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SiC nanowire toughened high temperature ablation resistant ZrB2-SiC composite coating and preparation method thereof

A nanowire toughening and composite coating technology, which is applied in the field of coating on the surface of carbon/carbon composite materials, can solve the problems of poor coating performance, easy cracking and peeling of the coating

Inactive Publication Date: 2014-07-16
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In the oxyacetylene ablation environment of about 2000°C, although the coating has good ablation resistance, the ZrB 2 The thermal expansion coefficient is different from SiC, the coating is easy to crack and peel off in high temperature environment, and the performance of the coating is poor in the process of oxidation and ablation for a long time at higher temperature

Method used

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  • SiC nanowire toughened high temperature ablation resistant ZrB2-SiC composite coating and preparation method thereof
  • SiC nanowire toughened high temperature ablation resistant ZrB2-SiC composite coating and preparation method thereof
  • SiC nanowire toughened high temperature ablation resistant ZrB2-SiC composite coating and preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0055] The main process of preparing the high-temperature anti-ablation composite coating proposed in this example is: SiC inner coating prepared by embedding method, ZrB prepared by plasma spraying method 2 - SiC outer coating. The specific process is:

[0056] Step 1: Grind and polish the C / C composite material with No. 400, No. 800 and No. 1000 sandpaper in sequence, wash with absolute ethanol, and dry in an oven for later use. The drying temperature is 65-80°C.

[0057] Step 2: Prepare SiC inner coating. The specific process is:

[0058] 1) Weigh 77g of Si powder, 15g of C powder, and 8g of Al respectively 2 o 3 The powder was placed in a turpentine ball mill jar, and agate balls of different numbers and diameters were put into the ball mill jar and mixed for 3 hours to obtain a mixed powder, which was used as an embedding material for subsequent use.

[0059] 2) Put half of the prepared mixed powder into the graphite crucible, then put the cleaned and dried C / C comp...

Embodiment 2

[0069] The SiC nanowires proposed in this example toughen ZrB 2 - The main process of preparing SiC high temperature anti-ablation composite coating is: SiC inner coating prepared by embedding method, SiC nanowire prepared by chemical vapor deposition method, ZrB prepared by plasma spraying method 2 - SiC outer coating. The specific process is:

[0070] Step 1: Grind and polish the C / C composite material with No. 400, No. 800 and No. 1000 sandpaper in sequence, wash with absolute ethanol, and dry in an oven for later use. The drying temperature is 65-80°C.

[0071] Step 2: Prepare SiC inner coating. The specific process is:

[0072] 1) Weigh 77g of Si powder, 15g of C powder, and 8g of Al respectively 2 o 3 The powder was placed in a turpentine ball mill jar, and agate balls of different numbers and diameters were put into the ball mill jar and mixed for 3 hours to obtain a mixed powder, which was used as an embedding material for subsequent use.

[0073]2) Put half of ...

Embodiment 3

[0083] The SiC nanowires proposed in this example toughen ZrB 2 - The main process of preparing SiC high temperature anti-ablation composite coating is: SiC inner coating prepared by embedding method, SiC nanowire prepared by chemical vapor deposition method, ZrB prepared by plasma spraying method 2 - SiC outer coating. The specific process is:

[0084] Step 1: Grind and polish the C / C composite material with No. 400, No. 800 and No. 1000 sandpaper in sequence, wash with absolute ethanol, and dry in an oven for later use. The drying temperature is 65-80°C.

[0085] Step 2: Prepare SiC inner coating. The specific process is:

[0086] 1) Weigh 77g of Si powder, 15g of C powder, and 8g of Al respectively 2 o 3 The powder was placed in a turpentine ball mill jar, and agate balls of different numbers and diameters were put into the ball mill jar and mixed for 3 hours to obtain a mixed powder, which was used as an embedding material for subsequent use.

[0087] 2) Put half of...

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Abstract

The invention relates to a SiC nanowire toughened high temperature ablation resistant ZrB2-SiC composite coating and a preparation method thereof. The preparation method comprises the steps of firstly, preparing an internal SiC coating on the surface of a C / C (Carbon / Carbon) composite material; then, preparing a SiC nanowire toughened ZrB2-SiC ceramic coating on the internal SiC coating by using a chemical vapor deposition and supersonic plasma spraying combined process; obtaining a ceramic coating with a compact structure through increasing the toughness of the ceramic coating and reducing the cracking tendency of the coating by means of the toughening effect of a nanowire. Known from the drawing 3, the SiC nanowire toughened ZrB2-SiC coating is relatively compact and free of cracks and holes on the surface; known from the drawing 4, a ZrB2-SiC coating which is not toughened by using the nanowire has obvious cracks and more defects on the surface. A SiC nanowire toughened test sample has the linear ablative rate of 8.7mu m / s and the mass ablative rate of 1.5*10<-3>g / s when eroded at the temperature of 2200 DEG C by oxyacetylene, and a test sample which is not toughened by using the SiC nanowire has the linear ablative rate of 16.4mu m / s and the mass ablative rate of 3.3*10<-3>g / s when eroded at the temperature of 2200 DEG C by oxyacetylene.

Description

technical field [0001] The invention belongs to the coating on the surface of carbon / carbon composite materials, in particular to a SiC nanowire toughened ZrB 2 -SiC high-temperature anti-ablation composite coating and its preparation method. Hereinafter referred to as carbon / carbon composite material is C / C composite material. Background technique [0002] Thermal structural C / C composites are widely used in the aerospace field because of their excellent properties such as low density, high specific strength, high specific modulus, high temperature resistance, and ablation resistance. However, the rapid oxidation of this material at a temperature higher than 400 °C greatly limits its wide application as a high-temperature material. In order to improve the anti-oxidation and anti-ablation properties of C / C composite materials, domestic and foreign researchers have proposed many solutions, and preparing an anti-oxidation and ablation coating on its surface is an effecti...

Claims

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Application Information

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IPC IPC(8): C04B35/58C04B35/565C04B35/622
Inventor 张雨雷胡志雄李贺军姚西媛褚衍辉任金翠
Owner NORTHWESTERN POLYTECHNICAL UNIV
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