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Method for preparing anti-oxidation coating of carbon/carbon composite material

A technology of carbon composite material and anti-oxidation coating is applied in the field of preparation of high-temperature anti-oxidation coating, which can solve the problems of low anti-oxidation performance, and achieve the improvement of anti-oxidation performance, surface density, and long-term service performance. Effect

Active Publication Date: 2013-04-10
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The present invention aims at the problem that the surface of the anti-oxidation coating prepared by the method in the prior art tends to have defects such as cracks and pores, resulting in low anti-oxidation performance, and provides a method for preparing an anti-oxidation coating of carbon / carbon composite materials to overcome the existing problems. Insufficient technical methods to realize the preparation of high-performance carbon / carbon composites anti-oxidation coating

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0021] 1) Using a thermosetting silicone resin as a carrier, mix elemental silicon powder with a particle size of 500 mesh at a volume ratio of 1:0.5 to form a silicon-rich slurry I. Set the density to 1.96g / cm 3 The carbon / carbon material placed in the slurry I was vacuum impregnated at -0.1MPa for 1h, and then pressure impregnated at 3MPa for 1h. After impregnation, take out the carbon / carbon material, remove excess slurry on the surface, and then use slurry II to brush the silicon-rich slurry with a thickness of about 2mm on the carbon / carbon surface. Wherein the volume ratio of thermosetting silicone resin and silicon powder in slurry II is 1:3. After the coating layer is dried, it is cured at 150°C and then treated at 800°C for 1 hour in an inert environment to form a silicon-rich layer;

[0022] 2) Put the carbon / carbon material coated with the silicon-rich layer in a chemical vapor deposition furnace, use propylene as the carbon source, and deposit it in an environmen...

Embodiment 2

[0026] 1) Using a thermosetting phenolic resin as a carrier, mix the elemental silicon powder with a particle size of 300 mesh at a volume ratio of 1:0.6 to form a silicon-rich slurry I. Set the density to 1.82g / cm 3 The carbon / carbon material placed in the slurry I was vacuum impregnated at -0.1MPa for 1h, and then pressure impregnated at 3MPa for 1h. After impregnation, take out the carbon / carbon material, remove excess slurry on the surface, and then use slurry II to brush the silicon-rich slurry with a thickness of about 2mm on the carbon / carbon surface. The volume ratio of the thermosetting phenolic resin and the silicon powder in the slurry II is 1:5, adding an appropriate amount of ethanol as a solvent, and stirring to form a slurry. After the coating layer is dried, the temperature is raised to 150°C at 10°C / h, and the temperature is kept constant for 2h. Then treat at 1000°C for 2h in an inert environment to form a silicon-rich layer;

[0027] 2) Put the carbon / car...

Embodiment 3

[0032] 1) Use the thermosetting phenolic resin as the carrier of the slurry I, and mix the elemental silicon powder with a particle size of 300 mesh at a volume ratio of 1:0.5 to form the silicon-rich slurry I. Set the density to 1.80g / cm 3 The carbon / carbon material placed in the slurry I was vacuum impregnated at -0.1MPa for 1h, and then pressure impregnated at 3MPa for 1h. After the impregnation is completed, take out the carbon / carbon material, remove the excess slurry on the surface, and then brush the silicon-rich slurry with a thickness of about 2 mm on the carbon / carbon surface with molten slurry II. The molten slurry II is a molten mixture of medium-temperature coal tar pitch and silicon powder at a volume ratio of 1:4 at a temperature of 120°C. After the coating layer is cooled, the temperature is raised to 800°C at 5°C / h, and the temperature is kept constant for 2h to form a silicon-rich layer;

[0033] 2) Put the carbon / carbon material coated with the silicon-ric...

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Abstract

The invention belongs to the field of inorganic functional coating materials and is mainly applied to preparation for a high-temperature anti-oxidation coating of a carbon / carbon composite material. The preparation method comprises the following steps: introducing a silicon-enriched layer into the surface of the carbon / carbon composite material in advance; depositing carbon on the surface of and in the holes of the silicon-enriched layer through chemical vapor deposition to form a continuous carbon layer; and forming a continuous silicon carbide coating through reactive sintering. Compared with a gradient transition silicon carbide coating obtained by the traditional sintering method, the silicon carbide coating obtained by the method provided by the invention greatly improves the surface density and improves the anti-oxidation performance by more than one time; and after the coating is sealed and glazed, the long-time service performance is greatly improved.

Description

technical field [0001] The invention belongs to the field of inorganic functional coating materials, and is mainly used for the preparation of high-temperature oxidation-resistant coatings of carbon / carbon composite materials. Background technique [0002] The preparation of an anti-oxidation coating on the surface is an important means to realize the long-term service of carbon / carbon composites in a high-temperature aerobic environment, and it is also a key process for using carbon / carbon composites as thermal structural materials. The anti-oxidation coating of carbon / carbon composites is usually a high-temperature resistant ceramic layer prepared on the surface of carbon / carbon by thermal spraying, plasma spraying, brushing, reaction sintering and other means. Due to the difference in the composition of the coating and the carbon / carbon material, there is a problem of thermal mismatch between them, and there are defects such as cracks and pores on the formed coating, whic...

Claims

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Application Information

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IPC IPC(8): C04B41/85
Inventor 李同起吴宁宁李钰梅
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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