Method for preparing novel gradient thermal barrier coating

A thermal barrier coating and gradient technology, which is applied in the preparation of thermal barrier coatings and the preparation of new gradient thermal barrier coatings, can solve the problems of high operation requirements, high implementation costs, complex process links, etc., and achieve compact process arrangement , Moderate cost and reasonable composition

Inactive Publication Date: 2012-11-14
KUSN QIAORUI METAL PRODS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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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 ox

Method used

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  • Method for preparing novel gradient thermal barrier coating

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Embodiment 1

[0018] The specific implementation steps of the preparation method of the novel gradient thermal barrier coating mentioned in the present invention are as follows:

[0019] a) Preparation of spray powder, which includes adhesive layer powder and ceramic layer powder; wherein, the adhesive layer powder is composed of MCrAlY alloy and oxide that can form an oxide film, and the two components need to be prepared separately The main components of MCrAlY alloy are: Co, Cr, Al, S and Ni, the particle size of MCrAlY alloy after grinding is 250 mesh; the oxide that can form an oxide film is selected from alumina, and the particle size of aluminum oxide after grinding is controlled at 350 mesh Mesh; The ceramic layer powder is selected from yttria-stabilized zirconia ceramics, and the particle size after grinding is 550 mesh;

[0020] b) Substrate pretreatment, which includes sandblasting, ultrasonic washing, deionized water cleaning and drying treatment; 150-mesh glass pellets are use...

Embodiment 2

[0025] The specific implementation steps of the preparation method of the novel gradient thermal barrier coating mentioned in the present invention are as follows:

[0026] a) Preparation of spray powder, which includes adhesive layer powder and ceramic layer powder; wherein, the adhesive layer powder is composed of MCrAlY alloy and oxide that can form an oxide film, and the two components need to be prepared separately The main components of MCrAlY alloy are: Co, Cr, Al, S and Ni, the particle size of MCrAlY alloy after grinding is 250 mesh; the oxide that can form an oxide film is magnesium oxide, and the particle size of magnesium oxide after grinding is controlled at 400 mesh mesh; the ceramic layer powder is calcium oxide stabilized zirconia ceramic material, and the particle size after grinding is 600 mesh;

[0027] b) Substrate pretreatment, which includes sandblasting, ultrasonic washing, deionized water cleaning and drying treatment; 150 mesh glass pellets are selecte...

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Abstract

The invention discloses a method for preparing a novel gradient thermal barrier coating, which comprises the following steps: a) preparing spraying powder material; b) pre-treating base material; c) spraying a bonding layer; d) spraying a ceramic layer; and e) post-treating the coating. The method for preparing the novel gradient thermal barrier coating is disclosed by the invention; the method is characterized by compact working procedure arrangement, reasonable component preparation and suitable coat; the bonding layer of the coating contains oxide which easily forms an oxide film; the content of the oxide is changed in a gradient manner; thus, the prepared thermal barrier coating has good heat-resistant performance while anti-oxidation capacity is highlighted.

Description

technical field [0001] The invention relates to a preparation method of a thermal barrier coating, in particular to a preparation method of a novel gradient thermal barrier coating with gradient anti-oxidation properties, and belongs to the technical field of metal coatings. Background technique [0002] In recent years, with the development of aero-engines in the direction of high flow ratio, high thrust-to-weight ratio and high turbine inlet temperature, the gas temperature and gas pressure in the engine combustion chamber continue to increase. When the thrust-to-weight ratio of the engine reaches 20, the gas inlet temperature will exceed 2000°C, which is beyond the temperature that the nickel-based superalloy used to manufacture turbine blades and guide vanes can withstand. unbearable. The cooling effect of compressed air on the blades is limited, and the cooling technology inevitably loses a large part of the heat while reducing the temperature of the blades, reducing t...

Claims

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Application Information

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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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