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A method for preparing a ceramic protective layer on a c/sic composite material and the ceramic protective layer prepared thereby

A technology for composite materials and protective layers, applied in the field of ceramic protective layers, can solve the problems of composite materials such as the decline in mechanical properties, large differences in thermal expansion coefficients, loss of coating protection, etc., to enhance oxidation resistance, enhance bonding, and improve The effect of high temperature oxidation resistance

Active Publication Date: 2021-10-22
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, when both ZrC and SiC are contained in the matrix, the mechanical properties of the composite material decrease due to the large difference in thermophysical properties of SiC and ZrC.
In addition, by preparing a coating containing zirconium carbide on the surface of the C / SiC composite material, the temperature resistance level of the C / SiC composite material can also be enhanced. 2 -ZrC coating, however, the thermal expansion coefficient of this coating is quite different from that of the substrate, which makes it easy to fall off at high temperature and loses the protective effect of the coating on the substrate

Method used

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  • A method for preparing a ceramic protective layer on a c/sic composite material and the ceramic protective layer prepared thereby

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preparation example Construction

[0045] S2. Preparation of ZrC anti-oxidation coating: use zirconium precursor as solute, phenolic resin as carbon source, and xylene as solvent to prepare zirconium precursor resin solution; uniformly coat zirconium precursor resin solution in step S1 The surface of the C / SiC composite material with SiC and ZrC transition layers, after curing is completed, placed in a high temperature cracking furnace for high temperature cracking to obtain a ZrC oxidation resistant coating, specifically including the following steps:

[0046] S21. In parts by weight, add 1 part of zirconium precursor and 1.5-2.5 parts of aminophenol aldehyde into 2.5-3.5 parts of xylene, stir at room temperature for 5-10 hours, and prepare a zirconium precursor resin solution;

[0047] S22. Uniformly coat the zirconium precursor resin solution on the surface of the C / SiC composite material with SiC and ZrC transition layers in step S1, and then place the C / SiC composite material in a curing tank, under 1-3MPa ...

Embodiment 1

[0054] A preparation method of a C / SiC composite gradient ceramic protective layer, the specific steps of which are:

[0055] ①Preparation of SiC and ZrC ceramic transition layer: by weight, add 1 part of zirconium precursor (polycarbozirane), 1 part of polycarbosilane, 2 parts of aminophenol aldehyde to 3 parts of xylene, at 80 ° C Stir under high temperature for 10 hours to prepare a zirconium-silicon integrated ceramic precursor solution; place the C / SiC composite material in the zirconium-silicon integrated ceramic precursor solution, vacuum impregnate for 10 hours, and then cure at 250°C and 0.5MPa pressure for 5 hours; After impregnation and curing, the C / SiC composite material was placed in a high-temperature pyrolysis furnace and pyrolyzed at 1400 °C for 2 hours to obtain a C / SiC composite material with SiC and ZrC ceramic transition layers.

[0056]②Preparation of ZrC anti-oxidation coating: In parts by weight, 1 part of zirconium precursor (polycarbozircone) and 1.5 ...

Embodiment 2

[0060] A preparation method of a C / SiC composite gradient ceramic protective layer, the specific steps of which are:

[0061] ① Preparation of SiC and ZrC ceramic transition layers: by weight, 4 parts of zirconium precursor (polycarbozirane), 1 part of polycarbosilane, and 5 parts of aminophenol aldehyde were added to 9 parts of xylene, at a temperature of 80 ° C Stir under high temperature for 10 hours to prepare a zirconium-silicon integrated ceramic precursor solution; place the C / SiC composite material in the zirconium-silicon integrated ceramic precursor solution, vacuum impregnate for 10 hours, and then cure at 250°C and 0.5MPa pressure for 5 hours; After impregnation and curing, the C / SiC composite material was placed in a high-temperature pyrolysis furnace and pyrolyzed at 1400 °C for 2 hours to obtain a C / SiC composite material with SiC and ZrC ceramic transition layers.

[0062] ②Preparation of ZrC anti-oxidation coating: In parts by weight, 1 part of zirconium precu...

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Abstract

The invention relates to a method for preparing a ceramic protective layer on a C / SiC composite material and the prepared ceramic protective layer. The method is as follows: a ZrC-SiC transition layer is prepared on the surface of the C / SiC composite material through an impregnation-curing-pyrolysis process, and the impregnating solution is zirconium-silicon containing zirconium and silicon with a weight ratio of (1-8):1 An integrated ceramic precursor solution; a ZrC oxidation-resistant coating is obtained on the basis of the ZrC-SiC transition layer by a brushing process; a SiC sealing layer is deposited on the surface of the ZrC oxidation-resistant coating obtained by chemical vapor deposition , thus making a ceramic protective layer on the C / SiC composite. The ceramic protective layer prepared by the present invention can have excellent oxidation resistance at a temperature above 2000°C, and also has a high bonding force with the substrate. with broadly application foreground.

Description

technical field [0001] The invention belongs to the technical field of coating preparation of composite materials, and in particular relates to a method for preparing a ceramic protective layer on a C / SiC composite material and the prepared ceramic protective layer. Background technique [0002] Carbon fiber toughened silicon carbide ceramic matrix composites (C / SiC composites) are high-performance thermal structural materials. It overcomes the Achilles' heel of brittleness of single-phase ceramic materials, and has excellent characteristics such as low density, high temperature resistance, high strength, oxidation resistance and ablation resistance. It can be used as aerospace structural materials, brake materials, and has been used on aircraft rudders got applied. However, long-term studies have shown that the long-term anti-oxidation service temperature of traditional C / SiC composites does not exceed 1650 °C. When the Mach number of the aircraft is high, its high-temper...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B41/89C04B35/565C04B35/80
CPCC04B41/009C04B41/52C04B41/89C04B35/565C04B35/806C04B41/5059C04B41/5057C04B41/4535C04B41/455C04B41/4531
Inventor 裴雨辰刘伟于艺宋环君金鑫刘俊鹏孙同臣
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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