中国激光, 2011, 38 (6): 0601009, 网络出版: 2011-05-20
发动机整体叶盘的激光冲击强化技术
Laser Peening of Turbine Engine Integrally Blade Rotor
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
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。
Abstract
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.
邹世坤, 巩水利, 郭恩明, 李斌. 发动机整体叶盘的激光冲击强化技术[J]. 中国激光, 2011, 38(6): 0601009. Zou Shikun, Gong Shuili, Guo Enming, Li Bin. Laser Peening of Turbine Engine Integrally Blade Rotor[J]. Chinese Journal of Lasers, 2011, 38(6): 0601009.
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