摘要
介绍了航空发动机叶片对激光冲击强化的需求,描述了国内外的一些研究成果。测试和对比了方形光斑和常规圆形光斑激光冲击强化后的表面轮廓,并采用方形光斑搭接激光冲击强化TC17钛合金叶片,初步验证了钛合金叶片强化改善振动疲劳性能的效果。分析了发动机整体叶盘(IBR)的叶片边缘激光冲击强化的关键难题,并对发动机整体叶盘激光冲击强化在中国的发展做了介绍和展望。
The requirement of laser peening of aeronautical turbine blades is introduced,and the relevant research results are described.The surface profile of laser peening with square spots is measured and compared with the case of common circle spots.TC17 titanium blades are treated by laser peening with overlapped square spots,and then the improvement of bend vibration fatigue properties is tested.The key problems of laser peening turbine engine integrally blade rotor（IBR） are researched.The application of laser peening IBR in China is introduced and prospected.
出处
《中国激光》
EI
CAS
CSCD
北大核心
2011年第6期76-82,共7页
Chinese Journal of Lasers
关键词
激光技术
激光冲击强化
涡轮发动机
钛合金
整体叶盘
疲劳性能
laser technique
laser peening
turbine engine
titanium alloy
integrally blade rotor
fatigue life
