Preparation method of high-entropy ceramic composite coating

A ceramic composite and coating technology, applied in the coating, metal material coating process, fusion spraying, etc., can solve the problems of less research on the preparation of high-entropy ceramic coatings, poor coating performance, low deposition efficiency, etc., to achieve The effect of tight interphase bonding, high cohesive strength of the coating, and simple preparation process

Active Publication Date: 2020-06-09
HEBEI UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The purpose of the present invention is to provide a method for preparing a high-entropy ceramic composite coating material for the defects that there are few studies on the preparation of high-entropy ceramic coatings and insufficient existing technologies
The present invention overcomes the defects of complex process, high cost, heavy pollution, low deposition efficiency, low coating thickness, poor coating performance and unsuitable application in large-scale industrial production in the prior art for preparing high-entropy ceramic composite coatings
Simultaneously, the present invention also overcomes the shortcoming that high-entropy ceramic composite powder needs to be prepared first in the process of preparing high-entropy ceramic composite coating in the prior art

Method used

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0037] The first step is to prepare the multi-element metal element / silicon carbide composite powder for thermal spraying: the multi-element metal element powder with a particle size range of 0.001 micron to 10 microns and the silicon carbide powder with a particle size range of 0.001 micron to 10 microns Uniformly mixed into a composite powder, in which, the mass ratio of Zr, Ti, Nb, Cr and V to the total mass of the multi-element metal powder is 27:16:28:14:15, and the difference between the multi-element metal powder and silicon carbide powder The mass ratio is 88:22; then evenly mixed into the binder, the amount of the binder is, the weight ratio is the above-mentioned composite powder: binder=100:0.1, thus being prepared as a multi-element metal element for thermal spraying / Silicon carbide composite powder.

[0038] The second step, the surface pretreatment of the base material:

[0039] The base material is 1Cr18Ni9Ti steel, and the pretreatment method is sandblasting...

Embodiment 2

[0045] The first step is to prepare the multi-element metal element / silicon carbide composite powder for thermal spraying: the multi-element metal element powder with a particle size range of 0.001 micron to 10 microns and the silicon carbide powder with a particle size range of 0.001 micron to 10 microns Uniformly mixed into a composite powder, wherein the mass ratio of the metal elemental powder Zr, Hf, Ti, Nb and Ta to the total mass of the multi-element metal element powder is 20:20:20:20:20, the difference between the multi-element metal element powder and the silicon carbide powder The mass ratio is 70:30; then evenly mixed into the binder, the amount of the binder is, the weight ratio is the above-mentioned composite powder: binder=100:0.1, thus being prepared as a multi-element metal element for thermal spraying / Silicon carbide composite powder;

[0046] The second step, the surface pretreatment of the base material:

[0047] The base material is titanium-aluminum in...

Embodiment 3

[0055] Other steps are the same as in Example 1, the difference is that the metal elemental powder is Zr, Hf, Ti, Mo and W, and the mass ratio of the multi-element metal elemental powder is 35:5:20:20:20, and the multi-element metal elemental powder and The mass ratio between the silicon carbide powders is 50:50; the coating performance obtained is close to that of Example 1.

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Abstract

The invention provides a preparation method of a high-entropy ceramic composite coating. The preparation method of the high-entropy ceramic composite coating comprises the following steps that step one, metal simple-substance powder, silicon carbide powder and a binder are prepared into metal simple-substance/silicon carbide composite powder, and the metal simple-substance powder is any five or more than five of zirconium, titanium, hafnium, tantalum, niobium, vanadium, chromium, molybdenum, tungsten, manganese or cobalt; step two, the surfaces of base materials needing coating are pretreated;and step three, a method of thermal spraying is adopted to spray the metal simple-substance/silicon carbide composite powder on the surfaces of the base materials, so that the high-entropy ceramic composite coating is synthesized through an in-situ reaction. The obtained coating has excellent performance, and the disadvantage that high-entropy ceramic composite powder is required to be prepared in the process of preparing the high-entropy ceramic composite coating in the prior art is further overcome.

Description

technical field [0001] The technical solution of the invention relates to the plating of materials by high-entropy ceramics, in particular to the preparation method of high-entropy ceramic composite coatings. Background technique [0002] Refractory carbides of transition metals (zirconium, titanium, hafnium, tantalum, niobium, vanadium, chromium, molybdenum, tungsten), with high melting point, good thermal stability, excellent thermal shock resistance, good oxidation and ablation resistance And many other excellent properties, it has become one of the most promising candidate materials for the preparation of new high-temperature material structural parts in the aerospace field, and has important application value in the fields of machinery, metallurgy, aerospace, nuclear and military. However, the high brittleness, poor thermal shock resistance and high temperature oxidation resistance of carbide ceramic coatings limit its further application to some extent. Studies have f...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C4/06C23C4/131C23C4/073C23C4/08
CPCC23C4/06C23C4/131C23C4/073C23C4/08
Inventor 杨勇王星宇王晓龙孙文韦马玉夺崔宇航
Owner HEBEI UNIV OF TECH
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