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Preparation method of CC-SiO2 ceramic-based composite material

A composite material and ceramic matrix technology, applied in the field of CC-SiO2 ceramic matrix composite material preparation, can solve the problems of long preparation cycle, high preparation cost, structural damage, etc. Effect

Active Publication Date: 2022-03-04
湖北三江航天江北机械工程有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The theoretical operating temperature of C / C composite materials is as high as 2600°C, but the material will be oxidized above 400°C, resulting in structural damage and rapid performance degradation
[0006] C / SiC composite materials have the advantages of high temperature resistance, oxidation resistance, ablation resistance, etc., but are generally manufactured by CVI, PIP and other methods, and the preparation cycle is long and the preparation cost is high.

Method used

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  • Preparation method of CC-SiO2 ceramic-based composite material

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0034] A CC-SiO 2 A method for preparing a ceramic matrix composite material, comprising the steps of:

[0035] 1) After laying up the carbon fiber cloth to reach 15mm in sequence, prepare the prefabricated body by suturing. The carbon fiber cloth is a satin cloth woven with T700 fiber, and the suture yarn is carbon fiber T300 two-way through stitching, and the stitching distance is 3mm / needle;

[0036] 2) Put the prefabricated body into a high-temperature furnace and perform degumming treatment. The degumming treatment temperature is 2100°C, the vacuum degree is -0.09MPa, and the time is 4h;

[0037] 3) Put the prefabricated body that has been degummed into a vapor deposition furnace for chemical vapor infiltration to the preset first density. The carbon source gas for chemical vapor infiltration is methane with a purity greater than 99.99%. The deposition temperature is 1050°C and the pressure is -0.09MPa, the time is 20h, the preset first density is 0.95g / cm 3 ;

[0038]...

Embodiment 2

[0046] A CC-SiO 2 A method for preparing a ceramic matrix composite material, comprising the steps of:

[0047] 1) After laying up the carbon fiber cloth to reach 16mm in sequence, prepare the prefabricated body by suturing. The carbon fiber cloth is a satin cloth woven with T700 fiber, and the suture yarn is carbon fiber T300 two-way through stitching, and the stitching distance is 2mm / needle;

[0048] 2) Put the prefabricated body into a high-temperature furnace and perform degumming treatment. The degumming treatment temperature is 1500°C, the vacuum degree is -0.08MPa, and the time is 2h;

[0049] 3) Put the prefabricated body that has been degummed into a vapor deposition furnace for chemical vapor infiltration to the preset first density. The carbon source gas for chemical vapor infiltration is propylene with a purity greater than 99.99%. The deposition temperature is 800°C and the pressure is -0.08MPa, the time is 30h, the preset first density is 0.9g / cm 3 ;

[0050]...

Embodiment 3

[0058] A CC-SiO 2 A method for preparing a ceramic matrix composite material, comprising the steps of:

[0059] 1) After stacking the carbon fiber cloth to reach 14mm in sequence, prepare the prefabricated body by suturing. The carbon fiber cloth is a satin cloth woven with T700 fiber, and the suture yarn is carbon fiber T300 two-way through stitching, and the stitching distance is 4mm / needle;

[0060] 2) Put the prefabricated body into a high-temperature furnace for degumming treatment, the degumming treatment temperature is 1800°C, the vacuum degree is -0.085MPa, and the time is 5h;

[0061] 3) Put the prefabricated body that has been degummed into a vapor deposition furnace for chemical vapor infiltration to the preset first density. The carbon source gas for chemical vapor infiltration is methane with a purity greater than 99.99%. The deposition temperature is 1200°C and the pressure is -0.085MPa, the time is 40h, the preset first density is 0.93g / cm 3 ;

[0062] 4) Put...

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Abstract

The invention relates to the technical field of thermal structure composite materials, and discloses a preparation method of a CC-SiO2 ceramic-based composite material. Comprising the following steps: sequentially laying carbon fiber cloth, sewing to prepare a preform, putting the preform into a high-temperature furnace for degumming treatment, putting the preform into a vapor deposition furnace for chemical vapor infiltration to a preset first density, putting the preform into a vacuum impregnation container for vacuum impregnation, transferring the preform into a curing oven for pressurization-catalytic crosslinking, and carrying out drying to obtain the carbon fiber composite material. And transferring into a carbonization furnace for carbonization, repeatedly dipping, pressurizing-catalytic crosslinking and carbonization to enable the preform to reach a preset second density, then carrying out high-temperature graphitization, then carrying out vacuum dipping, drying and sintering, and repeatedly dipping, drying and sintering until the weight gain rate of the preform is less than 1%. According to the preparation method of the CC-SiO2 ceramic-based composite material, the prepared material is resistant to high temperature, light in weight, capable of being used for a long time in an oxygen environment and short in preparation period.

Description

technical field [0001] The invention relates to the technical field of thermal structural composite materials, in particular to a CC-SiO 2 Preparation method of ceramic matrix composite material. Background technique [0002] Titanium alloy has become one of the main structural materials of advanced aircraft in the aerospace field because of its excellent comprehensive performance matching such as high specific strength, modulus, toughness, high damage tolerance, corrosion resistance and weldability. [0003] However, as the speed of the aircraft has expanded from subsonic to sonic, supersonic and even hypersonic, the temperature of many structural components has exceeded the service temperature of titanium alloys, such as the air rudder core, so a high temperature resistant structural material is needed to meet high performance. Aircraft development needs. [0004] At present, there have been many research reports on high-temperature structural materials, including C / C, C...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/80C04B35/52
CPCC04B35/80C04B35/521C04B2235/422C04B2235/3418C04B2235/5248C04B2235/656C04B2235/6567C04B2235/6581C04B2235/77C04B2235/96C04B2235/9684C04B2235/3217Y02T50/40
Inventor 陈海昆高银东艾余前吴广力李忠仕任海成
Owner 湖北三江航天江北机械工程有限公司