首页 | 本学科首页   官方微博 | 高级检索  
     检索      

考虑转捩的跨声速气冷涡轮叶片气热耦合计算
引用本文:王强,郭兆元,周驰,颜培刚,冯国泰,王仲奇.考虑转捩的跨声速气冷涡轮叶片气热耦合计算[J].航空动力学报,2009,24(12):2703-2710.
作者姓名:王强  郭兆元  周驰  颜培刚  冯国泰  王仲奇
作者单位:哈尔滨工业大学能源科学与工程学院,哈尔滨,150001
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-MARK Ⅱ跨声速叶片为算例,分别采用伞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.

关 键 词:涡轮  气热耦合  转捩流动  间歇因子  湍流模型
收稿时间:2008/11/26 0:00:00
修稿时间:1/7/2009 12:00:00 AM

Coupled heat transfer simulations of a transonic vane by taking account of transition flows
WANG Qiang,GUO Zhao-yuan,ZHOU Chi,YAN Pei-gang,FENG Guo-tai and WANG Zhong-qi.Coupled heat transfer simulations of a transonic vane by taking account of transition flows[J].Journal of Aerospace Power,2009,24(12):2703-2710.
Authors:WANG Qiang  GUO Zhao-yuan  ZHOU Chi  YAN Pei-gang  FENG Guo-tai and WANG Zhong-qi
Institution:School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China;School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China;School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China;School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China;School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China;School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China
Abstract: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-MARK Ⅱ vane,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 layer near the vane.and that the simulations with such models lead to thermal load matching well the experiments.Since the grids cells near the vane surface are coarse,the simulations with the intermittency equation lead to results worse than those with the algebraic transition model.
Keywords:turbine  coupled heat transfer  transition flow  intermittency factor  turbulence model
本文献已被 万方数据 等数据库收录!
点击此处可从《航空动力学报》浏览原始摘要信息
点击此处可从《航空动力学报》下载免费的PDF全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号