CMC Gas Turbine Outer Ring Simulator and Its Design Method

Abstract

This invention discloses a CMC gas turbine outer ring simulation component and its design method, comprising the following steps: S1: Obtain the fiber orientation distribution and porosity distribution of the real component; based on the fiber orientation distribution, porosity distribution, and material parameters under service conditions of the real component, establish a finite element model of the real component with thermo-mechanical-oxidative multi-field coupling; S2: Use multi-scale analysis to determine the damage location and damage parameter distribution curve of the real component; S3: Design the simulation component based on the damage location of the real component; S4: Verify the consistency between the simulation component and the real component; if the consistency meets the design requirements, output the design results; if the consistency does not meet the requirements, use the damage parameter distribution curve to correct the size of the simulation component, and repeat step S4. Compared with the prior art, this scheme achieves accurate simulation of the service performance of the real component, and significantly reduces the test cost and test cycle of the CMC gas turbine outer ring.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engine hot-end component test, in particular, relates to a CMC gas turbine outer ring simulation piece design method. Furthermore, it also relates to a CMC gas turbine outer ring simulation piece adopting the CMC gas turbine outer ring simulation piece design method. BACKGROUND

[0002] The progress of aero-engine technology has always revolved around the core goal of improving the thrust-to-weight ratio, and the lightweight of hot-end components is a key path to achieve this goal. With the continuous increase of turbine inlet temperature, traditional nickel-based superalloys have gradually reached their performance limits. In this context, ceramic matrix composites (CMC) are becoming the ideal choice for the next generation of aero-engine hot-end components due to their excellent high-temperature resistance (long-term use temperature can reach more than 1200℃), significant low-density characteristics (only 1 / 3 of nickel-based alloys), and excellent creep resistance. Among them, the gas turbine outer ring, as a key stator component surrounding the turbine rotor, directly affects the overall efficiency and reliability of the engine.

[0003] However, the gas turbine outer ring faces extremely harsh working environments during actual service. First, the gas turbine outer ring needs to withstand high-temperature gas periodic scouring of up to 1500℃ or more, while cooperating with the cooling system to form a sharp temperature gradient, causing the material to experience a complex thermal mechanical fatigue process; second, the non-uniform aerodynamic pressure generated by high-speed airflow, rotor interference vibration, and assembly prestress, etc. combined load makes the gas turbine outer ring in a multi-axial stress state; more critically, actual failure often starts from certain specific areas, such as the high heat flux area of the aerodynamic profile, the stress concentration area of the cooling hole edge, or the mortise and tenon connection interface, etc. The damage evolution of these local areas directly affects the service life of the gas turbine outer ring. Therefore, in order to realize the engineering application of CMC gas turbine outer ring in aero-engine, while reducing the cost and shortening the cycle of engineering application, related simulation pieces are often designed and manufactured to accurately simulate the service performance of real components.

[0004] However, the design materials of existing analogues are mostly high-temperature alloy materials. For example, CN CN120493569A discloses a design method of a periodically arranged porous thin-walled combustion chamber flame tube feature analogue, determines the dangerous position of the combustion chamber flame tube through flow-heat-solid coupling analysis, introduces an initial crack in the analogue and carries out crack propagation simulation, optimizes the parameters of the porous array to make the stress gradient consistent with the real component, and adopts a biaxial tensile test to match the stress intensity factor under different crack lengths, thereby providing an effective method for damage tolerance evaluation and life prediction of an aero-engine combustion chamber. For example, CN120217805A discloses a simulation piece design method based on stress gradient fitting and a blade root feature simulation piece, determines the dangerous area and feature parameters of the turbine blade through simulation, designs the simulation piece examination section configuration based on the low-cycle fatigue criterion; normalizes and compares the stress gradients of the blade and the simulation piece, adjusts the non-feature parameters to control the error; finally, designs the clamping section and the transition section that meet the strength requirements, and completes the overall configuration of the blade root feature simulation piece. Since CMC and high-temperature alloy materials have great differences in mechanical properties, the simulation piece obtained by using the existing simulation piece design method in the design of a CMC gas turbine outer ring simulation piece cannot accurately reflect the complex geometric features of the real CMC gas turbine outer ring, resulting in significant deviation of the stress concentration area and temperature distribution from the actual working condition, and the reliability of the test results is low. Although the full-size real piece test can obtain the most reliable data, the high cost and long cycle of the full-size real piece test seriously restrict the research and development efficiency. According to relevant research statistics, the cost of a complete gas turbine outer ring full-size thermal fatigue test exceeds 10 million yuan, and the cycle is more than 12 months.

[0005] In summary, there is an urgent need for a design method of a CMC gas turbine vane analogue to realize the engineering application of a CMC gas turbine outer ring in an aero-engine. SUMMARY

[0006] The present application provides a CMC gas turbine outer ring simulation piece and a design method thereof to solve the technical problems of low reliability of the test results of existing analogues for verifying the performance of CMC gas turbine vanes or high cost and long cycle of the test.

[0007] According to one aspect of the present application, a CMC gas turbine outer ring simulation piece design method is provided, comprising the following steps: S1: obtaining the fiber orientation distribution and porosity distribution of a real component, and establishing a real component finite element model of thermal-mechanical-oxidation multi-field coupling based on the fiber orientation distribution, porosity distribution and material parameters under the service environment of the real component; S2: determining the damage site of the real component and its damage parameter distribution curve by using a multi-scale analysis method; S3: designing a simulation piece based on the damage site of the real component; S4: verifying the consistency of the simulation piece and the real component, and if the consistency meets the design requirements, outputting the design result, and if the consistency does not meet the requirements, correcting the size of the simulation piece by using the damage parameter distribution curve, and then repeating step S4.

[0008] As a further improvement of the above technical solution:

[0009] Further, the step of verifying the consistency of the simulation piece and the real component specifically comprises the following steps: establishing a simulation piece finite element model, extracting the damage parameter distribution of the damage site of the simulation piece by using finite element analysis, and then comparing the damage parameter distribution consistency of the simulation piece and the real component at the damage site, so as to verify the consistency of the simulation piece and the real component based on the damage parameter distribution consistency.

[0010] Further, the standard for the consistency meeting the design requirements is that: the spatial coincidence degree of the damage peak position of the simulation piece and the real component is ≥ 90%, the relative error of the key damage parameter of the simulation piece and the real component is ≤ 5%; and / or the damage distribution correlation coefficient R² after two times of size correction is ≥ 0.98.

[0011] Further, step S2 specifically comprises the following steps: applying aerodynamic pressure, centrifugal load and temperature gradient field on a macro scale, and introducing an evolution function of the material parameter changing with temperature / time on a micro scale, so as to determine the strain field, temperature field and oxidation environment distribution of the real component under the set working condition, thereby identifying the damage site of the real component and quantifying the damage parameter distribution curve of the damage site.

[0012] Further, the evolution function is:

[0013] ;

[0014] wherein, is the material parameter, is the material parameter reference value, exp is the exponential function, is the apparent activation energy, R is the gas constant, T is the test temperature, is the reference temperature, is the proportional coefficient of long-term degradation amplitude, is the characteristic degradation time changing with temperature, tT is the cumulative time of the material at the test temperature, and m is the power index.

[0015] Further, the damage parameter distribution curve represents the damage parameter distribution law of the damage site on the real component in the form of a single variable function, and the single variable function is:

[0016] ;

[0017] In the formula, is the damage along the thickness direction, r is the radial coordinate, r 0 is the surface position; D 0 is the surface maximum damage value, and λ is the attenuation coefficient.

[0018] Further, the size correction includes the following steps: adopting a closed-loop feedback parameterization correction, taking the damage parameter distribution curve of the damage site on the real component as an optimization objective function, focusing on the geometric parameters of the damage site, and generating a size adjustment amount based on a damage distribution deviation vector to perform size correction iteration on the simulation piece.

[0019] Further, step S3 specifically includes the following steps: performing three-dimensional geometric reconstruction on the damage site of the real component to extract the geometric parameters of the characteristic section, and then determining the simulation piece according to the geometric parameters of the characteristic section, and retaining the key load-bearing features related to the thermal mechanical load in the real component in the simulation piece.

[0020] Further, the simulation piece is arranged in a ring shape, and a plurality of square notches are centrally arranged on the circumferential side wall, the plurality of square notches are uniformly arranged along the circumference of the simulation piece, the radial depth of the square notch is h, the axial width of the square notch is w, and the circumferential length of the square notch is l .

[0021] According to another aspect of the present application, a CMC gas turbine outer ring simulation piece is also provided, which adopts the above-mentioned CMC gas turbine outer ring simulation piece design method.

[0022] The present application has the following beneficial effects:

[0023] The CMC gas turbine outer ring simulation piece design method of the application, by obtaining the fiber orientation distribution and porosity distribution of the real component, establishes a real component finite element model of thermal-mechanical-oxidation multi-field coupling based on the fiber orientation distribution, porosity distribution and material parameters of the real component under the service environment, and ensures the consistency of the simulation piece and the real component in the microstructure characteristics by the fiber orientation distribution and porosity distribution; in the real component finite element model of thermal-mechanical-oxidation multi-field coupling, the damage site and damage parameter distribution curve of the real component are determined by using multi-scale analysis means, and the damage site and failure mode of the real component under the service condition are accurately identified; the simulation piece is designed according to the damage site of the real component, the characteristics of the damage site are completely retained, and the reliability of performance evaluation and life prediction is effectively improved; the consistency of the simulation piece and the real component is verified, if the consistency meets the design requirements, the design result is output, if the consistency does not meet the requirements, the size of the simulation piece is corrected by using the damage parameter distribution curve, then the verification and correction steps are repeated until the consistency meets the design requirements, so as to maximize the consistency of the simulation piece and the real component in the failure mechanism and service life prediction; compared with the prior art, the simulation piece and the real component are highly consistent in the microstructure characteristics, failure mode and life prediction, the service performance of the real component can be accurately simulated, the accuracy and reliability of the data in the subsequent test are ensured, the test cost and test cycle of the CMC gas turbine outer ring are greatly reduced, a reliable basis is provided for the performance evaluation and life prediction of the CMC gas turbine outer ring, the practicability is high, and the application is suitable for wide promotion and application.

[0024] In addition to the objects, features, and advantages described above, the application has other objects, features, and advantages. The application will be described in further detail below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0025] The accompanying drawings, which form a part of the present application, are included to provide a further understanding of the application, illustrate the preferred embodiments of the application, and assist in the explanation of the application. In the drawings, the same reference numbers represent the same elements throughout the several views of the drawings:

[0026] Figure 1 is a structural schematic diagram of the CMC gas turbine outer ring simulation piece design method of the preferred embodiment of the application;

[0027] Figure 2 is a distribution schematic diagram of the real component temperature field in the CMC gas turbine outer ring simulation piece design method of the preferred embodiment of the application;

[0028] Figure 3 is a distribution schematic diagram of the real component strain field in the CMC gas turbine outer ring simulation piece design method of the preferred embodiment of the application;

[0029] Figure 4 Figure 2 is a partial structural schematic of a CMC gas turbine outer ring mockup according to a preferred embodiment of the present invention;

[0030] Figure 5 Figure 3 is a structural schematic of a CMC gas turbine outer ring mockup according to a preferred embodiment of the present invention;

[0031] Figure 6 Figure 4 is a Mises stress plot of a CMC gas turbine outer ring mockup according to a preferred embodiment of the present invention. DETAILED DESCRIPTION

[0032] The following description provides specific applications and requirements of the present specification, in order to enable a person skilled in the art to make and use the content of the present specification. Various partial modifications of the disclosed embodiments are obvious to those skilled in the art, and the general principles defined herein can be applied to other embodiments and applications without departing from the spirit and scope of the present specification.

[0033] The terms used herein are only for the purpose of describing specific example embodiments, and are not limiting. For example, unless the context clearly indicates otherwise, as used herein, the singular forms "a", "an", and "the" can also include the plural. When used in the present specification, the terms "comprise", "comprise" and / or "contain" mean that the associated whole, step, operation, element and / or component exists, but do not exclude the presence or addition of one or more other features, whole, step, operation, element, component and / or group in the system / method.

[0034] In view of the following description, these features of the present specification and other features, as well as the operation and functions of related elements of the structure, and the combination and economy of manufacture of components can be significantly improved. With reference to the drawings, all of which form part of the present specification. However, it should be clearly understood that the drawings are for illustrative and descriptive purposes only, and are not intended to limit the scope of the present specification. It should also be understood that the drawings are not drawn to scale.

[0035] As Figure 1As shown, the design method for the CMC gas turbine outer ring simulator in this embodiment includes the following steps: S1: Obtain the fiber orientation distribution and porosity distribution of the real component. Based on the fiber orientation distribution, porosity distribution, and material parameters under service conditions of the real component, establish a finite element model of the real component with thermo-mechanical-oxidative multi-field coupling; S2: Use multi-scale analysis to determine the damage location and damage parameter distribution curve of the real component; S3: Design the simulator based on the damage location of the real component; S4: Verify the consistency between the simulator and the real component. If the consistency meets the design requirements, output the design results. If the consistency does not meet the requirements, use the damage parameter distribution curve to correct the size of the simulator, and then repeat step S4.

[0036] like Figure 1 As shown, specifically, the CMC gas turbine outer ring simulation component design method of the present invention obtains the fiber orientation distribution and porosity distribution of the real component. Based on the fiber orientation distribution, porosity distribution, and material parameters under service conditions of the real component, a thermo-mechanical-oxidative multi-field coupled finite element model of the real component is established. The fiber orientation distribution and porosity distribution ensure the consistency of the designed simulation component and the real component in terms of microstructural characteristics. In the thermo-mechanical-oxidative multi-field coupled finite element model of the real component, multi-scale analysis is used to determine the damage location and its damage parameter distribution curve of the real component, accurately identifying the damage location and failure mode of the real component under service conditions. The simulation component is designed based on the damage location of the real component to fully preserve the characteristics of the damage location, effectively improving the reliability of performance evaluation and life prediction. The simulation is verified. The simulation part and the real component are kept consistent. If the consistency meets the design requirements, the design results are output. If the consistency does not meet the requirements, the size of the simulation part is corrected using the damage parameter distribution curve. The verification and correction steps are repeated until the consistency meets the design requirements, so as to maximize the consistency between the simulation part and the real component in terms of failure mechanism and service life prediction. Compared with the existing technology, this solution can accurately simulate the service performance of the real component by ensuring that the simulation part and the real component maintain a high degree of consistency in microstructural characteristics, failure modes and service life prediction. This ensures the accuracy and reliability of data in subsequent tests. Moreover, it significantly reduces the test cost and test cycle of CMC gas turbine outer ring compared with full-scale test, and provides a reliable basis for the performance evaluation and service life prediction of CMC gas turbine outer ring. It is highly practical and suitable for widespread promotion and application.

[0037] It should be understood that the actual component refers to the actual part of the CMC gas turbine outer ring.

[0038] like Figure 6As shown, in the embodiment, the step of verifying the consistency between the simulation component and the real component specifically comprises the following steps: establishing a finite element model of the simulation component, extracting the damage parameter distribution of the damage site on the simulation component by using finite element analysis, and then comparing the damage parameter distribution consistency of the simulation component and the real component at the damage site, so as to verify the consistency between the simulation component and the real component based on the damage parameter distribution consistency. Specifically, the damage parameter distribution of the damage site on the simulation component is quickly extracted through parameterized modeling and finite element analysis, and then the consistency between the simulation component and the real component is verified through the damage parameter distribution consistency, so as to quickly verify the consistency between the simulation component and the real component, and significantly improve the design efficiency of the simulation component.

[0039] In the embodiment, the standard for meeting the design requirements of the consistency is: the spatial coincidence degree of the damage peak position of the simulation component and the real component is greater than or equal to 90%, and the relative error of the key damage parameter of the simulation component and the real component is less than or equal to 5%; and / or the damage distribution correlation coefficient R2 after two consecutive size corrections is greater than or equal to 0.98. Specifically, the consistency between the simulation component and the real component is accurately verified through the above standard, so as to ensure that the simulation component and the real component are highly consistent in terms of failure mode and life prediction, thereby accurately simulating the service performance of the real component through the simulation component, and quickly realizing the engineering application of the CMC gas turbine outer ring.

[0040] It should be understood that when designing the simulation component of the CMC gas turbine outer ring, the parameters of the simulation component need to be continuously corrected through iteration, so that the damage distribution gradually approaches the real component. When the distribution correlation coefficients (R2) of the damage distribution after two consecutive corrections and the real component both reach or exceed 0.98, it indicates that the simulation result is highly consistent with the real situation, and the difference can be ignored, so it is considered that the iteration has converged and can be ended. The correction result of the second time (the latest time) is taken as the final converged result. It plays the role of convergence criterion and termination condition in the design process, which can not only ensure the accuracy and reliability of the simulation result, but also avoid the waste of calculation resources caused by excessive iteration and improve the design efficiency.

[0041] As shown in Figure 2 and Figure 3 As shown, in the embodiment, the step S2 specifically comprises the following steps: applying aerodynamic pressure, centrifugal load and temperature gradient field on the macro scale, and introducing the evolution function of the material parameters changing with temperature / time on the micro scale, so as to determine the strain field, temperature field and oxidation environment distribution of the real component under the set working condition, thereby identifying the damage site of the real component and quantifying the damage parameter distribution curve of the damage site. Specifically, the information of the macro scale and the micro scale is organically combined through multi-scale analysis, so as to obtain comprehensive and efficient simulation results, thereby accurately identifying the damage site of the real component and the damage parameter distribution curve thereof.

[0042] In the embodiment, the evolution function is:

[0043] ;

[0044] wherein, is a material parameter, is a material parameter reference value, exp is an exponential function, is an apparent activation energy, R is a gas constant, T is a test temperature, is a reference temperature, is a proportional coefficient of long-term degradation amplitude, is a characteristic degradation time varying with temperature, t is a cumulative time of the material at the test temperature, m is a power index.

[0045] Specifically, the damage site of the real component and the damage parameter distribution curve thereof are ensured to be accurately identified by the evolution function.

[0046] It should be understood that, the material parameter represented is not a single constant, but a group of key mechanical property indexes (modulus, strength, interface strength, fracture energy, damage variable) that can reflect the performance evolution of the ceramic matrix composite with temperature and time under the condition of thermal-mechanical-oxidation coupling; the material parameter reference value is the initial performance of the material in the non-degradation state; the apparent activation energy reflects the sensitivity of the material performance to temperature; is a core parameter for describing the life and degradation rate of the material at high temperature.

[0047] In the embodiment, the damage parameter distribution curve represents the damage parameter distribution law of the damage site on the real component in the form of a univariate function, and the univariate function is:

[0048] ;

[0049] wherein, is the damage along the thickness direction, r is a radial coordinate, r 0 is a surface position; D 0 is a surface maximum damage value, and λ is an attenuation coefficient.

[0050] Specifically, the damage parameter distribution law of the damage site on the real component is ensured to be accurately represented by the univariate function.

[0051] In the embodiment, the size correction comprises the following steps: adopting a closed-loop feedback parameterization correction, taking the damage parameter distribution curve of the damage site on the real component as an optimization objective function, focusing on the geometric parameters of the damage site, and generating a size adjustment amount based on a damage distribution deviation vector to perform size correction iteration on the simulation component. Specifically, by performing size correction iteration, the consistency of the simulation component and the real component in failure mode and life prediction is improved as much as possible, thereby ensuring that the simulation component can accurately simulate the service performance of the real component and quickly realize the engineering application of the CMC gas turbine outer ring.

[0052] In the embodiment, step S3 specifically comprises the following steps: performing three-dimensional geometric reconstruction on the damage site of the real component to extract the geometric parameters of the characteristic section, and then determining the simulation component according to the geometric parameters of the characteristic section, and retaining the key load-bearing features related to the thermal-mechanical load in the simulation component. Specifically, through the above steps, the simulation component can effectively retain the damage characteristics of the damage site, thereby providing a reliable basis for performance evaluation and life prediction of the real component.

[0053] As shown in Figure 4 and Figure 5 In the embodiment, the simulation component is arranged in a ring shape, and a plurality of square notches are centrally formed on the circumferential side wall, the square notches are uniformly arranged along the circumference of the simulation component, the radial depth of the square notch is h, the axial width of the square notch is w, and the circumferential length of the square notch is l Specifically, the square notch can simulate the key load-bearing features related to the thermal-mechanical load in the real component, thereby effectively retaining the damage characteristics of the damage site, and in the size correction process, the size adjustment amount is generated based on the damage distribution deviation vector to perform correction iteration on the sizes h, w and l .

[0054] It should be understood that the radial, axial and circumferential directions are based on the radial, axial and circumferential directions of the simulation component.

[0055] The CMC gas turbine outer ring simulation component of the embodiment adopts the CMC gas turbine outer ring simulation component design method described above. Specifically, the CMC gas turbine outer ring simulation component is designed by adopting the CMC gas turbine outer ring simulation component design method described above, so as to ensure that the CMC gas turbine outer ring simulation component can accurately simulate the service performance of the real component and quickly realize the engineering application of the CMC gas turbine outer ring.

[0056] In addition, the processes depicted in the figures do not necessarily require the particular order shown, or sequential order, to achieve desirable results. In certain implementations, multitasking and parallel processing can be advantageous.

[0057] In view of the foregoing, after reading this detailed description, one skilled in the art will appreciate that the foregoing detailed description is presented for purposes of illustration and description. Although the present description has been described in some detail, it will be appreciated that many modifications can be made without materially departing from the concept and scope of the application. Accordingly, it is to be understood that the present description discloses a number of example embodiments, and that no limitation is intended thereby. Rather, the scope of the present description is limited only by the claims.

[0058] Furthermore, certain terminology has been used in this description for the purpose of reference only. For example, "one embodiment", "an embodiment" and / or "some embodiments" means that a particular feature, structure or characteristic described in connection with the embodiment is included in at least one embodiment. Thus, the appearance of the phrase "in one embodiment" or "in an embodiment" or "in some embodiments" in various places throughout this description are not necessarily referring to the same embodiment. Furthermore, the particular features, structures, or characteristics can be combined in any suitable manner on one or more embodiments without necessarily being included in the same embodiment.

[0059] It should be understood that in the foregoing description of embodiments of the present description, various features are sometimes grouped together in a single embodiment, figure, or description of a combination of features. This is done for the purpose of clarity in understanding the concepts of the present description. However, this should not be construed as a limitation of the present description, but rather a description of an embodiment, wherein each individual feature can be viewed as a separate embodiment, or in combination with a plurality of the features described in the present description. In other words, the embodiments of the present description can also be viewed as an integration of a plurality of sub-embodiments, wherein each sub-embodiment is characterized by less than all the features of the single embodiment described in the foregoing.

[0060] Each patent, patent application, publication, and other material cited in this document, e.g., articles, books, treatises, publications, documents, items, etc., are hereby incorporated by reference in their entirety. In the event of any inconsistency between the terminology, description, definition, and / or use of a term associated with any incorporated material and the terminology, description, definition, and / or use of that term in this document, the terminology, description, definition, and / or use of the term in this document shall control.

[0061] Finally, it should be understood that the embodiments of the application disclosed herein are illustrative of the principles of the present description. Other modifications that can be employed are within the scope of the description. As such, the present description should not be limited to the particular embodiments described herein but should be understood as including all embodiments that were potentially described herein, alone or in combination. The disclosure resides in the claims hereinafter appended.

Claims

1. A method of designing a CMC gas turbine outer ring mockup, characterized by, The method comprises the following steps: S1: obtaining the fiber orientation distribution and porosity distribution of the real component, and establishing a real component finite element model of thermal-mechanical-oxidation multi-field coupling based on the fiber orientation distribution, porosity distribution and material parameters under the service environment of the real component; S2: determining the damage site and damage parameter distribution curve of the real component by using multi-scale analysis means; S3: designing a simulation component based on the damage site of the real component; S4: verifying the consistency of the simulation component and the real component, if the consistency meets the design requirements, outputting the design result, if the consistency does not meet the requirements, correcting the size of the simulation component by using the damage parameter distribution curve, and repeating step S4; The verification of the consistency of the simulation component and the real component specifically comprises the following steps: establishing a simulation component finite element model, extracting the damage parameter distribution of the damage site of the simulation component by using finite element analysis, and comparing the damage parameter distribution consistency of the simulation component and the real component at the damage site, to verify the consistency of the simulation component and the real component based on the damage parameter distribution consistency; Step S2 specifically comprises the following steps: applying aerodynamic pressure, centrifugal load and temperature gradient field on the macro scale, and introducing the evolution function of the material parameters changing with temperature / time on the meso scale, to determine the strain field, temperature field and oxidation environment distribution of the real component under the set working condition, so as to identify the damage site of the real component and quantify the damage parameter distribution curve of the damage site; Step S3 specifically comprises the following steps: reconstructing the damage site of the real component in three dimensions to extract the geometric parameters of the characteristic section, and determining the simulation component according to the geometric parameters of the characteristic section, and retaining the key load-bearing features related to thermal-mechanical load in the simulation component.

2. The CMC gas turbine outer ring mockup design method of claim 1, wherein, The standard for the consistency meeting the design requirements is: the spatial coincidence degree of the damage peak position of the simulation component and the real component is ≥ 90%, and the relative error of the key damage parameters of the simulation component and the real component is ≤ 5%; and / or the damage distribution correlation coefficient R² after two times of size correction is ≥ 0.

98.

3. The CMC gas turbine outer ring mockup design method of claim 1, wherein, The evolution function is: ； wherein is a material parameter, is a material parameter reference value, exp is the exponential function, is the apparent activation energy, R is the gas constant, T is the test temperature, is the reference temperature, is the proportionality coefficient of the long-term degradation amplitude, is the characteristic degradation time as a function of temperature, t is the cumulative time of the material at the test temperature, m is the power index.

4. The CMC gas turbine outer ring mockup design method of claim 3, wherein, The damage parameter distribution curve represents the damage parameter distribution law of the damage site on the real component in the form of a single variable function, and the single variable function is: ； wherein is the damage along the thickness direction, r is the radial coordinate, r 0 is the surface position; D 0 is the surface maximum damage value, and λ is the attenuation coefficient.

5. The method of designing a CMC gas turbine outer ring mockup of any of claims 1-4, wherein, The size correction comprises the following steps: using closed-loop feedback parameterization correction, taking the damage parameter distribution curve of the damage site on the real component as the optimization objective function, focusing on the geometric parameters of the damage site, and generating a size adjustment amount based on a damage distribution deviation vector to iteratively correct the size of the simulation component.

6. The method of designing a CMC gas turbine outer ring mockup of any of claims 1-4, wherein, The simulation piece is arranged in a ring shape, and a plurality of square notches are centrally formed on the circumferential side wall, the plurality of square notches are uniformly arranged along the circumference of the simulation piece, the radial depth of the square notch is h, the axial width of the square notch is w, and the circumferential length of the square notch is l .

7. A CMC gas turbine outer ring mockup, characterized by, The CMC gas turbine outer ring simulation component design method of any one of claims 1-6 is adopted.

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