Titanium alloy Ti-6Al-4V is extensively employed in aero-engine as blade, disk, and casing components, which have a high risk to occur fatigue failure. The milled subsurface damage is one of the critical factors influencing fatigue property. This paper has a comprehensive overview on the subsurface damage in titanium alloy Ti-6Al-4V induced by milling. It was found that the milled subsurface damage was mainly the Ti-6Al-4V plastic deformation including the changes of grain size and shape (such as grain refinement); however, the phase transformation was not observed. Such subsurface damage results in compressive residual stress (− 266 MPa ~ − 528 MPa) and work hardening (375 HV~410 HV), which significantly affect the material’s fatigue property. Nevertheless, some studies reported that no subsurface damage appeared in titanium alloy Ti-6Al-4V after milling. This might be owning to the limitation of detection method. In particular, a novel methodology was proposed to study the fatigue life of components based on the interrelationship among machining, structure, and property. Lastly, several fundamental questions necessitating further researches are recommended herein.

钛合金Ti-6Al-4V被广泛用​​于航空发动机中的叶片，磁盘和外壳部件，极有可能发生疲劳破坏。研磨的表面损伤是影响疲劳性能的关键因素之一。本文全面概述了铣削引起的钛合金Ti-6Al-4V的表面损伤。研究发现，研磨后的表面损伤主要是Ti-6Al-4V塑性变形，包括晶粒尺寸和形状的变化（例如晶粒细化）。但是，没有观察到相变。这种表面下的损坏会导致残余压缩应力（-266 MPa〜-528 MPa）和加工硬化（375 HV〜410 HV），这极大地影响了材料的疲劳性能。尽管如此，一些研究报道，铣削后的钛合金Ti-6Al-4V没有出现亚表面损伤。这可能归因于检测方法的局限。特别是，提出了一种新的方法来研究零件的疲劳寿命，该方法基于机械加工，结构和性能之间的相互关系。最后，本文建议了一些需要进一步研究的基本问题。