Fretting wear between titanium alloy components in aero engine is prevailing in the blade dovetail, the blade crown, and the damping shoulders. In this study, the fretting wear behavior of Ti-6Al-4V alloy was investigated by changing the load and displacement under a high frequency (100 Hz). To simulate the actual working conditions in aero engines, both the ball and flat samples were Ti-6Al-4V alloy. It was found that as the load increased, or as the applied displacement decreased, the fretting regime changed from gross slip regime to partial slip regime. The coefficient of friction/traction at steady stage decreased as load increased. Wear scar morphologies varied with fretting running conditions. In gross slip regime, the central area was higher than the rest region of the wear scar. In the mixed slip regime, large material accumulation could be found at both ends of the reciprocating motion. In partial slip regime, a nearly original fretting sample surface was observed in the central area and wear occurred in the edge area. Furthermore, considering the wear of the paired samples, a method based on the fretting wear scar diameter was proposed to evaluate the fretting running conditions.

中文翻译：

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Ti-6Al-4V 微动磨损和微动状态评估的定量指标

航空发动机钛合金部件之间的微动磨损主要存在于叶片燕尾榫、叶片冠部和阻尼肩部。在这项研究中，通过在高频（100 Hz）下改变载荷和位移来研究 Ti-6Al-4V 合金的微动磨损行为。为了模拟航空发动机的实际工作条件，球状和扁平状样品均为 Ti-6Al-4V 合金。发现随着载荷的增加或施加的位移减小，微动状态从总滑动状态变为部分滑动状态。稳定阶段的摩擦/牵引系数随着负载的增加而降低。磨损疤痕形态因微动运行条件而异。在总滑动状态下，中心区域高于磨痕的其余区域。在混合滑移状态下，在往复运动的两端可以发现大量的材料堆积。在部分滑动状态下，在中心区域观察到几乎原始的微动样品表面，在边缘区域发生磨损。此外，考虑到配对样品的磨损，提出了一种基于微动磨痕直径的方法来评估微动运行条件。