摘要
为了研究跨音速风扇叶片叶尖间隙大小对叶片颤振特性的影响,以NASA rotor67转子为例建立了单排全环流动模型。求解定常和非定常流场使用雷诺平均Navier-Stokes方程（RANS）,结构动力学方程的求解使用模态叠加法,利用时间推进法模拟颤振的整个非定常过程直到达到收敛条件,对得到的模态位移曲线进行拟合得到对应状态的气动阻尼值。定常计算和颤振计算使用自行编制的HGFS计算程序,间隙范围从0.15%~1.26%span。数值计算结果表明,叶尖间隙的大小与气动阻尼为非线性关系,存在一个中间叶尖间隙使气动阻尼最大,气弹稳定性最优。
The purpose of this paper is to use numerical simulation method to research the influence of transonic fan blade tip clearance size on blade flutter characteristics. The NASA rotor67 is the example and establishes a single row of annular flow model. The steady and unsteady flow fields are solved by u- sing the Reynolds averaged Navier-Stokes equation （RANS）. The structural dynamic equations are solved using the modal superposition method. The time marching method is used to promote the whole unsteady process simulation chatter until the convergence conditions. Modal displacement curves are ob- tained by fitting the aerodynamic damping value. The HGFS calculation program is used to calculate the flow field and aerodynamic damping. The blade tip clearance size is 0.15% span to 1. 26% span. Numeri cal results show that tip clearance size and aerodynamic damping is Nonlinearity. There exists a middle tip clearance and it makes the aerodynamic damping maximum and aeroelastic stability optimal.
出处
《滨州学院学报》
2015年第6期28-33,共6页
Journal of Binzhou University
关键词
叶尖间隙
泄漏涡
颤振
气弹稳定性
tip gap
leakage vortex
flutter
aeroelastic stability
