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C/SiC-SiO2 composite material and preparation method thereof

A composite material and billet technology, which is applied in the field of thermal structural composite materials and preparation, can solve the problems that restrict the wide application of C/SiC composite materials, the low utilization rate of raw materials, and the high cost of C/SiC composite materials, and achieve good mechanical properties. Performance and ablation resistance, cost reduction, environmentally friendly results

Active Publication Date: 2022-05-10
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the raw material SiC precursor used in this process is as high as thousands of yuan per kilogram, and the utilization rate of raw materials is very low in the process of densification of special-shaped thermal structural parts, resulting in high cost of C / SiC composite materials, which seriously restricts C / SiC Wide application of SiC composite materials

Method used

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  • C/SiC-SiO2 composite material and preparation method thereof

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Effect test

preparation example Construction

[0041] A C / SiC-SiO of the present invention 2 The preparation method of composite material, its step is:

[0042] (1) Put the carbon fiber fabric into the heat treatment equipment, under the protection of inert gas, raise the temperature to 400°C-1400°C, remove the organic matter such as sizing agent inside the fabric, and clean the fiber surface.

[0043] (2) Put the carbon fiber fabric after removing the organic matter into a chemical vapor deposition furnace, deposit a pyrolytic carbon interface layer on the surface of the carbon fiber, and the thickness of the interface layer should reach 50nm-2μm.

[0044] (3) The carbon fiber fabric after the deposition of the interface layer is subjected to high-temperature treatment at a temperature of 1400°C to 2500°C. The purpose of this step is to graphitize the interface layer between the carbon fiber and pyrolytic carbon, and reduce the interfacial layer between the carbon fiber and pyrolytic carbon and the substrate. bond streng...

Embodiment 1

[0056] C / SiC-SiO is used for hollow special-shaped structure products with an outer dimension envelope of 1500m×400mm×50mm and a wall thickness of 3-10mm 2 Composite materials were developed. The specific development steps are as follows:

[0057] (1) According to the product drawing, use T300-3K carbon fiber and lay-up-sewing process to weave the fabric, take samples in the blank margin area, and determine whether the fabric density meets 0.7g / cm 3 The above; put the carbon fiber fabric that meets the requirements into the heat treatment equipment, and under the protection of argon, heat up to 600°C to remove the organic matter such as sizing agent inside the fabric to clean the fiber surface.

[0058] (2) Put the fabric after removing the organic matter into a chemical vapor deposition furnace, deposit a pyrolytic carbon interface layer on the surface of the carbon fiber, and the thickness of the interface layer is about 150nm.

[0059] (3) The deposited fabric is subjecte...

Embodiment 2

[0067] C / SiC-SiO is used for hollow special-shaped structure products with an outer dimension envelope of 1800m×500mm×50mm and a wall thickness of 5mm 2 Composite materials were developed. The specific development steps are as follows:

[0068] (1) According to the product drawing, use T300-1K fiber and lay-up-sewing process to weave the fabric, take samples in the blank margin area, and determine whether the fabric density meets 0.7g / cm 3 The above; put the carbon fiber fabric that meets the requirements into the heat treatment equipment, and under the protection of argon, heat up to 600°C to remove the organic matter such as sizing agent inside the fabric to clean the fiber surface.

[0069] (2) Put the fabric after removing the organic matter into a chemical vapor deposition furnace, deposit a pyrolytic carbon interface layer on the surface of the carbon fiber, and the thickness of the interface layer is about 500nm.

[0070] (3) The deposited fabric is subjected to high ...

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Abstract

The invention discloses a preparation method of a C / SiC-SiO2 composite material. The preparation method comprises the following steps: (1) cleaning a carbon fiber fabric; (2) depositing a pyrolytic carbon interface layer; (3) high-temperature treatment; (4) circularly carrying out SiC precursor vacuum impregnation, curing and cracking treatment for 2-7 rounds to obtain a C / SiC blank; (5) carrying out vacuum impregnation on the C / SiC blank by using silica sol, and then sequentially carrying out gelation, drying and heat treatment; and (6) circulating the step (5) until the single-round weight gain rate is lower than 0.5%. The invention also discloses a C / SiC-SiO2 composite material, which takes the carbon fiber as a reinforcement body, takes SiC and SiO2 as a matrix, and takes pyrolytic carbon as an interface layer between the reinforcement body and the matrix; siC in the fiber bundle mainly plays a role in high-temperature bearing and fiber protection; siO2 is mainly distributed among fiber bundles, so that a porous SiC matrix is connected into a compact whole, the mechanical property and ablation resistance of the material are further improved, and the obtained C / SiC-SiO2 composite material can be used as a heat-proof bearing integrated material and serves at high temperature.

Description

technical field [0001] The invention relates to a C / SiC-SiO 2 A ceramic matrix composite material and a preparation method thereof belong to the technical field of thermal structural composite materials and preparation. Background technique [0002] Ceramic matrix composites represented by C / SiC have important applications in the aerospace field as an integrated material for heat and load bearing due to their excellent high-temperature mechanics and ablation resistance. Among them, C / SiC composite material has high technology maturity, stable and reliable performance, and has become one of the most important material systems in the field of thermal structural materials. There are a variety of preparation processes for C / SiC composite materials. The precursor impregnation and pyrolysis (PIP) process has low preparation temperature, small fiber damage, strong process adaptability, and low equipment requirements. It has outstanding advantages in size forming, so it has import...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/80C04B35/571C04B35/622
CPCC04B35/80C04B35/571C04B35/622C04B2235/3418C04B2235/5248C04B2235/77C04B2235/96C04B2235/9607
Inventor 李军平王兆可龚晓冬孙新张国兵俸翔孙文婷赵建设王金明
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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