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A kind of anti-oxidation coating and preparation method thereof

An anti-oxidation coating and preparation technology, which is applied in the coating, metal material coating process, fusion spraying, etc., can solve the problems of weak water vapor corrosion resistance of the coating, complicated preparation technology, etc., and achieve excellent anti-oxidation performance , Good physical and chemical compatibility, solve the complicated effect of preparation technology

Active Publication Date: 2019-04-30
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to overcome the above-mentioned defects of the prior art, and to provide an anti-oxidation coating, which is prepared by a single plasma spraying process. Solved the technical problems of the complicated preparation technology of traditional coatings for carbon fiber reinforced ceramic matrix composites and the weak water vapor corrosion resistance of the prepared coatings

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  • A kind of anti-oxidation coating and preparation method thereof
  • A kind of anti-oxidation coating and preparation method thereof
  • A kind of anti-oxidation coating and preparation method thereof

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preparation example Construction

[0031] The preparation method of anti-oxidation coating of the present invention specifically comprises the following steps:

[0032] (1) Clean and degrease the carbon fiber reinforced ceramic matrix composite material matrix, and perform sandblasting to make the surface rough;

[0033] (2) Preheat the substrate, and control the substrate temperature between 100 and 200°C;

[0034] (3) On the pretreated substrate, the plasma spraying method is used to prepare an adhesive layer and a ceramic layer in sequence, wherein the adhesive layer material is W and the ceramic layer material is Yb 2 SiO 4 ;

[0035] Among them, the preparation process parameters of the adhesive layer material W after process optimization are: the main gas N 2 The flow rate is 65~85L / min, auxiliary gas H 2 The flow rate is 5-10L / min, the working voltage is 78-85V, the current is 450-520A, and the powder carrier gas is N 2 The air flow rate is 4-6L / min, the powder delivery rate is 30-50g / min, the spray...

Embodiment 1

[0039] The matrix is ​​made of C / C composite material, and the sample size is 200×100×10mm 3 . Firstly, the C / C composite matrix is ​​subjected to pre-spraying treatment, and the specific preparation method is as follows:

[0040] (1) Clean and degrease the C / C composite material, and perform sandblasting;

[0041] (2) Purify the surface of the sandblasted substrate in a high-pressure dry gas to remove sand grains retained on the surface;

[0042] (3) Preheat the substrate, and control the temperature of the substrate between 100 and 200°C;

[0043] (4) On the treated C / C composite material substrate, the plasma spraying method is used to prepare W bonding layer and Yb by sequential spraying 2 SiO 4 Ceramic layer, when spraying W, the main gas N 2 Flow rate is 75L / min, auxiliary gas H 2 The flow rate is 10L / min, the working voltage is 82V, the current is 510A, and the powder carrier gas is N 2 The air flow rate is 4L / min, the powder feeding rate is 30g / min, the spraying d...

Embodiment 2

[0049] The matrix is ​​made of C / SiC composite material, and the sample size is 200×100×10mm 3 . Firstly, the C / SiC composite material matrix is ​​sprayed before treatment, and the specific technical scheme is as follows:

[0050] (1) Clean and degrease the C / SiC composite material, and perform sandblasting;

[0051] (2) Purify the surface of the sandblasted substrate in a high-pressure dry gas to remove sand grains retained on the surface;

[0052] (3) Preheat the substrate, and control the temperature of the substrate between 100 and 200°C;

[0053] (4) On the treated C / SiC composite substrate by plasma spraying method, W bonding layer and Yb were prepared by spraying sequentially. 2 SiO 4 Ceramic layer, when spraying W, the main gas N 2 Flow rate is 77L / min, auxiliary gas H 2 The flow rate is 10L / min, the working voltage is 80V, the current is 505A, and the powder carrier gas is N 2 The air flow rate is 4L / min, the powder feeding rate is 32g / min, the spraying distanc...

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Abstract

The invention relates to anti-oxidation coating and a preparation method thereof.The anti-oxidation coating comprises an adhering layer and a ceramic layer which are sequentially prepared on a base, wherein the adhering layer is made of W, the ceramic layer is made of Yb2SiO4, the adhering layer is 0.05-0.15mm in thickness, and the ceramic layer is 0.15-0.3mm in thickness.The preparation method includes the steps of firstly, preheating the base, and controlling the temperature of the base to be 100-200 DEG C; secondly, using a plasma spraying method to sequentially prepare the adhering layer and the ceramic layer on the preheated base.The anti-oxidation coating and the preparation method thereof have the advantages that the coating is prepared by the single plasma spraying process; the preparation method is simple in process, low in cost and high in efficiency; the technical difficulties that traditional coating preparation technologies of carbon-fiber-reinforced ceramic-based composite materials are complex and the prepared coating is weak in steam corrosion resistance.

Description

technical field [0001] The invention relates to an anti-oxidation coating and a preparation method thereof, in particular to a W / Yb 2 SiO 4 The invention relates to an anti-oxidation coating and a preparation method thereof. The coating has properties of anti-oxidation, ablation resistance and water vapor corrosion resistance, and belongs to the coating field of carbon materials. Background technique [0002] Structural components such as rocket engine nozzles and hypersonic aircraft wing leading edges will be subjected to high temperature and high-speed airflow erosion and ablation during service, which will eventually lead to rapid loss of structural materials, or even failure and damage, affecting flight reliability. A series of carbon fiber reinforced ceramic matrix composites such as C / C and C / SiC are the most promising materials currently used in these structural parts due to their high melting point, high specific strength, low thermal expansion coefficient and excel...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C23C4/134C23C4/11C23C4/08
CPCC23C4/08
Inventor 文波卢鹉杨杰倪立勇杨震晓马康智吴朝军
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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