same time, or B exists alone. The character " / " generally indicates that the objects before and after are in an "or" relationship. The terms "first", "second", "third", etc. involved in this application are only used to distinguish similar objects and do not represent a specific order for the objects.

[0038] The present invention discloses a method for analyzing the thermal shock resistance of a ceramic matrix composite turbine guide blade. Taking a two-dimensional plain weave ceramic matrix composite turbine guide blade as an example, the method comprises the following steps:

[0039] The first step is to use 3D modeling software to establish a blade geometry model. The model is a two-dimensional plain weave double-cooling cavity structure. Since the turbine guide blades are periodic, a single periodic area is selected as the calculation domain for analysis. The model establishes fluid and solid calculation domains according to actual working conditions; the actual working conditions include the range of the fluid domain, whether the fluid domain is cooled, etc. The fluid and solid calculation domains include the external fluid calculation domain, the solid calculation domain and the internal fluid calculation domain. The external fluid calculation domain is formed by a periodic plane constrained fluid. The two ends of the middle arc line are extended along the tangential direction to form two straight line segments to the inlet and outlet boundaries. The shape of the periodic boundary is basically determined. Then, the periodic boundary can be obtained by axially translating half the pitch to the left and right. Among them, the middle arc line refers to the line connecting the centers of the inscribed circles of the blade profile, and extends from the centers of the leading and trailing edges in the tangential direction to the line intersecting the leading and trailing edges. The axial direction refers to the direction parallel to the engine axis, that is, the movement in the direction of the engine axis. Specifically, Figure 7-9 shown.

[0040] In the second step, first, the main unit direction of the blade is redefined according to the two-dimensional laying method of the CMC blade, where the local coordinate system X direction is defined as the weft direction, the Y direction is defined as the warp direction (i.e. the blade height direction), and the Z direction is defined as the layer thickness direction. The fluid calculation domain and the solid calculation domain are meshed using finite element software, such as Figure 3 As shown in the figure, the fluid-structure coupling surface adopts a shared topology, which enables one-to-one correspondence between grid nodes and generates an unstructured grid.

[0041] The thermal performance parameters of ceramic matrix composite materials are set, mainly including density, thermal conductivity and specific heat capacity. Among them, the thermal conductivity in the blade height direction is 19W / (m·K), and in other directions it is 9W / (m·K). CFD software is used to perform transient flow-heat coupling calculations of turbine guide blades. The transient mode is selected for calculation, and the energy equation is turned on. According to the actual working conditions, the standard k-ε turbulence model is used. The mainstream gas uses the pressure inlet and outlet boundaries, and the cold gas uses the mass flow inlet and outlet boundaries. The blade is initially set to room temperature, and the time step is set to 0.001s. The calculation takes 30s to make the blade reach a stable state. Finally, the temperature distribution of the blade from startup to the stable state is obtained, as shown below. Figure 4 As shown;

[0042] The third step is to perform finite element analysis pre-processing on the structure and mesh the structure. The meshing should be consistent with the solid calculation domain mesh in the second step to make data import more accurate. The main directions of the unit cells are also defined according to the method in the second step. The equivalent anisotropic thermal performance parameters and elastic mechanical parameters of the ceramic matrix composite material are defined, including the material's density, thermal conductivity, thermal expansion coefficient, specific heat capacity, elastic modulus, Poisson's ratio, and shear modulus.

[0043] The fourth step is to read the node temperature at a specific moment, obtained from the transient flow-heat coupling analysis in the second step, as the thermal load. Considering the relatively small constraints on the guide vanes in a real engine, the blade ends are not constrained in the thermal stress calculation. Only the temperature field at the same moment is loaded as the calculation condition, and a finite element analysis of the blade structure is performed. This step simplifies the transient thermal stress analysis of the blade into a quasi-static stress analysis at different moments, thereby obtaining the thermal stress distribution of each component of the blade at the corresponding moment and the transient changes of each stress component at each location. The analysis shows that the blade is subjected to significant stress in the warp direction, with the overall stress level increasing continuously and remaining stable for approximately 15 seconds. The pressure surface is subject to high compressive stress on both sides of the third row of film holes 5, while the leading edge inner surface is subject to high tensile stress on both sides of the film holes 5. From the transient changes of high stress parts in the warp direction, it can be seen that transient high stress appears in the warp direction at 2s, and the high stress area is concentrated around the air film hole 5; for shear stress, the blade is subjected to large YZ shear stress, and the high stress area is mainly distributed at the connection between the trailing edge spoiler and the inner wall of the blade, and the connection between the rib 2 and the inner wall. Similarly, transient high stress changes appear in the high stress parts at 2s, such as Figure 5 As shown;

[0044] The fifth step, from the fourth step, we know the high stress areas at each moment and the transient high stress generated at 2s. These areas may be the parts where the blade is damaged after thermal shock. 2s is the moment when damage is prone to occur. Based on the operation of the fourth step, the node coordinates and corresponding temperature data of the turbine guide blade at each moment are extracted, and the progressive damage algorithm is used to solve the damage position and failure mode of the turbine guide blade after thermal shock. The results show that the ceramic matrix composite turbine guide blade has almost no damage in the X direction, Y direction and XY direction, and the damaged units are mainly concentrated in the XZ direction and YZ direction. The blade has the most damaged units at 2s, but it only accounts for 0.246% of the total number of blade units. The damage in the YZ direction mainly occurs on the last row of spoiler columns and the intersection of rib 2 and the inner wall of the blade. The damage in the XZ direction mainly occurs on the middle row of spoiler columns. Figure 6 The damaged element is shown below the middle blade.

[0045] The above are merely preferred embodiments of the present invention. The scope of protection of the present invention is not limited to the above embodiments. All technical solutions based on the principles of the present invention are within the scope of protection of the present invention. It should be noted that for those skilled in the art, various improvements and modifications that do not depart from the principles of the present invention should be considered within the scope of protection of the present invention.

Claims

1. A method for analyzing the thermal shock resistance of ceramic matrix composite turbine guide blades, characterized in that: The following steps are involved: Step 1: Establish a blade geometry model that reflects the process characteristics of ceramic matrix composite turbine guide blades, and establish the fluid and solid computational domains based on actual operating conditions; Step 2: Define the principal element directions of the blade geometry model based on the fiber weaving direction of the ceramic matrix composite turbine guide blade, assign equivalent anisotropic thermal performance parameters to the blade geometry model, and perform transient flow-heat bidirectional coupling calculations in the fluid and solid computational domains under given boundary conditions to solve the temperature change data of the ceramic matrix composite turbine guide blade at any time during the process from startup to steady state. Step 3: Establish a finite element model of the ceramic matrix composite turbine guide blade, assign equivalent anisotropic thermal performance parameters and elastic mechanical parameters to the finite element model, and define the unit main direction of the finite element model according to the fiber orientation of the ceramic matrix composite turbine guide blade; Step 4: Import the node temperatures at different times in the temperature change data obtained in Step 2 as thermal loads into the finite element model, and impose constraints on the finite element model to perform finite element analysis of the ceramic matrix composite turbine guide blade. Simplify the blade transient thermal stress analysis into a quasi-static stress analysis at different times, thereby obtaining the anisotropic thermal stress distribution of the ceramic matrix composite turbine guide blade at the corresponding time. Step 5: Based on the anisotropic thermal stress distribution of the ceramic matrix composite turbine guide blade at the corresponding time, the high stress area of ​​the ceramic matrix composite turbine guide blade at each time can be known. The high stress area is the vulnerable part of the blade after thermal shock. The node coordinates of the vulnerable part and the temperature data corresponding to the node coordinates are extracted. The typical time is selected for progressive damage analysis to obtain the damage location and failure mode of the blade after thermal shock, thus completing the thermal shock resistance analysis of the ceramic matrix composite turbine guide blade; In step 2, the equivalent anisotropic thermal performance parameters specifically include the density, thermal conductivity and specific heat capacity of the material; the given boundary conditions are the working conditions of high-temperature gas impact and cold air cooling under the actual service of the ceramic matrix composite turbine guide blade. The fluid-heat bidirectional coupling is the process of mutual influence between fluid flow and solid heat conduction. The specific process of transient flow-heat bidirectional coupling calculation is to first mesh the fluid calculation domain and the solid calculation domain, and the coupling surface of the fluid calculation domain and the solid calculation domain share the topology. The CFD software is used to perform transient calculation of the blade flow-heat coupling to obtain the temperature change data of the ceramic matrix composite turbine guide blade at any time from startup to stabilization.

2. The method for analyzing the thermal shock resistance of a ceramic matrix composite turbine guide blade according to claim 1, characterized in that: The ceramic-based composite turbine guide blade is a two-dimensional plain-woven double-cold air cavity structure. The ceramic-based composite turbine guide blade includes a hollow blade body (1). A rib (2) extending in the span direction is provided in the middle of the blade body (1). The upper end of the rib (2) is connected to the upper edge surface of the blade body (1), and the lower end of the rib (2) is connected to the lower edge surface of the blade body (1). The rib (2) separates a front cold air cavity (3) and a rear cold air cavity (4) in the blade body (1). An air film hole (5) is provided on the blade body (1) to connect the outside of the blade body (1) and the corresponding cold air cavity. The trailing edge of the blade body (1) is an open trailing edge.

3. The method for analyzing the thermal shock resistance of a ceramic matrix composite turbine guide blade according to claim 2, characterized in that: The ceramic matrix composite turbine guide blade has periodicity in the span direction, and a periodic region is selected as a fluid and solid calculation domain. The fluid calculation domain includes an external fluid calculation domain and an internal fluid calculation domain. The external fluid calculation domain is the gas region outside the ceramic matrix composite turbine guide blade, the solid region is the ceramic matrix composite turbine guide blade itself, and the internal fluid calculation domain is the gas region of the front cooling air cavity (3) and the rear cooling air cavity (4). The external fluid calculation domain is formed by a periodic plane constrained fluid, and two straight line segments are extended from the two ends of the mid-arc along the tangent direction to the inlet and outlet boundaries, and the shape of the periodic boundary is basically determined.

4. The method for analyzing the thermal shock resistance of ceramic matrix composite turbine guide blades according to claim 3, characterized in that: In step 2, the unit main direction of the blade geometric model is defined according to the fiber weaving direction of the ceramic matrix composite turbine guide blade: the coordinate direction is defined according to the warp yarn, weft yarn and layer thickness direction of the ceramic matrix composite turbine guide blade.

5. The method for analyzing the thermal shock resistance of ceramic matrix composite turbine guide blades according to claim 4, characterized in that: In step 3, after establishing the finite element model of the ceramic matrix composite turbine guide blade, the ceramic matrix composite turbine guide blade in the finite element model is meshed. The meshing of the finite element model is consistent with the meshing of the solid calculation domain. The equivalent anisotropic thermal performance parameters and elastic mechanical parameters of the finite element model specifically include the material's density, thermal conductivity, thermal expansion coefficient, specific heat capacity, elastic modulus, Poisson's ratio and shear modulus.

6. The method for analyzing the thermal shock resistance of ceramic matrix composite turbine guide blades according to claim 5, characterized in that: In step 4, the node temperatures obtained in step 2 are imported into the finite element model as thermal loads by inputting the node temperatures of the solid computational domain mesh into the mesh of the finite element model one by one.

7. The method for analyzing the thermal shock resistance of ceramic matrix composite turbine guide blades according to claim 5, characterized in that: In step 4, the constraint conditions refer to limiting the degrees of freedom of the ceramic matrix composite material turbine guide blades based on the constraints imposed on the ceramic matrix composite material turbine guide blades in the engine as constraint conditions, and the constraint conditions include displacement constraints, fixed constraints and friction constraints.

8. The method for analyzing the thermal shock resistance of ceramic matrix composite turbine guide blades according to claim 1, characterized in that: In step 5, the typical moment refers to the moment with a transient high stress change in the transient stress change of the vulnerable part.

9. The method for analyzing the thermal shock resistance of ceramic matrix composite turbine guide blades according to claim 8, characterized in that: In step 5, typical moments include the moments of fiber tensile failure, compression failure, in-plane shear failure, and air film hole edge failure at vulnerable locations.

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