C/SiC composite material, oxidation resistant coating for C/SiC composite material and preparation method thereof

An anti-oxidation coating and composite material technology, applied in the field of composite materials, can solve the problems of general high-temperature anti-oxidation effect of the coating, low bonding strength between the coating and the substrate, and high cost, and achieve easy industrial implementation, excellent anti-oxidation performance, The effect of enhancing antioxidant properties

Active Publication Date: 2018-12-07
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Patent CN 201310545292.2 Preparation of carbon / carbon composite material HfB by suspension electrolysis 2 anti-oxidation outer coating, but the HfB prepared by this method 2 The bonding strength between the coating and the substrate is low, and it is not suitable for large-scale preparation of components
Patent CN200610091392.2 prepared ZrB by spraying method 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
Patent 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

Method used

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  • C/SiC composite material, oxidation resistant coating for C/SiC composite material and preparation method thereof
  • C/SiC composite material, oxidation resistant coating for C/SiC composite material and preparation method thereof
  • C/SiC composite material, oxidation resistant coating for C/SiC composite material and preparation method thereof

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Embodiment

[0038] Specific embodiments of the present invention will be described in detail below. In the following description, for the purpose of explanation and not limitation, specific details are set forth to help a more comprehensive understanding of the present invention. However, it should be understood by those skilled in the art that the present invention may also be practiced in other embodiments that do not include these specific details. It should be noted here that the claimed scope of the present invention is not limited to the following embodiments.

Embodiment 1

[0042] In this embodiment, an anti-oxidation coating for C / SiC composite material is prepared, and the specific process is as follows:

[0043] (1) Mechanically stir 1kg of the hafnium coordination blend resin prepared in the preparation example, 5kg of pyridineborane and 6kg of xylene for 5 hours, and then stand for 10 hours to prepare HfB 2 Ceramic precursor solution (viscosity 124.2mPa.s, solid content 45.3% by mass), and then brush the precursor solution onto the surface of a uniform and dense C / SiC composite matrix;

[0044] (2) Put the composite material in (1) in a curing tank, pressurize it to 2MPa, heat up to 200°C for 3 hours, and 350°C for 3 hours to make HfB 2 The ceramic precursor is fully cross-linked and solidified, and then placed in a cracking furnace under an argon atmosphere and cracked at 1500°C for 4 hours;

[0045] (3) Place the composite material in (2) in a deposition furnace, and pass in trichloromethylsilane under the conditions of 4KPa absolute pressure and ...

Embodiment 2

[0049] In this embodiment, another anti-oxidation coating of C / SiC composite material is prepared, and the specific process is as follows:

[0050] (1) Mechanically stir 1kg of the hafnium coordination blend resin prepared in the preparation example, 10kg of pyridineborane and 6kg of xylene for 5 hours, and after standing for 10 hours, prepare HfB 2 Ceramic precursor solution, and then brush the precursor solution onto the surface of the uniform and dense C / SiC composite matrix;

[0051] (2) Put the composite material in (1) in a curing tank, pressurize it to 2MPa, heat up to 200°C for 3 hours, and 350°C for 3 hours to make HfB 2 The ceramic precursor is fully cross-linked and solidified, and then placed in a cracking furnace under an argon atmosphere and cracked at 1500°C for 4 hours;

[0052] (3) Place the composite material in (2) in a deposition furnace, and pass in trichloromethylsilane under the conditions of 4KPa absolute pressure and 1000°C for a deposition time of 10 hours;

...

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Abstract

The invention relates to a C/SiC composite material, an oxidation resistant coating for the C/SiC composite material and a preparation method thereof. The oxidation resistant coating is used for alternatively forming an HfB2 coating and a SiC coating on a C/SiC composite base material. The preparation method comprises the following steps: coating a layer of HfB2 ceramic precursor solution on the surface of the C/SiC composite base material; forming the HfB2 coating after splitting decomposition; depositing the SiC coating, thereby acquiring an HfB2-SiC compound coating. The invention relates to the C/SiC composite material prepared according to the preparation method. The preparation method is simple in process, low in preparation cost, capable of solving the problems of uniform distribution of HfB2 and SiC and combination with a substrate and promoting the ablation resistance and oxidation resistance of the C/SiC composite material.

Description

Technical field [0001] The invention relates to an anti-oxidation coating for C / SiC composite materials and a preparation method thereof, and belongs to the field of composite materials. Background technique [0002] Carbon fiber toughened silicon carbide ceramic matrix composite material (ie C / SiC composite material) is a high-performance thermal structure material. It overcomes the fatal weakness of the brittleness of single-phase ceramic materials. It 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 in the wing of hypersonic aircraft. Used on the rudder. The SiC in the matrix will be oxidized to SiO under a long-term oxidation environment 2 , When the use temperature is lower than 1600℃, SiO 2 It is glassy and can prevent O 2 The penetration of the product has a better antioxidant effect. However, whe...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B41/87C04B41/52
CPCC04B41/52C04B41/87C04B41/507C04B41/4535C04B41/0072C04B41/5059C04B41/4531
Inventor 刘伟金鑫于艺宋环君刘俊鹏孙同臣于新民裴雨辰
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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