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A kind of ceramic protective layer for c/zrc-sic composite material and preparation method thereof

A technology for composite materials and protective layers, which is applied in the field of ceramic protective layers and its preparation, can solve the problems of general high-temperature oxidation resistance, high cost, and easy peeling off of coatings, and achieve high-temperature oxidation resistance. Improve the oxidation resistance temperature, Effect of improving thermal compatibility

Active Publication Date: 2021-05-14
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Claims
  • Application Information

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Problems solved by technology

For example, the Chinese patent application CN200610091392.2 utilizes the spraying method to prepare ZrB 2 - SiC composite coating, but ZrB 2 Easily oxidized to form ZrO 2 , its melting point is low, and the high-temperature oxidation resistance of the coating is general
Chinese patent application CN200610091392.2 prepared TaSi by embedding method combined with CVD method 2 / SiC composite coating, but TaSi 2 The deposition temperature is higher, exceeding 1800°C, the cost is high and the carbon fiber is easily damaged
Chinese patent application CN201911200144.0 has prepared a ceramic protective layer on the C / SiC composite material, which sequentially includes a ZrC-SiC transition layer, a ZrC anti-oxidation coating, and a SiC sealing layer, but the ceramic protective layer can only reach about 2000 ° C. When it is applied to the protection of C / ZrC-SiC composites, it cannot improve the oxidation resistance and temperature resistance of C / ZrC-SiC composites
Chinese patent application CN201911201327.4 prepared HfC-HfB on the surface of C / ZrC-SiC composite material 2 -SiC coating, which improves the service temperature and high temperature oxidation resistance of C / ZrC-SiC composite materials, but the material composition of the coating and the substrate is different, and the thermal expansion coefficient of the coating and the substrate is quite different, resulting in a long-term It is 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 kind of ceramic protective layer for c/zrc-sic composite material and preparation method thereof

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preparation example Construction

[0029] The present invention provides the preparation method of the ceramic protective layer for C / ZrC-SiC composite material described in the first aspect of the present invention in the second aspect, described method comprises the following steps:

[0030] (1) impregnate the C / ZrC-SiC composite material with the Ti-Zr-Hf-Ta-Si integrated ceramic precursor solution, and then perform the steps of solidification and high-temperature cracking sequentially, on the surface of the C / ZrC-SiC composite material Prepared (TiZrHfTa)C x -SiC transition layer; the Ti-Zr-Hf-Ta-Si integrated ceramic precursor solution is prepared by Ti-Zr-Hf-Ta high-entropy ceramic precursor resin, polycarbosilane, allyl phenolic resin and xylene made;

[0031] (2) Coat the Ti-Zr-Hf-Ta high-entropy ceramic precursor solution with the (TiZrHfTa)C obtained in step (1) x - the surface of the SiC transition layer, followed by the steps of solidification and pyrolysis, in the (TiZrHfTa)C x -SiC transition l...

Embodiment 1

[0054] A kind of preparation method for the ceramic protective layer of C / ZrC-SiC composite material, its specific steps are:

[0055] ①(TiZrHfTa)C x -Preparation of SiC transition layer: in parts by weight, add 1 part of Ti-Zr-Hf-Ta high-entropy ceramic precursor resin, 1 part of polycarbosilane, and 3 parts of allyl phenolic resin to 4 parts of xylene , stirred at 90°C for 6 hours to prepare a Ti-Zr-Hf-Ta-Si integrated ceramic precursor solution; put the C / ZrC-SiC composite material in the Ti-Zr-Hf-Ta-Si integrated ceramic In the precursor solution, vacuum impregnated for 5 hours, and then cured at 2 MPa pressure and 300 °C for 10 hours; after impregnation and curing, the C / ZrC-SiC composite material was placed in a high-temperature cracking furnace and pyrolyzed at 1400 °C for 5 hours to obtain With (TiZrHfTa)C x - C / ZrC-SiC composite material with SiC transition layer.

[0056] ②(TiZrHfTa)C x Preparation of anti-oxidation coating: in parts by weight, add 1 part of Ti-Zr-...

Embodiment 2

[0059] A kind of preparation method for the ceramic protective layer of C / ZrC-SiC composite material, its specific steps are:

[0060] ①(TiZrHfTa)C x -Preparation of SiC transition layer: In parts by weight, add 2 parts of Ti-Zr-Hf-Ta high-entropy ceramic precursor resin, 1 part of polycarbosilane, and 3 parts of allyl phenolic resin to 4 parts of xylene , stirred at 90°C for 6 hours to prepare a Ti-Zr-Hf-Ta-Si integrated ceramic precursor solution; put the C / ZrC-SiC composite material in the Ti-Zr-Hf-Ta-Si integrated ceramic In the precursor solution, vacuum impregnated for 5 hours, and then cured at 2 MPa pressure and 300 °C for 10 hours; after impregnation and curing, the C / ZrC-SiC composite material was placed in a high-temperature cracking furnace and pyrolyzed at 1400 °C for 5 hours to obtain With (TiZrHfTa)C x - C / ZrC-SiC composite material with SiC transition layer.

[0061] ②(TiZrHfTa)C x Preparation of anti-oxidation coating: in parts by weight, add 1 part of Ti-...

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Abstract

The invention relates to a ceramic protection layer for C / ZrC-SiC composite material and a preparation method thereof. The ceramic protective layer comprises (TiZrHfTa)C formed sequentially on the C / ZrC-SiC composite material. x ‑SiC transition layer, (TiZrHfTa)C x Anti-oxidation coating and SiC sealing layer. The method is: preparing (TiZrHfTa)C by PIP process x ‑SiC transition layer; (TiZrHfTa)C prepared on the basis of said transition layer by brushing process x An anti-oxidation coating; a SiC sealing layer is prepared on the basis of the anti-oxidation coating by a chemical vapor deposition process to obtain a ceramic protective layer. The ceramic protective layer prepared by the invention can have excellent oxidation resistance at a temperature above 2500° C., and also has a high bonding force with the substrate, and has broad application prospects on structural parts such as terminals and engines of new 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 ceramic protective layer for C / ZrC-SiC composite materials and a preparation method thereof. Background technique [0002] Carbon fiber toughened zirconium carbide-silicon carbide ceramic matrix composite (C / ZrC-SiC composite) is a high-performance thermal structural material. 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. has been applied. However, long-term studies have shown that ZrC and SiC in the matrix will be oxidized to ZrO in a long-term oxidation environment. 2 , SiO 2 , when the use temperature is lower than 2200℃, ZrO 2 with SiO 2 form a viscous glassy substance that can prevent O 2 Penetration, play a better antioxidant effect. However...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B41/89
CPCC04B41/009C04B41/52C04B41/89C04B41/5059C04B41/5057C04B41/4539C04B41/0072C04B41/4529C04B35/806
Inventor 裴雨辰刘伟杨良伟张宝鹏于艺刘俊鹏孙同臣王涛
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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