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

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...

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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 properties and easy delamination between the two-dimensional structure layers are made up for, but the preparation process of the three-dimensional needle-punched carbon felt is complicated. high cost