期刊文献+

通道参数对再生冷却通道流动换热的影响 被引量:2

Effects of cooling channel parameters on flow and heat transfer in regenerative cooling channels
原文传递
导出
摘要 应用RSM模型对冷却通道的流动与换热进行了三维数值模拟,冷却剂为气氢,考虑其物性随温度和压力的变化.所得结果表明:增加壁面粗糙度使冷却剂换热强化,但会增加流阻损失;在突扩突缩区域会出现旋涡,旋涡使局部流阻损失加大且使湍流加强,壁温在旋涡出现处降低;冷却通道内的流动发展不受入口湍流强度的影响;冷却剂离心力引发径向平面内的二次流动,二次流引起的冷却剂质量重新分布使传热在凹曲率段强化,凸曲率段恶化. To study the effects of wall roughness, sudden expansion/contraction, inlet turbulence intensity and cooling channel curvature on heat transfer and fluid flow in cooing channel, three-dimensional turbulent fluid flow and heat transfer were numerically investigated with RSM model, which was used to represent the turbulence; the coolant was gas hydrogen, whose thermophysical properties varied with both temperature and pressure. The results show that, the increase of wall roughness will increase not only the heat transfer but also the pressure loss; the vortex appears on the nearby sudden expansion/contraction point, the turbulence intensity and local pressure loss increase due to the vortex, while the wall temperature decreases at the place where the vortex appears; the coolant inlet turbulence intensity has no effects on the development of flow in cooling channel; the secondary flows which develop due to centrifugal force on the coolant will cause the mass redistribution, leading to heat transfer enhancement at the concave cooling channel but deterioration at convex cooling channel.
作者 康玉东 孙冰
出处 《航空动力学报》 EI CAS CSCD 北大核心 2010年第2期320-325,共6页 Journal of Aerospace Power
关键词 再生冷却 通道参数 流动 换热 数值模拟 regenerative cooling cooling channel parameters fluid flow heat transfer numerical investigation
  • 相关文献

参考文献6

  • 1Jason C, William E,Philip A, et al. Supercritieal flows in high aspect ratio cooling channels[R]. AIAA 2005-4302.
  • 2Preclik D, Wiedmann D, Oechslein W, et al. Cryo-ogenic rocket calorimeter chamber experiments and heat transfer simulations[R]. AIAA 98-3440.
  • 3Wadel F. Comparison of high aspect ratio cooling channel designs for a rocket combustion chamber[R]. AIAA 97 -2913.
  • 4Knab O, Frohlich A,Wennerberg D. Advanced cooling circult layout for the VINCI expander cycle thrust chamber [R]. AIAA 2002-4005.
  • 5Lebail F,Popp M. Numerical analysis of high aspect ratio cooling passage flow and heat transfer[R]. AIAA 93-1829.
  • 6康玉东,孙冰,高翔宇.液体火箭发动机推力室冷却通道温度分层数值研究[J].航空动力学报,2009,24(8):1904-1910. 被引量:8

共引文献7

同被引文献21

引证文献2

二级引证文献11

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部