Method for preparing ZrB2-SiC-ZrC diphase ceramic material

A multiphase ceramic, zrb2-sic-zrc technology, which is applied in the field of preparation of non-oxide-based ceramic materials, can solve the problems of residues, the adverse effects of high temperature mechanical properties and anti-oxidation properties of materials, etc., and achieves low price and high defect concentration. , the effect of low purity requirements

Inactive Publication Date: 2008-07-09
SHANGHAI INST OF CERAMIC CHEM & TECH CHINESE ACAD OF SCI
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Problems solved by technology

Although the introduction of sintering aids promotes the densification of materials to a certain extent, the added aids often remain at the grain boundaries in the form of glass phases or oxides, which is detrimental to the high-temperature mechanical properties and oxidation resistance of materials. Impact

Method used

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  • Method for preparing ZrB2-SiC-ZrC diphase ceramic material

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Experimental program
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Effect test

Embodiment 1

[0018] Zirconium powder (20-50 μm, 98%), silicon powder (20-50 μm, 99%) and boron carbide powder (≤2 μm, 99%) are used as raw materials. Design ZrB 2 -ZrC volume percentage content in SiC-ZrC is 5, that is, take the reaction equation (2+x)Zr+(1-x)Si+B 4 C=2ZrB 2 x=0.15628 ingredients in +(1-x)SiC+xZrC, with acetone as solvent, with a speed of 550 rpm, with ZrO 2 The balls and planets were milled for 8 hours, and the resulting slurry was dried by rotary evaporation to obtain a uniformly mixed powder. Put the uniformly mixed powder in the graphite mold coated with BN on the inner wall surface, and carry out reaction sintering in vacuum. The heating rate during sintering is 10-100°C / min. min, at 1450°C for 3 hrs, after the end of the hold, apply a pressure of 20-30MPa, then raise the temperature to 1600°C, hold the hold for 3 hrs. The material density reaches 98%. The XRD pattern and microstructure of the material are shown in Figure 1(b) and Figure 2.

Embodiment 2

[0020] Design ZrB 2 -ZrC volume percentage in SiC-ZrC is 1 5, that is, the reaction equation (2+x)Zr+(1-x)Si+B 4 C=2ZrB 2 x = 0.47955 in +(1-x)SiC+xZrC. Ceramics were prepared according to the method of Example 1, and the density of the material reached 99%. The XRD of the material is shown in Fig. 1(c).

Embodiment 3

[0022] Design ZrB 2 -The volume percentage of ZrC in SiC-ZrC is 10, that is, the reaction equation (2+x)Zr+(1-x)Si+B 4 C=2ZrB 2 x=0.31609 in +(1-x)SiC+xZrC. Ceramics were prepared according to the method of Example 1, and the density of the material was greater than 97%.

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Abstract

The invention relates to a process for preparing ZrB2-SiC-ZrC complex phase ceramic materials, which is characterized in that purity of zirconium powder is not less than 98%, silicon powder and boron carbide powder are used as raw materials, batching according to reaction equation (2+x)Zr+(1-x)Si+B4C=2ZrB2+(1-x)SiC+ZrC, 0<=x<=0.5 of generating ZrB2-SiC-ZrC, then, materials containing different components are obtained. The raw materials after being ball ground and dried are sintered with heat pressing between 1500-1700DEG C by adjusting sintering technique parameter and employing self-propagating reaction of the raw materials generated in the process of heating up, thereby obtaining the ZrB2-SiC-ZrC complex phase ceramic materials of different components. Relative density of the materials prepared by the invention is larger than 97%, bending strength is 600-900MPa, fracture toughness property is 4.5-6MPa,m1/2, and hardness is 16-19GPa.

Description

technical field [0001] The present invention relates to a kind of ZrB 2 - A preparation method of SiC-ZrC composite ceramic material. The invention belongs to the field of preparation of non-oxide-based ceramic materials. Background technique [0002] The development of aerospace flight technology has raised the demand for new high-temperature materials. During the flight of a hypersonic vehicle, its sharp surfaces, such as engine inlets, flanges and nose cones, will rub against the atmosphere strongly to generate high temperatures, so it needs to be able to repeat at 1800-2400°C in an environment with oxygen. The material used acts as a heat protection system. So far, there are few materials that can be used in the heat protection system of future supersonic vehicles. The high-temperature materials in use include carbon-carbon composite materials and silicon carbide-based composite materials, such as C-SiC, SiC-SiC, etc., but these materials The anti-oxidation temperatu...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/645C04B35/569C04B35/56C04B35/58
Inventor 张国军吴雯雯阚艳梅王佩玲
Owner SHANGHAI INST OF CERAMIC CHEM & TECH CHINESE ACAD OF SCI
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