Method for preparing carbon-silicon carbide composite material by using chemical gas-phase permeation method

A technology of chemical vapor infiltration and composite materials, which is applied in the field of composite material preparation, can solve the problems of complex preparation process and high cost of three-dimensional needle-punched carbon felt, and achieve the effect of improving interlayer shear strength, compensating for poor mechanical properties and high toughness

Inactive Publication Date: 2012-02-08
SHANDONG UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Because the three-dimensional needle-punched structure introduces fibers perpendicular to the laying direction, the interlayer shear strength is improved, and the shortcomings of poor mechanical pro

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0011] Place the carbon fiber braided body substrate in the deposition chamber and perform the following steps:

[0012] Steps for depositing carbon particles: There are two gas paths in the deposition chamber, one path uses methane as the reaction gas, the flow rate of methane gas is controlled at 200ml / min, the other path uses argon gas as the diluent gas, the flow rate of argon gas is 600ml / min, the deposition pressure in the deposition chamber is 6kPa, the deposition temperature is 900°C, and the deposition time is 3h;

[0013] Deposition of silicon carbide whiskers: change the two gas paths of the deposition chamber, one path uses trichloromethylsilane as the reaction gas, hydrogen as the carrier gas, and place methyltrichlorosilane in an evaporation kettle heated by a water bath. The temperature of the water bath is 35°C, the pressure of the evaporator is controlled at 0.2MPa, the total flow of hydrogen and trichloromethylsilane is controlled at 200ml / min, the hydrogen i...

Embodiment 2

[0015] Place the carbon fiber braided body substrate in the deposition chamber and perform the following steps:

[0016] Steps for depositing carbon particles: There are two gas paths in the deposition chamber, one path uses methane as the reaction gas, the flow rate of methane gas is controlled at 400ml / min, the other path uses argon gas as the diluent gas, the flow rate of argon gas is 800ml / min, the deposition pressure in the deposition chamber is 7kPa, the deposition temperature is 1000°C, and the deposition time is 12h;

[0017] Deposition of silicon carbide whiskers: change the two gas paths of the deposition chamber, one path uses trichloromethylsilane as the reaction gas, hydrogen as the carrier gas, and place methyltrichlorosilane in an evaporation kettle heated by a water bath. The temperature of the water bath is 40°C, the pressure of the evaporator is controlled at 0.3MPa, the total flow of hydrogen and trichloromethylsilane is controlled at 300ml / min, the hydrogen...

Embodiment 3

[0019] Place the carbon fiber braided body substrate in the deposition chamber and perform the following steps:

[0020] Steps for depositing carbon particles: There are two gas paths in the deposition chamber, one path uses methane as the reaction gas, the methane gas flow rate is controlled at 350ml / min, the other path uses argon gas as the diluent gas, the argon gas flow rate is 700ml / min, the deposition pressure in the deposition chamber is 6.7kPa, the deposition temperature is 950°C, and the deposition time is 8h;

[0021] Deposition of silicon carbide whiskers: change the two gas paths of the deposition chamber, one path uses trichloromethylsilane as the reaction gas, hydrogen as the carrier gas, and place methyltrichlorosilane in an evaporation kettle heated by a water bath. The temperature of the water bath is 38°C, the pressure of the evaporator is controlled at 0.3MPa, the total flow of hydrogen and trichloromethylsilane is controlled at 250ml / min, the hydrogen is se...

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Abstract

The invention provides a method for preparing a carbon-silicon carbide composite material by using a chemical gas-phase permeation method. The method is characterized in steps that: a carbon fiber weaved body is placed in a deposition chamber, and deposed carbon particles are adopted as a dividing surface, wherein methane is adopted as a reaction gas, argon is adopted as a diluting gas, a deposition pressure in the deposition chamber is 6 to 7kPa, a deposition temperature is 900 to 1000 DEG C, and a deposition time is 3 to 12 hours; then silicon carbide crystal whiskers are deposed, wherein methyl trichloro silane is adopted as a reaction gas, hydrogen is adopted as a carrier gas, methyl trichloro silane is positioned in a evaporation vessel for water bath heating, a water bath temperature is 35 to 40 DEG C, a pressure in the evaporation vessel is controlled at 0.2 to 0.3MPa, a total flow of hydrogen and methyl trichloro silane is controlled at 200 to 300ml/min, methyl trichloro silane is delivered into the deposition chamber by hydrogen through a bubbling method, argon is used as a diluting gas, a deposition pressure in the deposition chamber is 6 to 7kPa, a deposition temperature is 1100 to 1150 DEG C, and a deposition time is 1 to 7 days, such that the carbon-silicon carbide composite material is obtained. The composite material provided by the invention has good toughness and high anti-interlaminar shear strength.

Description

technical field [0001] The invention provides a method for preparing a carbon-silicon carbide composite material by a chemical vapor infiltration method, which belongs to the technical field of composite material preparation. Background technique [0002] Continuous fiber reinforced ceramic matrix composites (CMCs) have the characteristics of low density, high specific strength, high specific modulus, high temperature thermal structural properties and thermal shock resistance, and are one of the key supporting materials for the development of aerospace technology in the future. Among them, the carbon fiber reinforced silicon carbide matrix composite material is more prominent, as an ultra-high temperature composite material, it has a very broad application prospect in aerospace thermal protection systems. The full-scale C / SiC nozzle of the liquid rocket engine prepared by Northwestern Polytechnical University in my country has passed the high-altitude test run. The French S...

Claims

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Application Information

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IPC IPC(8): C04B35/83C04B35/81C04B35/622
Inventor 孟凡涛张艳平魏春城白佳海冯柳牛金叶
Owner SHANDONG UNIV OF TECH
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