| 多斜孔冷却方式气动参数对壁温梯度和冷却效率的影响 |
| |
| 引用本文： | 许全宏,徐剑,林宇震,刘高恩.多斜孔冷却方式气动参数对壁温梯度和冷却效率的影响[J].航空动力学报,2008,23(4):647-650. |
| |
| 作者姓名： | 许全宏 徐剑 林宇震 刘高恩 |
| |
| 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： | 针对高温升燃烧室以延长其火焰筒使用寿命为目的,实验研究了多斜孔冷却方式气动参数,如加温比、速度比和主流速度变化对主燃烧室火焰筒壁温梯度和冷却效率的影响.实验结果表明:减小加温比或增大速度比都可以减小壁温梯度的绝对值,同时冷却效率也会增加;当主流进入了自模区后,随着主流速度的增加,壁温梯度的绝对值会减小,冷却效率会增大.
|
| 关 键 词： | 航空、航天推进系统 航空发动机 燃烧室 火焰筒 冷却 多斜孔 壁温梯度 冷却效率 |
| 文章编号： | 1000-8055(2008)04-0647-04 |
| 收稿时间： | 2007/3/28 0:00:00 |
| 修稿时间： | 2007年3月28日 |
Influence of aerodynamic parameter on the temperature gradient and cooling efficiency for effusion wall cooling method |
| |
| XU Quan-hong,XU Jian,LIN Yu-zhen and LIU Gao-en.Influence of aerodynamic parameter on the temperature gradient and cooling efficiency for effusion wall cooling method[J].Journal of Aerospace Power,2008,23(4):647-650. |
| |
| Authors: | XU Quan-hong XU Jian LIN Yu-zhen and LIU Gao-en |
| |
| Institution: | National Key Laboratory on Aero-engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083;National Key Laboratory on Aero-engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083;National Key Laboratory on Aero-engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083;National Key Laboratory on Aero-engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083 |
| |
| Abstract: | As one of the most important factors influencing the combustor life-span,the temperature gradient of the effusion wall,as well as the cooling efficiency were investigated experimentally under the guidance of similarity theory.The effects of the temperature ratio of the main flow to the cooling air,the speed ratio of the cooling air to the main flow and the speed of the main flow were analyzed and discussed.IR thermograph was used to perform local measurements of the surface temperature field.The results reveal that these parameters which are investigated in this paper have strong influence on the temperature gradient and the cooling efficiency. |
| |
| Keywords: | aerospace propulsion system gas turbine engine combustor liner cooling effusion wall temperature gradient cooling efficiency |
| 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 |
|
