尾迹诱导下低压涡轮非定常转捩的数值模拟  

Numerical Simulation of Wake-Induced Unsteady 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,南京210016

出　　处：《南京航空航天大学学报》2013年第5期633-640,共8页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：为研究尾迹诱导下低压涡轮边界层的非定常发展,采用基于三阶MUSCL-Roe格式、引入转捩准则后的Spalart&Allmaras湍流模型、隐式牛顿迭代时间推进的非定常雷诺平均计算方法,对上游圆柱周期性尾迹作用下T106A低压涡轮边界层非定常转捩的流动进行了数值模拟。定常来流下,计算准确捕捉了分离诱导转捩以及雷诺数和负荷的影响,尾迹作用下的非定常计算则准确模拟了尾迹在叶栅通道内的输运过程、尾迹的负射流特性、尾迹对吸力面层流分离的抑制作用,并讨论了雷诺数、负荷和尾迹通过频率的影响。In order to study the wake-induced boundary-layer transition in low-pressure turbine,the unsteady Reynolds-averaged Navier-Stokes （RANS） method is adopted to simulate the unsteady boundarylayer transition flow of the T106A low-pressure turbine blade,which is subjected to the periodical wake of an upstream moving bar.The RANS code includes the third-order MUSCL-Roe scheme,the Spalart and Allmaras turbulence model combined with a transition correlation,and the Newton iterative method for implicit time advancement.In the steady case,the laminar separation induced transition,and influences of Reynolds number and blade loading are correctly predicted.While in the disturbed case,the convection of wake through cascade and wake＇s negative jet effect are perfectly captured.The laminar separation bubble is inhibited by the upstream wake.The influences of Reynolds number,blade loading and wake passing frequency on the interaction of wake and boundary layer are discussed.

关 键 词：上游周期性尾迹 边界层非定常转捩 抑制分离 沉寂效应 

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]