Preparation method of C/SiC composite material

A composite material and prefabricated technology, applied in the field of ceramic matrix composite materials, can solve the problems of high-performance C/SiC composite materials such as long-term engineering application, low mechanical properties, and complicated preparation process, and achieve easy large-scale industrial application, excellent Mechanical properties, the effect of simple preparation method

Active Publication Date: 2020-06-19
BEIJING INST OF ELECTRONICS SYST ENG
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the mechanical properties of the SiC / SiC composite material decay rapidly in a high-temperature environment higher than 1350 °C, which cannot meet the application requirements of thermal protection structures for high-altitude aircraft.
[0004] It can be seen that the mechanical properties of C / SiC composite materials prepared by traditional methods in the prior art are low, and the preparation process of high-performance C / SiC composite materials is complex and immature, and the engineering application of high-performance C / SiC composite materials is far away. It is still far away; the temperature resistance of existing SiC / SiC composite materials cannot meet the application requirements of hypersonic vehicles

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0024] The preparation process of C / SiC composites includes the following steps:

[0025] 1. Weave plain cloth with M40J carbon fiber, and control the fiber volume fraction at 40%, then lay and laminate the plain cloth into a prefabricated body with a 2D structure, and press it with a graphite mold to complete the shape;

[0026] 2. Put the preform into the chemical vapor deposition equipment, the deposition temperature is 600°C, the deposition equipment is evacuated to 20kPa, the flow rate of the dilution gas argon is 80L / min, the flow rate of the carbon source precursor gas propylene is 200L / min, and the deposition 30h, the thickness of the obtained pyrolytic carbon interface layer is 550 μm;

[0027] 3. Then put it into the CVI deposition equipment, set the deposition temperature to 1200°C, vacuum the deposition equipment to 20kPa, the flow rate of the carrier gas hydrogen is 70L / min, and the flow rate of the SiC matrix precursor gas trichloromethylsilane is 200L / min. min,...

Embodiment 2

[0032] 1. Weave plain cloth with M55J carbon fiber, control the fiber volume fraction at 45%, then lay the plain cloth into a prefabricated body with a 2D structure, and press it with a graphite mold to complete the shape;

[0033]2. Put the preform into the chemical vapor deposition equipment, the deposition temperature is 700°C, the deposition equipment is evacuated to 40kPa, the flow rate of the dilution gas argon is 70L / min, and the flow rate of the carbon source precursor gas propylene is 300L / min. 40h, the thickness of the pyrolytic carbon interface layer is 600 μm;

[0034] 3. Then put it into the CVI deposition equipment, set the deposition temperature to 1200°C, vacuum the deposition equipment to 50kPa, the flow rate of the carrier gas hydrogen is 65L / min, and the flow rate of the SiC matrix precursor gas trichloromethylsilane is 300L / min. min, single deposition time is 100h, multiple cycles of deposition, the density is greater than 1.4g / cm 3 C / SiC blank material; ...

Embodiment 3

[0039] 1. Weave plain cloth with M60J carbon fiber, control the fiber volume fraction at 50%, then lay the plain cloth into a prefabricated body with a 2D structure, press it with a graphite mold, and complete the shape;

[0040] 2. Put the preform into the chemical vapor deposition equipment, the deposition temperature is 700°C, the deposition equipment is evacuated to 50kPa, the flow rate of the dilution gas argon is 80L / min, the flow rate of the carbon source precursor gas propylene is 500L / min, and the deposition 50h, the thickness of the pyrolytic carbon interface layer is 700 μm;

[0041] 3. Then put it into the CVI deposition equipment, set the deposition temperature to 1300°C, vacuum the deposition equipment to 40kPa, the flow rate of the carrier gas hydrogen is 70L / min, and the flow rate of the SiC matrix precursor gas trichloromethylsilane is 500L / min. min, single deposition time is 100h, multiple cycles of deposition, the density is greater than 1.4g / cm 3 C / SiC bla...

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Abstract

The invention discloses a preparation method of a C/SiC composite material. The preparation method comprises the following steps: (1) depositing a pyrolytic carbon interface layer on the carbon fibersurface of a preform by adopting a chemical vapor deposition process, (2) depositing a SiC matrix by adopting a CVI process to form a C/SiC blank material, and (3) dipping the C/SiC blank material inthe SiC slurry, taking out the C/SiC blank material, and depositing a SiC matrix by adopting the CVI process to obtain the C/SiC composite material meeting the requirements. According to the method, aspecific carbon fiber raw material is selected, a process of combining a CVI deposition SiC matrix and a SiC slurry permeation process is adopted, and the prepared C/SiC composite material has excellent mechanical properties at normal temperature and high temperature of 1500 DEG C, and the preparation method is simple, efficient and easy for large-scale industrial application.

Description

technical field [0001] The invention relates to the technical field of ceramic matrix composite materials. More specifically, it relates to a preparation method of a C / SiC composite material. Background technique [0002] The temperature of the surface material of high-performance aircraft can reach 1800°C and above in an instant during high-speed flight above Mach 5, which requires extremely high temperature resistance and mechanical properties of thermal structural materials. As an important component of ceramic matrix composites, C / SiC composites have unique application value in the field of high-performance aircraft due to their light weight, high strength, and long-term use at temperatures above 1650°C. According to the difference of commonly used fibers and preform types, the tensile strength and tensile modulus of C / SiC composites vary from 200 to 300 MPa and 60 to 100 GPa, respectively. However, with the development of technology in the fields of hypersonic vehicle...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/80C04B35/565C04B35/571
CPCC04B35/565C04B35/571C04B2235/5248C04B2235/96C04B2235/77
Inventor 辛玲王大奎杨宁武练梅李君龙
Owner BEIJING INST OF ELECTRONICS SYST ENG
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