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Cf/ZrC-SiC ultra-high temperature ceramic-based composite material and preparation method thereof

A technology of ultra-high temperature ceramics and composite materials, which is applied in the field of preparation of ceramic matrix composite materials, can solve the problems affecting the high temperature thermal stability and mechanical properties of composite materials, residues, large metals, etc., and achieve the promotion of infiltration reaction kinetics, low silicon /Effect of carbon residue, low fiber/interface damage

Active Publication Date: 2018-09-28
SHANGHAI INST OF CERAMIC CHEM & TECH CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

In addition, the new product of metal melting reaction is easy to cover the surface of the internal pores of the preform, resulting in a large amount of metal residue in the prepared material, which affects the high temperature thermal stability and mechanical properties of the composite material [2]
The above shortcomings limit the application of reactive infiltration in the preparation of high-performance ultra-high temperature ceramic matrix composites to a certain extent.

Method used

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  • Cf/ZrC-SiC ultra-high temperature ceramic-based composite material and preparation method thereof
  • Cf/ZrC-SiC ultra-high temperature ceramic-based composite material and preparation method thereof
  • Cf/ZrC-SiC ultra-high temperature ceramic-based composite material and preparation method thereof

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preparation example Construction

[0036] as a C f / Examples of preparation methods of ZrC-SiC ultra-high temperature ceramic matrix composites, including: (1) modifying ZrC ceramic precursors with pore-forming agents and excess carbon sources to obtain ZrC-C ceramic precursors; (2) by vacuum The above-mentioned modified ZrC ceramic precursor was introduced into the carbon fiber preform by impregnation method, and after curing-cracking-carbothermal reduction, nanoporous C f / ZrC-C preform; (3) Infiltrating molten silicon or molten silicon-zirconium alloy into C f / ZrC-C porous preform for infiltration reaction to obtain C f / ZrC-SiC ultra-high temperature ceramic matrix composites.

[0037] In general, the present invention obtains C by vacuum impregnation of modified ZrC ceramic precursor combined with reactive infiltration f / ZrC-SiC composite material, using the prepared nanoporous C f / ZrC-C preform, which promotes infiltration reaction kinetics, reduces fiber / interface damage and large-size silicon / car...

Embodiment 1

[0041] according to figure 1 The process shown was carried out for preparation:

[0042] (1) Modification of ZrC ceramic precursor: add 20g phenolic resin and 5g polyacrylic acid to 100ml polyziroxane ZrC ceramic precursor, and mix well to obtain ZrC-C ceramic precursor;

[0043] (2) Vacuum impregnation: using the three-dimensional needle-punched carbon fiber braid with a silicon carbide interface as a prefabricated body, vacuum impregnate with the above precursor for 3 hours;

[0044] (3) Curing-cracking-carbothermal reduction: the impregnated material was cured at 140°C for 2h, cracked at 900°C for 2h in an Ar atmosphere, and vacuum carbothermally reduced at 1600°C for 2h to obtain C f / ZrC-C porous preform;

[0045] (4) Reaction infiltration: using high-purity silicon as the silicon source, carry out reaction infiltration in a vacuum environment at 1450 ° C for 1 hour, and the molten silicon and residual carbon react in situ to form a SiC matrix, and finally obtain C f / ...

Embodiment 2

[0049] Embodiment 2 is similar to Embodiment 1, except that steps (2) and (3) are repeated once. The C prepared in this embodiment 2 f / ZrC-C porous preform, the median diameter measured by AutoPore IV 9500V1.09 automatic mercury porosimeter is 9.6 μm, the pore diameter is distributed in a ladder shape and there are a large number of nanopores. C prepared in this example f The open porosity of the / ZrC-SiC composite material measured by the Archimedes drainage method is 1.7%, and the bending strength of the material is 402.5MPa. C prepared in this example f The / ZrC-SiC ultra-high temperature ceramic matrix composite mainly includes carbon fiber, SiC phase and ZrC phase, wherein the content of carbon fiber is 30vol%, and the volume content of ZrC phase and SiC phase are ~40vol% and ~30vol% respectively.

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Abstract

The invention provides a Cf / ZrC-SiC ultra-high temperature ceramic-based composite material and a preparation method thereof. The preparation method comprises the steps of: (1) mixing a pore-forming agent, a carbon source and a ZrC ceramic precursor so as to obtain a modified ZrC-C ceramic precursor; (2) introducing the modified ZrC-C ceramic precursor into a carbon fiber prefab, and then performing curing, cracking and carbothermic reduction to obtain a nanoporous Cf / ZrC-C prefab; and (3) infiltrating molten silicon or molten silicon-zirconium alloy into the porous Cf / ZrC-C prefab, and carrying out an infiltration reaction to obtain the Cf / ZrC-SiC ultra-high temperature ceramic-based composite material.

Description

technical field [0001] The present invention relates to a C f The invention relates to a ZrC-SiC ultra-high temperature ceramic matrix composite material and a preparation method thereof, belonging to the field of preparation of ceramic matrix composite materials. Background technique [0002] Ultra-high temperature ceramic matrix composites (such as C f / ZrC-SiC, C f / HfC-SiC, C f / ZrC-ZrB 2 -SiC, etc.), which solves the shortcomings of ceramic materials such as low fracture toughness, small fracture strain, and poor thermal shock resistance. Moreover, ultra-high temperature ceramic matrix composites have outstanding ultra-high temperature resistance and excellent high-temperature oxidation and ablation resistance. At the same time, they have the advantages of non-brittle fracture failure mode under stress and performance can be designed. One of the most promising candidate materials for aircraft thermal protection materials and thermal protection components for new ge...

Claims

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Application Information

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IPC IPC(8): C04B35/80C04B35/84C04B35/622C04B35/56C04B35/565
CPCC04B35/806C04B35/5622C04B35/573C04B35/622C04B2235/3826C04B2235/3839C04B2235/5248C04B2235/96
Inventor 倪德伟王敬晓董绍明阚艳梅张翔宇
Owner SHANGHAI INST OF CERAMIC CHEM & TECH CHINESE ACAD OF SCI
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