Fiber-toughened ceramic-based composite material with ternary-layer-shaped MAX phase interface layer and preparation method of composite material

A ternary layered and fiber toughening technology, which is applied in the field of fiber toughened ceramic matrix composites with a ternary layered MAX phase interface layer and its preparation, can solve the problem of low thermal conductivity and reduce the overall thermal conductivity of composite materials. It is difficult to meet the application requirements of ceramic matrix composites and other problems, so as to improve the anti-oxidation performance and improve the toughness.

Inactive Publication Date: 2016-11-09
NINGBO INST OF MATERIALS TECH & ENG CHINESE ACADEMY OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In addition, the traditional interface layer itself has low thermal conductivity, which seriously reduces the overall thermal conductivity of the composite material

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0036] In this embodiment, the ceramic matrix composite material uses silicon carbide ceramics as the matrix and carbon fiber as the toughening phase, and the interface layer between the matrix and the toughening phase is a ternary layered MAX phase material Ti 3 SiC 2 .

[0037] The preparation steps of the ceramic matrix composite material are as follows:

[0038] (1) Weave 1K T300 carbon fiber into a 3D carbon fiber prefabricated body with a carbon fiber volume fraction of 45%.

[0039] (2) Deposit Ti on the surface of carbon fiber preform by chemical vapor deposition 3 SiC 2 For the interface layer, the deposition conditions are as follows: silicon tetrachloride is used as the silicon source, titanium tetrachloride is used as the titanium source, carbon tetrachloride is used as the carbon source, hydrogen is used as the carrier gas, and the deposition temperature is 1300°C.

[0040] (3) The SiC ceramic substrate is deposited on the surface of the interface layer by che...

Embodiment 2

[0043] In this embodiment, the ceramic matrix composite material uses silicon carbide ceramics as the matrix and carbon fiber as the toughening phase, and the interface layer between the matrix and the toughening phase is Ti 3 SiC 2 / PyC multilayer interface.

[0044] The preparation steps of the ceramic matrix composite material are as follows:

[0045] (1) Weave 1K T300 carbon fibers into a 3D fiber preform with a fiber volume fraction of 45%.

[0046] (2) The PyC interface layer is deposited on the surface of the carbon fiber preform by chemical vapor deposition method. The deposition conditions are as follows: propylene is used as the source material, argon is used as the dilution gas, and the deposition temperature is 900-1000 ° C. Then, Ti was deposited by chemical vapor deposition 3 SiC 2 The interface layer is deposited under the following conditions: silicon tetrachloride as the silicon source, titanium tetrachloride as the titanium source, carbon tetrachloride as t...

Embodiment 3

[0050] In this embodiment, the ceramic matrix composite material uses silicon carbide ceramics as the matrix and silicon carbide fibers as the toughening phase, and the interface layer between the matrix and the toughening phase is a ternary layered MAX phase material Ti 3 SiC 2 .

[0051] The preparation steps of the ceramic matrix composite material are as follows:

[0052] (1) Weave 1K Tyranno SA-3 silicon carbide fibers into a 3D silicon carbide fiber preform, and the volume fraction of silicon carbide fibers is 45%.

[0053] (2) Deposit Ti on the surface of silicon carbide fiber preform by chemical vapor deposition 3 SiC 2 For the interface layer, the deposition conditions are as follows: silicon tetrachloride is used as the silicon source, titanium tetrachloride is used as the titanium source, carbon tetrachloride is used as the carbon source, hydrogen is used as the carrier gas, and the deposition temperature is 1300°C.

[0054] (3) The SiC matrix is ​​deposited on ...

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Abstract

The invention provides a fiber-toughened ceramic-based composite material with a ternary-layer-shaped MAX phase interface layer. A ternary-layer-shaped MAX phase material is introduced to serve as an interface layer, and therefore the anti-irradiation property, the heat-conducting property and the anti-oxidation property of the ceramic-based composite material can be effectively improved; in addition, through multiple fracture energy absorbing mechanisms of the MAX phase material, fracture energy can be effectively absorbed, extension of cracks in the ceramic-based composite material is hindered, and therefore the toughness and the damage tolerance of the ceramic-based composite material are improved. Accordingly, the application fields of the composite material are effectively widened, and the composite material has good application prospects in the fields of aerospace thermal structure materials, nuclear energy structural materials and the like.

Description

technical field [0001] The invention belongs to the technical field of fiber-toughened ceramic-based composite materials, and in particular relates to a fiber-toughened ceramic-based composite material with a ternary layered MAX phase interface layer and a preparation method thereof. Background technique [0002] Fiber-toughened ceramic matrix composites have excellent properties such as high strength, high temperature resistance, low density, and corrosion resistance, and have important applications in aerospace thermal structural materials, nuclear energy structural materials, and other fields. In fiber-toughened ceramic matrix composites, the interface layer between the ceramic matrix and fibers is an important component, which has an important impact on the mechanical properties, oxidation resistance, thermal conductivity, and radiation resistance of the composites. [0003] Traditional composite interface layers mainly include pyrolytic carbon (Pyrolytic Carbon, PyC), h...

Claims

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Application Information

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IPC IPC(8): C04B35/80C04B35/84C04B35/565C04B41/87C04B41/89
CPCC04B35/806C04B35/573C04B41/009C04B41/5057C04B41/52C04B41/87
Inventor 黄庆李勉陈凡燕司晓阳都时禹
Owner NINGBO INST OF MATERIALS TECH & ENG CHINESE ACADEMY OF SCI
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