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Gas turbine blade thermal barrier coating bonding layer and preparation method thereof

A technology for gas turbine blades and thermal barrier coatings, which is applied in coatings, metal material coating processes, pressure inorganic powder coating, etc., and can solve the problem of high porosity of the bonding layer of thermal barrier coatings and insufficient compactness of coatings, etc. problems, to achieve the effects of low cost, improved organization and structure, and high temperature oxidation resistance

Inactive Publication Date: 2015-12-09
ELECTRIC POWER RES INST OF GUANGDONG POWER GRID
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Problems solved by technology

[0003] The existing thermal spraying preparation of thermal barrier coatings has high porosity and insufficient coating density

Method used

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  • Gas turbine blade thermal barrier coating bonding layer and preparation method thereof
  • Gas turbine blade thermal barrier coating bonding layer and preparation method thereof
  • Gas turbine blade thermal barrier coating bonding layer and preparation method thereof

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Embodiment Construction

[0033] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0034] The embodiment of the bonding layer of the thermal barrier coating of the gas turbine blade of the present invention, the bonding layer components are metal powders that meet the composition requirements of the bonding layer prepared by the vacuum atomization technology of the German ALD company, and the components are respectively:

[0035] 31-33% Ni, 31-33% Cr, 7-9% Al, 0.5-0.8% Y, the remainder of Co, and the percentages of the components refer to mass percentages.

[0036] The preferred solution is: Ni32%, Cr32%, Al8%, Y0.5%, Co balance, the percentage of each component refers to the mass percentage, the particle size of the powder material is 10-50 μm, and it is prepared by vacuum air atomization technology.

[0037] It looks like figure 2 As shown, the spherical particles have a uniform particle size distribution, most ...

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Abstract

A gas turbine blade thermal barrier coating bonding layer is composed of powdery Co, Ni, Cr, Al and Y. The optimal range of the powder particle size is 10-50 micrometers. A preparation method comprises the steps that 1, oil removal, washing and drying are performed on the surface of a matrix before spraying is performed, 40-80-mesh corundum is used for sand-blasting roughening, and floating dust is removed to form the rough surface; 2, the powder forming the bonding layer is kept at the temperature of 200-300 DEG C for 4 h before spraying is performed, and the powder is sufficiently softened; 3, a cold spraying method is adopted for preparing the bonding layer on the surface of the matrix; 4, the surface of the bonding layer is sprayed through the plasma technology to obtain an 8YSZ ceramic surface layer; 5, a complete thermal barrier coating is kept at the temperature of 900-1100 DEG C in a vacuum heat treatment furnace for 4 h, and the vacuum degree is lower than 10<-3>Pa. The technology is simple and low in cost; the porosity of the bonding layer is controlled to be smaller than 1%, and the structure is compact; pressure stress exists inside the coating, and the thermal expansion matching in the coating service process can be relieved; the bonding strength of the coating is improved, and the oxidation resistance of the coating is improved.

Description

technical field [0001] The invention relates to a component design of a CoNiCrAlY thermal barrier coating bonding layer of a gas turbine blade. The invention also relates to a method for preparing the bonding layer of the CoNiCrAlY thermal barrier coating of the gas turbine blade. Background technique [0002] The gas turbine blade is an important hot-end part of the gas turbine, and its working temperature determines the thermal efficiency of the gas turbine, so it is subjected to the harshest working environment. How to improve the thermal efficiency of gas turbine blades in severe service environments including corrosion and oxidation is the main direction of gas turbine development. The technology commonly used at present is to prepare thermal barrier coating on the blade surface. A typical thermal barrier coating consists of a partial yttria-stabilized zirconia (YSZ) ceramic surface layer and an MCrAlY bonding layer, and the quality of the bonding layer determines the...

Claims

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Application Information

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IPC IPC(8): C23C24/04C22C30/00C23C4/02
CPCC23C24/04C22C30/00C23C4/02
Inventor 黄丰彭伟平林介东聂铭梁永纯
Owner ELECTRIC POWER RES INST OF GUANGDONG POWER GRID
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