Design and test method of CMC turbine vane mockup for aero-engine

Abstract

The application discloses an aero-engine CMC turbine guide vane simulation piece design and test method, comprising the following steps: S1: establishing a turbine guide vane assembly finite element model; S2: setting the interaction boundary conditions between each part in the turbine guide vane assembly, and applying temperature and pressure boundary conditions according to the specified working condition; S3: setting the lay-up scheme and material parameters of the CMC turbine guide vane; S4: performing finite element simulation solving of the model, obtaining the stress distribution in the model, and determining the stress concentration area; S5: calculating the stress concentration coefficient one of the stress concentration area; S6: performing feature simplification and stress analysis of the stress concentration area, designing the simulation piece according to the feature simplification result, and then performing tool design and simulation piece test according to the stress analysis result, so as to obtain the stress distribution of the simulation piece; and S7: confirming whether the design consistency of the simulation piece and the CMC turbine guide vane meets the design requirement.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of turbine guide vane of an aero-engine, in particular, to a design and test method of a CMC turbine guide vane simulation piece. BACKGROUND

[0002] Ceramic matrix composites (CMC) have many advantages such as low density, high hardness, high temperature resistance, oxidation resistance, and longer service life, and are gradually applied to turbine outer rings, turbine guide vanes and other aero-engine hot end components as a new generation of advanced materials. The turbine guide vane is an important component part of the hot end of the aero-engine, which is generally composed of a hollow blade body and upper and lower edge plates, and has a complex curved surface structure. In order to realize the engineering application of CMC turbine guide vanes in aero-engines, a "building block" design and verification method is usually adopted, and the design process is carried out step by step through "sample → element → simulation piece → part → component → whole machine". Among them, the simulation piece level evaluation is the key bridge connecting the sample level and the complex component level, and its performance status has a guiding role for the later component examination and verification, so the CMC turbine guide vane simulation piece level research has been focused by domestic and foreign.

[0003] For example, Chinese invention patent CN118194637A discloses a design and test method of a CMC guide vane blade body-edge plate connection area feature simulation piece, which includes the following steps: first, a full-size macro model of the CMC turbine guide vane is established; second, the stress distribution of the CMC turbine guide vane under service conditions is obtained; third, the high stress area of the CMC turbine guide vane, i.e. the blade body-edge plate connection part, is extracted; fourth, a feature simulation piece is established; fifth, the load characteristics are optimized to determine the load size and angular direction of the CMC guide vane blade body-edge plate connection simulation piece; sixth, the high temperature static strength test of the feature simulation piece of the CMC turbine guide vane blade body-edge plate connection area is carried out. The present application can obtain the bearing capacity and failure mode type of the connection structure. Compared with the traditional method, the failure behavior of the CMC guide vane blade body-edge plate connection structure can be more economically and effectively predicted.

[0004] However, the above method only designs and tests the simulation piece for the weak part (blade body-edge plate connection) of the turbine guide vane under the action of aerodynamic load, that is, the typical features of the blade body-edge plate connection on the turbine guide vane are directly copied in the design process, but the layup scheme and material parameters of the CMC turbine guide vane are not given in the model setting process, resulting in that the model simulation result cannot truly reflect the part failure area, so that there is a large deviation between the test result and the engineering application, and there is a lack of quantitative judgment basis for the consistency of the simulation piece and the CMC turbine guide vane design. SUMMARY

[0005] The application provides an aero-engine CMC turbine vane simulation piece design and test method to solve the technical problem that the model simulation result cannot truly reflect the easily damaged area of the part, the test result is greatly deviated from the engineering application, and there is no quantitative judgment basis for the consistency of the simulation piece and the CMC turbine vane design in the existing CMC turbine vane simulation piece design and test process.

[0006] According to one aspect of the application, an aero-engine CMC turbine vane simulation piece design and test method is provided, comprising the following steps: S1: establishing a turbine vane assembly finite element model to clearly define the assembly position relationship between each part in the turbine vane assembly; S2: setting the interaction boundary conditions between each part in the turbine vane assembly, and applying temperature and pressure boundary conditions according to the specified working condition; S3: setting the layup scheme and material parameters of the CMC turbine vane based on the processing technology of CMC; S4: performing finite element simulation solution of the model to obtain the stress distribution in the model and determine the stress concentration area; S5: calculating the stress concentration coefficient one of the stress concentration area; S6: performing feature simplification and stress analysis of the stress concentration area, designing the simulation piece according to the feature simplification result, and performing tooling design and simulation piece test according to the stress analysis result to obtain the stress distribution of the simulation piece; S7: calculating the stress concentration coefficient two of the simulation piece to confirm whether the design consistency of the simulation piece and the CMC turbine vane meets the design requirements.

[0007] As a further improvement of the above technical solution:

[0008] Further, the layup scheme of the CMC turbine vane includes the number of layers, the thickness of the layers, and the angle of the layers, in step S3, the number of layers is 12, the thickness of the layers is 0.2mm, and the angle of the layers includes 0° and 90°, wherein the angle of 6 layers is 0° and the angle of 6 layers is 90°, and the layers are alternately laid.

[0009] Further, the material parameters of the CMC turbine vane include the tensile modulus, the shear modulus, and the Poisson's ratio in three directions, the three directions include a first direction parallel to the layup material, a second direction perpendicular to the first direction in each layer, and a third direction perpendicular to the first direction and the second direction, 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, 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.

[0010] Further, the stress concentration area is a middle area of the trailing edge of the CMC turbine vane blade body, and in step S6, the feature simplification process is as follows: the upper and lower edge plate structures of the CMC turbine vane are removed by geometric pruning, and the fillets between the blade body and the edge plate are removed; the fillet shape on one side of the trailing edge of the blade body 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 the plane to form a V-shaped structure with a circular arc tip.

[0011] Further, in step S6, the stress analysis process is as follows: the resultant force and the resultant moment of the cross section position of the stress concentration area are calculated, and the mechanical action of the stress concentration area is analyzed according to the size and direction of the resultant force and the resultant moment.

[0012] Further, the finite element model of the turbine vane assembly includes a casing, a turbine vane body, a support ring, and an assembly connecting piece.

[0013] Further, the interaction boundary conditions include a set contact boundary condition between the casing and the turbine vane body, a set contact boundary condition between the casing and the assembly connecting piece, a set contact boundary condition between the support ring and the turbine vane body, and a fixed support constraint boundary condition at the far end of the casing.

[0014] Further, the temperature and pressure boundary conditions include the overall temperature field of the turbine vane assembly and the gas pressure of each surface of each part in the turbine vane assembly.

[0015] Further, the calculation formula of the stress concentration coefficient K is as follows:

[0016] ;

[0017] In the formula, σ max is the maximum stress of the calculation part, σ 0 is the average stress of the calculation part.

[0018] Further, the specific steps of confirming whether the design consistency of the simulation piece and the CMC turbine vane meets the design requirements are as follows: a permissible value is given, and the absolute value of the difference between the first stress concentration coefficient and the second stress concentration coefficient is calculated, when the absolute value is less than the permissible value, the design consistency of the simulation piece and the CMC turbine vane meets the design requirements; when the absolute value is greater than the permissible value, the design consistency of the simulation piece and the CMC turbine vane does not meet the design requirements.

[0019] The present application has the following beneficial effects:

[0020] The aero-engine CMC turbine guide vane simulation piece design and test method of the application, by establishing a turbine guide vane assembly finite element model, the assembly position relationship between each part in the turbine guide vane assembly is clear, so as to set the interaction boundary conditions between each part in the turbine guide vane assembly, and according to the specified working condition, the temperature and pressure boundary conditions are applied, so as to obtain accurate finite element simulation results subsequently; based on the processing technology of CMC, the lay-up scheme and material parameters of CMC turbine guide vane are set to accurately simulate the actual stress condition of CMC lay-up, and then ensure that the stress distribution in the model obtained when the finite element simulation solving of the model is accurate, the stress concentration area is accurate, so that the simulation result can truly reflect the easy-to-break area of CMC turbine guide vane, so as to minimize or even eliminate the deviation between the subsequent test results and engineering application; the stress concentration coefficient one of the stress concentration area is obtained by calculation, so as to provide quantitative judgment basis for confirming the consistency of the simulation piece and the CMC turbine guide vane design; by simplifying the characteristics of the stress concentration area and stress analysis, the simulation piece is designed according to the simplified results, and the test tooling and simulation piece test are carried out according to the stress analysis results, so as to obtain the stress distribution of the simulation piece; the test tooling is designed based on the stress analysis structure, so that the test result can truly reflect the loading condition of the CMC turbine guide vane, and the accuracy of the test result is improved; finally, the stress concentration coefficient two of the simulation piece is calculated to confirm whether the design consistency of the simulation piece and the CMC turbine guide vane meets the design requirements, so as to realize the accurate judgment of the consistency of the simulation piece and the CMC turbine guide vane through the quantitative judgment basis; compared with the prior art, the model simulation result can truly reflect the easy-to-break area of the CMC turbine guide vane by reasonably setting the conditions after the model is established, the accuracy of the model simulation result is improved, the quantitative judgment basis of the consistency of the simulation piece and the CMC turbine guide vane design is calculated, the accurate judgment of the consistency of the simulation piece and the CMC turbine guide vane design is realized, the practicability is strong, and the method is suitable for wide promotion and application.

[0021] In addition to the objects, features, and advantages described above, the present application has other objects, features, and advantages. The present application will be described in further detail below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0022] The accompanying drawings, which form a part of this application, are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification. The illustrations are shown for the purpose of explaining the application and are not intended to limit the application in an inappropriate manner. In the drawings:

[0023] Figure 1 The step block diagram of the aero-engine CMC turbine guide vane simulation piece design and test method of the preferred embodiment of the application is shown in the figure;

[0024] Figure 2is a schematic structural diagram of a simulation piece in an aero-engine CMC turbine guide vane simulation piece design and test method of a preferred embodiment of the present application;

[0025] Figure 3 is a simulation piece test tool and loading schematic diagram in an aero-engine CMC turbine guide vane simulation piece design and test method of a preferred embodiment of the present application;

[0026] Figure 4 is a stress distribution situation schematic diagram of a simulation piece in an aero-engine CMC turbine guide vane simulation piece design and test method of a preferred embodiment of the present application. DETAILED DESCRIPTION

[0027] The following description provides specific applications and requirements of the present specification, and aims to enable those skilled in the art to manufacture and use the contents of the present specification. Various local 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. Therefore, the present specification is not limited to the shown embodiments, but is consistent with the widest scope of the claims.

[0028] 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 forms. When used in the present specification, the terms "include", "contain" and / or "have" mean that the associated integers, steps, operations, elements and / or components exist, but do not exclude the presence of one or more other features, integers, steps, operations, elements, components and / or groups.

[0029] These features and other features of the present specification, and the operation and function of related elements of the structure, and the combination and economy of manufacture of components can be obviously improved in view of the following description. 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.

[0030] As Figures 1-4As shown, the turbine vane assembly finite element model is established, the assembly position relationship between the parts in the turbine vane assembly is determined, the interaction boundary conditions between the parts in the turbine vane assembly are set, and the temperature and pressure boundary conditions are applied according to the specified working condition; S3: based on the processing technology of CMC, the lay-up scheme and material parameters of the CMC turbine vane are set; S4: the finite element simulation solution of the model is carried out, the stress distribution in the model is obtained, and the stress concentration area is determined; S5: the stress concentration coefficient one of the stress concentration area is calculated and obtained; S6: the feature simplification and stress analysis of the stress concentration area are carried out, the simulation part is designed according to the feature simplification result, the tooling design and simulation part test are carried out according to the stress analysis result, and the stress distribution of the simulation part is obtained; S7: the stress concentration coefficient two of the simulation part is calculated and obtained, so as to confirm whether the design consistency of the simulation part and the CMC turbine vane meets the design requirement.

[0031] As Figures 1-4As shown, specifically, the turbine vane simulation piece design and test method of the aero-engine CMC turbine vane of the application, by establishing a turbine vane assembly finite element model, the assembly position relationship between each part in the turbine vane assembly is determined, so as to set the interaction boundary conditions between each part in the turbine vane assembly, and according to the specified working condition, the temperature and pressure boundary conditions are applied, so as to obtain accurate finite element simulation results subsequently; based on the processing technology of CMC, the lay-up scheme and material parameters of CMC turbine vane are set to accurately simulate the actual stress condition of CMC lay-up, and then when the finite element simulation solving of the model is carried out, the stress distribution in the model obtained is accurate, the stress concentration area determined is accurate, and the simulation result can truly reflect the easy-to-break area of CMC turbine vane, so as to minimize or even eliminate the deviation between the subsequent test results and engineering application; the stress concentration coefficient one of the stress concentration area is obtained by calculation, so as to provide quantitative judgment basis for confirming the consistency of the simulation piece and the CMC turbine vane design; by simplifying the features of the stress concentration area and analyzing the stress, the simulation piece is designed according to the simplified feature results, and the test tooling and simulation piece test are carried out according to the stress analysis results, so as to obtain the stress distribution of the simulation piece. The test tooling is designed based on the stress analysis structure, so that the test result can truly reflect the loading condition of the CMC turbine vane, and the accuracy of the test result is improved; finally, the stress concentration coefficient two of the simulation piece is calculated to confirm whether the consistency of the simulation piece and the CMC turbine vane meets the design requirements, so as to realize the accurate judgment of the consistency of the simulation piece and the CMC turbine vane design through the quantitative judgment basis. Compared with the prior art, after the model is established, the accuracy of the model simulation result is improved by reasonably setting the conditions, so that the model simulation result can truly reflect the easy-to-break area of the CMC turbine vane, and then the quantitative judgment basis of the consistency of the simulation piece and the CMC turbine vane design is calculated to realize the accurate judgment of the consistency of the simulation piece and the CMC turbine vane design, which has strong practicability and is suitable for wide promotion and application.

[0032] In this embodiment, the lay-up scheme of the CMC turbine vane includes the number of layers, the thickness of the layers and the angle of the layers. In step S3, the number of layers is 12, the thickness of the layers is 0.2mm, and the angle of the layers includes 0° and 90°, wherein the angle of 6 layers is 0° and the angle of 6 layers is 90°, and the layers are alternately laid.

[0033] Specifically, by using the above-mentioned lay-up scheme of the CMC turbine vane, the model simulation result can truly reflect the easy-to-break area of the CMC turbine vane when the model simulation is carried out, so as to minimize or even eliminate the deviation between the subsequent test results and engineering application.

[0034] It should be understood that in the embodiment, the CMC layup is 12 layers, and the layup is 0° / 90° alternately, that is, the first layer is 0°, the second layer is 90°, the third layer is 0°, the fourth layer is 90°, and so on, the eleventh layer is 0°, and the twelfth layer is 90°.

[0035] In the embodiment, the material parameters of the CMC turbine vane include tensile modulus, shear modulus and Poisson's ratio in three directions, the three directions include a first direction parallel to the layup material, a second direction perpendicular to the first direction in each layer, and a third direction perpendicular to the first direction and the second direction, in step S3, the first direction tensile modulus is 285 GPa, the second direction tensile modulus is 285 GPa, the third direction tensile modulus is 201 GPa, the first direction shear modulus is 14.5 GPa, the second direction shear modulus is 12.8 GPa, the third direction shear modulus is 12.8 GPa, the first direction Poisson's ratio is 0.12, the second direction Poisson's ratio is 0.24, and the third direction Poisson's ratio is 0.24.

[0036] Specifically, by using the material parameters of the CMC turbine vane as described above, the actual stress of the CMC layup is accurately simulated to obtain accurate simulation stress when model simulation is performed, and the model simulation result can truly reflect the easily damaged area of the CMC turbine vane, thereby minimizing or even eliminating the deviation between the subsequent test result and the engineering application.

[0037] Optionally, according to the maximum stress failure criterion, the stress concentration area is determined.

[0038] As shown in Figure 2 and Figure 4 In the embodiment, the stress concentration area is the middle area of the trailing edge of the CMC turbine vane, and in step S6, the feature simplification process is as follows: the upper and lower edge plate structures of the CMC turbine vane are removed by geometric pruning, and the fillet between the blade body and the edge plate is removed; the shape of the fillet on one side of the trailing edge 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 the plane to form a V-shaped structure with a circular arc tip. Specifically, by using the above process to simplify the features of the stress concentration area, the simulation piece can truly reflect the loading condition of the CMC turbine vane while saving the processing cost.

[0039] In the embodiment, in step S6, the stress analysis process is as follows: the resultant force and the resultant moment of the stress concentration area at the cross section position are calculated, and the mechanical action of the stress concentration area is analyzed according to the size and direction of the resultant force and the resultant moment. Specifically, by using the above stress analysis process, it is ensured that the simulation piece can reflect the real loading condition of the CMC turbine vane when the test is performed by the manufactured tooling.

[0040] In the embodiment, the finite element model of the turbine vane assembly includes a casing, a turbine vane body, a support ring, and an assembly connector. Specifically, each part in the turbine vane assembly is determined so as to clearly define the assembly positional relationship between the parts (the casing, the turbine vane body, the support ring, and the assembly connector).

[0041] In the embodiment, the interaction boundary conditions include a set contact boundary condition between the casing and the turbine vane body, a set contact boundary condition between the casing and the assembly connector, a set contact boundary condition between the support ring and the turbine vane body, and a fixed support constraint boundary condition at the distal end of the casing. Specifically, by setting the above interaction boundary conditions, the actual working state of the CMC turbine vane is truly simulated so as to accurately obtain the subsequent finite element simulation results.

[0042] In the embodiment, the temperature and pressure boundary conditions include the overall temperature field of the turbine vane assembly and the gas pressure on each surface of each part in the turbine vane assembly. Specifically, by setting the above temperature and pressure boundary conditions, the actual working state of the CMC turbine vane is truly simulated so as to accurately obtain the subsequent finite element simulation results.

[0043] It should be understood that the specified working condition refers to the working condition of the CMC turbine vane when it is actually working.

[0044] In the embodiment, the calculation formula of the stress concentration coefficient K is as follows:

[0045] ;

[0046] In the formula, σ max to calculate the maximum stress of the calculation site, σ 0to calculate the average stress of the calculation site.

[0047] Specifically, the stress concentration coefficient K is calculated by the above calculation formula to provide a quantitative basis for judging the consistency of the simulation part and the CMC turbine vane design.

[0048] In the embodiment, the specific steps of confirming whether the design consistency of the simulation part and the CMC turbine vane meets the design requirements are as follows: a permissible value is given, and the absolute value of the difference between the stress concentration coefficient one and the stress concentration coefficient two is calculated. When the absolute value is less than the permissible value, the consistency of the simulation part and the CMC turbine vane meets the design requirements; when the absolute value is greater than the permissible value, the consistency of the simulation part and the CMC turbine vane does not meet the design requirements. Specifically, by the above steps, the quantitative basis for judging the consistency of the simulation part and the CMC turbine vane design is realized to accurately judge the consistency of the simulation part and the CMC turbine vane design, thereby determining whether the simulation part design is effective to provide data support for the iterative optimization of the simulation part.

[0049] The foregoing description of specific embodiments of the disclosure has been presented for the purposes of illustration and description. Other embodiments are within the scope of the following claims. In some cases, the actions or steps recited in the claims can be performed in a different order and still accomplish the desired results. Additionally, the processes depicted in the accompanying figures do not necessarily require the particular order shown, or sequential order to achieve the desired results. In certain implementations, multitasking and parallel processing can be advantageous.

[0050] In light of the above, it should be appreciated that the detailed disclosure made hereinabove in connection with specific embodiments of the present disclosure can be made only by way of example and the present disclosure can not be construed as being limited to such specific embodiments. Although specific terms have been employed herein, such terms are intended in a descriptive sense and not for purposes of limitation. The disclosure herein is intended to cover adaptations and modifications of the various embodiments of the present disclosure. Such adaptations and modifications can be made in the light of the above detailed disclosure and the spirit of the present disclosure.

[0051] Furthermore, certain terminology has been used in the present specification 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 of the disclosure. Thus, the appearance of the phrase "in one embodiment" or "in an embodiment" or "in some embodiments" in various places throughout the specification are not necessarily referring to the same embodiment. Furthermore, the particular features, structures or characteristics can be combined in any suitable manner in one or more embodiments.

[0052] It should be understood that in the foregoing description of embodiments of the present disclosure, various features can be combined in a single embodiment or in multiple embodiments of the present disclosure. It is therefore contemplated that the features of the present disclosure can be combined in a single embodiment or in multiple embodiments of the present disclosure. It is further contemplated that the embodiments of the present disclosure can be combined with other embodiments of the present disclosure in any suitable manner.

[0053] Each patent, patent application, publication of a patent application, and other material, for example articles, books, specifications, publications, documents, things, or the like which can be cited in the present document can be accorded with the scope of their respective copyrights. The contents of all such cited patents, patent applications, publications of patent applications, and other material are hereby incorporated by reference for all purposes to the same extent as each is accorded for its respective copyright laws. Except to the extent necessary or required to be disclaimed by law, neither the prior document history of any incorporated-by-reference material nor any prior document history of any incorporated-by- reference material is hereby incorporated by reference, and all such prior document histories are disclaimed. In the event that any of the incorporated-by-reference material contradicts any of this document, including definition or use of any term

[0054] Finally, it should be understood that the embodiments of the application disclosed herein are illustrative of specific embodiments of a principle of the application. Other modifications can be adopted without departing from the scope of this specification. Accordingly, the embodiments disclosed in this specification are merely for exemplification and are not to be considered as limiting the scope of the application.

Claims

1. An aeroengine CMC turbine vane mockup design and test method, characterized by, The method comprises the following steps: S1: a finite element model of the turbine vane assembly is established to determine the assembly position relationship between each part in the turbine vane assembly; S2: the interaction boundary conditions between each part in the turbine vane assembly are set, and the temperature and pressure boundary conditions are applied according to the specified working condition; S3: based on the CMC processing technology, the layup scheme and material parameters of the CMC turbine vane are set; S4: the finite element simulation solution of the model is performed to obtain the stress distribution in the model and determine the stress concentration area; S5: the stress concentration coefficient one of the stress concentration area is calculated and obtained; S6: the feature simplification and stress analysis of the stress concentration area are performed, the simulation part is designed according to the feature simplification result, and the tooling design and simulation part test are performed according to the stress analysis result to obtain the stress distribution of the simulation part; S7: the stress concentration coefficient two of the simulation part is calculated and obtained to confirm whether the design consistency of the simulation part and the CMC turbine vane meets the design requirement; The layup scheme of the CMC turbine vane includes the number of layers, the thickness of the layers and the layup angle; The material parameters of the CMC turbine vane include the tensile modulus, the shear modulus and the Poisson's ratio in three directions, including the first direction parallel to the layup material, the second direction perpendicular to the first direction in each layer, and the third direction perpendicular to the first direction and the second direction; The stress concentration area is the middle area of the trailing edge of the CMC turbine vane, and in step S6, the feature simplification process is as follows: The upper and lower edge plate structures of the CMC turbine vane are removed by geometric pruning, and the fillet between the blade body and the edge plate is removed; The fillet shape on one side of the trailing edge 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 the plane to form a V-shaped structure with a circular arc tip.

2. The gas turbine engine CMC vane mockup design and test method of claim 1, wherein, In step S3, the number of layers is 12, the thickness of the layers is 0.2 mm, and the layup angle includes 0° and 90°, wherein 6 layers are 0° and 6 layers are 90°, and the layers are alternately laid.

3. The gas turbine engine CMC vane mockup design and test method of claim 1, wherein, In step S3, the first direction tensile modulus is 285 GPa, the second direction tensile modulus is 285 GPa, the third direction tensile modulus is 201 GPa, the first direction shear modulus is 14.5 GPa, the second direction shear modulus is 12.8 GPa, the third direction shear modulus is 12.8 GPa, the first direction Poisson's ratio is 0.12, the second direction Poisson's ratio is 0.24, and the third direction Poisson's ratio is 0.

24.

4. The gas turbine engine CMC vane mockup design and test method of claim 1, wherein, In step S6, the stress analysis process is as follows: The resultant force and the resultant moment of the cross section position of the stress concentration area are calculated, and the mechanical action of the stress concentration area is analyzed according to the size and direction of the resultant force and the resultant moment.

5. The gas turbine engine CMC vane mockup design and test method of any of claims 1-4, wherein, The finite element model of the turbine vane assembly includes a casing, a turbine vane body, a support ring and an assembly connecting piece.

6. The gas turbine engine CMC vane mockup design and test method of claim 5, wherein, The interaction boundary conditions include the set contact boundary condition between the casing and the turbine vane body, the set contact boundary condition between the casing and the assembly connecting piece, the set contact boundary condition between the support ring and the turbine vane body, and the fixed constraint boundary condition of the far end of the casing.

7. The gas turbine engine CMC vane mockup design and test method of claim 5, wherein, The temperature and pressure boundary conditions include the overall temperature field of the turbine vane assembly and the gas pressure on each surface of each part in the turbine vane assembly.

8. The gas turbine engine CMC vane segment design and test method of claims 1-4, wherein, The calculation formula of the stress concentration coefficient K is as follows: ； wherein σ max to calculate the maximum stress at the site, σ 0 to calculate the average stress at the site.

9. The gas turbine engine CMC vane segment design and test method of claims 1-4, wherein, The specific steps for confirming whether the design consistency of the simulation piece and the CMC turbine vane meets the design requirements are as follows: Given the allowable value, the absolute value of the difference between the stress concentration coefficient one and the stress concentration coefficient two is calculated, and when the absolute value is less than the allowable value, the design consistency of the simulation piece and the CMC turbine vane meets the design requirements; when the absolute value is greater than the allowable value, the design consistency of the simulation piece and the CMC turbine vane does not meet the design requirements.

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