Study of Aerodynamic Damping for Transonic Blade in Turbo-machine

摘要：

The focus of the present investigation is on a method to predicting aerodynamic damping. This method, on the basis of separating the aerodynamic force along the surface of the blade, is different from the energy method. By means of this method, the aerodynamic damping of transonic blades in high order modes is computed, which plays an important role in calculating blade vibration induced by stator-rotor interaction in turbo-machines. The distribution of the aerodynamic damping on the blade surface is given and the effects of shock waves on the aerodynamic damping are also investigated.

关键词： forced response aerodynamic damping natural frequency mode shape shock wave

作者: LI Lin GUO Xuelian

作者单位: School of Jet Propulsion Beijing University of Aeronautics and Astronautics Beijing, China

会议类型: 国际会议

会议名称: The 3rd International Symposium on Jet Propulsion and Power Engineering(第三届喷气推进与动力工程国际会议 ISJPPE)

会议地点: 南京

会议语种:英文

页码: 540-544

在线出版日期: 2010-09-13（万方平台首次上网日期，不代表论文的发表时间）