摘要
从气动阻尼产生的机理出发,建立合理的气动阻尼模型;利用动网格技术,结合等效模态气动阻尼比的计算式,以Rotor37跨声叶栅为例,用弱耦合方法数值计算得到一弯、一扭与弯扭耦合模态的气动阻尼比,并考虑流场压力水平及叶片振幅对气动阻尼的影响.计算结果表明,在保证进出口压比不变的情况下,气动阻尼与压力成线性关系;在小振幅下,气动阻尼基本与叶片振幅无关.
Based on the theory of aerodynamic damping,the appropriate damping model was established;with the help of moving meshes technology and in combination with the equation of equivalent mode aerodynamic damping ratio,the weakly coupled method was applied.In the researches of Rotor 37 transonic blade with excitation of the 1st bend mode,the 1st torsion mode and the 1st bend-torsion mode,the aerodynamic damping was gained.The pressure and the blade amplitude were considered.The results demonstrate that when the p...
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2009年第4期819-824,共6页
Journal of Aerospace Power
关键词
气动阻尼机理
动网格
模态气动阻尼比
弱耦合方法
turbomachinery
moving meshes technology
mode aerodynamic damping ratio
weakly coupled methods
