Preparation method for anti-high-temperature oxidative damage ZrB2-SiC-ZrC-W multiphase ceramic

A zrb2-sic-zrc-w, high temperature oxidation resistance technology, applied in the field of engineering material preparation, can solve problems such as poor stability, and achieve the effects of improving temperature resistance, highlighting high temperature oxidation damage resistance, and improving high temperature stability

Active Publication Date: 2016-03-30
LASER FUSION RES CENT CHINA ACAD OF ENG PHYSICS +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Purpose of the present invention will solve existing ZrB 2 Based on the problem of poor stability of ceramic-based materials at more than 1600 ° C, and to provide a high-temperature oxidation-resistant ZrB 2 - Preparation method of SiC-ZrC-W composite ceramics

Method used

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Examples

Experimental program
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Effect test

specific Embodiment approach 1

[0011] Specific implementation mode 1: This implementation mode is a kind of anti-high temperature oxidation damage ZrB 2 -The preparation method of SiC-ZrC-W composite phase ceramics, specifically prepare according to the following steps:

[0012] 1. Prepare raw materials: weigh 30% to 85% of zirconium boride powder, 5% to 25% of silicon carbide powder, 5% to 20% of zirconium carbide powder and 5% to 25% of tungsten powder by volume percentage;

[0013] 2. Mixing: Weigh 30% to 85% of zirconium boride powder, 5% to 25% of silicon carbide powder, 5% to 20% of zirconium carbide powder and 5% to 25% of Mix tungsten powder to obtain the mixed powder, and add absolute ethanol to the mixed powder to obtain the material to be ball-milled, and then use a planetary ball mill for ball-milling dispersion. The mass ratio of the ball to the material to be ball-milled is (2-4):1 , ball milling at a ball mill speed of 150rpm-250rpm for 8h-20h to obtain a slurry; the mass ratio of the volume...

specific Embodiment approach 2

[0016] Embodiment 2: The difference between this embodiment and Embodiment 1 is that the zirconium boride powder in step 1 has an average particle size of 1 μm to 5 μm and a purity of ≥99%. Others are the same as the first embodiment.

specific Embodiment approach 3

[0017] Embodiment 3: This embodiment differs from Embodiment 1 or Embodiment 2 in that: the average particle size of the silicon carbide powder in step 1 is 0.5 μm-2 μm, and the purity is ≥99%. Others are the same as those in Embodiment 1 or 2.

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Abstract

The invention belongs to the technical field of engineering material preparing, and specifically relates to a preparation method for anti-high-temperature oxidative damage ZrB2-SiC-ZrC-W multiphase ceramic. The preparation method aims at solving the problem that when the temperature is over 1600 DEG C, the stability of an existing ZrB2 base ceramic material is poor. The preparation method comprises the steps that 1, raw materials are prepared; 2, mixing and ball milling are conducted, and sizing agents are obtained; 3, drying and grinding are carried out, and mixed powder materials are obtained; and 4, hot pressed sintering is conducted, and the ZrB2-SiC-ZrC-W multiphase ceramic is obtained. The anti-high-temperature oxidative damage ZrB2-SiC-ZrC-W multiphase ceramic has the advantages that 1, the consistency is greater than 99%; 2, compared with the existing ZrB2 base ceramic material, the anti-high-temperature oxidative damage performance is more prominent. The method is mainly used for preparing the anti-high-temperature oxidative damage ZrB2-SiC-ZrC-W multiphase ceramic.

Description

technical field [0001] The invention belongs to the technical field of engineering material preparation, and specifically relates to a ZrB anti-high temperature oxidation damage 2 - A preparation method of SiC-ZrC-W composite ceramics. Background technique [0002] With people's continuous pursuit of aircraft performance, the traditional ablative thermal protection materials that sacrifice the material itself to achieve heat protection can no longer meet the harsh service environment and strict structural integrity requirements of future aircraft. The development of new thermal protection materials that can maintain physical and chemical stability in ultra-high temperature environments and reactive atmospheres has become one of the key conditions for the development of aircraft. Among many ultra-high temperature structural materials, ZrB 2 Ceramic-based materials have attracted much attention due to their outstanding comprehensive properties, and are considered to be one o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22C29/14C22C30/00C22C1/05
CPCB22F2998/10B22F2999/00C22C1/051C22C29/14C22C30/00B22F1/0003B22F2003/145B22F2201/20B22F2201/11
Inventor 李宁张幸红柯博赵利平胡平李翠
Owner LASER FUSION RES CENT CHINA ACAD OF ENG PHYSICS
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