考虑转捩的跨声速气冷涡轮叶片气热耦合计算  

Coupled heat transfer simulations of a transonic vane by taking account of transition flows

作　　者：王强[1] 郭兆元[1] 周驰[1] 颜培刚[1] 冯国泰[1] 王仲奇[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,哈尔滨150001

出　　处：《航空动力学报》2009年第12期2703-2710,共8页Journal of Aerospace Power

基　　金：国家自然科学基金(50476028;50576017;50706009)

摘　　要：为了研究转捩对气热耦合计算的影响,在B-L代数模型与SST(shear stress transport)k-ω二方程模型的基础上,增加了两类基于间歇因子的转捩模型:代数AGS(Abu-Gharmam Shaw)模型与一方程间歇因子输运方程.选取NASA-MARKⅡ跨声速叶片为算例,分别采用全湍流模型与加入转捩的模型进行气热耦合计算.数值计算结果与试验对比表明由于能够预测附面层中的转捩过程,采用转捩模型的耦合计算得到的结果与试验吻合最好,由于在叶片壁面附近的网格较粗,采用间歇因子输运方程的转捩模型计算的结果要逊于采用代数转捩模型的结果.The Abu-Gharmam Shaw(AGS) transition model and a one-equation intermittency transition model were added into the Navier-Stokes(N-S) solver,HIT-3D,so as to investigate the effect of laminar-turbulent transition on predicting thermal load of vane.The test case was 5411 run of NASA-MARKⅡvane,a transonic turbine vane.The full turbulent models and transition models were employed by the coupled heat transfer simulations.The results show that the transition model can predict the transition process in the boundary ...

关 键 词：涡轮 气热耦合 转捩流动 间歇因子 湍流模型 

分 类 号：V211.6[航空宇航科学与技术—航空宇航推进理论与工程]