阅读说明：本技术 一种具有扰流结构的陶瓷基复合材料涡轮导向叶片及其制备方法 (Ceramic matrix composite turbine guide blade with turbulence structure and preparation method thereof ) 是由 刘持栋 张晰 栗尼娜 涂建勇 刘小冲 成来飞 于 2021-11-19 设计创作，主要内容包括：本发明公开了一种具有扰流结构的陶瓷基复合材料涡轮导向叶片及其制备方法,该导向叶片内腔具有多个贯穿叶盆和叶背的柱状扰流结构,其材质均为陶瓷基复合材料,本发明还提供该叶片的制备方法,包括以下步骤：先制备具有通气孔模具,然后根据模具制备纤维预制体,再依次沉积界面层和陶瓷基体,去除模具后,加工至设计尺寸,然后在制得的叶身壳体的扰流柱部位上,制备垂直于叶片型面的通孔,然后将销钉插入通孔内,再将制得的装配体同质连接,加工、修复后,得到具有扰流结构的陶瓷基复合材料涡轮导向叶片。本发明制备的导向叶片的耐温性得到大幅提升,同时结构重量显著降低,且能够保证型面和尺寸的精度及导向叶片的冷却效果。(The invention discloses a ceramic matrix composite turbine guide vane with a flow disturbance structure and a preparation method thereof, wherein the inner cavity of the guide vane is provided with a plurality of columnar flow disturbance structures penetrating through a vane basin and a vane back, and the material of the columnar flow disturbance structures is ceramic matrix composite material, and the preparation method of the vane comprises the following steps: firstly preparing a mold with an air vent, then preparing a fiber preform according to the mold, then sequentially depositing an interface layer and a ceramic matrix, removing the mold, processing to a design size, then preparing a through hole vertical to the blade profile on the turbulence column part of the prepared blade body shell, then inserting a pin into the through hole, then connecting the prepared assembly body in a homogeneous manner, and obtaining the ceramic matrix composite turbine guide blade with the turbulence structure after processing and repairing. The temperature resistance of the guide vane prepared by the method is greatly improved, the structural weight is obviously reduced, and the precision of the profile and the size and the cooling effect of the guide vane can be ensured.)

1. The utility model provides a ceramic matrix composite turbine guide vane with vortex structure, its characterized in that, guide vane's inner chamber has if disturbing flow post (4), disturb flow post (4) and run through guide vane's lobe basin (3) and blade back (2), the material of guide vane and disturbing flow post (4) is ceramic matrix composite.

2. The ceramic matrix composite turbine nozzle vane with a flow disturbing structure of claim 1, wherein the reinforcement of the ceramic matrix composite is carbon fiber and/or silicon carbide fiber, the ceramic matrix is silicon carbide or silicon nitride, and the ceramic matrix may be silicon carbide or boron carbide.

3. The method for preparing the ceramic matrix composite turbine guide vane with the flow disturbing structure as recited in any one of claims 1 to 2, comprising the steps of:

(1) preparing a through hole vertical to a molded surface on a turbulence column (4) of a blade body shell (1) of the ceramic matrix composite turbine guide blade, inserting a pin made of the same material as the blade body shell (1) into the through hole, penetrating the pin through the through hole, depositing a ceramic matrix made of the same material as the blade body shell (1) on the surface of the prepared assembly body, and completing the homogeneous connection of the pin and the blade body shell (1) to obtain a semi-finished product of the ceramic matrix composite turbine guide blade with a turbulence structure;

(2) and (3) processing the semi-finished product of the ceramic matrix composite turbine guide blade with the turbulent flow structure to the design size, depositing a ceramic matrix which is the same as the blade body shell (1) on the surface, and performing damage repair to obtain the ceramic matrix composite turbine guide blade with the turbulent flow structure.

4. The method for preparing a ceramic matrix composite turbine guide vane with a flow disturbing structure according to claim 3, wherein the pin and the through hole in the step (1) are in interference fit, and the interference is 0.01-0.08 mm.

5. The method for preparing a ceramic matrix composite turbine guide vane with a flow disturbing structure according to claim 3, wherein the ceramic matrix is deposited by chemical vapor deposition in steps (1) and (2), and the number of times of cycle execution is 1-3.

6. The method for preparing the ceramic matrix composite turbine guide vane with the flow disturbing structure according to the claim 3, wherein the blade body shell (1) of the ceramic matrix composite turbine guide vane in the step (1) is prepared by the following steps:

(1.1) preparing an inner mold of the turbine guide blade, a blade basin (3) mold and a blade back (2) mold which are all provided with vent holes by using high-temperature resistant materials;

(1.2) winding carbon fiber cloth and/or silicon carbide fiber cloth on the outer surface of an inner mold, covering the outer surface with a mold of a leaf basin (3) and a mold of a leaf back (2), sewing the inner mold, the mold of the leaf basin (3), the mold of the leaf back (2) and the carbon fiber cloth and/or the silicon carbide fiber cloth wound on the inner mold into a whole by taking a carbon fiber bundle or a silicon carbide fiber bundle as a sewing line and taking a vent hole as a sewing path, and thus obtaining a turbine guide blade fiber prefabricated body clamped with the molds;

(1.3) sequentially depositing an interface layer and a ceramic matrix on the surface of the turbine guide blade fiber preform, then removing the mold, and processing to the designed size to obtain the blade body shell (1) of the ceramic matrix composite turbine guide blade.

7. The method for preparing a ceramic matrix composite turbine guide vane with a flow disturbing structure according to claim 6, wherein the high temperature resistant material in the step (1.1) is electrode graphite or high purity graphite.

8. The method for preparing a ceramic matrix composite turbine guide vane with a turbulent flow structure of claim 6, wherein the thickness of the wound carbon fiber cloth and/or silicon carbide fiber cloth in step (1.2) is 1.05-1.2 times of the designed thickness of the ceramic matrix composite turbine guide vane with a turbulent flow structure.

9. The method for preparing a ceramic matrix composite turbine guide vane with a turbulated structure in claim 6, wherein in step (1.3), the interfacial layer is a boron nitride interfacial layer.

Technical Field

The invention relates to the technical field of gas turbine engine manufacturing, in particular to a ceramic matrix composite turbine guide vane with a turbulent flow structure and a preparation method thereof.

Background

In gas turbine engines such as aircraft engines and gas turbines, increasing the pre-turbine gas temperature is one of the most direct and effective methods for improving engine performance. For the turbine system of the engine, increasing the temperature of the gas before the turbine means increasing the design requirement of the turbine guide vane, which requires the turbine guide vane to work in the severe environment of high temperature, high pressure and high speed gas flow scouring for a long time. The gas temperature before the turbine of the prior advanced aeroengine can reach more than 2000K, the commonly used high-temperature alloy turbine guide blade can not meet the use requirement, even with the world's recognized potential for ceramic matrix composites as the host material for high pressure turbine guide vanes, in the face of severe working conditions and increasing demands, cooling measures are still needed to ensure that the structure works in a proper temperature environment, and under the general condition, the turbine guide vane is of a hollow structure, the cooling form is divided into external cooling and internal cooling, in the internal cooling form, the turbulence column array is arranged in the inner cavity of the guide blade, which is one of the main technical approaches for obtaining the blade cooling effect, the turbulence column array is generally arranged on the pressure side surface and the suction side surface of the internal cooling channel, the internal cooling channel has the characteristics of simple structure and good heat exchange performance, and the turbulence column array enhances the structural strength and the rigidity of the tail edge while enhancing the heat exchange.

However, when the ceramic matrix composite is used as the main material of the turbine guide vane, the spoiler column array structure is difficult to directly shape at the fiber preform preparation stage, and if the prepared solid ceramic matrix composite is used to prepare the vane by a machining way, the continuity of fibers is damaged, the strength and the service life of the vane are further influenced, and the complicated processing of a plurality of spoiler columns is difficult to realize.

Disclosure of Invention

In order to solve the technical problems, the invention aims to provide a ceramic matrix composite turbine guide vane with a turbulence structure and a preparation method thereof, so as to solve the problem that in the prior art, when a ceramic matrix composite is used as a main material of the turbine guide vane, the turbulence column array structure is difficult to directly shape at the preparation stage of a fiber preform.

The technical scheme for solving the technical problems is as follows: the utility model provides a ceramic matrix composite turbine guide vane with vortex structure, this guide vane inner chamber have if disturb the flow post, disturb the flow post and run through guide vane's basin and blade back, guide vane and the material that disturbs the flow post are ceramic matrix composite.

The invention has the beneficial effects that: according to the invention, the ceramic matrix composite material turbulence columns are arranged between the blade basin and the blade back of the ceramic matrix composite material turbine guide blade, so that the integral material unification is realized, the rigidity and the strength of the tail edge part of the blade are enhanced, the turbulence column array is realized, the temperature resistance is improved by about 300 ℃, and the structural weight is reduced by more than 50%.

On the basis of the technical scheme, the invention can be further improved as follows:

furthermore, the reinforcement of the ceramic matrix composite material is carbon fiber and/or silicon carbide fiber, the ceramic matrix is silicon carbide or silicon nitride, and the ceramic matrix can also be silicon carbide and boron carbide.

The invention also provides a preparation method of the ceramic matrix composite turbine guide vane with the turbulent flow structure, which comprises the following steps:

(1) preparing a through hole vertical to the molded surface on a turbulence column part of a blade body shell of the ceramic matrix composite turbine guide blade, then inserting a pin made of the same material as the blade body shell into the through hole, penetrating the pin through the through hole, depositing a ceramic matrix made of the same material as the blade body shell on the surface of the prepared assembly body, and completing the homogeneous connection of the pin and the blade body shell to obtain a semi-finished product of the ceramic matrix composite turbine guide blade with a turbulence structure;

(2) and processing the semi-finished product of the ceramic matrix composite turbine guide blade with the turbulent flow structure to a design size, depositing a ceramic matrix which is the same as the blade body shell on the surface, and then performing damage repair to obtain the ceramic matrix composite turbine guide blade with the turbulent flow structure.

Further, the diameter of the through hole in the step (1) is consistent with that of the turbulence column.

Further, in the step (1), the pin and the through hole are in interference fit, and the interference magnitude is 0.01-0.08 mm.

Further, the deposition of the ceramic substrate in the steps (1) and (2) is carried out by using a chemical vapor deposition method, and the cycle execution times are 1-3 times.

Further, the blade body shell of the ceramic matrix composite turbine guide blade in the step (1) is prepared through the following steps:

(1.1) preparing an inner mould, a blade basin mould and a blade back mould of the turbine guide blade with the vent holes by using high-temperature resistant materials;

(1.2) winding carbon fiber cloth and/or silicon carbide fiber cloth on the outer surface of an inner mold, covering the inner mold with a leaf basin mold and a leaf back mold, sewing the inner mold, the leaf basin mold, the leaf back mold and the fiber cloth wound on the inner mold into a whole by taking carbon fiber bundles or silicon carbide fiber bundles as sewing lines and taking vent holes as sewing paths, and thus obtaining a turbine guide blade fiber preform clamped with the mold;

and (1.3) sequentially depositing an interface layer and a ceramic matrix on the surface of the turbine guide blade fiber preform, then removing the mold, and processing to the designed size to obtain the blade body shell of the ceramic matrix composite turbine guide blade.

Further, the high-temperature resistant material in the step (1.1) is electrode graphite or high-purity graphite.

Further, high purity graphite means that the carbon content of graphite is > 99.99%.

Further, the wall thickness of the inner mould, the leaf basin mould and the leaf back mould in the step (1.1) is 2.5-8 mm.

Further, the aperture of the vent hole in the step (1.1) is 3-8 mm.

Further, the thickness of the wound carbon fiber cloth and/or silicon carbide fiber cloth in the step (1.2) is 1.05-1.2 times of the designed thickness of the ceramic matrix composite turbine guide blade with the turbulent flow structure.

Further, in the step (1.2), the carbon fiber cloth and/or the silicon carbide fiber cloth is 2.5-dimensional fiber woven cloth, two-dimensional plain-weave fiber woven cloth or two-dimensional satin-weave fiber woven cloth.

Further, the step (1.3) of depositing the interface layer and the ceramic matrix is depositing by using a chemical vapor deposition method.

Further, the thickness of the interface layer in step (1.3) is 100-600 nm.

Further, the interface layer in step (1.3) is a boron nitride interface layer.

Further, the preparation process of the boron nitride interface layer is as follows: heating to 650-1000P at the pressure of 50-1000P, keeping the temperature for 1-2h, introducing mixed gas of argon, hydrogen, ammonia and boron trichloride, depositing for 15-35h, keeping the temperature for 1-2h, and cooling to room temperature; wherein the flow ratio of argon, hydrogen, ammonia and boron trichloride is 1: 1-3: 2-8: 2-8.

Further, the preparation cycle of the boron nitride interface layer is performed 1-3 times.

Further, in the step (1.3), the ceramic matrix is silicon carbide or silicon nitride, and the ceramic matrix can also be silicon carbide or boron carbide.

Further, when the ceramic matrix is silicon carbide, the preparation process is as follows: heating to 900-class sand 1200 ℃ under the pressure of 200-class sand 5000Pa, keeping the temperature for 1-2h, introducing mixed gas of trichloromethylsilane, hydrogen and argon, depositing for 30-60h, keeping the temperature for 1-2h, and cooling to room temperature; the loop is executed 4-8 times.

Further, when the ceramic matrix is silicon nitride, the preparation process is as follows: heating to 700-1200 ℃ under the pressure of 200-5000Pa, preserving heat for 1-2h, then mixing hydrogen, argon, trichloromethylsilane and ammonia gas at the flow ratio of 1: 5-50, depositing for 24-80h, then continuing preserving heat for 1-2h, and cooling to room temperature; the loop is executed 4-8 times.

Further, when the ceramic matrix is silicon carbide and boron carbide, the preparation process is as follows: firstly preparing a silicon carbide ceramic matrix, then executing a preparation process of the boron carbide ceramic matrix once, and then executing a preparation process of the silicon carbide ceramic matrix once, and thus circularly operating the steps executed once for 1-4 times;

wherein the preparation process of the boron carbide ceramic matrix comprises the following steps: heating to 850-1100 ℃ under the pressure of 2-50kPa, keeping the temperature for 1-2h, introducing a mixed gas of methane, boron trichloride and hydrogen, wherein the flow ratio of the methane, the boron trichloride and the hydrogen is 1: 1-10: 5-50, depositing for 10-80h, keeping the temperature for 1-2h, and cooling to room temperature.

Further, the processes of the chemical vapor deposition methods in the steps (1) and (2) are identical to the process of preparing the ceramic substrate in the step (1.3).

The invention has the following beneficial effects:

firstly, the density of the ceramic matrix composite material is 2.0 to 2.5g/cm³The density of the traditional high-temperature alloy material is about 8.5-8.9g/cm³Therefore, the ceramic matrix composite material is used as the main material of the turbine guide vane, and the weight of the component structure can be reduced by more than 50%; in addition, the ceramic matrix composite can maintain more than 85% of mechanical property below 1350 ℃ for a long time without cooling measures, and compared with the temperature resistance of a high-temperature alloy material at 1050 ℃, the temperature resistance of the component can be greatly improved.

The guide blade and the turbulence column adopted by the invention are made of homogeneous ceramic matrix composite materials with completely consistent mechanical and physical properties, so that all components of the blade member have good physical and chemical compatibility. The technology can realize the preparation of the ceramic matrix composite guide vane member with the complex turbulence column array characteristics, the member precision can meet the requirements of m-grade size precision specified by GB/T1804-.

Drawings

FIG. 1 is a schematic structural view of a ceramic matrix composite turbine vane having a turbulation structure in accordance with the present invention;

FIG. 2 is a top view of a ceramic matrix composite turbine vane having a turbulator structure in accordance with the present invention;

fig. 3 is a cross-sectional view at a in fig. 2.

Wherein, 1, a blade body shell; 2. leaf back; 3. leaf basin; 4. and (4) a turbulence column.

Detailed Description

The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention. The examples, in which specific conditions are not specified, were conducted under conventional conditions or conditions recommended by the manufacturer. The reagents or instruments used are not indicated by the manufacturer, and are all conventional products available commercially.

Example 1:

a ceramic matrix composite turbine guide vane with a turbulent flow structure is prepared by the following steps:

(1) designing and preparing an inner mold according to the size of the molded surface of the inner cavity of the guide blade by using electrode graphite as a raw material, and respectively designing and preparing a blade basin 3 mold and a blade back 2 mold according to the sizes of the molded surfaces of a blade basin and a blade back of the guide blade; wherein, the wall thickness of the inner mould, the leaf basin 3 mould and the leaf back 2 mould is 4mm, and a large number of vent holes with the aperture of 4mm are arranged on the inner mould, the leaf basin 3 mould and the leaf back 2 mould;

(2) winding 2.5-dimensional silicon carbide fiber woven cloth on the outer surface of an inner mold, wherein the winding thickness is 1.1 times of the design thickness of the guide blade, covering the guide blade by using a leaf basin 3 mold and a leaf back 2 mold, sewing the inner mold, the leaf basin 3 mold, the leaf back 2 mold and the fiber woven cloth wound on the inner mold into a whole by using a silicon carbide fiber bundle as a sewing line and using a vent hole as a sewing path, and thus obtaining a turbine guide blade fiber preform clamped with the molds;

(3) placing the turbine guide blade fiber preform clamped with the mold in a chemical vapor deposition furnace, sequentially depositing a 580nm boron nitride interface layer and a silicon carbide ceramic matrix on the surface of the turbine guide blade fiber preform, then removing the mold, and processing the turbine guide blade fiber preform to a design size according to a design drawing to obtain a blade body shell 1 of the ceramic matrix composite turbine guide blade;

the preparation process of the boron nitride interface layer comprises the following steps: the pressure in the furnace body is 800Pa, the temperature is raised to 680 ℃, after 2h of heat preservation, mixed gas of argon, hydrogen, ammonia and boron trichloride gas is introduced, and the flow ratio of the argon, the hydrogen, the ammonia and the boron trichloride is 1: 1-3: 2-8: 2-8, depositing for 30h, then keeping the temperature for 2h, and cooling to room temperature; the above operation is performed circularly for 2 times;

the preparation process of the silicon carbide ceramic matrix comprises the following steps: the pressure in the furnace body is 1500Pa, the temperature is raised to 1100 ℃, after 2h of heat preservation, mixed gas of trichloromethyl silane, hydrogen and argon is introduced, the flow ratio of trichloromethyl silane, hydrogen and argon is 1: 10: 18, after 48h of deposition, the temperature is kept for 2h, and the temperature is reduced to room temperature; the above operation is cyclically executed for 8 times;

(4) preparing a through hole vertical to the blade profile on a turbulence column 4 part of a blade body shell 1 of the ceramic matrix composite turbine guide blade in a machining mode, wherein the diameter of the through hole is consistent with that of the turbulence column 4, then inserting a silicon carbide ceramic matrix composite pin into the through hole, wherein the pin penetrates through the through hole, the pin and the through hole are in interference fit, and the interference magnitude is 0.05mm, then placing the prepared assembly body in a silicon carbide chemical vapor deposition furnace, and completing the homogeneous connection of the pin and the blade body shell 1 to obtain a semi-finished product of the ceramic matrix composite turbine guide blade with a turbulence structure; wherein, the process of homogeneous connection is the same as the preparation process of the silicon carbide ceramic matrix in the step (3), and the cycle is executed for 2 times.

(5) Machining a semi-finished product of the ceramic matrix composite turbine guide blade with the turbulent flow structure to a designed size by adopting a mechanical machining method, and then placing the semi-finished product in a silicon carbide chemical vapor deposition furnace for damage repair to obtain the ceramic matrix composite turbine guide blade with the turbulent flow structure; wherein, the damage repairing process is the same as the preparation process of the silicon carbide ceramic matrix in the step (3), and the cycle is executed for 2 times.

Example 2:

a ceramic matrix composite turbine guide vane with a turbulent flow structure is prepared by the following steps:

(1) designing and preparing an inner mold according to the size of the molded surface of the inner cavity of the guide blade by using electrode graphite as a raw material, and respectively designing and preparing a blade basin 3 mold and a blade back 2 mold according to the sizes of the molded surfaces of a blade basin and a blade back of the guide blade; wherein, the wall thickness of the inner mould, the leaf basin 3 mould and the leaf back 2 mould is 2.5mm, and a large number of vent holes with the aperture of 3mm are arranged on the inner mould, the leaf basin 3 mould and the leaf back 2 mould;

(2) winding two-dimensional plain woven carbon fiber cloth on the outer surface of an inner mold, wherein the winding thickness is 1.05 times of the design thickness of the guide blade, covering the guide blade by using a blade basin 3 mold and a blade back 2 mold, sewing the inner mold, the blade basin 3 mold, the blade back 2 mold and the woven fiber cloth wound on the inner mold into a whole by using a silicon carbide fiber bundle as a sewing line and using a vent hole as a sewing path, and thus obtaining a turbine guide blade fiber preform clamped with the molds;

(3) placing the turbine guide blade fiber preform clamped with the mold in a chemical vapor deposition furnace, sequentially depositing a 100nm boron nitride interface layer and a silicon nitride ceramic matrix on the surface of the turbine guide blade fiber preform, then removing the mold, and processing the turbine guide blade fiber preform to a design size according to a design drawing to obtain a blade body shell 1 of the ceramic matrix composite turbine guide blade;

the preparation process of the boron nitride interface layer comprises the following steps: the pressure in the furnace body is 50Pa, the temperature is raised to 1000 ℃, after 2h of heat preservation, mixed gas of argon, hydrogen, ammonia and boron trichloride gas is introduced, and the flow ratio of the argon, the hydrogen, the ammonia and the boron trichloride is 1: 1-3: 2-8: 2-8, depositing for 15h, then keeping the temperature for 2h, and cooling to room temperature; the above operation is performed circularly for 2 times;

the preparation process of the silicon nitride ceramic matrix comprises the following steps: heating to 750 ℃ under the pressure of 2000Pa, keeping the temperature for 2h, introducing mixed gas of hydrogen, argon, trichloromethylsilane and ammonia gas, wherein the flow ratio of the hydrogen, the argon, the trichloromethylsilane and the ammonia gas is 1: 20: 15, depositing for 60h, keeping the temperature for 2h, and cooling to room temperature; the above operation is cyclically executed for 6 times;

(4) preparing a through hole vertical to the blade profile on a turbulence column 4 part of a blade body shell 1 of the ceramic matrix composite turbine guide blade in a machining mode, wherein the diameter of the through hole is consistent with that of the turbulence column 4, then inserting a pin of the silicon nitride ceramic matrix composite into the through hole, the pin penetrates through the through hole, the pin and the through hole are in interference fit, and the interference magnitude is 0.01mm, then placing the prepared assembly body in a silicon nitride chemical vapor deposition furnace, and completing the homogeneous connection of the pin and the blade body shell 1 to obtain a semi-finished product of the ceramic matrix composite turbine guide blade with a turbulence structure; wherein, the process of homogeneous connection is the same as the preparation process of the silicon nitride ceramic matrix in the step (3).

(5) Machining a semi-finished product of the ceramic matrix composite turbine guide blade with the turbulent flow structure to a designed size by adopting a mechanical machining method, and then placing the semi-finished product in a silicon nitride chemical vapor deposition furnace for damage repair to obtain the ceramic matrix composite turbine guide blade with the turbulent flow structure; wherein, the damage repairing process is the same as the preparation process of the silicon nitride ceramic matrix in the step (3).

Example 3:

a ceramic matrix composite turbine guide vane with a turbulent flow structure is prepared by the following steps:

(1) designing and preparing an inner mold according to the size of the molded surface of the inner cavity of the guide blade by using electrode graphite as a raw material, and respectively designing and preparing a blade basin 3 mold and a blade back 2 mold according to the sizes of the molded surfaces of a blade basin and a blade back of the guide blade; wherein, the wall thickness of the inner mould, the leaf basin 3 mould and the leaf back 2 mould is 8mm, and a large number of vent holes with the aperture of 8mm are arranged on the inner mould, the leaf basin 3 mould and the leaf back 2 mould;

(2) winding two-dimensional satin silicon carbide fiber woven cloth on the outer surface of an inner mold, wherein the winding thickness is 1.2 times of the design thickness of the guide blade, then covering the guide blade by using a leaf basin 3 mold and a leaf back 2 mold, using a silicon carbide fiber bundle as a suture line, and sewing the inner mold, the leaf basin 3 mold, the leaf back 2 mold and the fiber woven cloth wound on the inner mold into a whole by using a vent hole as a suture path to obtain a turbine guide blade fiber preform clamped with the molds;

(3) placing the turbine guide blade fiber preform clamped with the mold in a chemical vapor deposition furnace, depositing a 600nm boron nitride interface layer on the surface of the turbine guide blade fiber preform, then depositing a silicon carbide and boron carbide ceramic matrix on the interface layer, removing the mold, and processing the turbine guide blade fiber preform to a design size according to a design drawing to obtain a blade body shell 1 of the ceramic matrix composite turbine guide blade;

the preparation process of the boron nitride interface layer comprises the following steps: the pressure in the furnace body is 1000Pa, the temperature is raised to 650 ℃, after 2h of heat preservation, mixed gas of argon, hydrogen, ammonia and boron trichloride gas is introduced, and the flow ratio of the argon, the hydrogen, the ammonia and the boron trichloride is 1: 1-3: 2-8: 2-8, depositing for 32h, then keeping the temperature for 2h, and cooling to room temperature. The above operation is cyclically executed for 3 times;

the preparation process of the ceramic matrix of silicon carbide and boron carbide comprises the following steps: firstly preparing a silicon carbide ceramic matrix, then executing a preparation process of the boron carbide ceramic matrix once, and then executing a preparation process of the silicon carbide ceramic matrix once, and thus circularly operating the steps executed once for 2 times;

the preparation process of the silicon carbide ceramic matrix comprises the following steps: the pressure in the furnace body is 1500Pa, the temperature is raised to 1100 ℃, after heat preservation is carried out for 2h, mixed gas of trichloromethyl silane, hydrogen and argon is introduced, the flow ratio of trichloromethyl silane, hydrogen and argon is 1: 8: 16, after deposition is carried out for 48h, heat preservation is carried out for 2h, and the temperature is reduced to room temperature; the above operation is performed 7 times circularly;

the preparation process of the boron carbide ceramic matrix comprises the following steps: heating to 850 ℃ under the condition that the pressure in the furnace body is 25kPa, keeping the temperature for 2h, introducing a mixed gas of methane, boron trichloride and hydrogen, wherein the flow ratio of the methane, the boron trichloride and the hydrogen is 1: 5: 20, depositing for 50h, keeping the temperature for 2h, and cooling to room temperature.

(4) Preparing a through hole vertical to the blade profile on a turbulence column 4 part of a blade body shell 1 of the ceramic matrix composite turbine guide blade in a machining mode, wherein the diameter of the through hole is consistent with that of the turbulence column 4, then inserting a boron carbide ceramic matrix composite pin into the through hole, wherein the pin penetrates through the through hole, the pin and the through hole are in interference fit, and the interference magnitude is 0.08mm, then placing the prepared assembly body in a chemical vapor deposition furnace, and completing the homogeneous connection of the pin and the blade body shell 1 to obtain a semi-finished product of the ceramic matrix composite turbine guide blade with a turbulence structure; wherein, the process of homogeneous connection is the same as the preparation process of the silicon carbide and boron carbide ceramic matrix in the step (3).

(5) Machining a semi-finished product of the ceramic matrix composite turbine guide blade with the turbulent flow structure to a designed size by adopting a mechanical machining method, and then placing the semi-finished product in a carborundum chemical vapor deposition furnace for damage repair to obtain the ceramic matrix composite turbine guide blade with the turbulent flow structure; wherein the damage repairing process is the same as the preparation process of the silicon carbide and boron carbide ceramic matrix in the step (3).

Effect verification

The method comprises the following steps of firstly, carrying out performance detection on the ceramic matrix composite turbine guide vane with the turbulent flow structure prepared in the embodiment 1-3, wherein the test method of density detection comprises the following steps: GB/T2997-: in the Q/AVIC 06185-2015 continuous fiber reinforced ceramic matrix composite high-temperature mechanical property test method, the test results are shown in Table 1, and the test results shown in Table 1 show that the invention can increase the long-term service temperature of the member to 1350 ℃, compared with the 1050 ℃ temperature resistance of the high-temperature alloy material, the temperature resistance of the member is greatly improved, and the structural weight of the member can be reduced by about 50%.

TABLE 1 Long-term service temperature and density of ceramic matrix composite turbine guide vane with turbulent flow structure

Examples	Long service temperature (. degree. C.)	Density (g/cm)3)
			Example 1	1350	2.67
Example 2	1350	2.58
			Example 3	1350	2.62

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.