航空发动机高压转子的结构动力学设计方法  

Structure dynamics design method of aero-engine high pressure rotor

作　　者：廖明夫[1] 谭大力[2] 耿建明[2] 宋明波[1] 吕品[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]海军装备研究院舰船论证研究所,北京100073

出　　处：《航空动力学报》2014年第7期1505-1519,共15页Journal of Aerospace Power

摘　　要：建立了航空发动机高压转子的动力学模型,该模型包含所有的结构动力学设计参数,揭示了设计参数与转子振动特性间的关系,提出了转子临界转速界值的估计方法,并予以理论证明.建立了分别基于两阶临界响应的支承刚度设计准则.发现了转子参数临界转速现象,在参数临界转速处,阻尼器将失去阻尼作用,振动趋于无穷大;给出了参数临界转速出现的条件,上述的结论对于航空发动机高压转子的设计具有重要的指导意义.Taking all design parameters into account,this model was applied for dynamic design of aero-engine high pressure rotors in practice.The influences of design parameters on the vibration features of the rotors were revealed,and an estimation method of critical speeds of rotor was theoretically proven,giving a clear limit value estimation of critical speeds of rotor.A design criterion of the stiffness was suggested with different effects two orders critical responses.A special phenomenon of critical speeds was observed,and a certain combination of rotor parameters can result in an additional critical speed,at which the damper will not reduce the vibration and the vibration peak will reach a very high level.This critical speed is defined as parameter critical speed.The parameter conditions corresponding to this critical speed were obtained,giving important guidelines for the design of high pressure rotors of aero-engines.

关 键 词：航空发动机 高压转子 转子结构动力学设计 临界转速估计 参数临界转速 

分 类 号：V231.96[航空宇航科学与技术—航空宇航推进理论与工程]