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C/C composite material superhigh temperature ceramic coating, and preparation method thereof

A technology of ultra-high temperature ceramics and composite materials, which is applied in the field of preparation of ultra-high temperature thermal protection structures, can solve the problems of poor thermal shock resistance of ceramic coatings, weak bonding force of matrix materials, and easy cracking, etc., so as to improve the overall bonding ability. And thermal shock resistance, good oxidation resistance and ablation resistance, the effect of improving the service life

Inactive Publication Date: 2018-09-14
CENT SOUTH UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The purpose of the present invention is to provide a ceramic coating of a C / C composite material with good anti-oxidation and ablation resistance at ultra-high temperature and its preparation method, so as to solve the problem of poor thermal shock resistance of the ceramic coating and weak bonding force with the base material , prone to cracking defects

Method used

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  • C/C composite material superhigh temperature ceramic coating, and preparation method thereof
  • C/C composite material superhigh temperature ceramic coating, and preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0029] Set the density to 1.73g / cm 3 The C / C composite material is processed into a pre-coated sample, the surface is polished with sandpaper, put into anhydrous ethanol for ultrasonic cleaning, and cleaned twice, and the cleaning time is 10 minutes each time; after cleaning, put it in a drying oven for drying. .

[0030] Si and SiO 2 Mix the powder according to the mass ratio of 2:1 to obtain the mixed powder; then put the C / C composite material sample and the above mixed powder into the graphite crucible. When placed, the distance between the C / C composite material and the mixed powder is 50mm. Put the graphite crucible with mixed powder and C / C sample into a high-temperature graphitization furnace, evacuate to below 0.8kPa, fill in an inert gas as a protective gas, and raise the temperature to 2100°C at a heating rate of 10°C / min. After 2 hours of heat preservation, the temperature was naturally lowered to room temperature, and a C / C composite material with a SiC coating ...

Embodiment 2

[0036] Set the density to 1.78g / cm 3 The C / C composite material is processed into a pre-coated sample, the surface is polished with sandpaper, put into anhydrous ethanol for ultrasonic cleaning, and cleaned twice, and the cleaning time is 10 minutes each time; after cleaning, put it in a drying oven for drying. .

[0037] Si and SiO 2 Mix evenly according to the mass ratio of 2:1 to obtain mixed powder; then put the C / C composite material sample and the above mixed powder into a graphite crucible. When placed, the distance between the C / C composite material sample and the mixed powder is 45mm. Then put the graphite crucible with mixed powder and C / C sample into the high-temperature graphitization furnace, evacuate to below 0.8kPa, fill in inert gas as protective gas, and raise the temperature to 2200 at a heating rate of 5°C / min. ℃, heat preservation for more than 2 hours, and then naturally cool down to room temperature to obtain a C / C composite material with a SiC coating,...

Embodiment 3

[0041] Set the density to 1.82g / cm 3 The C / C composite material is processed into a pre-coated sample, the surface is polished with sandpaper, put into anhydrous ethanol for ultrasonic cleaning, and cleaned twice, each cleaning time is 15 minutes; after cleaning, put it in a drying oven to dry for later use .

[0042] Si and SiO 2 Mix evenly according to the mass ratio of 1.2:1 to obtain the mixed powder, then put the C / C composite material sample and the above mixed powder into the graphite crucible. When placed, the distance between the C / C composite material sample and the mixed powder is 40mm. Then put the graphite crucible with mixed powder and C / C sample into the high-temperature graphitization furnace, evacuate to below 0.8kPa, fill in an inert gas as a protective gas, and raise the temperature to 2000 at a heating rate of 15°C / min. ℃, heat preservation for more than 2 hours, and then naturally cool down to room temperature to obtain a C / C composite material with a Si...

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Abstract

The invention discloses a C / C composite material superhigh temperature ceramic coating, and a preparation method thereof. The C / C composite material superhigh temperature ceramic coating is composed of an anti-oxidation SiC transition internal layer and a superhigh temperature ablation-resistant ceramic external layer; the superhigh temperature ablation-resistant ceramic external layer is composedof more than one ingredients selected from SiC, ZrC, HfC, TaC, TiC, ZrB2, HfB2, TaB2, and TiB2. The preparation method is suitable for industrialized production, is simple in equipment, is convenientin operation, is capable of controlling coating thickness, satisfying preparation requirements of large size C / C composite material superhigh temperature ceramic coating with complex shapes, and is asuperhigh temperature ceramic coating preparation method with excellent development potential.

Description

technical field [0001] The invention belongs to the technical field of preparation of an ultra-high temperature thermal protection structure, and in particular relates to an ultra-high temperature ceramic coating of a C / C composite material and a preparation method thereof. Background technique [0002] C / C composite materials have become important high-temperature structural materials due to their excellent high-temperature mechanical properties and good thermal shock resistance, and have been widely used in the aerospace field, and their unique properties and application value have been generally recognized. However, carbon materials are easily oxidized in an aerobic environment, and the characteristics of rapid oxidation above 500 °C make their physical and chemical properties deteriorate rapidly, thus restricting their practical application as high-temperature structural materials. [0003] With the development of aerospace technology and the improvement of research and ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B41/89
CPCC04B41/009C04B41/52C04B41/89C04B35/83C04B41/5059C04B41/5057C04B41/4545C04B41/4527C04B41/507
Inventor 杨鑫黄启忠
Owner CENT SOUTH UNIV
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