某风机叶片的弯扭耦合颤振问题分析与验证  

Analysis and experiment on coupled flutter of a wide-chord blade

作　　者：吴长波[1,2] 崔海涛[1] 徐拓[2] 王春健[2] 

机构地区：[1]南京航空航天大学,能源与动力学院,南京210016 [2]中国燃气涡轮研究院强度技术研究室,成都610500

出　　处：《航空动力学报》2012年第3期623-627,共5页Journal of Aerospace Power

摘　　要：研究了某风机宽弦转子叶片系统本身的耦合颤振问题,针对该风机转子叶片,理论分析表明原始型叶片存在典型的一阶弯曲与一阶扭转耦合颤振问题.改进型叶片则从转子叶片结构上采取了措施,调整了宽弦转子叶片的一阶弯曲与一阶扭转频率,有效地避免了转子叶片的耦合颤振问题.可靠性累积试车对转子叶片的耦合颤振问题进行了验证,原始型转子叶片80h后因耦合颤振导致转子叶片发生了高周疲劳断裂问题,改进型转子叶片顺利通过了200h的试车考核.The coupled flutter of a pinwheel wide-chord blade was studied. In view of the pinwheel blade, the theoretical analysis made for the original pinwheel blade showed that some typicaly coupled flutter problems between the first-order bending vibration and the first-order torsion vibration occured on the blade. The blade was re-designed and the fre- quencies of the first-order bending vibration and the first-order torsion of the modified blade were changed so as to effectively avoid the coupled flutter. The cumulative test of the relia- bility shows that the cracks are found in the original pinwheel blade after running 80 hours, while the modified blade can run safely over 200 hours.

关 键 词：转子叶片 弯曲与扭转 耦合颤振 可靠性累积试车 断裂 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]