Design and test method of aero-engine CMC turbine guide vane simulator

Abstract

The invention discloses an aero-engine CMC turbine guide vane simulation part design and test method. The method comprises the following steps that S1, a turbine guide vane assembly finite element model is established; s2, interaction boundary conditions among parts in the turbine guide vane assembly are set, and temperature and pressure boundary conditions are applied according to specified working conditions; s3, a layering scheme and material parameters of the CMC turbine guide vane are set; s4, carrying out finite element simulation solution on the model, obtaining a stress distribution condition in the model, and determining a stress concentration area; s5, calculating to obtain a stress concentration coefficient I of the stress concentration area; s6, performing feature simplification and stress analysis on the stress concentration area, designing a simulation part according to a feature simplification result, and performing tool design and simulation part test according to a stress analysis result to obtain a stress distribution condition of the simulation part; and S7, whether the design consistency of the simulation piece and the CMC turbine guide vane meets the design requirement or not is confirmed.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine turbine guide vanes, and in particular to a design and testing method for a CMC turbine guide vane simulation component of an aero-engine. Background Art

[0002] Ceramic matrix composites (CMCs) offer numerous advantages, including low density, high hardness, high-temperature resistance, and oxidation resistance, resulting in a longer service life. As a new generation of advanced materials, they are gradually being used in aeroengine hot-end components, such as turbine outer rings and turbine guide vanes. Turbine guide vanes are crucial components in the hot-end of an aeroengine, typically consisting of a hollow airfoil and upper and lower lip plates, with a complex curved surface structure. To achieve the engineering application of CMC turbine guide vanes in aeroengines, a "building block" design and verification approach is typically employed, with a step-by-step design and verification process from "sample → component → simulator → part → component → complete unit". Simulator-level evaluation is a critical stepping stone between the sample and complex component levels, and its performance guides subsequent component evaluation and verification. Consequently, CMC turbine guide vane simulator-level research has garnered significant attention both domestically and internationally.

[0003] For example, Chinese invention patent CN118194637A discloses a design and testing method for a characteristic simulation component of the CMC guide blade airfoil-edge connection region. The method includes the following steps: first, establishing a full-scale macroscopic model of the CMC turbine guide blade; second, obtaining the stress distribution of the CMC turbine guide blade under service conditions; third, extracting the high-stress region of the CMC turbine guide blade, namely the airfoil-edge connection; fourth, establishing a characteristic simulation component; fifth, optimizing the design load characteristics to determine the load magnitude and angular orientation of the CMC guide blade airfoil-edge connection simulation component; and sixth, conducting a high-temperature static strength test on the characteristic simulation component of the CMC turbine guide blade airfoil-edge connection region. This method can determine the load capacity and failure mode type of the connection structure. Compared to traditional methods, it can more economically and effectively predict the failure behavior of the CMC guide blade airfoil-edge connection structure.

[0004] However, the above method only performs simulation part design and experimental design for the weak parts (the blade-edge plate connection) of the turbine guide vane caused by aerodynamic loads. That is, the typical characteristics of the blade-edge plate connection on the turbine guide vane are directly replicated during the design process. However, the layup scheme and material parameters of the CMC turbine guide vane are not given during the model setting process. As a result, the model simulation results cannot truly reflect the easily damaged areas of the parts, resulting in a large deviation between the test results and engineering applications, and there is a lack of quantitative judgment basis for the consistency between the simulation part and the CMC turbine guide vane design. Summary of the Invention

[0005] The present invention provides a design and testing method for a CMC turbine guide vane simulation component for an aircraft engine, aiming to address the technical problems in existing CMC turbine guide vane simulation component design and testing processes, such as the inability of model simulation results to truly reflect the easily damaged areas of the component, the significant deviation between the test results and engineering applications, and the lack of a quantitative basis for determining the design consistency between the simulation component and the CMC turbine guide vane.

[0006] According to one aspect of the present invention, a design and test method for a CMC turbine guide vane simulation component of an aero-engine is provided, comprising the following steps: S1: establishing a finite element model of a turbine guide vane assembly to clarify the assembly position relationship between the various parts in the turbine guide vane assembly; S2: setting the interaction boundary conditions between the various parts in the turbine guide vane assembly, and applying temperature and pressure boundary conditions according to specified working conditions; S3: setting the layup scheme and material parameters of the CMC turbine guide vane based on the CMC processing technology; S4: performing finite element simulation and solution of the model to obtain the stress distribution in the model and determine the stress concentration area; S5: calculating and obtaining the stress concentration coefficient I of the stress concentration area; S6: performing feature simplification and force analysis on the stress concentration area, designing a simulation component based on the feature simplification results, and then performing tooling design and simulation component testing based on the force analysis results to obtain the stress distribution of the simulation component; S7: calculating and obtaining the stress concentration coefficient II of the simulation component to confirm whether the design consistency between the simulation component and the CMC turbine guide vane meets the design requirements.

[0007] As a further improvement of the above technical solution: Furthermore, the layup scheme of the CMC turbine guide vane includes the number of layers, layer thickness, and layer angle. In step S3, the number of layers is 12, the layer thickness is 0.2 mm, and the layer angles include 0° and 90°, among which 6 layers have an angle of 0° and 6 layers have an angle of 90°, and the layers are laid alternately.

[0008] Furthermore, the material parameters of the CMC turbine guide vane include tensile modulus, shear modulus, and Poisson's ratio in three directions. The three directions include a first direction parallel to the laminate material, a second direction perpendicular to the first direction within each layer, and a third direction perpendicular to the first and second directions. In step S3, the tensile modulus in the first direction is 285 GPa, the tensile modulus in the second direction is 285 GPa, the tensile modulus in the third direction is 201 GPa, the shear modulus in the first direction is 14.5 GPa, the shear modulus in the second direction is 12.8 GPa, and the shear modulus in the third direction is 12.8 GPa. The Poisson's ratio in the first direction is 0.12, the Poisson's ratio in the second direction is 0.24, and the Poisson's ratio in the third direction is 0.24.

[0009] Furthermore, the stress concentration area is the middle area of ​​the trailing edge of the CMC turbine guide vane. In step S6, the feature simplification process is as follows: the upper and lower edge plate structures of the CMC turbine guide vane are removed by geometric trimming, and the fillet between the blade and the edge plate is removed; the fillet shape on one side of the trailing edge of the blade is retained, the other side opposite to the trailing edge is simplified into a plane, and the trailing edge cross section is stretched out of plane to form a V-shaped structure with a rounded tip.

[0010] Furthermore, in step S6, the force analysis process is as follows: calculating the resultant force and resultant moment acting on the cross-sectional position of the stress concentration area, and analyzing the mechanical effect of the stress concentration area according to the magnitude and direction of the resultant force and resultant moment.

[0011] Furthermore, the finite element model of the turbine guide vane assembly includes a casing, a turbine guide vane body, a support ring, and assembly connectors.

[0012] Furthermore, the interaction boundary conditions include set contact boundary conditions between the casing and the turbine guide vane body, set contact boundary conditions between the casing and the assembly connection, set contact boundary conditions between the support ring and the turbine guide vane body, and fixed support constraint boundary conditions at the far end of the casing.

[0013] Furthermore, the temperature and pressure boundary conditions include the overall temperature field of the turbine guide vane assembly and the gas pressure on each surface of each component in the turbine guide vane assembly.

[0014] Furthermore, the calculation formula of the stress concentration factor K is as follows: ; Where, σ max is the maximum stress in the calculated part, σ 0 The average stress at the calculation location.

[0015] Furthermore, the specific steps to confirm whether the design consistency between the simulation part and the CMC turbine guide vane meets the design requirements are as follows: given an allowable value, and the absolute value of the difference between the stress concentration factor 1 and the stress concentration factor 2 is calculated. When the absolute value is less than the allowable value, the design consistency between the simulation part and the CMC turbine guide vane meets the design requirements; when the absolute value is greater than the allowable value, the design consistency between the simulation part and the CMC turbine guide vane does not meet the design requirements.

[0016] The present invention has the following beneficial effects: The design and test method of the aviation engine CMC turbine guide vane simulation part of the present invention establishes a finite element model of the turbine guide vane assembly to clarify the assembly position relationship between the various parts in the turbine guide vane assembly, so as to set the interaction boundary conditions between the various parts in the turbine guide vane assembly, and apply temperature and pressure boundary conditions according to the specified working conditions, so as to obtain accurate finite element simulation results subsequently; based on the CMC processing technology, the laying scheme and material parameters of the CMC turbine guide vane are set to accurately simulate the actual stress conditions of the CMC laying, thereby ensuring that when the finite element simulation solution of the model is performed, the stress distribution in the model is obtained accurately and the stress concentration area is determined accurately, so that the simulation results can truly reflect the easily damaged area of ​​the CMC turbine guide vane, so as to minimize or even eliminate the deviation between the subsequent test results and engineering applications; the stress concentration coefficient of the stress concentration area is obtained by calculation to provide a quantitative judgment basis for confirming the design consistency of the simulation part and the CMC turbine guide vane; by performing The characteristics of the stress concentration area are simplified and the force analysis is carried out. The simulation part is designed according to the result of the characteristic simplification. Then, the tooling design and simulation part test are carried out according to the force analysis result to obtain the stress distribution of the simulation part. The test tooling is designed based on the force analysis structure, so that the test results can truly reflect the load condition of the CMC turbine guide vane and improve the accuracy of the test results. Finally, the stress concentration coefficient 2 of the simulation part is calculated to confirm whether the design consistency between the simulation part and the CMC turbine guide vane meets the design requirements, so as to achieve accurate judgment of the consistency between the simulation part and the CMC turbine guide vane through quantitative judgment basis. Compared with the existing technology, after the model is established, this scheme improves the accuracy of the model simulation results by reasonably setting the conditions, so that the model simulation results can truly reflect the easily damaged areas of the CMC turbine guide vane, and then achieves accurate judgment of the design consistency between the simulation part and the CMC turbine guide vane through the quantitative judgment basis of the calculated simulation part. It is highly practical and suitable for wide promotion and application.

[0017] In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The accompanying drawings, which constitute part of the present invention, are provided to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are provided to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings: Figure 1 This is a flowchart of the steps of the design and testing method of an aircraft engine CMC turbine guide vane simulation component according to a preferred embodiment of the present invention; Figure 2 1. It is a schematic structural diagram of a simulation component in a design and test method for a CMC turbine guide vane simulation component for an aero-engine according to a preferred embodiment of the present invention; Figure 3 This is a schematic diagram of the simulation test fixture and loading in the design and test method of the aircraft engine CMC turbine guide vane simulation in the preferred embodiment of the present invention; Figure 4 It is a schematic diagram of the stress distribution of the simulation part in the design and test method of the aircraft engine CMC turbine guide vane simulation part according to the preferred embodiment of the present invention. DETAILED DESCRIPTION

[0019] The following description provides specific application scenarios and requirements for this specification, intended to enable those skilled in the art to make and use the contents of this specification. Various modifications to the disclosed embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be applied to other embodiments and applications without departing from the spirit and scope of this specification. Therefore, this specification is not limited to the embodiments shown, but is intended to be accorded the broadest scope consistent with the claims.

[0020] The terminology used herein is for the purpose of describing specific example embodiments only and is not intended to be limiting. For example, as used herein, the singular forms "a," "an," and "the" may also include the plural forms unless the context clearly indicates otherwise. When used in this specification, the terms "comprise," "include," and / or "contain" are intended to refer to the presence of the associated integers, steps, operations, elements, and / or components, but do not preclude the presence of one or more other features, integers, steps, operations, elements, components, and / or groups or the addition of other features, integers, steps, operations, elements, components, and / or groups to the system / method.

[0021] These and other features of this specification, as well as the operation and function of the associated elements of the structure, and the economical assembly and manufacture of the components, can be significantly improved with consideration of the following description. Reference is made to the accompanying drawings, all of which form a part of this specification. However, it should be expressly understood that the drawings are for illustration and description purposes only and are not intended to limit the scope of this specification. It should also be understood that the drawings are not drawn to scale.

[0022] like Figures 1-4As shown, the design and testing method of the aircraft engine CMC turbine guide vane simulation component of this embodiment includes the following steps: S1: establishing a finite element model of the turbine guide vane assembly to clarify the assembly position relationship between the various parts in the turbine guide vane assembly; S2: setting the interaction boundary conditions between the various parts in the turbine guide vane assembly, and applying temperature and pressure boundary conditions according to specified working conditions; S3: setting the layup scheme and material parameters of the CMC turbine guide vane based on the CMC processing technology; S4: performing finite element simulation and solving the model to obtain the stress distribution in the model and determine the stress concentration area; S5: calculating the stress concentration coefficient I of the stress concentration area; S6: performing feature simplification and force analysis on the stress concentration area, designing a simulation component based on the feature simplification results, and then performing tooling design and simulation component testing based on the force analysis results to obtain the stress distribution of the simulation component; S7: calculating the stress concentration coefficient II of the simulation component to confirm whether the design consistency of the simulation component and the CMC turbine guide vane meets the design requirements.

[0023] like Figures 1-4Specifically, the present invention provides a design and testing method for an aero-engine CMC turbine guide vane simulation component. By establishing a finite element model of the turbine guide vane assembly, the assembly positional relationship between the various components in the turbine guide vane assembly is clarified to facilitate setting the interaction boundary conditions between the various components in the turbine guide vane assembly. Temperature and pressure boundary conditions are then applied according to specified operating conditions to subsequently obtain accurate finite element simulation results. Based on the CMC processing technology, the layup scheme and material parameters of the CMC turbine guide vane are set to accurately simulate the actual stress conditions of the CMC layup. This ensures that the stress distribution in the model is accurate and the stress concentration areas are accurately determined during the finite element simulation of the model. This ensures that the simulation results truly reflect the vulnerable areas of the CMC turbine guide vane, minimizing or even eliminating any deviations between subsequent test results and engineering applications. Furthermore, the stress concentration coefficient of the stress concentration area is calculated to provide a quantitative basis for confirming the design consistency between the simulation component and the CMC turbine guide vane. By simplifying the characteristics and performing force analysis in the stress concentration area, a simulation part is designed based on the result of the characteristic simplification, and then the tooling design and simulation part test are carried out based on the force analysis result to obtain the stress distribution of the simulation part. The test tooling is designed based on the force analysis structure, so that the test results can truly reflect the load condition of the CMC turbine guide vane, thereby improving the accuracy of the test results. Finally, the stress concentration coefficient 2 of the simulation part is calculated to confirm whether the consistency between the simulation part and the CMC turbine guide vane meets the design requirements, thereby achieving an accurate judgment on the design consistency between the simulation part and the CMC turbine guide vane through a quantitative judgment basis. Compared with the existing technology, after establishing the model, this solution improves the accuracy of the model simulation results by reasonably setting conditions, so that the model simulation results can truly reflect the easily damaged areas of the CMC turbine guide vane, and then achieves an accurate judgment on the design consistency between the simulation part and the CMC turbine guide vane by calculating the quantitative judgment basis of the design consistency between the simulation part and the CMC turbine guide vane. It is highly practical and suitable for wide promotion and application.

[0024] In this embodiment, the layup scheme for the CMC turbine guide vanes includes the number of layers, layer thickness, and layer angle. In step S3, the number of layers is 12, the layer thickness is 0.2 mm, and the layer angles include 0° and 90°. Among them, 6 layers have an angle of 0° and 6 layers have an angle of 90°, and the layers are laid alternately.

[0025] Specifically, by adopting the above-mentioned CMC turbine guide vane layup scheme, when performing model simulation, the model simulation results can truly reflect the vulnerable areas of the CMC turbine guide vanes, thereby minimizing or even eliminating the deviation between subsequent test results and engineering applications.

[0026] It should be understood that in this embodiment, there are 12 CMC layers, which are laid alternately at 0° / 90°, that is, the first layer is 0°, the second layer is 90°, the third layer is 0°, the fourth layer is 90°, ..., the eleventh layer is 0°, and the twelfth layer is 90°.

[0027] In this embodiment, the material parameters of the CMC turbine guide vane include tensile modulus, shear modulus, and Poisson's ratio in three directions. The three directions include a first direction parallel to the laminate material, a second direction perpendicular to the first direction within each layer, and a third direction perpendicular to the first and second directions. In step S3, the tensile modulus in the first direction is 285 GPa, the tensile modulus in the second direction is 285 GPa, and the tensile modulus in the third direction is 201 GPa. The shear modulus in the first direction is 14.5 GPa, the shear modulus in the second direction is 12.8 GPa, and the shear modulus in the third direction is 12.8 GPa. The Poisson's ratio in the first direction is 0.12, the Poisson's ratio in the second direction is 0.24, and the Poisson's ratio in the third direction is 0.24.

[0028] Specifically, by adopting the aforementioned material parameters of the CMC turbine guide vanes, the actual stress conditions of the CMC laminate are accurately simulated, thereby obtaining accurate simulated stress during model simulation. The model simulation results can truly reflect the vulnerable areas of the CMC turbine guide vanes, thereby minimizing or even eliminating the deviation between subsequent test results and engineering applications.

[0029] Optionally, the stress concentration area is determined according to a maximum stress failure criterion.

[0030] like Figure 2 and Figure 4 As shown, in this embodiment, the stress concentration area is the middle region of the CMC turbine guide vane's trailing edge. In step S6, the feature simplification process is as follows: The upper and lower lip plates of the CMC turbine guide vane are removed through geometric trimming, and the fillet between the blade and lip plates is removed. The fillet shape on one side of the blade's trailing edge is retained, while the opposite side is simplified into a flat surface. The trailing edge cross-section is then stretched out-of-plane to form a V-shaped structure with a rounded tip. Specifically, by applying this process to the stress concentration area, feature simplification allows the simulated part to realistically reflect the load conditions of the CMC turbine guide vane while reducing processing costs.

[0031] In this embodiment, the force analysis process in step S6 is as follows: the resultant force and moment acting on the cross-sectional location of the stress concentration area are calculated, and the mechanical effects of the stress concentration area are analyzed based on the magnitude and direction of the resultant force and moment. Specifically, this force analysis process ensures that the simulated component reflects the actual loading conditions of the CMC turbine guide vane during testing of the manufactured tooling.

[0032] In this embodiment, the finite element model of the turbine guide vane assembly includes the casing, turbine guide vane body, support ring, and assembly connectors. Specifically, by identifying the individual parts in the turbine guide vane assembly, the assembly positional relationships between these parts (casing, turbine guide vane body, support ring, and assembly connectors) are clearly defined.

[0033] In this embodiment, the interaction boundary conditions include set contact boundary conditions between the casing and the turbine guide vane body, set contact boundary conditions between the casing and the assembly connector, set contact boundary conditions between the support ring and the turbine guide vane body, and a clamped constraint boundary condition at the far end of the casing. Specifically, by setting these interaction boundary conditions, the actual operating state of the CMC turbine guide vane is realistically simulated, ensuring accurate finite element simulation results.

[0034] In this embodiment, the temperature and pressure boundary conditions include the overall temperature field of the turbine guide vane assembly and the gas pressure on each surface of each component within the turbine guide vane assembly. Specifically, by setting these temperature and pressure boundary conditions, the actual operating conditions of the CMC turbine guide vanes are realistically simulated, ensuring accurate finite element simulation results.

[0035] It should be understood that the designated operating conditions refer to the operating conditions when the CMC turbine guide vanes are actually working.

[0036] In this embodiment, the calculation formula of the stress concentration factor K is as follows: ; Where, σ max is the maximum stress in the calculated part, σ 0 The average stress at the calculation location.

[0037] Specifically, the stress concentration factor K is calculated using the above formula to provide a quantitative basis for judging the design consistency between the simulation component and the CMC turbine guide vane.

[0038] In this embodiment, the specific steps for confirming whether the design consistency between the simulated component and the CMC turbine guide vane meets the design requirements are as follows: given an allowable value, the absolute value of the difference between the stress concentration factor 1 and the stress concentration factor 2 is calculated. When the absolute value is less than the allowable value, the consistency between the simulated component and the CMC turbine guide vane meets the design requirements; when the absolute value is greater than the allowable value, the consistency between the simulated component and the CMC turbine guide vane does not meet the design requirements. Specifically, through the above steps, based on the quantitative judgment basis for the design consistency between the simulated component and the CMC turbine guide vane, the consistency between the simulated component and the CMC turbine guide vane is accurately judged, thereby determining whether the simulated component design is valid and providing data support for iterative optimization of the simulated component.

[0039] The foregoing description of this specification describes specific embodiments. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recited in the claims can be performed in an order different from that described in the embodiments and still achieve the desired results. Furthermore, the processes depicted in the accompanying drawings do not necessarily require the particular order or sequential order shown to achieve the desired results. In certain embodiments, multitasking and parallel processing are also possible or may be advantageous.

[0040] In summary, after reading the detailed disclosure of this specification, those skilled in the art will appreciate that the foregoing detailed disclosure may be presented by way of example only and may not be limiting. Although not expressly stated herein, those skilled in the art will understand that this specification encompasses various reasonable changes, improvements, and modifications to the embodiments. Such changes, improvements, and modifications are intended to be suggested by this specification and are within the spirit and scope of the exemplary embodiments of this specification.

[0041] Furthermore, certain terms in this specification have been used to describe embodiments of this specification. For example, “one embodiment,” “an embodiment,” and / or “some embodiments” mean that a particular feature, structure, or characteristic described in connection with that embodiment may be included in at least one embodiment of this specification. Therefore, it is emphasized and should be understood that two or more references to “an embodiment,” “one embodiment,” or “an alternative embodiment” in various parts of this specification do not necessarily refer to the same embodiment. Furthermore, particular features, structures, or characteristics may be appropriately combined in one or more embodiments of this specification.

[0042] It should be understood that in the foregoing descriptions of the embodiments of this specification, to facilitate understanding of a feature and to simplify this specification, various features are combined in a single embodiment, figure, or description thereof. However, this does not necessarily mean that these features are combined. When reading this specification, a person skilled in the art may label some of the devices as separate embodiments. In other words, the embodiments of this specification can also be understood as the integration of multiple sub-embodiments. This also applies when each sub-embodiment contains fewer than all the features of a single previously disclosed embodiment.

[0043] Each patent, patent application, patent application publication, and other materials, such as articles, books, specifications, publications, documents, articles, etc., cited herein is hereby incorporated by reference in its entirety for all purposes, except for any prosecution document history related thereto, any equivalent that may be inconsistent or conflicting with this document, or any equivalent prosecution document history that may have a limiting effect on the broadest scope of the claims now or hereafter associated with this document. For example, if there is any inconsistency or conflict between the description, definition, and / or use of terms associated with any incorporated material and the terminology, description, definition, and / or use associated with this document, the terminology in this document shall control.

[0044] Finally, it should be understood that the embodiments of the application disclosed herein are illustrative of the principles of the embodiments of this specification. Other modified embodiments are also within the scope of this specification. Therefore, the embodiments disclosed in this specification are merely examples and not limitations. Those skilled in the art can adopt alternative configurations based on the embodiments in this specification to implement the application in this specification. Therefore, the embodiments of this specification are not limited to the embodiments precisely described in the application.

Claims

1. A design and test method for an aircraft engine CMC turbine guide vane simulation component, characterized in that: The following steps are involved: S1: Establish a finite element model of the turbine guide vane assembly and clarify the assembly position relationship between the various parts in the turbine guide vane assembly; S2: Set the interaction boundary conditions between the parts in the turbine guide vane assembly and apply temperature and pressure boundary conditions according to the specified operating conditions; S3: Based on the CMC processing technology, set the layup plan and material parameters of the CMC turbine guide vanes; S4: Perform finite element simulation on the model to obtain the stress distribution in the model and determine the stress concentration area; S5: Calculate and obtain the stress concentration coefficient of the stress concentration area; S6: Simplify the characteristics of the stress concentration area and perform force analysis. Design a simulation part based on the simplified characteristics. Then, design the tooling and test the simulation part based on the force analysis results to obtain the stress distribution of the simulation part. S7: Calculate the stress concentration factor 2 of the simulated component to confirm whether the design consistency between the simulated component and the CMC turbine guide vane meets the design requirements.

2. The design and testing method for an aircraft engine CMC turbine guide vane simulation component according to claim 1, characterized in that: The layup scheme for the CMC turbine guide vanes includes the number of layers, layer thickness, and layer angle. In step S3, the number of layers is 12, the layer thickness is 0.2 mm, and the layer angles include 0° and 90°. Among them, 6 layers have an angle of 0° and 6 layers have an angle of 90°, and the layers are laid alternately.

3. The design and testing method for an aircraft engine CMC turbine guide vane simulation component according to claim 1, characterized in that: The material parameters of the CMC turbine guide vane include the tensile modulus, shear modulus, and Poisson's ratio in three directions. The three directions include a first direction parallel to the laminate material, a second direction perpendicular to the first direction within each layer, and a third direction perpendicular to the first and second directions. In step S3, the tensile modulus in the first direction is 285 GPa, the tensile modulus in the second direction is 285 GPa, and the tensile modulus in the third direction is 201 GPa. The shear modulus in the first direction is 14.5 GPa, the shear modulus in the second direction is 12.8 GPa, and the shear modulus in the third direction is 12.8 GPa. The Poisson's ratio in the first direction is 0.12, the Poisson's ratio in the second direction is 0.24, and the Poisson's ratio in the third direction is 0.

24.

4. The design and testing method for an aircraft engine CMC turbine guide vane simulation component according to claim 1, characterized in that: The stress concentration area is the middle area of ​​the trailing edge of the CMC turbine guide vane. In step S6, the feature simplification process is as follows: The upper and lower lip structures of the CMC turbine guide vanes are removed through geometric trimming, and the fillet between the blade body and the lip is removed; The rounded shape of one side of the trailing edge of the blade is retained, the other side opposite to the trailing edge is simplified into a plane, and the trailing edge section is stretched out of the plane to form a V-shaped structure with a rounded tip.

5. The design and testing method for a CMC turbine guide vane simulation component of an aero-engine according to claim 1, characterized in that: In step S6, the force analysis process is as follows: Calculate the resultant force and moment at the cross-sectional position of the stress concentration area, and analyze the mechanical action of the stress concentration area based on the magnitude and direction of the resultant force and moment.

6. The design and testing method for a CMC turbine guide vane simulation component for an aero-engine according to any one of claims 1 to 5, characterized in that: The finite element model of the turbine guide vane assembly includes the casing, turbine guide vane body, support ring and assembly connectors.

7. The design and testing method for an aircraft engine CMC turbine guide vane simulation component according to claim 6, characterized in that: The interaction boundary conditions include the set contact boundary conditions between the casing and the turbine guide vane body, the set contact boundary conditions between the casing and the assembly connector, the set contact boundary conditions between the support ring and the turbine guide vane body, and the fixed support constraint boundary conditions at the far end of the casing.

8. The design and testing method for an aircraft engine CMC turbine guide vane simulation component according to claim 6, characterized in that: The temperature and pressure boundary conditions include the overall temperature field of the turbine guide vane assembly and the gas pressure on each surface of each part in the turbine guide vane assembly.

9. The design and testing method for a CMC turbine guide vane simulation component for an aero-engine according to any one of claims 1 to 5, characterized in that: The calculation formula of stress concentration factor K is as follows: ； Where, σ max is the maximum stress in the calculated part, σ 0 The average stress at the calculation location.

10. The design and testing method for an aircraft engine CMC turbine guide vane simulation component according to any one of claims 1 to 5, characterized in that: The specific steps to confirm whether the design consistency between the simulation part and the CMC turbine guide vane meets the design requirements are as follows: Given an allowable value, the absolute value of the difference between stress concentration factor 1 and stress concentration factor 2 is calculated. When the absolute value is less than the allowable value, the design consistency between the simulation component and the CMC turbine guide vane meets the design requirements; when the absolute value is greater than the allowable value, the design consistency between the simulation component and the CMC turbine guide vane does not meet the design requirements.

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