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Si-Y-C ternary ceramic matrix composite material and preparation method

A technology of ternary ceramics and composite materials, which is applied in the field of composite materials to improve the water and oxygen corrosion resistance and ablation resistance of ceramic matrix composite materials, can solve the problems of incapability of large-scale production, high preparation temperature and long preparation cycle, and achieve equipment The effect of low requirements, low preparation temperature and short preparation time

Active Publication Date: 2020-05-19
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0009] In order to avoid the deficiencies of the prior art, the present invention proposes a Si-Y-C ternary ceramic matrix composite material and a preparation method, which improves the service life of the composite material in extreme environments and solves the problem of preparing a rare earth element modified composite material. Process defects, overcome the shortcomings of high preparation temperature, long preparation cycle, low mass fraction introduced, and incapable of large-scale production

Method used

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  • Si-Y-C ternary ceramic matrix composite material and preparation method
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  • Si-Y-C ternary ceramic matrix composite material and preparation method

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Embodiment 1

[0051] Step 1. Preparation of fiber preform: 0° non-woven fabric, tire mesh, 90° non-woven fabric, and tire mesh are successively superimposed to the thickness of the carbon fiber preform, and the carbon fiber preform is prepared by relay needle punching.

[0052] Step 2. Deposition of the interface layer: The pyrolytic carbon interface layer is deposited on the carbon fiber preform by chemical vapor infiltration.

[0053] Step 3. Preparation of matrix: with propylene (C 3 H 6 ) is the gas source, Ar gas is the diluent gas, the deposition temperature of the CVI process is 900 °C, the deposition time is 500 h, and the system pressure is 5 kPa, to obtain a sample with an open porosity of 18.5%.

[0054] Step 4. Introducing silicon-yttrium alloy by reactive melt infiltration method: The composite material and the silicon-yttrium alloy are placed in a graphite box, and the contact method adopts a one-way method. Put the graphite box into a graphite crucible with an inner diamete...

Embodiment 2

[0056] Step 1. Preparation of fiber preform: 0° non-woven fabric, tire mesh, 90° non-woven fabric, and tire mesh are successively superimposed to the thickness of the carbon fiber preform, and the carbon fiber preform is prepared by relay needle punching.

[0057] Step 2. Deposition of the interface layer: The pyrolytic carbon interface layer is deposited on the carbon fiber preform by chemical vapor infiltration.

[0058] Step 3: Preparation of matrix: with propylene (C 3 H 6 ) is the gas source, Ar gas is the diluent gas, the deposition temperature of the CVI process is 900 °C, the deposition time is 500 h, and the system pressure is 5 kPa, to obtain a sample with an open porosity of 19.9%.

[0059] Step 4. Introducing silicon-yttrium alloy by reactive melt infiltration method: The composite material and the silicon-yttrium alloy are placed in a graphite box, and the contact method adopts the embedding method. Put the graphite box into a graphite crucible with an inner dia...

Embodiment 3

[0061] Step 1. Preparing a fiber preform: After cutting the silicon carbide plain fiber cloth into a suitable size, lamination, and shaping with a graphite mold to prepare a silicon carbide fiber preform.

[0062] Step 2. Deposition of interface layer: A boron nitride interface layer is deposited on the carbon fiber preform by chemical vapor infiltration.

[0063] Step 3. Preparation of substrate: with trichloromethylsilane (CH 3 SiCl 3 , MTS) is the gas source, Ar is the diluent gas, and H is used by bubbling 2 As the carrier gas, MTS was brought into the reactor, the deposition temperature was 1050°C, the total system pressure was 5kPa, H 2 The molar ratio to MTS is 10:1, and the chemical reaction for preparing SiC is: CH 3 SiCl 3 +H 2 →SiC+HCl. A sample with an open porosity of 24.6% was obtained by depositing several heats.

[0064] Step 4. Introducing the carbon source: Mix the phenolic resin and absolute ethanol in a mass ratio of 3:10, and stir magnetically for 2...

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Abstract

The invention relates to a composite material with a Si-Y-C ternary ceramic matrix and a preparation method, a silicon-yttrium alloy is introduced into the ceramic matrix composite material by utilizing a reaction melt permeation method, and the composite material containing the Si-Y-C ternary ceramic matrix is prepared. According to the method, the mass fraction of the introduced rare earth compound is increased, and continuous permeation and uniform distribution are achieved. The preparation temperature is relatively low, so that the performance of the original reinforcements such as fibersor whiskers can be fully exerted. On the premise of ensuring the mechanical properties of the composite material, the water and oxygen corrosion resistance is enhanced by 100-200%, and the thermal shock resistance is enhanced by 100-150%. Moreover, the method is simple and controllable in process, low in equipment requirement and beneficial to large-scale production.

Description

technical field [0001] The invention belongs to the field of composite materials, and relates to a composite material with a Si-Y-C ternary ceramic matrix and a preparation method, which are mainly used in the fields of improving the water-oxygen corrosion resistance and ablation resistance of the ceramic matrix composite material. Background technique [0002] With the development of industrial production technology and aerospace technology, the demand for composite materials is more diverse, and the requirements for material properties are getting higher and higher. The working conditions of the new generation of high-performance aero-engines are severe, and higher requirements are placed on the material's resistance to water and oxygen corrosion; for the thermal protection system of rocket engines, it is required to have excellent ablation resistance. Therefore, one of the main development directions of ceramic matrix composites is to improve the service life of materials...

Claims

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Application Information

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IPC IPC(8): C04B35/80C04B35/58C04B35/622
CPCC04B35/58085C04B35/622C04B2235/5248C04B2235/3826C04B2235/422C04B2235/5244C04B2235/656C04B2235/6562C04B2235/6567C04B2235/77
Inventor 刘永胜高雨晴董宁王晶贺芳
Owner NORTHWESTERN POLYTECHNICAL UNIV
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