摘要
针对某小型短寿命涡扇发动机台架试车中涡轮叶片断裂故障,进行了叶片断口分析、振动监测信号对比和结构动力学特性分析.讨论了叶片的固有振动特性与激振因素,阐明了该叶片故障主要是由叶片机匣严重碰摩激起的叶片以第一阶、第二阶及其耦合模态自由振动,导致的叶片根部高周疲劳破坏.提出合理控制转静子初始间隙和提高叶片根部阻尼,能有效防止该类型故障发生.
For the fracture fault of the high-pressure turbine blade in the miniature short-life turbofan engine during a certain rig test, the blade fractography, the vibration signal and the fault blade dynamics was observed and analyzed. Blades natural characteristics and exciting sources were analyzed in details; the faults mainly stemmed from fatigue for the 1st order, the 2nd order and the coupled mode vibrations due to the instantaneous severe rub impact force. Reasonable control of the clearance and improving the blade root damping can prevent the fault effectively.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2012年第3期604-609,共6页
Journal of Aerospace Power
关键词
叶片
疲劳
振动
碰摩
断裂
blade
fatigue
vibration
rub impact
fracture
