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A kind of variable structure ultra-high temperature ceramic matrix composite material and preparation method thereof

A technology of ultra-high temperature ceramics and composite materials, applied in the field of composite materials, can solve problems such as difficulty in forming a uniform distribution structure, difficulty in slurry impregnation, low powder content and main distribution, etc., to achieve easy operation, excellent anti-oxidation and erosion resistance performance , solve the effect of poor thermal shock resistance

Active Publication Date: 2021-05-28
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, for composite materials prepared by resin impregnation combined with RMI, the fiber preforms are mostly needle-punched, stitched, 2.5D or three-dimensional orthogonal, three-dimensional four-directional preforms with a fiber volume fraction of more than 25%. Slurry impregnation is difficult, so the powder content in the matrix is ​​low and mainly distributed in the shallow layer near the surface. On the other hand, it is easy to produce large-sized residual C and large-sized ultra-high temperature components in the matrix. The ones present an isolated distribution, so it is difficult to form a uniform distribution structure on the microscopic scale of each component

Method used

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  • A kind of variable structure ultra-high temperature ceramic matrix composite material and preparation method thereof
  • A kind of variable structure ultra-high temperature ceramic matrix composite material and preparation method thereof
  • A kind of variable structure ultra-high temperature ceramic matrix composite material and preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0030] Example 1: Acupuncture structure C / SiC-ZrC-ZrB 2 composite material

[0031] (1) Preparation of variable structure fiber preform: by needle punching at a bulk density of 0.45g / cm 3 The volume density prepared on the high-density carbon fiber prefabricated body (T700-12k carbon fiber of Toray Corporation of Japan) is a low density of 0.15g / cm 3 The short fiber (T700-12k carbon fiber from Japan Toray Co., Ltd.) was needled into the layer to obtain the variable structure fiber preform.

[0032] (2) Depositing a PyC / SiC double-layer interface layer on the surface of the variable structure fiber preform by chemical vapor deposition to obtain a modified preform, wherein the thickness of the PyC layer is 0.3 μm, and the total thickness of the interface layer is 1.5 μm. For the deposition of the PyC layer, propane was used as the carbon source, argon was used as the dilution gas, the flow rate of propane was 800ml / min, the flow rate of argon gas was 600ml / min, the deposition ...

Embodiment 2-9 and comparative example 1-5

[0044] Using the parameters described in Table 1, the variable-structure fiber-toughened ultra-high temperature ceramic matrix composite product 2-12 was prepared by the method described in Example 1, and its properties are shown in Table 1.

[0045]

[0046]

[0047]

[0048]

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PUM

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Abstract

The invention relates to a variable-structure fiber-toughened ultra-high temperature ceramic matrix composite material and a preparation method thereof. The variable-structure fiber-toughened ultra-high temperature ceramic matrix composite material includes a high-fiber-content layer and a low-fiber-content layer. The method includes: preparation of variable structure fiber prefabricated body, preparation of interface layer, surface processing and cleaning, preparation of precursor resin slurry, slurry injection and drying treatment, high temperature cracking treatment, densification of matrix carbon and reaction Infiltration step.

Description

technical field [0001] The invention relates to the field of composite materials, in particular to a method for preparing a variable-structure fiber-toughened ultra-high temperature ceramic matrix composite material. Background technique [0002] Continuous carbon fiber toughened ultra-high temperature ceramic matrix composites (such as C / SiC-ZrC, C / SiC-HfC, C / SiC-ZrC-ZrB 2 , C / SiC-HfC-HfB 2 , C / HfC-TaC-SiC and C / HfB2-SiC, etc.) have the advantages of light weight, ultra-high temperature oxidation resistance, ablation resistance, ductile fracture, and high temperature and high specific strength. They are advanced power systems and external defense systems for new high-performance aerospace vehicles Ideal thermal structural material for thermal systems. For example, the C / SiC-ZrC composite material developed in the United States has an anti-oxidation and ablation resistance temperature of 2691 °C, and the C / ZrC combustion chamber has passed the ignition test of 2399 °C. ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C22C47/12C22C47/04C22C49/02C22C49/14C22C101/10
CPCC22C47/04C22C47/12C22C49/02C22C49/14
Inventor 于新民王鹏于艺刘俊鹏王涛李晓东张昊
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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