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

内冷涡轮叶栅三维气热耦合数值模拟
引用本文:苏生,刘建军,安柏涛.内冷涡轮叶栅三维气热耦合数值模拟[J].航空动力学报,2007,22(12):2018-2024.
作者姓名:苏生  刘建军  安柏涛
作者单位:1.中国科学院 工程热物理研究所, 北京 100080
基金项目:国家高技术研究发展计划(863计划)
摘    要:为了研究涡轮动叶的内部冷却技术,对采用绝热边界的实心叶片、采用气热耦合的实心叶片和采用气热耦合的空冷叶片进行了研究.发现叶片导热对叶片温度场的影响相当显著;具有带肋蛇形通道和涡流矩阵肋片的内冷结构能使叶片温度大幅下降,但叶片表面温度分布不均匀性增大,换热系数沿叶片表面呈不规则分布. 

关 键 词:航空、航天推进系统    三维涡轮叶栅    带肋蛇形通道    涡流矩阵肋片    气热耦合
文章编号:1000-8055(2007)12-2018-07
收稿时间:2006/11/22 0:00:00
修稿时间:2006年11月22

Numerical simulation of conjugate heat transfer for an internally cooled 3-D turbine blade
SU Sheng,LIU Jian-jun and AN Bai-tao.Numerical simulation of conjugate heat transfer for an internally cooled 3-D turbine blade[J].Journal of Aerospace Power,2007,22(12):2018-2024.
Authors:SU Sheng  LIU Jian-jun and AN Bai-tao
Institution:1.Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100080, China2.Graduate University of Chinese Academy of Sciences, Beijing 100080, China
Abstract:To study the internal cooling technology of turbine blade,three types of blades,i.e.non-cooled blade using adiabatic boundary condition,non-cooled blade using conjugate heat transfer method,and air-cooled blade using conjugate heat transfer method,were studied.The results show that heat conductivity of the blade has a significant influence on blade temperature distribution;the structure of rib-roughened cooling and latticework cooling makes the blade temperature drop markedly.However,this leads to increased non-uniformity of blade temperature distribution and irregular heat transfer coefficient distribution on the blade surface.
Keywords:aerospace propulsion system  3-D turbine blade  rib-roughened serpentine passage  latticework passage  conjugate heat transfer
本文献已被 CNKI 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