Method for preparing ceramic protection layer on C/SiC composite material, and ceramic protection layer prepared therethrough

A technology for composite materials and protective layers, which is applied in the field of ceramic protective layers, can solve the problems of reduced mechanical properties of composite materials, large differences in thermal expansion coefficients, and large differences in thermophysical properties, etc. binding effect

Active Publication Date: 2020-02-25
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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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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  • Method for preparing ceramic protection layer on C/SiC composite material, and ceramic protection layer prepared therethrough

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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 protection layer on a C/SiC composite material, and the ceramic protection layer prepared therethrough. The method comprises the following steps: preparing a ZrC-SiC transition layer on the surface of the C/SiC composite material through an impregnation-solidification-high temperature cracking process by using an impregnation solution beinga zirconium-silicon integrated ceramic precursor solution containing zirconium and silicon according to a weight ratio of (1-8):1; preparing a ZrC anti-oxidation coating layer on the basis of the ZrC-SiC transition layer through a brush coating process; and depositing a SiC hole sealing layer on the surface of the obtained ZrC antioxidant coating through a chemical vapor deposition technology toprepare the ceramic protection layer on the C/SiC composite material. The prepared ceramic protection layer has excellent oxidation resistance at a temperature of 2000 DEG C or above, has high bindingforce with a substrate, and has wide application prospects in structural parts such as a wing rudder, a leading edge, an end and an engine of a novel hypersonic aircraft.

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 Applications(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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