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肋的几何参数对网格式肋化通道的传热与总压损失特性的影响
引用本文:张勃,吉洪湖,张靖周,高潮,王鸣.肋的几何参数对网格式肋化通道的传热与总压损失特性的影响[J].航空动力学报,2004,19(2):206-212.
作者姓名:张勃  吉洪湖  张靖周  高潮  王鸣
作者单位:1. 南京航空航天大学,能源与动力学院,江苏,南京,210016
2. 沈阳发动机设计研究所,辽宁,沈阳,110015
基金项目:航空科学基金资助项目(No.99C52023)
摘    要:通过10个实验模型研究了肋宽与肋间距之比t/p以及肋宽与肋高之比t/e对网格式肋化通道的换热与总压损失的影响。实验模型分为两组:第一组5个45/45模型是由两块肋向角分别为45°与-45°的肋化板形成的;第二组5个45/60模型是由肋向角分别为45°和-60°的两块肋化板形成的。模型的t/e分别为0.25,0.30,0.50,t/p分别为0.25,0.33,0.50。在雷诺数为0.5×105~1.5×105时,t/e=0.30与t/p=0.50的模型换热效果最好,但同时压损也最大。45/45模型与45/60模型的换热效果没有明显的区别,但后者的压损却是前者的近两倍。根据实验数据拟合得到了有关参数的准则关系式。

关 键 词:航空、航天推进系统  涡轮叶片  肋化通道  强化传热  总压损失
文章编号:1000-8055(2004)02-0206-07
收稿时间:2003/5/27 0:00:00
修稿时间:2003年5月27日

Influence of Rib's Geometric Parameters upon Heat Transfer and Total Pressure Loss in Grid-Ribbed Channel
ZHANG Bo,JI Hong-hu,ZHANG Jing-zhou,Gao Chao and Wang Ming.Influence of Rib''s Geometric Parameters upon Heat Transfer and Total Pressure Loss in Grid-Ribbed Channel[J].Journal of Aerospace Power,2004,19(2):206-212.
Authors:ZHANG Bo  JI Hong-hu  ZHANG Jing-zhou  Gao Chao and Wang Ming
Institution:ZHANG Bo~1,JI Hong-hu~1,ZHANG Jing-zhou~1,Gao Chao~1,Wang Ming~2
Abstract:The influence of width-to-pitch ratio t/p and width-to-height ratio t/e of ribs upon heat transfer and total pressure loss of rectangular grid-ribbed channel was studied experimentally.Two groups of experimental models were used.The first group was consisted of two ribbed plates with ribs at 45° and -45° to the axis of the channel,respectively,named as 45/45 model.The second group of experimental models was consisted of two plates with rib angle at 45° and,-60° and named as 45/60 model.For these models,t/e varies among 0.25,0.3,0.5,and t/p varies among 0.25,0.33,0.5.The Reynolds numbers varied from 0.5×105 to 1.5×105.The results showed that the models with t/p=0.5 and t/e=0.3 got the best heat transfer enhancement,but also caused highest total pressure drop.The 45/45 model and 45/60 model have similar heat transfer performance,while the latter caused much higher total pressure loss than the former.
Keywords:aerospace propulsion system  turbine blade  ribbed channel  heat transfer enhancement  total pressure loss
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