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Method for preparing novel gradient thermal barrier coating

A thermal barrier coating and gradient technology, applied in the chemical field, can solve the problems of complex process links, high operation requirements and poor practicability.

Inactive Publication Date: 2014-07-23
KUSN QIAORUI METAL PRODS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In the current process, the solid embedding infiltration method can realize the gradient infiltration of aluminum, magnesium and other elements to form a high-quality oxide film, but the implementation cost of this process is high, the process links are complicated, the operation requirements are high, and the practicability is not good.

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  • Method for preparing novel gradient thermal barrier coating

Examples

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Effect test

Embodiment 1

[0018] Example 1 The specific implementation steps of the preparation method of the gradient thermal barrier coating mentioned in the present invention are as follows: a) Prepare the spray powder, which includes the bonding layer powder and the ceramic layer powder; wherein, the bonding layer The powder is composed of MCrAlY alloy and an oxide that can form an oxide film. The two components need to be prepared separately; the main components of the MCrAlY alloy are: Co, Cr, Al, S and Ni. The particle size of the MCrAlY alloy after grinding is 250 mesh ; The oxide that can form an oxide film is selected from alumina, and the particle size of alumina after grinding is controlled at 350 mesh; the ceramic layer powder is made of yttria-stabilized zirconia ceramics, and the particle size after grinding is 550 mesh; Treatment, substrate pretreatment includes sandblasting, ultrasonic cleaning, deionized water cleaning and drying treatment; sandblasting uses 150-mesh glass pellets, the...

Embodiment 2

[0019] Example 2 The specific implementation steps of the preparation method of the gradient thermal barrier coating mentioned in the present invention are as follows: a) Prepare the spray powder, which includes the bonding layer powder and the ceramic layer powder; wherein, the bonding layer The powder is composed of MCrAlY alloy and an oxide that can form an oxide film. The two components need to be prepared separately; the main components of the MCrAlY alloy are: Co, Cr, Al, S and Ni. The particle size of the MCrAlY alloy after grinding is 250 mesh ; The oxide that can form an oxide film is selected from magnesium oxide, and the particle size of magnesium oxide after grinding is controlled at 400 mesh; the ceramic layer powder is calcium oxide stabilized zirconia ceramic material, and the particle size after grinding is 600 mesh; b) the base material Pre-treatment, substrate pre-treatment includes sand blasting, ultrasonic cleaning, deionized water cleaning and drying; sand ...

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Abstract

The invention discloses a preparation method of a novel gradient thermal barrier coating. The preparation method comprises the following steps: a) preparing a spray powder, b) pre-treating a base material, c) spraying an adhesive layer, d) spraying a ceramic layer, e) Post-coating treatment. The invention discloses a preparation method of a novel gradient thermal barrier coating. The preparation method has compact process arrangement, reasonable component preparation, and moderate cost. The bonding layer of the coating contains oxides that are easy to form oxide films, and the oxide content The gradient change makes the prepared thermal barrier coating not only have good heat resistance, but also have outstanding oxidation resistance.

Description

technical field [0001] The invention relates to a preparation method of a thermal barrier coating, in particular to a preparation method of a gradient thermal barrier coating with gradient anti-oxidation performance, and belongs to the technical field of metal coatings. Background technique [0002] In recent years, with the development of aero-engines towards high flow ratio, high thrust-to-weight ratio and high turbine inlet temperature, the gas temperature and gas pressure in the engine combustion chamber have been continuously increasing. When the thrust-to-weight ratio of the engine reaches 20, the gas inlet temperature will exceed 2000°C. This temperature has exceeded the temperature that the nickel-based superalloys used to manufacture turbine blades and guide vanes can withstand. Even if intermetallic compound materials and directional solidification technology are used unbearable. The cooling effect of compressed air on the blades is limited, and the cooling techno...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C23C28/00C23C4/12C23C4/06C23C14/34C23C14/08C23C4/073C23C4/134
CPCY02T50/60
Inventor 蒋泽锋
Owner KUSN QIAORUI METAL PRODS
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