动力学粗糙度对高载荷低压涡轮气动性能影响的研究

Effect of Dynamic Roughness on Aerodynamic Performance of High-Lift LPT

动力学粗糙度是一种新型流动控制方法,通过分布式粗糙元高度沿壁面法向的非定常变化达到主动控制效果.本文基于高载荷低压涡轮叶栅T106D研究了静/动力学粗糙度对涡轮气动性能的影响,研究以FLUENT为计算工具,采用了动网格技术实现动力学粗糙度的数值模拟。首先开展了静力学粗糙度影响涡轮气动性能的研究,分析不同位置下的静力学粗糙度控制效果优异;在该研究结果基础上选取最优位置开展动力学粗糙度的数值模拟,结果表明,动力学粗糙度对气动性能的提升主要来自振动区域的压力/速度脉动产生的非定常涡与附面层相互作用。

Dynamic roughness is a new active flow control method, which achieves the desired effect through unsteady transformation by distributed roughness elements height. The research is based on LPT blade named T106 D.FLUENT was used to perform the numerical simulation. Dynamic mesh method was adopted to realize numerical simulation of dynamic roughness. To analysis the effect of statics roughness under different location, research of statics roughness was conducted at first;then,select the optimal position to carry out the dynamic roughness numerical simulation on the basis of the former study. The result shows that the aerodynamic performance of ascension come mainly from the interaction between the unsteady vortex and boundary layer.