小型航空发动机转子连接刚性分析与验证  

Joint Rigidity Analysis and Experimental Study on Rotor of a Small Aero-Engine

作　　者：吴长波[1,2] 崔海涛[1] 梁恩波[2] 高雄兵[2] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016 [2]中国燃气涡轮研究院,四川成都610500

出　　处：《燃气涡轮试验与研究》2012年第3期12-15,25,共5页Gas Turbine Experiment and Research

摘　　要：某小型航空发动机在原理样机阶段存在整机振动大的现象,发动机试验时机匣上的最大振动监测值达179mm/s,严重影响发动机试验安全。通过对发动机的转子动力学设计和试验研究,找出转子连接刚性差是造成发动机振动大的关键原因。在验证机阶段设计中,对转子连接刚性进行了针对性改进。改进后的试验表明,发动机振动得到明显改善,最大振动监测值为33 mm/s,确保了发动机试验安全。Violent vibration appeared in the phase of principle prototype of a small aero-engine. During engine tests, the maximum vibration monitoring value of casing was up to 179mm/s, which seriously affected the safety of engine test. Through dynamic design and experimental research on the rotor, it was found that the rotor joint rigidity was the key factor causing engine vio lent vibration. Therefore the improvements on rotor joint rigidity were made during the design of demonstrator. Test results showed that the engine vibra- tion was greatly reduced and the maximum value was only 33 mm/s, which ensured the safety of engine test.

关 键 词：整机振动 振动监测值 转子动力学 连接刚性 

分 类 号：V231.91[航空宇航科学与技术—航空宇航推进理论与工程]