Thermal barrier coating layer resisting CMAS erosion and preparation method

A technology of thermal barrier coating and bonding layer, which is applied in the direction of coating, metal material coating process, liquid chemical plating, etc., can solve problems such as failure and CMAS corrosion, and achieve compact structure, high interface matching degree, phase good stability effect

Active Publication Date: 2020-10-30
JIANGSU UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In order to effectively solve the problems of CMAS corrosion of thermal barrier coatings in service and lead to their failure, the present invention provides a new type of thermal barrier coating resistant to CMAS erosion The layer and the preparation method can effectively improve the anti-CMAS corrosion performance of the thermal barrier coating and improve the stability of the thermal barrier coating

Method used

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  • Thermal barrier coating layer resisting CMAS erosion and preparation method
  • Thermal barrier coating layer resisting CMAS erosion and preparation method
  • Thermal barrier coating layer resisting CMAS erosion and preparation method

Examples

Experimental program
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Effect test

Embodiment 1

[0036] (1) Grinding with 100-mesh, 500-mesh, and 1000-mesh sandpaper on the surface of 5 samples of superalloy GH4586 to remove surface scratches, and then polishing to the mirror surface with diamond polishing agent, followed by surface sandblasting to form roughness on the surface degree, and the CoCrAlYTaSi bonding layer was prepared by plasma spraying method, and the spraying process was optimized at the same time (power 40kW, main gas flow rate 50L / min, auxiliary gas flow rate 25L / min, powder feeding rate 2r / min, carrier gas flow rate 7L / min, The spraying distance is 80μm), the spraying time is 30s, and the thickness is controlled to be 80μm. Then, the prepared adhesive layer is subjected to vacuum diffusion heat treatment (900°C) and surface sandblasting to improve the surface roughness.

[0037] (2) Spray Gd on the surface of the sample prepared with the bonding layer by plasma spraying 2 Zr 2 o 7 Ceramic layer, and by optimizing the spraying process parameters (powe...

Embodiment 2

[0042] (1) Grinding with 100-mesh, 500-mesh, and 1000-mesh sandpaper on the surface of 5 samples of superalloy GH4586 to remove surface scratches, and then polishing to the mirror surface with diamond polishing agent, followed by surface sandblasting to form roughness on the surface degree, and the CoCrAlYTaSi bonding layer was prepared by plasma spraying method, and the spraying process was optimized at the same time (power 40kW, main gas flow rate 50L / min, auxiliary gas flow rate 25L / min, powder feeding rate 2r / min, carrier gas flow rate 7L / min, The spraying distance is 80μm), the spraying time is 30s, and the thickness is controlled to be 80μm. Then, the prepared adhesive layer is subjected to vacuum diffusion heat treatment (900°C) and surface sandblasting to improve the surface roughness.

[0043] (2) adopt plasma spraying method to spray (La 0.5 Gd 0.5 ) 2 Zr 2 o 7 Ceramic layer, and by optimizing the spraying process parameters (power 60kW, main gas flow 60L / min, au...

Embodiment 3

[0048] (1) Grinding with 100-mesh, 500-mesh, and 1000-mesh sandpaper on the surface of 5 samples of superalloy GH4586 to remove surface scratches, and then polishing to the mirror surface with diamond polishing agent, followed by surface sandblasting to form roughness on the surface degree, and the CoCrAlYTaSi bonding layer was prepared by plasma spraying method, and the spraying process was optimized at the same time (power 40kW, main gas flow rate 50L / min, auxiliary gas flow rate 25L / min, powder feeding rate 2r / min, carrier gas flow rate 7L / min, The spraying distance is 80μm), the spraying time is 30s, and the thickness is controlled to be 80μm. Then, the prepared adhesive layer is subjected to vacuum diffusion heat treatment (900°C) and surface sandblasting to improve the surface roughness.

[0049] (2) Spray (Gd) on the prepared bonding layer surface by plasma spraying 0.7 Yb 0.3 ) 2 Zr 2 o 7 Ceramic layer, and by optimizing the spraying process parameters (power 60kW,...

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Abstract

The invention relates to the technical field of surface corrosion and protection of thermal barrier coating layers, specifically to a thermal barrier coating layer resisting CMAS erosion and a preparation method. In the technical solution of the invention, prefabricated CMAS suspension is uniformly coated on the surface of a thermal barrier coating layer; and then, the coating layer is sintered for a period of time in a high-temperature furnace to form a compact apatite phase barrier layer on the surface. The layer has the features of high melting point, high compactness, excellent phase stability and high bonding force, not only can fill inevitable holes and cracks in the surface spraying process of ceramic layers, but also can block CMAS diffusion channels in the ceramic layers, effectively improves the CMAS erosion resistance of the thermal barrier coating layer.

Description

technical field [0001] The invention relates to the technical field of thermal barrier coating surface corrosion and protection, in particular to a CMAS corrosion-resistant thermal barrier coating and a preparation method thereof. Background technique [0002] The turbine engine is the core component of aircraft and other aviation equipment. With the continuous improvement of its thrust-to-weight ratio, its operating temperature can reach up to 1650 ° C, while the common single crystal superalloy blade can only withstand a maximum temperature of 1150 ° C. Generally, thermal barrier coating TBCs (Thermal Barrier Coating) technology and air cooling technology are used to reduce the surface temperature of the blade to ensure the long-term operation of the engine at a temperature higher than the melting point of the blade alloy. However, with the increasingly harsh service environment, one of the main components is CaO, MgO, Al 2 o 3 and SiO 2 (CMAS) Silicate corrosion produc...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C4/134C23C4/067C23C4/11C23C18/12
CPCC23C4/134C23C4/067C23C4/11C23C18/1208Y02T50/60
Inventor 花银群帅文文钱伟戴峰泽叶云霞陈瑞芳
Owner JIANGSU UNIV
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