A kind of preparation method of co-growth of SIC nanowire and SIC-Mosi2-CRSi2 coating

A sic-mosi2-crsi2 and nanowire technology, applied in the field of C/C composite material manufacturing, can solve problems such as coating damage, achieve the effects of reducing thermal damage, alleviating thermal stress mismatch, and reducing cracking tendency

Active Publication Date: 2019-06-04
NORTHWESTERN POLYTECHNICAL UNIV
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  • Description
  • Claims
  • Application Information

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Problems solved by technology

To achieve long-term oxidation resistance of the coating, it is necessary to have a sufficient amount of MoSi in the coating 2 and CrSi 2 phase, but because its thermal expansion coefficient is much larger than that of C / C composite materials, the increase of these two phases in the coating will lead to a large thermal mismatch between the coating and the substrate, resulting in rapid destruction of the coating

Method used

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  • A kind of preparation method of co-growth of SIC nanowire and SIC-Mosi2-CRSi2 coating
  • A kind of preparation method of co-growth of SIC nanowire and SIC-Mosi2-CRSi2 coating
  • A kind of preparation method of co-growth of SIC nanowire and SIC-Mosi2-CRSi2 coating

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0024] Step 1: Grind and polish the C / C composite material with No. 400, No. 800, and No. 1000 sandpaper, then ultrasonically clean it with water and absolute ethanol for 15-20 minutes, and dry it in a drying oven for later use;

[0025] Step 2: Weigh MoSi with a mass percentage of 10-20% respectively 2 Powder, 65-80% of Si powder, 10-20% of Cr powder, 5%-10% of C powder, put in the turpentine ball ink tank, take different numbers of agate balls with different diameters and put them into the ball mill tank, in the ball mill Go up the ball mill and mix for 2 hours to get the embedding powder, dry it for 12 hours and set aside;

[0026] Step 3: Put the above 1 / 3 of the embedding powder into the graphite crucible, then put the pretreated C / C composite material, and then put the above 1 / 3 of the embedding powder to make the C / C composite material cover.

[0027] Step 4: Put the graphite crucible into a vacuum heating furnace, raise the furnace temperature from room temperature t...

Embodiment 2

[0029] Step 1: Grind and polish the C / C composite material with No. 400, No. 800, and No. 1000 sandpaper, then ultrasonically clean it with water and absolute ethanol for 15-20 minutes, and dry it in a drying oven for later use;

[0030] Step 2: Weigh 60-80% silicon powder, 10-25% carbon powder, and 5-15% aluminum oxide powder in the turpentine ball ink tank, and put different numbers and diameters of agate balls into the In the ball mill tank, ball mill and mix on a ball mill for 2 hours to obtain embedding powder, dry for 12 hours and set aside;

[0031] Step 3: Put the above-mentioned powder into the graphite crucible, bury the spare carbon / carbon composite material in the mixed powder respectively, then put the graphite crucible into the vertical vacuum furnace, and pass the argon gas into the whole process as the protective atmosphere , the temperature rise rate of the vertical vacuum furnace is controlled at 5°C / min. When the furnace temperature rises to 2000°C, it is ke...

Embodiment 3

[0036] Step 1: Grind and polish the C / C composite material with No. 400, No. 800, and No. 1000 sandpaper, then ultrasonically clean it with water and absolute ethanol for 15-20 minutes, and dry it in a drying oven for later use;

[0037] Step 2: Weigh MoSi with a mass percentage of 10-20% respectively 2 Powder, 65-80% of Si powder, 10-20% of Cr powder, 5%-10% of C powder, put in the turpentine ball ink tank, take different numbers of agate balls with different diameters and put them into the ball mill tank, in the ball mill Go up the ball mill and mix for 2 hours to get the embedding powder, dry it for 12 hours and set aside;

[0038] Step 3: Put the above-mentioned powder into the graphite crucible, bury the carbon / carbon composite material in the mixed powder respectively, then put the graphite crucible into the vertical vacuum furnace, and put Ar as the protective atmosphere in the whole process, vertical The temperature rise rate of the vacuum furnace was controlled at 5°...

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Abstract

The invention relates to a preparation method of a SiC nano-wire and SiC-MoSi2-CrSi2 coating co-growth composite. A SiC nano-wire and a SiC-MoSi2-CrSi2 coating are prepared on the surface of a C / C composite through an embedding method. The C / C composite sample with the density of 1.63-1.75 g / cm<3> is cleaned and then dried for use; embedding powder with a certain proportion is prepared, and the embedding powder is put in a vacuum heating furnace with argon shielding available in the whole process. The SiC nano-wire and SiC-MoSi2-CrSi2 coating co-growth composite is finally prepared. The thermal expansion mismatch problem between coatings can be relieved through the method of transition coating and nano-wire co-growth, the toughness of a ceramic coating is improved, the cracking trend of the ceramic coating is reduced, and finally the anti-oxidation performance of the coating is improved. Compared with the mode that thermal stress mismatch is relieved through traditional nano-wire toughening or transition coatings to improve binding force, heating damage of the material in the multiple preparation processes can be reduced through one preparation process, the toughness of the ceramic coating is improved, the cracking trend of the ceramic coating is reduced, and the anti-oxidation capacity of the ceramic coating is improved.

Description

technical field [0001] The invention belongs to C / C composite material manufacturing technology, and relates to a SiC nanowire and SiC-MoSi 2 -CrSi 2 Preparation method of coating co-growth, specifically related to one-step embedding method to realize SiC nanowire and SiC-MoSi 2 -CrSi 2 Preparation method of coating co-growth to enhance and toughen oxidation-resistant coatings on carbon / carbon composites. Background technique [0002] The problem of easy oxidation at high temperature limits the practical application of carbon / carbon composites as thermal structural materials. Coating technology is an effective means to solve this problem, such as ZrC, HfC, etc., which can be used as thermal protection and anti-ablation components of aerospace vehicles. However, the thermal expansion coefficients of ZrC, HfC and C / C composites differ greatly. Alleviating the thermal expansion mismatch problem is the most difficult bottleneck in the practical application of high-temperatu...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B41/87
CPCC04B41/009C04B41/5071C04B41/87C04B2235/9684C04B35/83C04B41/5059C04B41/5057
Inventor 郭领军霍彩霞刘跃寇钢王昌聪徐东东
Owner NORTHWESTERN POLYTECHNICAL UNIV
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