Preparation method of thermal barrier coating containing long-service-life antioxidant bonding layer

Abstract

The invention relates to a preparation method of a thermal barrier coating containing a long-service-life antioxidant bonding layer. The preparation method comprises the following steps: (1) sequentially performing deoiling and sand blasting treatment on a high-temperature alloy matrix; (2) preparing a metal bonding layer on the high-temperature alloy matrix by virtue of atmosphere plasma spraying, low-pressure plasma spraying, high-speed oxygen flame spraying or high-speed compressed air flame spraying; and (3) then depositing a ceramic layer on the metal bonding layer by virtue of atmosphere plasma spraying, high-speed oxygen flame spraying, supersonic plasma spraying, solution plasma spraying or electron beam physical vapor deposition. Compared with the prior art, the thermal barrier coating prepared by using an FeCrAlY bonding layer, disclosed by the invention, has higher working temperature and slower oxidation layer growth rate compared with that of a conventional MCrAlY thermal barrier coating (M refers to Ni and Co) so as to avoid the interfacial properties of the bonding layer and the ceramic layer from forming a brittle Ni2Al2O4 phase; and the thermal barrier coating has excellent high-temperature oxidation resistance and longer service life.

Description

technical field [0001] The invention relates to the field of thermal barrier coatings, in particular to a preparation method of a thermal barrier coating containing a long-life anti-oxidation bonding layer. Background technique [0002] Thermal barrier coatings usually refer to ceramic coatings that are deposited on metal surfaces and have good heat insulation effects. They are mainly used to reduce the working temperature of the substrate and prevent high-temperature oxidation, corrosion, and wear. A coating system consisting of a thermal insulation layer and a ceramic layer with thermal insulation effect. It is of great significance to ensure the long-term service of hot-end components such as gas turbines and engines, and the bonding layer is an important part of the thermal barrier coating of gas turbines, and its performance directly affects the life of the thermal barrier coating system. At present, the composition of the bonding layer is mainly MCrAlY (M=Ni, Co) and ...

AI Technical Summary

Problems solved by technology

However, the high-temperature mechanical properties and oxidation resistance of such coatings can no longer fully meet the needs

Compared with it, (Ni,Pt)Al, the mainstream bonding layer material of modern aero-engine thermal barrier coatings, has more excellent high temperature oxidation resistance and high temperature creep strength, but the bonding layer has disadvantages: this technology uses precious metals Pt and CVD preparation process, the cost is high; secondly, the yield strength at high temperature is low, and under the action of high temperature stress, it is easy to form undulations at the interface between the ceramic layer and the bonding layer, which will cause cracks and cause thermal barrier coating failure

[0003] Studies have shown that the FeCrAlY alloy has better high temperature oxidation resistance than the traditional bonding layer, and the FeCrAlY layer can quickly form a dense layer of Al 2 o 3 (ie TGO), and TGO grows slowly, will not form Ni2Al2O4 brittle phase to destroy the compactness and continuity of the oxide layer, but has not been used to prepare the bonding layer of thermal barrier coating

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