摘要
分析了某型涡喷发动机压气机转子叶片断裂的故障,确定了叶片的断裂机理,提出了采用叶片错频的方式和实现叶片错频的工程方法解决叶片颤振问题.最终的实验结果验证了分析和解决方法的正确性.
Failure of compressor rotor blade used in turbojet engine as the baseline is analyzed. The failure mechanism of blade is determined. Stagger frequency technique of blade is presented, and engineering method is used to resist vibration fatigue failure of blade. The experimental results show that the validity of analysis method and problem-solving is proved.
出处
《战术导弹技术》
北大核心
2007年第4期25-27,共3页
Tactical Missile Technology
关键词
涡喷发动机
压气机
叶片
故障
颤振
turbojet engine
compressor
blade
failure
vibration
