摘要
将挤压油膜阻尼器设计与转子动力学设计相结合,建立了航空发动机转子挤压油膜阻尼器设计方法和设计流程.转子参数为转子阻尼、临界转速配置、最大不平衡量、转子振动峰值,以及支承外传力等,挤压油膜阻尼器设计参数为轴颈偏心率、油膜半径间隙、油膜长度和鼠笼刚度.设计目标是控制转子临界峰值和支承外传力.其中转子阻尼与最大不平衡量为挤压油膜阻尼器设计的关键参数.利用一实验器,对该设计方法进行了数值仿真和实验验证,结果表明:转子振动响应临界峰值减振比例可达60%以上,说明所建立的设计方法是正确有效的,可为挤压油膜阻尼器设计提供指导.
The design process and method of squeeze film damper （SFD） for aero-engine were proposed, in which the relationship between the dynamic characters of rotors and the SFD design parameters was taken in consideration. The rotor parameters include damping ra- tio, setting of critical speeds, maximum unbalance, vibration peak and force transmitted to foundations, etc, and the SFD design parameters include the eccentricity ratio, radial clear- ance and length of the film as well as rotor cage stiffness. The design was made for purpose of control of the critical peak value and force transmitted to foundations. The damping ratio and maximum unbalance of the rotor were found to be critical parameters for the SFD de- sign. Numerical and experimental verification were carried out based on a rotor system. Re- sults show that vibration attenuation of critical vibration peak can be reduced by 60%, and the correctness and effectiveness of the method provide a guideline for the SFD design.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2015年第11期2762-2770,共9页
Journal of Aerospace Power
