风力机翼型颤振及射流减振技术的气动弹性研究

AEROELASTIC ANALYSIS ON AN AIRFOIL'S FLUTTER AND FLUTTER CONTROL TECHNIQUE OF BLOWING

采用流固耦合的数值计算方法研究了S80 9风力机翼型在大攻角 (15°～ 5 0°)范围的颤振 ,以及在翼型背部部分引入射流的减振技术。在流体区域用高精度、高分辨率算法求解Farve平均的Navier Stokes方程 ,在固体区域用四阶Runge Kutta法求解振动方程 ,并且每一个时间步后都在两个区域之间传递边界条件。计算结果表明在翼型背部引入适当射流会降低振动 ,并且基本上不影响翼型的升力系数。但如果引入射流的速度过高 ,会在叶背处形成新的分离流 。

FLuid-structure coupling numerical mdthod was used to analyze S809 airfoil's flutter and flutter control technique of blowing at large incidence angles (15-50 degrees). A higher-order, high resolution MUSCL TVD scheme was used to solve the Farve-averaged Navier-Stokes equations in the fluid zone. Fourth-order Runge-Kutta method was used to solve the oscillation equations in the solid zone. Boundary conditions are transferred between the two zones after each time-step. The numerical results show that the appropriate blowing would reduce the oscillation amplitude, without significant influence to the lift coefficient. Surplus blowing would create new vortical structures near the airfoil, which causes the lift coefficient to drop.