ZrC-TiC modified C/C-SiC composite material and preparation method thereof

A composite material and modification technology, which is applied in the field of ZrC-TiC modified C/C-SiC composite material and its preparation, can solve the problems of material isolation, difficulty in SiC components, limiting material ablation resistance, etc. Short, suitable for a wide range of workpiece sizes, and has the effect of preventing erosion

Active Publication Date: 2015-06-03
深圳金羽先进材料有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although the composite material can form a solid-liquid two-phase oxide protective layer to increase the viscosity of the ablated surface layer, it is difficult for the SiC component to form a stable liquid-phase oxide layer in an ablation environment exceeding 1800 °C, and SiO 2 The evaporation rate is faster, and at the same time, the solid phase ZrO 2 The structure is relatively loose, and it is still difficult to effectively isolate the material from the external environment, which limits the ablation resistance of the material

Method used

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  • ZrC-TiC modified C/C-SiC composite material and preparation method thereof
  • ZrC-TiC modified C/C-SiC composite material and preparation method thereof
  • ZrC-TiC modified C/C-SiC composite material and preparation method thereof

Examples

Experimental program
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Effect test

Embodiment 1

[0049] Set the density to 0.58g / cm 3 The carbon fiber fine-woven puncture felt is placed in a closed furnace cavity, methane and hydrogen are introduced, and the temperature is kept at 1100°C for 100h, and the pressure in the furnace is 1.6Kpa. The surface of the fibers in the carbon fiber braid is gradually deposited to form pyrolytic carbon by chemical vapor infiltration, and a density of 1.20 g / cm is obtained. 3 -1.33g / cm 3 The C / C composite material is prepared for subsequent steps after ultrasonic cleaning and low-temperature vacuum drying.

[0050] Put silicon powder, zirconium powder and titanium powder with a purity greater than 99% in the ball mill tank at an atomic ratio of 84%, 12%, and 3%, respectively, and simultaneously add copper powder at an atomic ratio of 1%, and process it through a planetary ball mill A mixed powder is obtained. The ball milling medium is stainless steel, the ball-to-material ratio is 4:1, the milling speed is 150r / min, and the milling t...

Embodiment 2

[0055] Set the density to 0.78g / cm 3 The carbon fiber needle-punched integral felt is placed in a closed furnace cavity, propylene and hydrogen are introduced, and the temperature is kept at 1100°C for 90h, and the pressure in the furnace is 1.7Kpa. The surface of the fibers in the carbon fiber braid is gradually deposited to form pyrolytic carbon by chemical vapor infiltration, and a density of 1.27 g / cm is obtained. 3 –1.36g / cm 3 The C / C composite material is prepared for subsequent steps after ultrasonic cleaning and low-temperature vacuum drying.

[0056] Put silicon powder, zirconium powder and titanium powder with a purity greater than 99% in the atomic ratio of 66%, 22%, and 11%, respectively, in a ball mill tank, and at the same time add iron powder in an atomic ratio of 1%, and process it through a planetary ball mill A mixed powder is obtained. The ball milling medium is stainless steel, the ball-to-material ratio is 8:1, the milling speed is 200r / min, and the mil...

Embodiment 3

[0061] Set the density to 0.32g / cm 3 The chopped carbon fiber laminated needle felt is placed in a closed furnace cavity, propylene and hydrogen are introduced, and the temperature is kept at 1200 ° C for 90 hours, and the pressure in the furnace is 1.8Kpa. The surface of the fibers in the carbon fiber braid is gradually deposited to form pyrolytic carbon by chemical vapor infiltration, and a density of 1.00 g / cm is obtained 3 –1.28g / cm 3 The C / C composite material is prepared for subsequent steps after ultrasonic cleaning and low-temperature vacuum drying.

[0062] Put silicon powder, zirconium powder and titanium powder with a purity greater than 99% in a ball mill tank at an atomic ratio of 77%, 18%, and 4% respectively, and at the same time add aluminum powder at an atomic ratio of 1%, and process it through a planetary ball mill A mixed powder is obtained. The ball milling medium is ZrO 2 , the ball-to-material ratio is 10:1, the milling speed is 300r / min, and the mil...

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Abstract

The invention relates to a ZrC-TiC modified C/C-SiC composite material and a preparation method thereof, belonging to the technical field of preparation of composite materials. The composite material disclosed by the invention comprises carbon fibers, a pyrolytic carbon layer, SiC and ZrC-TiC, wherein the pyrolytic carbon layer coats the surface of the carbon fibers; SiC and ZrC-TiC coat the surface of the pyrolytic carbon layer; and ZrC-TiC is uniformly distributed in SiC. The preparation method comprises the following steps: preparing a low-density C/C composite material by adopting chemical vapor infiltration; melting Si, Zr and Ti powder, infiltrating the powder into the C/C composite material by virtue of a capillary action, and forming a ceramic phase in pores by virtue of a high-temperature in-situ reaction, thereby obtaining the ZrC-TiC modified C/C-SiC composite material. With the adoption of the process method which is low in cost, rapid and convenient, the service temperature of the C/C-SiC composite material is effectively improved, and the ultra-high temperature ablation resistance of the material is greatly enhanced.

Description

technical field [0001] The invention relates to a ZrC-TiC modified C / C-SiC composite material and a preparation method thereof, belonging to the technical field of composite material preparation. Background technique [0002] C / C-SiC composite material is a composite material composed of SiC and pyrolytic carbon as the matrix phase and carbon fiber as the reinforcing phase. It has excellent properties such as low density, high strength, high temperature resistance, oxidation resistance, and thermal shock resistance. Ideal high temperature resistant structural material, widely used in aerospace field. [0003] Since SiC can form continuous SiO at high temperature 2 The glass phase protective layer, the matrix of the C / C-SiC composite material will not fail due to a large amount of oxidation in a high temperature environment within 1800 ° C; but after exceeding this temperature, SiO 2 The evaporation pressure will gradually increase, and the protective layer formed by it wil...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/83C04B35/565C04B35/56C04B35/622
Inventor 熊翔曾毅王滴泥张红波孙威王雅雷吴强张响
Owner 深圳金羽先进材料有限公司
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