激光冲击强化TC17钛合金室温和高温拉伸性能研究

目的分析激光冲击强化对钛合金室温和高温拉伸性能的影响。方法用YAG纳秒脉冲激光器对TC17钛合金板状拉伸试样表面进行双面激光冲击强化,脉冲能量为25 J,脉冲宽度为15 ns,光斑尺寸为4.2 mm×4.2 mm,搭接率为10%,强化1次。通过室温及400℃下拉伸试验,获得强化前后试样的抗拉强度、屈服强度和断裂伸长率,利用X射线衍射法测试拉伸前后试样表面的残余应力,并在扫描电镜下观察拉伸试样断口微观形貌。结果室温拉伸试验时,激光冲击强化对TC17钛合金的室温抗拉强度和伸长率几乎无影响,但强化后的室温屈服强度下降约6.1%,有/无强化试样均没有明显的屈服点,距离强化试样断裂位置10 mm的表面残余压应力较拉伸前下降约12%。400℃拉伸试验时,激光冲击对TC17钛合金的高温抗拉强度和屈服强度均影响较小,有/无强化试样均出现明显的屈服点,距离强化试样断裂位置10 mm的表面残余压应力较拉伸前下降约44%。结论激光冲击强化在TC17钛合金表面引入显著的残余压应力分布,对屈服强度具有一定程度的影响。强化后试样的屈服强度与拉伸过程中残余压应力松弛速率有关,室温拉伸过程的残余应力松弛较高温拉伸过程慢,试样内部的平衡拉应力区更容易先发生屈服。这是造成室温拉伸屈服强度小幅降低的主要原因。     

A Critical Review of Laser Shock Peening of Aircraft Engine Components

Many aviation accidents are caused by the failure of aircraft engine components, and engine blades are especially vulnerable to high-cycle fatigue fracture in severe working environments as well as to impact damage caused by foreign objects. To address this problem, the United States took the lead and has been successful in implementing laser shock peening (LSP) as a surface treatment for aircraft engine components to enhance their fatigue performance. This review provides an overview of the development of LSP for use in treating aircraft engine components over the past three decades, with a brief introduction to the development of high-energy pulsed lasers for LSP. A particular focus of this review is on the limitations and challenges associated with the application of LSP for treating critical aircraft engine components. It is hoped that this review serves as a reference for future research and development that can lead to better performance of these components.     

面向等离子体材料钨厚涂层的制备及表征

等离子体喷涂技术在面向等离子体材料钨涂层的制备中占据主导地位,本实验采用CuMo/MoW作为涂层的中间过渡层,分别以结晶钨粉和羰基钨粉为原料,用大气等离子体喷涂技术在CuCrZr合金基体(110 mm×130mm)上制备了3-4 mm厚的3种钨涂层.对钨涂层微观组织、力学性能和热学性能研究表明,羰基钨粉制备的钨涂层的综合性能优于结晶钨粉,且薄涂层的结合强度优于厚涂层.优化喷涂工艺后,金相法测得钨涂层孔隙率＜2％,涂层的结合强度最大值为10 MPa,EDS测得氧含量为6％左右,纯钨层热导率最大值为12.52 W/(m.K),涂层氧含量过高导致涂层热导率显著降低.研究表明采用大气等离子体喷涂技术在铜合金上制备3～4mm厚的钨涂层是可行的,该技术可为下一步低成本、高性能厚钨涂层的制备奠定基础.