A method for manufacturing a ceramic matrix composite blade equipped with a micro-perturbation column

Abstract

The present application relates to a kind of ceramic matrix composite vane preparation methods with micro small spoiler column, belong to the technical field of aero-engine component preparation, solve the technical problems that the spoiler column vane prepared with on-line riveting mode exists long cycle, process is complicated, including spoiler column processing, mold spoiler hole processing, blade fiber cloth wrapping, mold setting, blade chemical vapor infiltration, blade again chemical vapor infiltration step.The preparation method is used for the preparation of ceramic matrix composite vane with micro small spoiler column.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine component manufacturing technology, specifically relating to a method for preparing ceramic matrix composite blades equipped with micro-turbulence pillars. Background Technology

[0002] Blades are a crucial component of aero-engines, exhibiting high strength, stiffness, and structural stability under the high temperatures and dynamic / static loads of aero-engine environments. Next-generation aero-engine blades must withstand increasingly stringent working stresses and environmental loads such as high temperatures and high pressures, making their development and manufacturing levels significantly impact engine performance. Rapid ventilation and heat dissipation of aero-engine blades are essential for ensuring structural stability under harsh conditions. Due to the small size of blades, the number of tiny heat dissipation and ventilation holes on their surface is limited and difficult to manufacture. Therefore, reserving a heat dissipation slot at the blade tail has become a research trend for new blades. To prevent overheating at the heat dissipation slot at the blade tail, micro-turbulence columns need to be designed at the slot to disperse heat, thereby improving its service life.

[0003] Blade spoiler structures are generally fabricated using in-line riveting. The blade and carbon-ceramic composite pins are riveted together in-line using chemical vapor infiltration. The fabrication process of blade spoiler structures requires specialized riveting fixtures for precision control, making it relatively complex. Summary of the Invention

[0004] To overcome the shortcomings of long cycle and complicated process in the online riveting method for preparing blades with micro-turbulence pillars, this invention proposes a method for preparing ceramic matrix composite blades with micro-turbulence pillars.

[0005] The technical solution adopted by this invention to solve its technical problem is:

[0006] A method for preparing a ceramic matrix composite blade equipped with micro-turbulence-inducing pillars includes the following steps:

[0007] Step S1, baffle column processing: According to the design structure dimensions of the baffle column, the fiber cloth is shaped into a flat plate of the required thickness; the boron nitride interface and silicon carbide matrix are prepared on the flat plate using a chemical vapor infiltration process. When the density of the flat plate matrix reaches the required density, the flat plate is processed into a baffle column of the required size.

[0008] Step S2, mold turbulence hole processing: Design the mold according to the pre-reserved processing allowance of the blade, and process turbulence holes on the outer surface of the mold.

[0009] Step S3, Blade fiber cloth wrapping: Wrap the fiber cloth on the inner mold surface according to the blade design thickness, and fill the heat dissipation slit at the tail of the blade with hard paper.

[0010] Step S4, mold closing and shaping: The inner mold and outer mold of the blade are closed and shaped. The turbulence column is inserted into the turbulence hole reserved in the outer mold, so that the two ends of the turbulence column protrude from the surface of the outer mold.

[0011] Step S5, Chemical Vapor Infiltration of Blades: The boron nitride interface and silicon carbide matrix of the blade are prepared by chemical vapor infiltration process; after the boron nitride interface is prepared, the hard paper padding the heat dissipation slit at the tail of the blade is removed, and a high-density C / SiC composite strip of the same height is padding the local area of ​​the slit as a support; when the density of the blade matrix reaches the required density, the inner mold and outer mold are removed.

[0012] Step S6, the blade is chemically vapor-impregnated again: the silicon carbide matrix is ​​prepared on the blade again, and when the density of the blade matrix reaches the final required density, it is machined according to the actual size requirements of the blade to obtain a blade equipped with a baffle column.

[0013] In the above preparation method, the process of shaping the fiber cloth into a flat plate of the required thickness in step S1 is as follows: the fiber cloth is laid flat and then tightly molded and fixed using a flat plate mold of the corresponding size.

[0014] In the above preparation method, step S1 involves preparing a boron nitride interface and a silicon carbide substrate on the plate. The plate substrate is required to have a density greater than 1.4 g / cm³. 3 The flat plate is processed into a spoiler column of the required size, with a 15mm to 20mm allowance reserved on one side in the length direction.

[0015] The column preparation method described above, wherein step S2 further includes:

[0016] Based on the size and location of the blade spoiler columns, corresponding spoiler holes are machined.

[0017] In the above preparation method, in step S5, the density of the leaf matrix is ​​required to be greater than 1.4 g / cm³. 3 .

[0018] In the above preparation method, in step S6, the final density of the blade matrix is ​​required to be greater than 2.0 g / cm³. 3 .

[0019] The beneficial effects of this invention are:

[0020] A method for preparing ceramic matrix composite blades with micro-turbulence pillars is proposed. The processing requires the use of special riveting fixtures for precision control, which overcomes the shortcomings of online riveting and welding methods for preparing blades with micro-turbulence pillars, such as long cycle time, high cost, and complicated process. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the turbulence column discharge plate structure according to an embodiment of the present invention;

[0022] Figure 2 This is a schematic diagram of the fiber cloth wrapping structure according to an embodiment of the present invention;

[0023] Figure 3 This is a schematic diagram of the blade mold closing according to an embodiment of the present invention;

[0024] Figure 4 This is a schematic diagram of the installation of the baffle column after mold closing in an embodiment of the present invention;

[0025] Figure 5 This is a schematic diagram of the blade deflector column after demolding in an embodiment of the present invention;

[0026] Figure 6 This is a schematic diagram of the blade spoiler column after processing according to an embodiment of the present invention;

[0027] Figure 7 This is a front view of the blade spoiler column after processing according to an embodiment of the present invention. Detailed Implementation

[0028] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0029] Example 1

[0030] A method for preparing a ceramic matrix composite blade equipped with micro-turbulence-inducing pillars includes the following steps:

[0031] Step S1: Based on the design dimensions of the turbulence column, use fiber cloth to shape a flat plate of the required thickness (lay the fiber cloth flat and use a mold of the corresponding size to tightly close and fix it). Use chemical vapor infiltration to prepare the boron nitride interface and silicon carbide matrix on the flat plate until the matrix density of the flat plate is greater than 1.4 g / cm³. 3 At that time, the flat plate is processed into a spoiler column of the required size (with a 15-20mm allowance on one side in the length direction);

[0032] Step S2: Design a mold according to the pre-reserved machining allowance of the blade, and machine the corresponding size and number of deflection holes on the surface of the outer mold according to the size and position of the blade deflection column;

[0033] Step S3: Wrap the fiber cloth around the inner mold surface according to the blade's designed thickness. Fill the heat dissipation slit at the blade's tail with stiff paper;

[0034] Step S4: After the inner and outer molds of the blade are closed and shaped, insert the pre-processed turbulence column into the turbulence hole reserved in the outer mold, ensuring that both ends of the turbulence column extend out of the surface of the outer mold.

[0035] Step S5 involves using the same process as for the turbulence column to prepare the boron nitride interface and silicon carbide substrate on the blade. After the boron nitride interface is prepared, the hard paper used to pad the heat dissipation slit at the tail of the blade is removed. A high-density C / SiC composite strip of the same height is then used as support in the localized area of ​​the slit. The blade substrate density is increased to greater than 1.4 g / cm³. 3 At that time, remove its inner and outer molds;

[0036] Step S6: Continue preparing the silicon carbide matrix for the blade until its matrix density is greater than 2.0 g / cm³. 3 At that time, the blades are processed according to their actual dimensions to obtain blades equipped with turbulence columns.

Claims

1. A method for preparing a ceramic matrix composite blade equipped with micro-turbulence-inducing pillars, characterized in that, Includes the following steps: Step S1: Based on the design structural dimensions of the turbulence column, shape the fiber cloth into a flat plate of the required thickness; use chemical vapor infiltration process to prepare the boron nitride interface and silicon carbide matrix on the flat plate; when the density of the flat plate matrix reaches the required density, process the flat plate into a turbulence column of the required size. Step S2: Design the mold according to the machining allowance reserved for the blade, and machine the turbulence holes on the outer surface of the mold. Step S3: Wrap the fiber cloth on the inner mold surface according to the blade design thickness, and fill the heat dissipation slit at the tail of the blade with hard paper. Step S4: The inner and outer molds of the blade are closed and shaped. The turbulence column is inserted into the turbulence hole reserved in the outer mold, so that the two ends of the turbulence column protrude from the surface of the outer mold. Step S5: Use chemical vapor infiltration process to prepare boron nitride interface and silicon carbide matrix for the blade; after the boron nitride interface is prepared, remove the hard paper padding the heat dissipation slit at the tail of the blade, and pad the local area of ​​the slit with high-density C / SiC composite strip of the same height as it as support; when the density of the blade matrix reaches the required density, remove the inner mold and outer mold. Step S6: Continue to prepare the silicon carbide matrix for the blade. When the density of the blade matrix reaches the final required density, perform machining according to the actual size requirements of the blade to obtain a blade equipped with a baffle column.

2. The preparation method according to claim 1, characterized in that, In step S1, the process of shaping the fiber cloth into a flat plate of the required thickness is as follows: the fiber cloth is laid flat and then tightly molded and fixed using a flat plate mold of the corresponding size.

3. The preparation method according to claim 1, characterized in that, In step S1, a boron nitride interface and a silicon carbide substrate are prepared on the plate. The density of the plate substrate is required to be greater than 1.4 g / cm³. 3 The flat plate is processed into a spoiler column of the required size, with a 15mm to 20mm allowance reserved on one side in the length direction.

4. The preparation method according to claim 1, characterized in that, Step S2 further includes: Based on the size and location of the blade spoiler columns, corresponding spoiler holes are machined.

5. The preparation method according to claim 1, characterized in that, In step S5, the density of the blade matrix is ​​required to be greater than 1.4 g / cm³. 3 .

6. The preparation method according to claim 1, characterized in that, In step S6, the final required density of the blade matrix is ​​greater than 2.0 g / cm³. 3 .

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