尾迹诱导下低压涡轮边界层转捩的数值模拟  

Numerical Simulation of Wake-Induced Boundary Layer Transition in Low-Pressure Turbine

作　　者：向欢[1] 杨荣菲[1] 葛宁[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《燃气涡轮试验与研究》2013年第3期29-33,62,共6页Gas Turbine Experiment and Research

摘　　要：为研究尾迹诱导下低压涡轮的边界层发展,采用基于三阶MUSCL-Roe格式、引入转捩准则后的一方程Spalart&Allmaras模型和隐式牛顿迭代时间推进的非定常雷诺平均计算方法,对上游运动圆柱产生的周期性尾迹作用下的T106低压涡轮叶片边界层转捩流动进行了数值模拟。定常来流下,准确捕捉到分离诱导转捩及雷诺数效应现象;尾迹作用下的非定常计算,则揭示了尾迹在叶栅通道内的输运过程,及尾迹对低压涡轮吸力面上层流分离的抑制作用。In order to study the wake-induced boundary layer transition in low-pressure turbine, the un?steady Reynolds-averaged Navier-Stokes (RANS) method was adopted to simulate the boundary layer tran?sition flow of the T106 low-pressure turbine blade which was subjected to the periodical wake of the up?stream moving bar. The RANS code included third order MUSCL-Roe scheme, the Spalart&Allmaras tur?bulence model combined with a transition correlation, and Newton iterative method for implicit time ad?vancement. In the steady case without any wake disturbance, the laminar separation bubble induced transi?tion and the Reynolds number effects were correctly predicted. While in the disturbed case, the convection of wake through a turbine cascade was presented and the laminar separation on the suction side was inhibit?ed by the wake of upstream moving bar.

关 键 词：T106低压涡轮叶片 上游运动圆柱 非定常尾迹 边界层转捩 雷诺数效应 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]