Method for preparing carbon-fiber reinforced silicon carbonate base composite by gas-phase siliconizing technology

A composite material and vapor-phase siliconizing technology are applied in the preparation of dense fiber-reinforced ceramic matrix composite materials, and the vapor-phase siliconizing process is used to prepare dense carbon fiber-reinforced SiC-based composite materials. and performance issues

Inactive Publication Date: 2006-10-25
SHANGHAI INST OF CERAMIC CHEM & TECH CHINESE ACAD OF SCI
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  • Application Information

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Problems solved by technology

Therefore, during the whole process, the infiltration of liquid silicon has a great influence on the final performance of the material.
For a long time, people have done a lot of research on the infiltration reaction of liquid-phase silicon, and found that its process control is relativel

Method used

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  • Method for preparing carbon-fiber reinforced silicon carbonate base composite by gas-phase siliconizing technology
  • Method for preparing carbon-fiber reinforced silicon carbonate base composite by gas-phase siliconizing technology
  • Method for preparing carbon-fiber reinforced silicon carbonate base composite by gas-phase siliconizing technology

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Experimental program
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Effect test

Embodiment 1

[0026] Example 1 3DC f / SiC composite material preparation

[0027] Weaving carbon fiber into 3D braided body, using pulsed CVI or forced pulsed CVI (another application), respectively using methane (CH 4 ) and MTS are the gaseous precursors, and the pyrolytic C / SiC bilayer interface is deposited on the surface of the C fiber with a thickness of ~150 and ~250nm, respectively (such as image 3 ). The pyrolysis temperature is 900-1200°C, and the pressure is several thousand Pa to tens of kilo Pa and the time is several seconds to tens of seconds. Then the resulting 3D braids with pyrolyzed C and bilayer interfaces were sequentially dipped in SiC / PCS slurries with SiC contents of 50 vol.%, 30 vol.% and 0 vol.%, and cracked at 1100 °C, and finally Phenolic resin impregnation, high temperature treatment at 1800°C to form a porous matrix. Its density is about 1.50g / cm 3 , The opening porosity is about 20%. according to figure 2 Place the sample and the graphite carbon tube f...

Embodiment 2

[0028] Embodiment 2 Unidirectional (UD)C f / SiC composite material preparation

[0029] With methane (CH 4 ) and MTS are vapor phase precursors, which are deposited on the surface of C fibers by pulsed CVI or forced pulsed CVI (C-SiC) 6 The multilayer interface has a thickness of about 100 nm. The fiber bundles are impregnated in nano-SiC / PCS slurry with SiC content of 50vol.%, wound into unidirectional sheets, stacked at 0°, pressurized at 200-300°C, and then impregnated with phenolic resin slurry , cracked at 1800°C to obtain a porous body with a density of about 1.47g / cm 3 , The opening porosity is about 21.6%. After sintering by vapor phase siliconizing reaction under vacuum condition at 1700℃, its density is 2.31g / cm 3 , the porosity is 3.1%, the three-point flexural strength is 220MPa, showing non-brittle fracture (such as Figure 6 ).

Embodiment 3

[0031] Preparation of SiC-based composites containing two-dimensional carbon fiber cloth.

[0032] Deposit BN / SiC multilayer interface on the surface of carbon fiber cloth, using BCl 3 -NH 3 Using MTS as a precursor, at 900-1200 ° C, using pulsed CVI or forced pulsed CVI process, the carbon fiber cloth is coated with a multi-layer (BN-SiC) interface. Then carry out in the mode of embodiment 1. SiC-based composite materials with similar properties are obtained.

[0033] The forced pulse CVI process involved in the above-mentioned embodiments is based on the pulsed CVI process, which is characterized in that the method of introducing forced pulse flow is used to improve the interface deposition rate while maintaining uniform deposition at the interface; the specific process is the upper opening of the graphite mold, The gas conduit is located at the bottom of the graphite mold. During the interface deposition process, the fiber, fiber braid or preform is placed on the upper p...

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Abstract

This invention relates to preparation method gas phase siliconizing technique preparing high compact fiber reinforcement SiC group composite material. Protection layer interface is formed on fiber surface through gas phase or liquid phase, then they are dipped and cracked through nm SiC slime to make certain density precast body of fiber reinforcement SiC group. Carbon is added into the body through dipping and cracking way to form group body with certain pore, the group body penetrates inner part of the multi-hole body through gas phase silicon after it is high temperature treated, then it reacts with carbon and fills the pore to get compact basal body. The density of the material can reach 2.25-2.30g/cm3, open porosity is 3-6 percent; it is large more higher than traditional method of getting Cf/SiC material.

Description

technical field [0001] The invention relates to a method for preparing a dense fiber-reinforced ceramic-based composite material, more precisely, relates to a method for preparing a dense carbon fiber-reinforced SiC-based composite material by a gas-phase siliconizing process, which belongs to the field of reaction sintering technology. Background technique [0002] Fiber-reinforced SiC-based composite materials have excellent high-temperature mechanical properties and oxidation resistance, and have improved the shortcomings of ceramic materials that are prone to sudden failure, and have strong anti-destructive capabilities, so they have broad application prospects, especially in aerospace, national defense Fields such as military and new energy have more potential practical value. [0003] At present, the preparation methods of fiber-reinforced SiC-based composites mainly include chemical vapor infiltration (CVI) method, organic precursor impregnation pyrolysis (PIP) method...

Claims

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Application Information

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IPC IPC(8): C04B35/80C04B35/565C04B35/622
Inventor 周清董绍明丁玉生张翔宇王震江东亮
Owner SHANGHAI INST OF CERAMIC CHEM & TECH CHINESE ACAD OF SCI
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