Preparation method of ceramic matrix composite multi-cavity structure high-pressure turbine guide vane

Abstract

The present application relates to a kind of high-pressure turbine guide vane, and specifically relates to a kind of preparation method of ceramic matrix composite multi-cavity structure high-pressure turbine guide vane.Solve the technical problems that ceramic matrix composite high-pressure turbine guide vane component forming is difficult, blade component size difference and pre-embedded split joint model is easy to be bonded with blade.The method of the present application comprises the following steps:1) preparing upper edge plate component preform, lower edge plate component preform and blade body preform;2) preparing boron nitride interface layer for each preform respectively;3) preparing SiC matrix for each preform respectively, during the densification process of blade body preform, new graphite tooling and graphite paper pad are used at split joint structure for each furnace deposition;4) preparing self-healing matrix for each preform respectively;5) processing each component;Installing inner core baffle and multiple spoiler columns;Online assembly of each component, deposition and processing obtain turbine guide vane.

Description

Technical Field

[0001] This invention relates to a high-pressure turbine guide vane for aero-engines, and more specifically to a method for preparing a ceramic matrix composite multi-cavity high-pressure turbine guide vane. Background Technology

[0002] High-pressure turbine guide vanes are critical components in aero-engines, enduring extreme high-temperature and high-pressure environments. Traditional metal alloys used in high-pressure turbine guide vanes often suffer from creep and oxidation under prolonged high temperatures, leading to performance degradation and shortened lifespan. Ceramic matrix composites (CMCs), composed of a ceramic matrix and reinforcing materials, possess excellent high-temperature stability, oxidation resistance, and mechanical properties, maintaining good performance even in extreme environments. Compared to traditional metal alloys, CMCs also exhibit higher specific strength and specific stiffness, enabling them to withstand greater loads, while possessing lower density, contributing to reduced overall structural weight. Therefore, they are considered a preferred alternative to traditional metal alloys, particularly in the application of high-pressure turbine guide vanes.

[0003] Existing high-pressure turbine guide vane structures for aero-engines mainly consist of structural components such as the blade body, upper edge plate, and lower edge plate. The blade body is a monolithic structure with an irregular curved surface. The upper and lower edge plate components are located on the upper and lower sides of the blade body, respectively (see Chinese patent application number 202211369211.3 for details). Solid blade body components are typically made of metal, such as titanium alloys or nickel-based alloys, exhibiting uniform density and mass. However, due to the solid structure of solid turbine guide vanes, their thermal conductivity is poor, limiting their ability to conduct heat within the blade. Furthermore, because solid turbine guide vanes are relatively heavy, solid blades of the same size are heavier than hollow blades.

[0004] The hollow structure of multi-cavity turbine guide vanes provides better heat conduction capabilities, extending the residence time of cooling airflow inside the guide vane and allowing heat energy to be transferred more efficiently from the inside of the vane to the outside. Due to the characteristics of its hollow structure, hollow turbine guide vanes are lighter, reducing the load on the entire turbomachinery system. Because of their lightweight design and better heat conduction performance, hollow turbine guide vanes typically exhibit better dynamic performance and thermal efficiency, enabling them to provide higher rotational speeds and higher operating temperatures, thereby improving the performance of the turbomachinery system. Currently, multi-cavity turbine guide vanes have gradually become a hot topic at the forefront of turbine guide vane technology. A small number of related studies have been reported. For example, Chinese patent (application number 202111391815.3) mentions a method for shaping a multi-cooling-cavity blade structure in a ceramic matrix composite turbine guide vane. The blade components are integrally formed using a multi-core mold shaping method, while the multi-cavity guide vanes are prepared using a split mold forming method. Silicon carbide fiber cloth is used for the layup. Silicon carbide fiber cloth has high hardness, but the inner film size is small and the processing is difficult. The preform in the inner cavity corner area is difficult to shape, resulting in poor dimensional accuracy. Chinese patent (application number 202210720664.X) mentions a method for preparing a ceramic matrix composite guide blade with a trailing edge slit, which uses a pre-embedded slit to prepare the trailing edge slit of the blade. However, during the CVI densification process, the pre-embedded slit model is prone to adhesion to the blade, leading to difficulties in demolding. Summary of the Invention

[0005] The purpose of this invention is to solve the technical problems of existing ceramic matrix composite high-pressure turbine guide vane manufacturing methods, such as the difficulty in molding small inner membrane components, the easy deformation during blade component manufacturing leading to dimensional deviations, or the easy adhesion of pre-embedded splitting models to the blades during CVI densification. The invention provides a method for manufacturing ceramic matrix composite multi-cavity high-pressure turbine guide vanes.

[0006] The technical solution of this invention is:

[0007] This invention discloses a method for fabricating a ceramic matrix composite multi-cavity high-pressure turbine guide vane. The fabricated turbine guide vane includes a blade body component and upper and lower edge plate components respectively disposed on both sides of the blade body component. The blade body component includes a blade body, at least one inner core baffle, and multiple baffles. The blade body includes a curved blade back and a blade basin, which are smoothly connected to form a curved structure containing cavities, and the trailing edge forms a slit structure. The at least one inner core baffle is disposed in the middle of the cavity within the blade body, dividing the cavity into multiple sub-cavities. The multiple baffles are arranged in an array within the cavity near the slit structure, with both ends of the baffles penetrating the blade back and blade basin respectively.

[0008] Its special feature lies in the following preparation steps:

[0009] 1) Preparation of preforms

[0010] 1.1) Using fiber cloth and molds, the precast upper edge plate component and the precast lower edge plate component are respectively woven;

[0011] 1.2) Prepare the first outer mold, the second outer mold, the inner mold, and the graphite tooling respectively;

[0012] 1.3) Using fiber cloth, the first outer mold, the second outer mold and the inner mold are used to weave the blade body preform and make the trailing edge form a split structure of a specified size;

[0013] 2) Based on the required thickness of the boron nitride interface layer, prepare the boron nitride interface layer for each preform.

[0014] 3) Prepare SiC matrix for the preforms of the upper edge plate component, the lower edge plate component, and the blade body preform, respectively, to ensure that the density meets the predetermined requirements; each preform needs to be corrected after each deposition in each batch; during the densification process of the blade body preform, the split structure area needs to be inspected before each deposition in order to prevent adhesion; each batch requires the use of new graphite tooling and graphite paper pads at the split structure.

[0015] 4) Prepare self-healing matrix for each preform to obtain upper edge plate component, lower edge plate component and blade body that meet the density requirements;

[0016] 5) The upper edge plate component, lower edge plate component and blade body are processed separately; the inner core baffle and multiple turbulence columns are installed at the designated positions on the blade body; the upper edge plate component, lower edge plate component and blade body are assembled online, and then deposited and processed in sequence to obtain turbine guide vanes that meet the requirements.

[0017] Further, step 1.2) specifically involves: using the back of the leaf and the leaf base as references, preparing the first outer mold and the second outer mold respectively; using the cavity of the leaf body as a reference, preparing the inner mold; using the splitting structure as a reference, preparing the graphite tooling; wherein, the first outer mold, the second outer mold and the inner mold are all provided with several ventilation holes perpendicular to the mold surface and used for sewing, and the materials used to prepare the first outer mold, the second outer mold, the inner mold and the splitting structure are all high temperature resistant materials.

[0018] Further, the fiber cloth described in steps 1.1) and 1.3) is carbon fiber and / or silicon carbide fiber.

[0019] Further, step 1.3) specifically involves: winding the fiber cloth along the inner mold to the designed thickness and forming a split structure at the tail edge, ensuring that the dimensions of the split structure meet the requirements; closing and fixing the first outer mold, the second outer mold, and the inner mold; and using the ventilation holes as the stitching path to weave the blade body preform.

[0020] Further, step 2) specifically involves: according to the boron nitride interface layer thickness requirements, using a chemical vapor deposition furnace, preparing the boron nitride interface layer for the upper edge plate component preform, the lower edge plate component preform, and the blade body preform, respectively, and depositing for 3 to 5 cycles according to the boron nitride interface layer thickness requirements; before deposition, laying graphite fixtures and graphite paper at the split structure of the blade body preform, and using new graphite fixtures and graphite paper for each cycle.

[0021] Further, step 5) includes the following steps:

[0022] 5.1) According to the pre-designed process part model requirements, process the upper edge plate component, lower edge plate component and blade body respectively;

[0023] 5.2) The upper edge plate component, lower edge plate component and blade body are subjected to densification and shaping treatment respectively to meet the assembly density requirements; before assembly, excess deposits at the split structure are cleaned.

[0024] 5.3) Trim the inner core baffle to the dimensions according to the cavity shape, and then install it into the cavity; trim the dimensions of the multiple baffles and install them onto the blade body;

[0025] 5.4) Use composite pins to assemble the upper edge plate component, lower edge plate component and blade body online, deposit them in the furnace, and then process the turbine guide blade to ensure that the final size and profile meet the requirements, thus obtaining the turbine guide blade.

[0026] Furthermore, in step 5.3), before installing the inner core baffle, multiple limiting pins are installed at designated positions within the cavity, and then the inner core baffle is installed, with the position of the inner core baffle being limited by the multiple limiting pins.

[0027] Further, in step 5.3), before installing multiple baffles, a corresponding number of countersunk conical holes are machined at designated positions on the blade back and blade basin, and then the multiple baffles are adjusted in size and installed into the countersunk conical holes on the blade back and blade basin.

[0028] Furthermore, in step 4), the self-healing matrix is ​​a B4C self-healing matrix.

[0029] The beneficial effects of this invention are:

[0030] 1. The present invention relates to a method for fabricating a multi-cavity high-pressure turbine guide vane made of ceramic matrix composite material. The blade components are fabricated separately, reducing molding difficulty. The blade components are multi-cavity structures, achieved by combining the blade body and an inner core baffle. Compared to integrally molded multi-cavity structures, the present invention uses a modular assembly method to achieve the multi-cavity structure of the blade components. This method is simple to fabricate, convenient to assemble, and improves operability. Furthermore, the inner core baffle provides support, increasing the strength of the blade components.

[0031] 2. The method for fabricating a ceramic matrix composite multi-cavity high-pressure turbine guide vane of this invention employs specialized graphite tooling to ensure the slit structure of the blade body. The process requires updating the tooling with the slit structure between adjacent batches, solving the molding problem of small-sized multi-cavity blades, reducing installation difficulty, and improving installation reliability. By combining tooling and process methods, high dimensional accuracy of the open slit at the blade tip is ensured, solving the molding problem of micro-slits in ceramic matrix composites. Furthermore, the use of ceramic matrix composites reduces the overall weight of the component while ensuring reliable component strength.

[0032] 3. The method for preparing the ceramic matrix composite multi-cavity high-pressure turbine guide vane of the present invention includes an array of through holes near the slit region of the blade body. The upper and lower shapes of the through holes are machined into countersunk conical holes. A turbulence column is installed in the through hole. During the CVI-SiC deposition process after the turbulence column is installed, the SiC deposit adheres to the gap between the conical hole and the turbulence column, realizing the online "riveting" connection of the turbulence column and improving the connection strength of the turbulence column. Attached Figure Description

[0033] Figure 1 This is a schematic diagram of the turbine guide vane product in an embodiment of the method for preparing a ceramic matrix composite multi-cavity high-pressure turbine guide vane of the present invention;

[0034] Figure 2 This is a schematic diagram of the blade component in an embodiment of the method for preparing a ceramic matrix composite multi-cavity high-pressure turbine guide blade of the present invention;

[0035] Figure 3This is a schematic diagram of the installation of the turbulence column in an embodiment of the method for preparing the ceramic matrix composite multi-cavity high-pressure turbine guide vane of the present invention;

[0036] Figure 4 This is an enlarged schematic diagram of the countersunk conical hole for installing the turbulence column in an embodiment of the method for preparing the multi-cavity high-pressure turbine guide vane of ceramic matrix composite material of the present invention;

[0037] Figure 5 This is an exploded view of the inner mold, graphite tooling, and blade body in an embodiment of the method for preparing a ceramic matrix composite multi-cavity high-pressure turbine guide blade of the present invention.

[0038] Figure 6 This is a diagram illustrating the installation of the limiting pin, inner core baffle, and turbulence column on the blade body in an embodiment of the preparation method of the ceramic matrix composite multi-cavity high-pressure turbine guide vane of the present invention.

[0039] Figure label:

[0040] 1-Blade body component; 11-Inner core baffle; 12-Break column; 13-Slit structure; 14-Blade body; 15-Limiting pin; 16-Blade back; 17-Blade basin; 2-Lower edge plate component; 3-Upper edge plate component; 4-Composite pin; 5-Inner mold; 6-Graphite tooling. Detailed Implementation

[0041] The present invention will now be described in detail with reference to embodiments and accompanying drawings.

[0042] This invention discloses a method for preparing a ceramic matrix composite multi-cavity high-pressure turbine guide vane, the structure of which is as follows: Figure 1 As shown, the blade includes a blade assembly 1 and upper edge plate 3 and lower edge plate 2 respectively disposed on both sides of the blade assembly 1. The upper edge plate 3 includes upper edge plate one, upper edge plate two, upper edge plate three, and upper edge plate four, etc. The upper edge plate one, upper edge plate two, upper edge plate three, and upper edge plate four are surface-fitted together, and the parts of the upper edge plate 3 are riveted and welded together using composite pins 4. The lower edge plate 2 is located on the opposite side of the upper edge plate 3. The lower edge plate 2 includes lower edge plate one, lower edge plate two, and lower edge plate three, etc. The inner surface of lower edge plate three is fitted with the outer surfaces of lower edge plate one and lower edge plate two, respectively. The parts of the lower edge plate 2 are riveted and welded together using composite pins 4. See also Figure 2The blade component 1 includes a blade body 14, an inner core baffle 11, and multiple spoiler columns 12. The blade body 14 includes a curved blade back 16 and a blade base 17, which are smoothly connected to form a curved structure containing a cavity, and the trailing edge forms a slit structure 13. An inner core baffle 11 is disposed in the middle of the cavity within the blade body 14, dividing the cavity into two sub-cavities. Multiple limiting pins 15 are disposed within the cavity to limit the position of the inner core baffle 11 within the cavity. An array of through holes is respectively provided on the blade back 16 and the blade base 17 near the slit structure 13, with the through holes on the blade back 16 and the blade base 17 corresponding to each other, for mounting multiple spoiler columns 12. The through holes have a size of φ1.5. The multiple spoiler columns 12 form two arrayed spoiler columns 12, arranged one after the other with a gap in between. See also... Figure 3 and Figure 4 The through holes on the back of the blade 16 and the through holes on the base of the blade 17 are both countersunk conical holes. The upper and lower shapes of the through holes (i.e., the turbulence column holes) are countersunk conical holes. There is a gap between the countersunk conical holes and the cylindrical pins. During the subsequent CVI-SiC deposition process, the SiC deposits adhere to the gaps, realizing the online "riveting" connection of the pins.

[0043] In this invention, the multi-cavity structure of the high-pressure turbine guide vane is achieved by assembling the blade body 14 and the inner core baffle 11. The components of the ceramic matrix composite high-pressure turbine guide vane are formed using two-dimensional layup and then fabricated using CVI-SIC and self-healing processes. The trailing edge of the ceramic matrix composite high-pressure turbine guide vane has a slit structure 13. During the fabrication of the blade body 14, a special mold is used to weave silicon carbide fiber cloth, and the blade is formed using a combination of an inner core mold and an outer mold. A specially designed graphite tooling 6 is used to separate the slit structure 13 in the trailing edge region. The inner core mold and the graphite tooling 6 ensure that the dimensions of the slit region in the trailing edge of the blade meet the requirements.

[0044] The above-mentioned method for manufacturing turbine guide vanes includes the following steps:

[0045] 1) Preparation of turbine guide vane preform

[0046] 1.1) Using fiber cloth, the prefabricated upper edge plate component 3 and lower edge plate component 2 are respectively woven using the upper edge plate component 3 mold and the lower edge plate component 2 mold, with allowance in the external dimensions. The fiber cloth mentioned in this invention is made of carbon fiber and / or silicon carbide fiber.

[0047] 1.2) Prepare the first outer mold, the second outer mold, the inner mold 5, and the graphite tooling 6 respectively;

[0048] Using the leaf back 16 and leaf basin 17 as references, the first and second outer molds were prepared respectively; see [link to documentation]. Figure 5Using the cavity of the blade body 14 as a reference, an inner mold 5 is prepared; using the slit structure 13 as a reference, a graphite tooling 6 is prepared; wherein, the first outer mold, the second outer mold, and the inner mold 5 are all provided with a number of ventilation holes perpendicular to the mold surface and used for sewing, and the materials used to prepare the first outer mold, the second outer mold, the inner mold 5, and the slit structure 13 are all high temperature resistant materials.

[0049] 1.3) Use fiber cloth to wind the fiber cloth along the inner mold 5 to the designed thickness and make the tail edge form a split structure 13 to ensure that the size of the split structure 13 meets the requirements; close and fix the first outer mold, the second outer mold and the inner mold 5; use the ventilation hole as the stitching path to weave the preform of the blade body 14.

[0050] 2) According to the boron nitride interface layer thickness requirements, a chemical vapor deposition furnace is used to prepare the boron nitride interface layer for the prefabricated upper edge plate component 3, the prefabricated lower edge plate component 2, and the prefabricated blade body 14, respectively. The boron nitride interface layer is deposited in 3 to 5 batches according to the thickness requirements. Before deposition, graphite tooling 6 and graphite paper are laid at the split structure 13 of the prefabricated blade body 14. New graphite tooling 6 and graphite paper are used for each batch.

[0051] 3) Using a CVI-SiC vapor deposition system, SiC substrates were prepared for the preforms of the upper edge plate component 3, the lower edge plate component 2, and the blade body 14, respectively. Each preform was deposited in multiple batches to ensure that the density met the predetermined requirements. After each batch of deposition, a special tooling was used to correct the shape of the corresponding preform. During the densification process of the blade body 14 preform, the area of ​​the split structure 13 was inspected before each batch of deposition to prevent adhesion in the area of ​​the split structure 13 and to ensure that the dimensions of the split structure 13 met the requirements. For each batch of deposition, a new graphite tooling 6 and graphite paper pads were used at the split structure 13.

[0052] 4) Within the specified density requirement range, B4C self-healing matrix was prepared for the prefabricated upper edge plate component 3, the prefabricated lower edge plate component 2, and the prefabricated blade body 14, respectively, to obtain the upper edge plate component 3, the lower edge plate component 2, and the blade body 14.

[0053] 5) Processing and assembly

[0054] 5.1) According to the pre-designed process part numerical model requirements, CNC machining equipment is used to process the upper edge plate component 3, the lower edge plate component 2 and the blade body 14 respectively.

[0055] 5.2) The upper edge plate component 3, the lower edge plate component 2 and the blade body 14 are respectively subjected to density enhancement treatment and are corrected using special tooling until the assembly density requirements are met; before assembly, excess deposits at the split structure 13 are cleaned using special tools.

[0056] 5.3) Install multiple limiting pins 15 into designated positions within the cavity; trim the inner core baffle 11 to the dimensions of the cavity's internal shape, install the inner core baffle 11 into the cavity, and fix the position of the inner core baffle 11 using the limiting pins 15; before installing multiple baffle columns 12, machine a corresponding number of countersunk conical holes at designated positions on the blade back 16 and blade base 17, then trim the dimensions of the multiple baffle columns 12 and install them into the countersunk conical holes from the blade body 14 to the blade back 16 and blade base 17, see [reference]. Figure 6 .

[0057] 5.4) The upper edge plate component 3, the lower edge plate component 2 and the blade body 14 are assembled online using tooling using composite pins 4 and connected online using composite pins 4. Then, the pins are deposited in the furnace to achieve "riveting and welding". The turbine guide blade is then processed using tooling. The dimensions and profile are checked with the help of tooling to obtain the turbine guide blade with the final dimensions and profile that meet the requirements.

[0058] 6) Coating preparation: Prepare a specific ratio of coating material and apply it by brushing and high-temperature curing to prepare a glass coating for the turbine guide vane product.

[0059] 7) Perform final inspection on the turbine guide vanes; the final density of the vane components is 2.4–2.5 g / cm³. 3 .

Claims

1. A method for preparing a ceramic matrix composite multi-cavity high-pressure turbine guide vane, wherein the turbine guide vane comprises a blade component (1) and an upper edge plate component (3) and a lower edge plate component (2) respectively disposed on both sides of the blade component (1); the blade component (1) comprises a blade body (14), at least one inner core baffle (11) and multiple turbulence columns (12); the blade body (14) comprises a curved blade back (16) and a blade basin (17), the blade back (16) and the blade basin (17) are smoothly connected to form a curved surface structure containing cavities, and the trailing edge forms a slit structure (13); the at least one inner core baffle (11) is disposed in the middle of the cavity in the blade body (14) to divide the cavity into multiple sub-cavities; the multiple turbulence columns (12) are arranged in an array in the cavity near the slit structure (13), and the two ends of the turbulence columns (12) penetrate the blade back (16) and the blade basin (17) respectively; Its characteristic is that it includes the following preparation steps: 1) Preparation of preforms 1.1) Using fiber cloth, the upper edge plate component (3) prefabricated body and the lower edge plate component (2) prefabricated body are respectively woven using molds; 1.2) Prepare the first outer mold, the second outer mold, the inner mold (5), and the graphite tooling (6) respectively; 1.3) Using fiber cloth, the first outer mold, the second outer mold and the inner mold (5) are used to make the blade body (14) preform, and the trailing edge forms a split structure (13) of a specified size; 2) Based on the required thickness of the boron nitride interface layer, prepare the boron nitride interface layer for each preform. 3) Prepare SiC matrix for the preforms of the upper edge plate component (3), the lower edge plate component (2), and the blade body (14) respectively, to ensure that the density meets the predetermined requirements; each preform needs to be corrected after each batch of deposition; during the densification process of the blade body (14) preform, the area of ​​the split structure (13) needs to be inspected before each batch of deposition to prevent adhesion; each batch needs to use a new graphite tooling (6) and graphite paper pad at the split structure (13); 4) Each preform was prepared with a self-healing matrix to obtain an upper edge plate component (3), a lower edge plate component (2), and a blade body (14) that meet the density requirements. 5) The upper edge plate component (3), the lower edge plate component (2) and the blade body (14) are processed respectively; the inner core baffle (11) and multiple turbulence columns (12) are installed at the designated positions of the blade body (14); the upper edge plate component (3), the lower edge plate component (2) and the blade body (14) are assembled online, and then deposited and processed in sequence to obtain turbine guide vanes that meet the requirements.

2. The method for preparing a ceramic matrix composite multi-cavity high-pressure turbine guide vane according to claim 1, characterized in that, Step 1.2) specifically refers to: Using the back of the leaf (16) and the leaf basin (17) as references, the first outer mold and the second outer mold are prepared respectively; using the cavity of the leaf body (14) as references, the inner mold (5) is prepared; using the splitting structure (13) as references, the graphite tooling (6) is prepared; wherein, the first outer mold, the second outer mold and the inner mold (5) are all provided with a number of ventilation holes perpendicular to the mold surface and used for sewing, and the materials used to prepare the first outer mold, the second outer mold, the inner mold (5) and the splitting structure (13) are all high temperature resistant materials.

3. The method for preparing a ceramic matrix composite multi-cavity high-pressure turbine guide vane according to claim 1 or 2, characterized in that: The fiber cloth described in steps 1.1) and 1.3) is carbon fiber and / or silicon carbide fiber.

4. The method for preparing a ceramic matrix composite multi-cavity high-pressure turbine guide vane according to claim 3, characterized in that, Step 1.3) specifically refers to: The fiber cloth is wound along the inner mold (5) to the designed thickness, and the tail edge forms a split structure (13) to ensure that the size of the split structure (13) meets the requirements; the first outer mold, the second outer mold and the inner mold (5) are closed and fixed; the blade body (14) preform is obtained by using the ventilation hole as the stitching path.

5. The method for preparing a ceramic matrix composite multi-cavity high-pressure turbine guide vane according to claim 4, characterized in that, Step 2) specifically involves: According to the boron nitride interface layer thickness requirements, a chemical vapor deposition furnace was used to prepare the boron nitride interface layer for the preforms of the upper edge plate component (3), the lower edge plate component (2), and the blade body (14), respectively. The boron nitride interface layer was deposited in 3 to 5 furnaces according to the boron nitride interface layer thickness requirements. Before deposition, graphite tooling (6) and graphite paper were laid on the split structure (13) of the blade body (14) preform. New graphite tooling (6) and graphite paper were used for each furnace.

6. The method for preparing a ceramic matrix composite multi-cavity high-pressure turbine guide vane according to claim 5, characterized in that, Step 5) includes the following steps: 5.1) According to the pre-designed process part numerical model requirements, process parts are processed for the upper edge plate component (3), the lower edge plate component (2) and the blade body (14); 5.2) The upper edge plate component (3), the lower edge plate component (2) and the blade body (14) are subjected to densification and shaping treatment respectively until the assembly density requirements are met; before assembly, the excess deposits at the split structure (13) are cleaned. 5.3) Trim the inner core baffle (11) to the size according to the cavity shape and then install it into the cavity; trim the size of multiple turbulence columns (12) and install them onto the blade body (14); 5.4) Use composite pins (4) to assemble the upper edge plate component (3), lower edge plate component (2) and blade body (14) online, deposit them in the furnace, and then process the turbine guide blade to ensure that the final size and profile meet the requirements, and obtain the turbine guide blade.

7. The method for preparing a ceramic matrix composite multi-cavity high-pressure turbine guide vane according to claim 6, characterized in that: In step 5.3), before installing the inner core baffle (11), multiple limiting pins (15) are installed at designated positions in the cavity, and then the inner core baffle (11) is installed. The position of the inner core baffle (11) is limited by the multiple limiting pins (15).

8. The method for preparing a ceramic matrix composite multi-cavity high-pressure turbine guide vane according to claim 7, characterized in that: In step 5.3), before installing multiple turbulence columns (12), a corresponding number of countersunk conical holes are machined at designated positions on the blade back (16) and blade base (17), and then the multiple turbulence columns (12) are adjusted in size and installed into the countersunk conical holes on the blade back (16) and blade base (17).

9. The method for preparing a ceramic matrix composite multi-cavity high-pressure turbine guide vane according to claim 8, characterized in that: In step 4), the self-healing matrix is ​​a B4C self-healing matrix.

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