Multielement rare earth oxide doped zirconia thermal barrier coating with craze crack structure and preparing method thereof

Abstract

The invention discloses a method for preparing a rare earth oxide doped zirconia thermal barrier coating with a craze crack structure, which solves the problems of low thermal shock resistance property, difficult further thermal conductivity reduction and the like of the thermal coating prepared by conventional plasma spraying. Under the condition of the plasma spraying technology, the preheating temperature of a base body, the moving speed of a plasma spraying gun and a powder delivery rate are adjusted, then a rare earth oxide doped zirconia thermal barrier coating (BH-TBCO1) with a craze crack structure and stable thermodynamics is prepared. The rare earth oxide doped zirconia thermal barrier coating with a craze crack structure has good high-temperature phase stability at the temperature below 1300 DEG C; the thermal insulation property of the thermal barrier coating is further enhanced, and the thermal insulation temperature achieves more than 150 DEG C and is enhanced by more than 50% when compared with the coating prepared by the conventional plasma spraying; the thermal shock life of the coating exceeds 4000 cycles and is enhanced by more than 1 time when compared with the coating prepared by the conventional plasma spraying.

Description

technical field [0001] The invention relates to a method for preparing a thermal barrier coating, more particularly, it improves the conventional plasma spraying process, so that the ceramic layer of the rare earth oxide doped zirconia thermal barrier coating prepared by this method has a network The crack structure can improve the thermal insulation performance and thermal shock resistance of thermal barrier coatings. Background technique [0002] With the development of aero turbine engines in the direction of high flow ratio and high thrust-to-weight ratio, the design inlet temperature of aero-engines with a thrust ratio of 10 has reached above 1577°C, and the design inlet temperature of aero-engines with a thrust ratio of 15 and above will exceed 1800°C. From the 1940s to the 1970s, after years of development, a series of high-temperature alloy systems have been developed. The preparation technology of these alloy materials has also developed relatively mature, from trad...

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Problems solved by technology

The traditional plasma sprayed coating has a layered structure, and the thermal insulation performance of the coating is better than that of the electron beam physical vapor deposition coating, and the coating cost is low, but the bonding force of the plasma sprayed coating is poor, and the thermal shock resistance of the coating is significantly lower For electron beam physical vapor deposition thermal barrier coatings, the thermal shock life usually does not exceed 2000 times, so the current plasma sprayed thermal barrier coatings are limited to the stationary parts of the engine, such as the inner wall of the combustion chamber and the throat, etc.

Similarly, the thermal shock life of the rare earth oxide doped zirconia coating prepared by the conventional plasma spraying process does not exceed 2000 times

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