| 涡轮叶片尾缘通道中纵向肋对换热特性的影响 |
| |
| 引用本文： | 陶智,袁星,丁水汀,徐国强,邓宏武.涡轮叶片尾缘通道中纵向肋对换热特性的影响[J].航空动力学报,2008,23(7):1189-1193. |
| |
| 作者姓名： | 陶智 袁星 丁水汀 徐国强 邓宏武 |
| |
| 作者单位： | 北京航空航天大学能源与动力工程学院,航空发动机气动热力重点实验室,北京,100083 |
| |
| 摘 要： | 采用冷凝水蒸汽的实验方法,测量三种不同类型纵向肋对叶片尾缘通道的换热影响.系统的研究了孔径为2.6 mm的带孔平肋,波峰孔径为3 mm、波谷孔径为2.2 mm的波浪肋,和不带孔平肋之间的换热和流阻比较,实验结果表明:当Re<20 000时,波浪肋的换热优于带孔平肋,当Re>50 000时,波浪肋换热不及不带孔平肋.且波浪肋流阻远低于不带孔平肋和带孔平肋.
|
| 关 键 词： | 换热特性 涡轮叶片尾缘通道 隔板 流阻 |
| 收稿时间： | 2007/6/21 0:00:00 |
| 修稿时间： | 4/8/2008 12:00:00 AM |
Effect of different clapboards structure in turbine blade trailing edge complex passages on heat transfer characteristics |
| |
| TAO Zhi,YUAN Xing,DING Shui-ting,XU Guo-qiang and DENG Hong-wu.Effect of different clapboards structure in turbine blade trailing edge complex passages on heat transfer characteristics[J].Journal of Aerospace Power,2008,23(7):1189-1193. |
| |
| Authors: | TAO Zhi YUAN Xing DING Shui-ting XU Guo-qiang and DENG Hong-wu |
| |
| Institution: | National Key Laboratory on Aero-engines, School of Jet Propulsion, Beijing Universty of Aeronautics and Astronautics, Beijing 100083, China;National Key Laboratory on Aero-engines, School of Jet Propulsion, Beijing Universty of Aeronautics and Astronautics, Beijing 100083, China;National Key Laboratory on Aero-engines, School of Jet Propulsion, Beijing Universty of Aeronautics and Astronautics, Beijing 100083, China;National Key Laboratory on Aero-engines, School of Jet Propulsion, Beijing Universty of Aeronautics and Astronautics, Beijing 100083, China;National Key Laboratory on Aero-engines, School of Jet Propulsion, Beijing Universty of Aeronautics and Astronautics, Beijing 100083, China |
| |
| Abstract: | The effect of three different dividers on the heat transfer of turbine blade trailing passage was investigated experimentally.The condensation vapor method was used in the experiment.Heat transfer and hydrodynamic drag were compared among the straight divider with hole of 2.6 mm in diameter,waved divider with hole of 3 mm in diameter on wave crest and hole of 2.2 mm in diameter on trough,and straight divider without hole.The waved divider gave better heat transfer than the straight divider with hole when the Re<20 000.For the case of Re>50 000,the waved divider showed worse heat transfer than the straight divider without hole.The drag of the waved divider was far less than that of the straight divider with or without hole. |
| |
| Keywords: | heat transfer characteristics turbine blade trailing edge dividers flowing resistance |
| 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 |
|
