Anti-CMAS protective layer for TBCs or EBCs, preparation method of anti-CMAS protective layer and protective structure obtained by anti-CMAS protective layer

A protective structure and protective layer technology, applied in coating, metal material coating process, ion implantation plating, etc., can solve problems such as corrosion degradation, reduce the cost of preparation and processing, and achieve good thermal mechanical and chemical compatibility , Improve the effect of ultra-high temperature service stability and thermal cycle life

Pending Publication Date: 2021-12-31
JINAN UNIVERSITY +2
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to solve the problems such as the corrosion degradation of TBCs or EBCs under the action of CMAS in the above-mentioned prior art, the present invention provides a kind of anti-CMAS protective layer for TBCs or EBCs and preparation method thereof and the protective structure obtained therefrom

Method used

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  • Anti-CMAS protective layer for TBCs or EBCs, preparation method of anti-CMAS protective layer and protective structure obtained by anti-CMAS protective layer
  • Anti-CMAS protective layer for TBCs or EBCs, preparation method of anti-CMAS protective layer and protective structure obtained by anti-CMAS protective layer
  • Anti-CMAS protective layer for TBCs or EBCs, preparation method of anti-CMAS protective layer and protective structure obtained by anti-CMAS protective layer

Examples

Experimental program
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Effect test

Embodiment 1

[0034] Using directionally solidified nickel-based superalloy DZ125 as the substrate, it is processed by wire cutting and grinding and polishing. Use 60-mesh corundum to sandblast the surface of the sample under compressed air, and then use acetone and absolute alcohol to perform ultrasonic cleaning in sequence to remove stains or adhered fine corundum grains on the surface of the sample and fully dry it. The NiCoCrAlYHf bonding layer was prepared on the surface of the DZ125 superalloy substrate by supersonic flame spraying or low-pressure plasma spraying, with a thickness of 120 μm. Subsequently, a layer of 150 μm thick YSZ ceramic thermal barrier layer was prepared on the adhesive layer by atmospheric plasma spraying, and then a 150 μm thick new high-temperature thermal barrier ceramic layer (chemical composition LaMgAl was prepared on the surface of the YSZ layer. 11 o 19 、Gd 2 Zr 2 o 7 , (Gd 0.9 Yb 0.1 ) 2 Zr 2 o 7 , La 2 (Ce 0.3 Zr 0.7 ) 2 o 7 、YSZ+xGd 2 o...

Embodiment 2

[0037] Based on the third generation nickel-based single crystal superalloy DD10, it is processed by wire cutting and grinding and polishing. Use sandpaper to polish the surface of the sample with a roughness of Ra≤1μm, and then use acetone and absolute alcohol to perform ultrasonic cleaning in order to remove stains on the experimental surface or fine corundum particles adhering to the surface and fully dry. The NiCoCrAlYTa bonding layer was prepared on the DD10 superalloy substrate by PS-PVD method, with a thickness of 100 μm. Then, a layer of columnar crystal YSZ ceramic thermal barrier layer with a thickness of 300 μm was prepared on the adhesive layer by PS-PVD method, and then a layer of (Gd 0.5 Tb 0.5 ) 4 al 2 o 9 (GdTbAM) anti-CMAS protective layer with a thickness of 100 μm and a porosity of 0.5%. Adopt Oerlikon Metco PS-PVD system, O3CP plasma spray gun, spraying distance is 1000mm, spray gun working power is 130kW, plasma gas is Ar-110slpm, He-20slpm, preheati...

Embodiment 3

[0040] Using the directionally solidified nickel-based superalloy DZ125 as the substrate, it is processed into a 30mm×30mm×3mm sample by wire cutting and grinding. The surface of the sample is sandblasted with 120 mesh corundum sand under compressed air, and then the sample is Put it in acetone and absolute alcohol for ultrasonic cleaning, fully remove the residual impurities and corundum fine sand on the surface of the sample, and then dry it; use supersonic flame spraying or low-pressure plasma spraying to prepare 120 μm thick NiCoCrAlYSi on the DZ125 alloy substrate Bonding layer, using atmospheric plasma spraying to prepare a 150 μm YSZ thermal barrier layer on the surface of the metal bonding layer, and then preparing a 250 μm thick new high-temperature thermal barrier ceramic coating on the surface of YSZ, the chemical composition is LaMgAl 11 o 19 、Gd 2 Zr 2 o 7 , (Gd 0.9 Yb 0.1 ) 2 Zr 2 o 7 , La 2 (Ce 0.3 Zr 0.7 ) 2 o 7 One of the materials (not limited to...

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Abstract

The invention relates to an anti-CMAS protective layer for TBCs or EBCs. The anti-CMAS protective layer is a rare earth aluminate compound Re4Al2O9, Re is any one or two of Gd, Tb, Dy and Yb, the thickness of the anti-CMAS protective layer is 10-100 [mu] m, and the porosity of the anti-CMAS protective layer is 0.5%-20%. The invention also relates to a preparation method of the anti-CMAS protective layer. The preparation method comprises the step of preparing the anti-CMAS protective layer on the surface of the TBCs or the EBCs by adopting APS, PS-PVD or SPS. The invention also relates to a protective structure which comprises a matrix layer, TBCs or EBCs and the anti-CMAS protective layer. According to the anti-CMAS protective layer disclosed by the invention, the permeation of molten CMAS can be quickly blocked in a working temperature range of 1200-1650 DEG C, and the ultrahigh-temperature service stability and the thermal cycle life of a thermal barrier coating in a CMAS environment are improved.

Description

technical field [0001] The invention relates to a high temperature resistant coating, more particularly to a CMAS-resistant protective layer for TBCs or EBCs, a preparation method thereof and a protective structure obtained therefrom. Background technique [0002] Advanced aerospace, ship and energy power equipment put forward higher requirements on the working temperature, service life and comprehensive performance of the high-temperature hot-end components of the two machines. At present, the turbine inlet temperature of the world's most advanced aero-engine has exceeded 1800°C, and the turbine inlet temperature of heavy-duty gas turbines is approaching 1700°C. Nickel-cobalt-based superalloys are commonly used structural materials for high-temperature hot-end parts of two machines. However, the working temperature of the most advanced nickel-based single-crystal superalloys is about 1120°C, which is close to its service temperature limit. Therefore, the development of adv...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C4/073C23C4/11C23C4/129C23C4/134C23C14/08C23C14/16C04B41/89
CPCC23C4/073C23C4/134C23C4/129C23C4/11C23C14/16C23C14/08C23C14/083C04B41/009C04B41/89C04B41/52C04B35/80C04B35/565C04B41/5096C04B41/4527C04B41/5027C04B41/5032C04B41/4539C04B41/4543
Inventor 陈小龙张显程赵晓峰石俊秒王卫泽刘利强
Owner JINAN UNIVERSITY
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