| 涡轮叶冠间隙流动特性实验 |
| |
| 引用本文： | 喻雷,常海萍.涡轮叶冠间隙流动特性实验[J].航空动力学报,2011,26(12):2772-2776. |
| |
| 作者姓名： | 喻雷 常海萍 |
| |
| 作者单位： | 南京航空航天大学能源与动力学院,南京,210016 |
| |
| 摘 要： | 针对叶冠腔内有冷却气流的转子叶片叶冠,通过改变主流雷诺数、前后孔岀流比、叶尖间隙等参数得到静止状态下叶冠间隙流动的总压损失系数.实验结果表明：增大主流雷诺数与前孔岀流比,叶冠总压损失系数增大;减小叶尖间隙,总压损失系数也增大,小叶尖间隙下,总压损失系数随主流雷诺数与前孔岀流比增长更快,而后孔岀流比对叶冠总压损失系数影响...
|
| 关 键 词： | 叶冠 间隙流动 雷诺数 岀流比 总压损失系数 |
| 收稿时间： | 1/7/2011 12:00:00 AM |
| 修稿时间： | 2011/5/11 0:00:00 |
Experiment of tip leakage flow characteristics in turbine shroud |
| |
| YU Lei and CHANG Hai-ping.Experiment of tip leakage flow characteristics in turbine shroud[J].Journal of Aerospace Power,2011,26(12):2772-2776. |
| |
| Authors: | YU Lei and CHANG Hai-ping |
| |
| Institution: | College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
| |
| Abstract: | For rotor shrouded blade with cooling air,the total pressure loss coefficient of tip leakage flow in stationary state was investigated in different mainstream Reynolds numbers,outflow ratio of the former and the latter holes,tip clearance at so on.The results show:(1)total pressure loss coefficient increases as mainstream Reynolds number and outflow ratio of the former hole increase;(2)total pressure loss coefficient also increases by reducing tip clearance,which increases faster with the mainstream Reynolds number and outflow ratio especially in small tip clearance;(3)outflow ratio of the latter hole has litter impact on total pressure loss coefficient. |
| |
| Keywords: | shroud tip clearance Reynolds number outflow ratio total pressure loss coefficient |
| 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 |
|
