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Silicon boron zirconium carbonitride ceramic composite material and preparation methods thereof

A ceramic composite material, silicon boron carbon nitride zirconium technology, which is applied in the field of ceramic composite materials and its preparation, can solve the problems of unsafe service, thermal shock damage resistance and high temperature ablation damage resistance, etc. Thermal shock damage performance, comprehensive mechanical properties, good high temperature resistance, and improved fracture toughness

Active Publication Date: 2014-02-19
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The present invention aims to solve the problem that the thermal shock damage resistance and high temperature ablation damage resistance of the existing silicon-boron-carbon-nitrogen ceramic composite materials are still not ideal, and cannot serve safely in a high-temperature ablation environment higher than 1500°C, and provides Silicon boron carbon nitrogen zirconium ceramic composite material and preparation method thereof

Method used

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  • Silicon boron zirconium carbonitride ceramic composite material and preparation methods thereof
  • Silicon boron zirconium carbonitride ceramic composite material and preparation methods thereof
  • Silicon boron zirconium carbonitride ceramic composite material and preparation methods thereof

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specific Embodiment approach 1

[0024] Specific Embodiment 1: In this embodiment, the silicon-boron-carbon-nitrogen-zirconium ceramic composite material is made of silicon powder, graphite powder, hexagonal boron nitride powder, zirconium powder and boron powder as raw materials, mixed by ball milling and sintered by hot pressing; The molar ratio of silicon powder and graphite powder in the raw material is 2:3, the molar ratio of graphite powder and hexagonal boron nitride powder is 3:1, the molar ratio of zirconium powder and boron powder is 1:2, graphite powder and zirconium powder The molar ratio is (1~10):1, and the molar ratio of graphite powder and boron powder is (0.5~8):1; the purity of the silicon powder is 99%~99.9%, and the particle size is 1 μm~20 μm; The purity of the graphite powder is 99% to 99.9%, and the particle size is 1 μm to 20 μm; the purity of the hexagonal boron nitride powder is 99% to 99.9%, and the particle size is 1 μm to 20 μm; the zirconium powder The purity is 99%-99.9%, and th...

specific Embodiment approach 2

[0026] Specific embodiment two: the preparation method of the silicon boron carbon nitrogen zirconium ceramic composite material of specific embodiment one, carry out according to the following steps:

[0027] 1. Weigh each component: Weigh silicon powder, graphite powder, hexagonal boron nitride powder, zirconium powder and boron powder as raw materials, the molar ratio of silicon powder and graphite powder in the raw materials is 2:3, graphite powder The molar ratio of hexagonal boron nitride powder to hexagonal boron nitride powder is 3:1, the molar ratio of zirconium powder to boron powder is 1:2, the molar ratio of graphite powder to zirconium powder is (1-10):1, and the molar ratio of graphite powder to boron powder The ratio is (0.5-8): 1; the purity of the silicon powder is 99%-99.9%, and the particle size is 1μm-20μm; the purity of the graphite powder is 99%-99.9%, and the particle size is 1μm ~20 μm; the purity of the hexagonal boron nitride powder is 99% to 99.9%, a...

specific Embodiment approach 3

[0034] Specific embodiment three: the difference between this embodiment and specific embodiment two is that in step two, the raw materials weighed in step one are put into a ball mill jar, the ball-to-material ratio is (10~90):1, and the Perform ball milling for 15h to 35h to obtain amorphous composite powder; the ball-to-material ratio is the mass ratio of the ball to the raw material weighed in step 1, and the diameter of the ball is 5mm to 8mm. Others are the same as in the second embodiment.

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Abstract

The invention provides a silicon boron zirconium carbonitride ceramic composite material and preparation methods thereof and relates to a ceramic composite material and a preparation method thereof. The objective of the invention is to overcome the problems that a conventional silicon boron carbonitride ceramic composite material has insufficient thermal shock damage resistance and high temperature ablation resistance and cannot safely take service in a high temperature ablation environment with a temperature of more than 1500 DEG C. The silicon boron zirconium carbonitride ceramic composite material is prepared from raw materials consisting of silicon powder, graphite powder, hexagonal boron nitride powder, zirconium powder and boron powder through ball milling, mixing and hot pressed sintering. One of the preparation methods comprises the following steps: weighing the raw materials in proportion; subjecting the raw materials to ball milling and mixing; and then carrying out sintering so as to obtain the silicon boron zirconium carbonitride ceramic composite material. The other preparation method comprises the following steps: subjecting weighed zirconium powder and boron powder to ball milling and mixing; then adding silicon powder, graphite powder and hexagonal boron nitride powder and continuing ball milling and mixing; and then carrying out sintering so as to obtain the silicon boron zirconium carbonitride ceramic composite material. The preparation methods provided by the invention are applicable to preparation of the silicon boron zirconium carbonitride ceramic composite material.

Description

technical field [0001] The invention relates to a ceramic composite material and a preparation method thereof. Background technique [0002] The rapid development of aviation, aerospace, metallurgy, machinery, energy, chemical and other technologies has put forward higher requirements for high temperature resistant materials. For example, supersonic aircraft with a speed greater than Mach 5 and aero turbine engines with a thrust-to-weight ratio greater than 15 require materials that can safely serve in a high-temperature ablation environment with a temperature higher than 2200 °C. After years of hard work by researchers, high-temperature resistant ceramic material systems represented by silicon carbide and silicon nitride have been well applied in the aerospace field. However, regardless of silicon carbide or silicon nitride, when the temperature is higher than 1500 ° C, its strength, oxidation resistance, thermal shock resistance and high temperature ablation resistance wi...

Claims

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Application Information

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IPC IPC(8): C04B35/515C04B35/622
Inventor 杨治华贾德昌胡成川段小明王胜金梁斌
Owner HARBIN INST OF TECH
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