| 用短周期风洞进行涡轮叶片传热实验的初探 |
| |
| 引用本文： | 李静美,赵润民,王吉南.用短周期风洞进行涡轮叶片传热实验的初探[J].航空动力学报,1987,2(1):18-22,89. |
| |
| 作者姓名： | 李静美 赵润民 王吉南 |
| |
| 作者单位： | 中国科学院力学研究所 |
| |
| 摘 要： | 本文介绍了短周期激波叶栅风洞的结构,原理和实验模型,以及在来流条件为Ma入口=0.21和0.15,Re∞/L=1×107,TO/TW=2.2时,进行涡轮叶片测压和传热实验的初步结果。结果表明10毫秒的实验时间是足够的,目前的实验方案完全可行。
|
| 收稿时间： | 7/1/1986 12:00:00 AM |
APPLICATION OF SHOCK TUNNEL TO HEAT TRANSFER EXPERIMENTS ON TURBINE BLADE |
| |
| Li Jingmei,Zhao Runming and Wang Jinan.APPLICATION OF SHOCK TUNNEL TO HEAT TRANSFER EXPERIMENTS ON TURBINE BLADE[J].Journal of Aerospace Power,1987,2(1):18-22,89. |
| |
| Authors: | Li Jingmei Zhao Runming and Wang Jinan |
| |
| Institution: | Institute of Mechanics, Academia sinica |
| |
| Abstract: | Transient wind tunnels and their supplementary instrumentation have been used to examine the flow and heat transfer around hypersonic vehicles. The purpose of this paper is to describe their application to turbine cascade testing and refinements of its heat transfer measurement techniques. |
| |
| Keywords: | |
| 本文献已被 CNKI 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 |
|
