Heat barrier composite plating and preparation technique thereof

A composite coating and preparation process technology, which is applied in the field of thermal barrier composite coating and its preparation, can solve the problems of the influence of the mechanical properties of the coating, cannot be implemented industrially, and the thermal barrier coating fails, and achieves good thermal oxidation resistance. Promotion and application, less environmental pollution

Inactive Publication Date: 2009-02-04
SHANGHAI UNIV OF ENG SCI
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Although the plasma spraying method has a wide range of applications, there are pores and unmelted powder particles in the coating, which will affect the mechanical properties of the coating. At the same time, they will also become channels for corrosive gases, oxidizing the intermediate layer, and causing thermal b

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  • Heat barrier composite plating and preparation technique thereof

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[0033] Example 1

[0034] a) Pre-treat the surface of high-temperature alloy K17 according to conventional operations

[0035] ①Mechanically treat the oxide layer on the surface of the high-temperature alloy;

[0036] ②Organic solvent degreasing: Use acetone to clean the oil stain on the sample surface;

[0037] ③Inorganic chemical reagent degreasing: Use an inorganic chemical degreasing agent at 60~80℃ to clean the oil stains on the surface of the sample. After the degreasing water is washed, the water film on the surface of the workpiece is a continuous and uniform water film as the standard for degreasing cleanness. The best degreasing time, the formula of inorganic chemical degreasing agent is:

[0038] NaCO3 20~30g / L

[0039] Na 3 PO 4 30~40g / L

[0040] NaOH 50~60g / L

[0041] Na 2 SiO 3 5~10g / L;

[0042] ④ Dilute sulfuric acid activation: Place the sample in a 20% dilute sulfuric acid aqueous solution at 20-30°C for 30 minutes.

[0043] b) Using electrophoretic...

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Abstract

The invention discloses a heat barrier composite cladding layer which consists of a MCrAlY alloy adhesive layer, a NiAl alloy barrier layer, a ZrO2-CeO2 ceramic layer and an Al2O3 protective layer; the NiAl alloy barrier layer is arranged between the MCrAlY alloy adhesive layer and the ZrO2-CeO2 ceramic layer, and the Al2O3 protective layer is arranged on the surface of the ZrO2-CeO2 ceramic layer. The invention adopts a preparation process integrated with electrophoretic deposition, high-speed electrical spray-plating and plasma arc plating layer scanning, and has the advantages of simple operation method, quite low preparation cost, capability of realizing industrialized production and the like, and the prepared heat barrier composite cladding layer also has the advantages of low heat conductivity, low roughness of the cladding layer surface, high integration strength of the cladding layer and the matrix, good hot corrosion resistance performance, good hot oxidation resistance performance and the like, solves the difficulties of poor high-temperature oxidation resistance and high-temperature corrosion resistance of high temperature resistant parts, and prolongs the service life of the high temperature resistant parts.

Description

technical field [0001] The invention relates to a thermal barrier composite coating and its preparation process, in particular to a thermal barrier composite coating structure on a high temperature resistant component with high temperature corrosion resistance and high temperature oxidation, and high bonding force with the substrate and its Preparation Process. Background technique [0002] With the rapid development of modern industry and technology, marine or power station gas turbines and large civil aircraft engines are developing towards high flow ratio, high thrust-to-weight ratio, and high turbine inlet temperature. The airflow circulates around the blades, destroying and blowing off the protective oxide film on the parts, which intensifies corrosion. High-temperature equipment such as marine gas turbines and large civil aircraft engines working at sea or offshore, hot-end parts (such as blades) work under gas conditions, will absorb Na from seawater 2 SO 4 , NaCl ...

Claims

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Application Information

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IPC IPC(8): C25D5/00C25D5/10
Inventor 王伟钱士强李培耀李曼萍黄晨
Owner SHANGHAI UNIV OF ENG SCI
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