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A gel infiltration ceramic modification method for special-shaped parts of c/c composite materials

A technology for composite materials and special-shaped parts, which is applied in the field of ceramic matrix composite material preparation, can solve the problems of deteriorating mechanical properties, cumbersome process, easy to fall off, etc., and achieves the effects of low process cost, simple process operation and small volume shrinkage rate.

Active Publication Date: 2021-10-29
NAT UNIV OF DEFENSE TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, it needs to be pointed out that many C / C composites that need to be modified are not regular structures, but special-shaped parts with complex structures, such as rocket engine nozzles
The traditional RMI method has certain defects in the ceramic modification of such C / C composite materials: first, the infiltrant block or powder cannot be placed evenly on the special-shaped C / C composite material, and the carbon / carbon obtained after RMI -The texture of the ceramic composite is uneven, which may lead to a decrease in its ablation resistance and mechanical properties, which affects the reliability of the material; second, in order to obtain a carbon / carbon-ceramic composite with a uniform structure, if the C / C composite Too much infiltration agent on the special-shaped parts may cause the carbon fiber in the composite material to be ceramicized, which will cause the C / C composite special-shaped parts to become brittle and deteriorate their mechanical properties; third, the traditional RMI method is difficult to be able to C / C Partial ceramic modification of C composite materials; finally, too much infiltration agent leads to waste of raw materials and may also cause irreversible pollution to the high-temperature sintering furnace, affecting the service life of the high-temperature sintering furnace
However, this method is not only cumbersome, but also only suitable for workpieces with a small angle between the coating and the horizontal plane during the sintering process, otherwise the coating will easily fall off on the composite material during the process, and the surface morphology of special-shaped parts is often varied , so the use of this method has great limitations; and in the process of infiltration, the infiltration agent preferentially reacts with epoxy resin pyrolytic carbon to form a ceramic layer, which not only leads to the loss of infiltration raw materials, but also needs to be further removed in the subsequent process The ceramic layer formed on the surface of the composite material hinders the flow of the infiltration agent melt during infiltration, resulting in the inability of the infiltration reaction to continue

Method used

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  • A gel infiltration ceramic modification method for special-shaped parts of c/c composite materials
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  • A gel infiltration ceramic modification method for special-shaped parts of c/c composite materials

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Embodiment 1

[0048] A kind of gel infiltration ceramization modification method of C / C composite special-shaped parts of the present invention, the technological process is as follows figure 1 shown, including the following steps:

[0049] (1) Take 15 g of silicon powder with a particle size of 10 μm and 5 g of polycarbosilane, mix them uniformly and knead them for 10 min;

[0050] (2) The cutting density is 1.35g / cm 3 10g of special-shaped C / C composite material, put it in ethanol and ultrasonically clean it for 5 minutes to remove surface impurities and dry it;

[0051] (3) Brush the prepared silica powder sol onto the surface of the C / C composite special-shaped part with a curved structure (the coating is perpendicular to the horizontal plane), and the coating thickness is 3mm, as shown figure 2 shown;

[0052] (4) Place the special-shaped C / C composite material containing silica powder sol in a carbon tube sintering furnace, evacuate the carbon tube sintering furnace to 5 Pa, heat ...

Embodiment 2

[0057] A kind of gel infiltration ceramization modification method of C / C composite special-shaped parts of the present invention, the technological process is as follows figure 1 shown, including the following steps:

[0058] (1) Take 20 g of silicon-zirconium alloy powder with a particle size of 10 μm (the atomic ratio of silicon to zirconium is 90:10) and 7 g of polycarbosilane, mix them uniformly and knead them for 10 minutes;

[0059] (2) The cutting density is 1.40g / cm 3 15g of special-shaped C / C composite material, put it in ethanol and ultrasonically clean it for 5 minutes to remove surface impurities and dry it;

[0060] (3) Brush the prepared silicon-zirconium alloy powder sol onto the surface of the C / C composite special-shaped part with an arc structure (the coating is perpendicular to the horizontal plane), and the coating thickness is 3 mm, as shown figure 2 shown;

[0061] (4) Place the C / C composite special-shaped part containing silicon-zirconium alloy pow...

Embodiment 3

[0066] A method for infiltration and ceramization modification of C / C composite special-shaped parts of the present invention, the process flow is as follows figure 1 shown, including the following steps:

[0067] (1) Take 15g of silicon powder with a particle size of 10μm and 5g of polycarbaziborosilane, mix them uniformly and knead them for 10min;

[0068] (2) The cutting density is 1.4g / cm 3 10g of special-shaped C / C composite material, put it in ethanol and ultrasonically clean it for 5 minutes to remove surface impurities and dry it;

[0069] (3) Brush the prepared silica powder sol onto the surface of the C / C composite special-shaped part (with a curved structure and the coating is perpendicular to the horizontal plane), the coating thickness is 3mm, as shown figure 2 shown;

[0070] (4) Place the special-shaped C / C composite material containing silica powder sol in a carbon tube sintering furnace, evacuate the carbon tube sintering furnace to 5 Pa, heat the sinterin...

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Abstract

The invention discloses a gel infiltration ceramic modification method for C / C composite special-shaped parts, which includes the following steps: (1) Mix and knead ceramic precursor polymer binder and infiltration agent powder to obtain The sol in which the penetrant powder is evenly dispersed; (2) Coat the sol prepared in step (1) on the surface of the C / C composite special-shaped parts; (3) Apply the C containing sol coating prepared in step (2) / C composite special-shaped parts are heated under vacuum or in an inert atmosphere to solidify the sol and pyrolyze it to form a ceramic aerogel. After the temperature reaches 40 to 100°C above the melting point of the penetrant powder, the heat is maintained to make the gel in The infiltration agent powder is melted and fully infiltrated into C / C composite special-shaped parts to obtain carbon / carbon-ceramic composite special-shaped parts. The method of the present invention has good infiltration effect, the coating is not easy to fall off, the process is simple, and the utilization rate of infiltration materials is high. The mechanical properties of C / C composite special-shaped parts are greatly improved after being modified by this method.

Description

Technical field [0001] The invention relates to the technical field of ceramic matrix composite material preparation, and in particular to a gel infiltration ceramic modification method for C / C composite special-shaped parts. Background technique [0002] C / C composite materials have a series of excellent properties such as high specific strength, high specific modulus and fracture toughness, superior ablation resistance, excellent friction and wear properties, thermal shock resistance and good chemical stability. They are widely used in Manufacturing of throat liners for aero engines and rockets, turbine blade components, space shuttle solid boosters, missile end caps, heat exchangers, heat sinks for high-power electronic devices, etc. As thermal structural materials, C / C composite materials are generally used in high-temperature aerobic environments. However, carbon materials are easily oxidized by air at higher temperatures. Research shows that C / C composite materials be...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B41/87C04B35/84
CPCC04B41/009C04B41/5059C04B35/83C04B41/4554C04B41/5057
Inventor 叶益聪白书欣郭文建朱利安任俊李顺唐宇万红
Owner NAT UNIV OF DEFENSE TECH
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