Thermal barrier coating provided with prefabricated microcosmic longitudinal crack structure and preparing method of thermal barrier coating

Abstract

The invention discloses a thermal barrier coating provided with a prefabricated microcosmic longitudinal crack structure and a preparing method of the thermal barrier coating. A ceramic heat isolationlayer of the thermal barrier coating comprises an implanted high-density microcosmic longitudinal crack. According to the preparing method, the atmosphere plasma spraying technology is utilized for being coupled with the dry ice particle spraying technology to prepare the ceramic heat isolation layer, and the microcosmic longitudinal crack is implanted in the ceramic heat isolation layer throughonline quenching on ceramic fusion particles via the dry ice particle spraying technology. Compared with thermal barrier coatings prepared through traditional atmosphere plasma spraying and EB-PVD (Electron beam-physical vapor deposition) methods, the thermal barrier coating provided with the prefabricated microcosmic longitudinal crack structure and prepared through the design has the low heat conductivity of the thermal barrier coating prepared through traditional plasma spraying and also has high strain tolerance of the thermal barrier coating prepared through the EB-PVD technology, stressgenerated due to unmatched heat stress can be effectively released under the premise that the coating heat impacts, heat isolation and CMAS (CaO-MgO-Al2O3-SiO2) corrosion resistance are not lowered, and accordingly the heat cycle service life of the thermal barrier coating under the severe working condition is prolonged.

Description

technical field [0001] The invention belongs to the technical field of materials, and in particular relates to a thermal barrier coating with a prefabricated microscopic longitudinal crack structure and a preparation method thereof. Background technique [0002] With the development of aviation, aerospace, ship, electric power and automobile technology, the research and development level of aero-engine and gas-turbine engine technology has become a bottleneck restricting the continuous progress of modern industry. At present, continuously increasing the working temperature of metal hot-end parts is the key to the development of high-efficiency and long-service-life engines. Therefore, the use of thermal barrier coatings (TBCs) with high temperature oxidation resistance and heat insulation functions on the surface of metal hot end parts is the most effective and feasible technical way to increase the operating temperature of aviation and gas turbine engines. [0003] Thermal...

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Problems solved by technology

At present, the most commonly used methods for preparing thermal barrier coatings are atmospheric plasma spraying (APS) and electron beam physical vapor deposition (EB-PVD); among them, the coating prepared by APS has a typical layered structure and has better thermal insulation performance, but TBCs serve in a very severe thermodynamic load environment, and usually encounter thermal fatigue failure, resulting in premature cracking and peeling of the coating; the thermal barrier coating prepared by EB-PVD has a columnar crystal microstructure, and the structure The coating has better strain tolerance and longer service life than the coating prepared by APS

However, such TBCs with macroscopic columnar gaps or macroscopic longitudinal crack structures often have high thermal conductivity and are prone to CMAS corrosion failure; and EB-PVD equipment is expensive, deposition efficiency is low, coating thickness is uncontrollable, and surface cleaning is complicated, so it is not suitable for Preparation of structurally complex workpieces and coatings on large devices

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