Ti2AlNb alloys are often used to fabricate high-pressure compressor blades and casings in aircraft engines with high thrust/weight ratios. In this study, a three-layered seal coating, NiCrFeAlBN-YSZ-NiCrAl, was prepared by thermal spraying on a titanium alloy (Ti2AlNb) substrate. The microstructure, surface hardness, and bond strength of coatings as well as their thermal cycling performance and abradability under simulated working conditions were investigated. The coating surface hardness was 61 HR15Y and the bond strength was 7.13 MPa. The coating maintained a good bonding to the substrate with no cracks after 40 cycles of water-cooling from 750 °C to room temperature. The abradability of the as-sprayed coating and the coating heat-treated at 750 °C for 200 h was tested against a Ti2AlNb blade at 750 °C, with a tip line speed of 300 m/s, and feed rates of 5, 50 and 480 m/s. The coating wear mechanisms involved micro-ruptures. The Cr2O3 phase formation and a decrease in the number of micropores in the heat-treated coating decreased its abradability.

中文翻译：

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航空发动机耐磨NiCrFeAlBN-YSZ-NiCrAl层状密封涂层的制备及性能

Ti2AlNb 合金通常用于制造具有高推力/重量比的飞机发动机中的高压压气机叶片和机壳。在这项研究中，通过热喷涂在钛合金 (Ti2AlNb) 基材上制备了三层密封涂层 NiCrFeAlBN-YSZ-NiCrAl。研究了涂层的微观结构、表面硬度和结合强度，以及它们在模拟工作条件下的热循环性能和耐磨性。涂层表面硬度为61 HR15Y，结合强度为7.13 MPa。从750℃到室温经过40次水冷循环后，涂层与基材保持良好的结合，无裂纹。喷涂涂层和在 750°C 下热处理 200 小时的涂层的耐磨性在 750°C 下对 Ti2AlNb 刀片进行测试，尖端线速度为 300 m/s，进给速度为 5、50 和 480 m/s。涂层磨损机制涉及微破裂。Cr2O3 相的形成和热处理涂层中微孔数量的减少降低了其耐磨性。