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A kind of reinforcement method of fiber-reinforced silicon carbide ceramic matrix composite material

A technology of silicon carbide ceramic matrix and composite materials, which is applied in the field of ceramic matrix composite materials, can solve the problems of strength and high temperature oxidation resistance, performance and oxidation resistance, and affect the aesthetics of composite materials, etc., to reduce the risk of falling off , reduce porosity, improve strength

Active Publication Date: 2022-04-19
AVIC BEIJING AERONAUTICAL MFG TECH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the ceramic matrix composites prepared by the current technology have the problem of high porosity (8% to 15%), and the porosity will reduce the strength and high temperature oxidation resistance of the material at room temperature, because the porosity will allow more air to enter at high temperature To the inside of the material, the fiber is further oxidized, which reduces the performance and oxidation resistance of the material at high temperature
At the same time, the defects of apparent pores will also affect the aesthetics of composite materials.

Method used

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  • A kind of reinforcement method of fiber-reinforced silicon carbide ceramic matrix composite material
  • A kind of reinforcement method of fiber-reinforced silicon carbide ceramic matrix composite material
  • A kind of reinforcement method of fiber-reinforced silicon carbide ceramic matrix composite material

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0024] This implementation is a flat plate with more micropores and coarse pores, and the steps of using the method of the present invention to reinforce are as follows:

[0025] (1) Polish the surface of the flat part with sandpaper to remove fine particles on the surface, and ultrasonically clean it in deionized water for 30 minutes;

[0026] (2) Dry in an oven at 100°C for 1 hour;

[0027] (3) Put the dried plate in the dipping tank, vacuumize to -0.1MPa, and keep it for 30min;

[0028] (4) Weigh 0.5 L of liquid polycarbosilane with a viscosity of 50 cP, pour it into a dipping tank, and dip it for 8 hours;

[0029] (5) Complete cracking in 1000°C vacuum cracking furnace for 2 hours after taking it out;

[0030] (6) Take by weighing 0.5kg liquid polycarbosilane and 0.025kg nano-silicon carbide particles, and mix them uniformly with high-speed stirring;

[0031] (7) Clean the surface of the cracked plate, put it in a dipping tank and vacuumize to -0.1MPa, and keep it for 3...

Embodiment 2

[0042] This embodiment is a workpiece with more surface holes, and the steps of adopting the method of the present invention for reinforcement are as follows:

[0043] (1) Polish the surface of the workpiece with sandpaper to remove fine particles on the surface, and ultrasonically clean it in deionized water for 30 minutes;

[0044] (2) Dry in an oven at 100°C for 1 hour;

[0045] (3) Put the dried plate in the dipping tank, vacuumize to -0.1MPa, and keep it for 60min;

[0046] (4) Weigh 0.2 L of liquid polycarbosilane with a viscosity of 80 cP, pour it into a dipping tank, and dip it for 15 hours;

[0047] (5) After taking it out, complete the cracking in a vacuum cracking furnace at 1300°C for 1 hour;

[0048] (6) Take by weighing 0.2kg liquid polycarbosilane and 0.005kg nano-silicon carbide particles, and mix them uniformly with high-speed stirring;

[0049] (7) Clean up the cracked test sample, put it in the dipping tank and vacuumize it to -0.1MPa, and keep it for 60m...

Embodiment 3

[0060] This embodiment is a part with more fine pores and surface holes, such as figure 1 As shown, the steps of adopting the method of the present invention to reinforce are as follows:

[0061] (1) Polish the surface of the workpiece with sandpaper to remove fine particles on the surface, and ultrasonically clean it in deionized water for 30 minutes;

[0062] (2) Dry in an oven at 100°C for 1 hour;

[0063] (3) Put the dried plate in the dipping tank, vacuumize to -0.1MPa, and keep it for 10min;

[0064] (4) Weigh 0.2 L of liquid polycarbosilane with a viscosity of 30 cP, pour it into a dipping tank, and dip it for 3 hours;

[0065] (5) Complete cracking in 700°C vacuum cracking furnace for 4 hours after taking it out;

[0066] (6) Take by weighing 0.2kg liquid polycarbosilane and 0.04kg nano-silicon carbide particles, and mix them uniformly with high-speed stirring;

[0067] (7) Clean the cracked test sample, put it in the dipping tank and vacuumize it to -0.1MPa, and kee...

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PUM

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Abstract

The invention relates to a reinforcing method for a fiber-reinforced silicon carbide ceramic matrix composite material. In the method, the parts are impregnated and cracked with liquid polycarbosilane to fill up the internal micropores; Mixing, the resulting mixed solution is dipped and cracked to fill the internal coarse pores; finally, liquid polycarbosilane and micron silicon carbide particles are mixed in a certain mass ratio, and the mixed solution is scraped to fill the defect holes on the surface of the sample. The invention can fill up the micropores, coarse pores and surface defect holes of the sample, and at the same time make the reinforcement material and the matrix material have a strong force, the reinforcement period is short, the operation is simple, and the original thickness of the sample will not be changed. , to achieve net size reinforcement effect.

Description

technical field [0001] The invention relates to a reinforcing method for a fiber-reinforced silicon carbide ceramic-based composite material, which belongs to the field of ceramic-based composite materials. Background technique [0002] Fiber-reinforced silicon carbide (SiC) ceramic matrix composites have become one of the most promising high-temperature thermal structural materials due to their excellent properties such as light weight, high strength, and high temperature resistance, and have broad application prospects in the aerospace field. At present, the main preparation processes include chemical vapor infiltration (CVI), precursor impregnation pyrolysis (PIP), etc., which can complete the densification of ceramic matrix composites, achieve high strength and improve their toughness. However, the ceramic matrix composites prepared by the current technology have the problem of high porosity (8% to 15%), and the porosity will reduce the strength and high temperature oxid...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B35/80C04B35/565
CPCC04B35/565C04B2235/616C04B2235/656C04B2235/6567C04B2235/6581C04B2235/96
Inventor 王晓猛邱海鹏王岭谢巍杰赵禹良关宏
Owner AVIC BEIJING AERONAUTICAL MFG TECH RES INST
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