论文部分内容阅读
发展了一种流固弱耦合数值方法来判断涡轮机械叶片气弹稳定性.通过一种数据交换方法将计算结构动力学(CSD)的节点振动位移施加到计算流体力学(CFD)的叶片表面网格点上,CFD分析采用多层动网格技术实时更新可动域的网格点坐标,并通过有限体积法求解了用k-ε湍流模型封闭的雷诺平均Navier-Stokes(RANS)方程.以NASA 67转子叶片为例,在设计状态下,对比了叶片前4阶模态下一个振动周期内的气动功及模态气动阻尼比,初步分析了叶片的气弹稳定性.计算结果表明:所发展的流固弱耦合数值方法用于判断涡轮机械叶片气弹稳定性是可行的.
A fluid-solid coupling numerical method is developed to evaluate the aeroelastic stability of turbomachinery blades.The vibration displacement of the node of computational structural dynamics (CSD) is applied to the blade surface net of computational fluid dynamics (CFD) by a data exchange method At the grid point, the CFD analysis uses multi-layer moving-grid technology to update the grid coordinates of the moving region in real time and solves the Reynolds-averaged Navier-Stokes (RANS) equation closed by k-ε turbulence model by the finite volume method Taking the rotor blade of NASA 67 as an example, aerodynamic work and modal aerodynamic damping ratio in one vibration period under the first four modes of blade are compared under the design condition, and the aerodynamic stability of the blade is analyzed preliminarily. The calculation results show that It is feasible to develop the fluid-solid coupling numerical method to judge the aeroelastic stability of turbomachinery blades.