Preparation method of ultra-temperature oxidative damage resistant zirconium diboride-silicon carbide ceramic base composite material

The technology of silicon carbide ceramic base and zirconium diboride is applied in the field of preparation of ceramic matrix composite materials, which can solve the problems of poor stability of oxide layer, and achieve the effects of good oxidation resistance, simple and effective oxidation damage, and improvement of oxidation resistance.

Active Publication Date: 2013-06-26
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The present invention aims to solve the problem that the existing zirconium diboride-silicon carbide ceramic matrix composite material has poor stability of the oxide layer at ult

Method used

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  • Preparation method of ultra-temperature oxidative damage resistant zirconium diboride-silicon carbide ceramic base composite material
  • Preparation method of ultra-temperature oxidative damage resistant zirconium diboride-silicon carbide ceramic base composite material
  • Preparation method of ultra-temperature oxidative damage resistant zirconium diboride-silicon carbide ceramic base composite material

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specific Embodiment approach 1

[0012] Specific embodiment 1: This embodiment is a method for preparing a zirconium diboride-silicon carbide ceramic matrix composite material resistant to ultra-high temperature oxidation damage, which is carried out in the following steps:

[0013] 1. Preparation of zirconium diboride-silicon carbide ceramic matrix composite material: weigh 70~90 parts of zirconium diboride powder and 30~10 parts of silicon carbide powder by weight, and carbonize the zirconium diboride powder The silicon powder is ball-milled and wet-mixed to obtain a slurry, and then the obtained slurry is dried by a rotary evaporator at a temperature of 50°C to 90°C for 1 hour to 4 hours to obtain a dried mixed powder. The obtained dried mixed powder is hot-pressed and sintered at a temperature of 1700°C~190°C under vacuum or inert gas atmosphere, the hot pressing pressure is 30MPa, the holding time is 20 minutes to 60 minutes, and it is naturally cooled to room temperature. Take out, that is, zirconium dibor...

specific Embodiment approach 2

[0021] Specific embodiment two: this embodiment is different from specific embodiment one in that: the particle size of the zirconium diboride powder described in step one is less than 10 microns; the particle size of the silicon carbide powder described in step one is less than 10 microns . Others are the same as the first embodiment.

specific Embodiment approach 3

[0022] Specific embodiment three: This embodiment is different from specific embodiment one or two in that the inert gas described in step one is argon. Others are the same as the first or second embodiment.

[0023] Specific implementation manner 4: combination figure 1 The difference between this embodiment and specific embodiments 1 to 3 is that the oxidation suppression treatment device described in step 2 includes a flow meter 1, an optical pyrometer 2, a calcium fluoride glass 3, a top cover 4, a quartz tube 5, Zirconia support 6, bottom cover 7, electromagnetic induction heating coil 8, pressure gauge 9 and vacuum pump 10; the flow meter 1 is connected to the air inlet of the top cover 4, and the calcium fluoride glass 3 is embedded in the top cover 4 enables light to penetrate from the inside of the quartz tube 5, the top cover 4 is hermetically connected to the upper end of the quartz tube 5, the bottom cover 7 is hermetically connected to the bottom end of the quartz tu...

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Abstract

The invention relates to a preparation method of an ultra-temperature oxidative damage resistant zirconium diboride-silicon carbide ceramic base composite material, and relates to a preparation method of an ultra-temperature oxidative damage resistant ceramic base composite material. The preparation method aims to solve the problem of poor oxide layer stability of the traditional zirconium diboride-silicon carbide ceramic base composite material at a superhigh temperature (more than 1700 DEG C). The preparation method comprises the following steps of: 1, preparing the zirconium diboride-silicon carbide ceramic base composite material; and 2, carrying out oxidization inhibition processing to obtain the superhigh temperature oxidative damage resistant zirconium diboride-silicon carbide ceramic base composite material. The preparation method disclosed by the invention can be used for preparing the superhigh temperature oxidative damage resistant zirconium diboride-silicon carbide ceramic base composite material.

Description

Technical field [0001] The invention relates to a preparation method of a ceramic matrix composite material resistant to ultra-high temperature oxidation damage. Background technique [0002] The development of hypersonic flight technology puts forward harsh requirements on thermal protection materials. ZrB 2 Ceramic matrix composites have a very high melting point, high thermal and electrical conductivity, excellent resistance to chemical corrosion, relatively low density, and moderate price. The excellent comprehensive performance enables it to be competent in the extreme aerodynamic thermal environment of the key parts of the hypersonic aircraft tip and wing leading edge, while meeting the aircraft's strict requirements for the structural integrity of the thermal protection system. It is a very promising non-ablative Type structure material. [0003] Pure ZrB 2 Oxidation of ceramic materials to produce ZrO 2 And B 2 O 3 , The resulting glass phase covers the surface of the mat...

Claims

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Application Information

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IPC IPC(8): C04B35/58C04B35/622
Inventor 张幸红李宁胡平韩文波金鑫鑫洪长青
Owner HARBIN INST OF TECH
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