| 主燃烧室冲击/发散双层壁冷却方式壁温验证试验研究 |
| |
| 引用本文： | 许全宏,林宇震,刘高恩.主燃烧室冲击/发散双层壁冷却方式壁温验证试验研究[J].航空动力学报,2005,20(2):197-201. |
| |
| 作者姓名： | 许全宏 林宇震 刘高恩 |
| |
| 作者单位： | 北京航空航天大学,航空发动机气动热力国防科技重点实验室,北京,100083 |
| |
| 摘 要： | 为检验冲击/发散双层壁冷却方式在真实工况下的冷却效果,在单头部高温高压燃烧试验台上对3种结构的冲击/发散双层壁实验件进行单头部高温高压综合验证考核试验。实验参数模拟推比10一级发动机燃烧室设计点参数进行综合考核验证。实验结果表明冲击/发散双层壁火焰筒冷却气量约为20%,总冷却效率在0.85～0.96之间,壁温低于1150K。
|
| 关 键 词： | 航空、航天推进系统 航空发动机 主燃烧室 冲击 发散 冷却 |
| 文章编号： | 1000-8055(2005)02-0197-05 |
| 收稿时间： | 3/4/2004 12:00:00 AM |
| 修稿时间： | 2004年3月4日 |
Rig Test of Impingement/Effusion Double Wall Cooling Methods for the Main Combustor |
| |
| XU Quan-hong,LIN Yu-zhen and LIU Gao-en.Rig Test of Impingement/Effusion Double Wall Cooling Methods for the Main Combustor[J].Journal of Aerospace Power,2005,20(2):197-201. |
| |
| Authors: | XU Quan-hong LIN Yu-zhen and LIU Gao-en |
| |
| Institution: | National Key Laboratory of Aircraft Engine,Beijing University of Aeronautics and Astronautics,Beijing100083,China;National Key Laboratory of Aircraft Engine,Beijing University of Aeronautics and Astronautics,Beijing100083,China;National Key Laboratory of Aircraft Engine,Beijing University of Aeronautics and Astronautics,Beijing100083,China |
| |
| Abstract: | For the investigation, a combustor sector with one burner head was used.Three different test pieces with impingement/effusion double wall cooling were selected for testing under high-temperature and high-pressure working conditions,which were equivalent to that of engines with a thrust/weight ratio of 10.The liner temperatures were measured using thermocouples.The test result shows that the amount of cooling airflow of double-layer wall combustor is 20% of the overall airflow,and the overall cooling effectiveness is in the range of 0.85 to 0.96.The wall temperatures of all test pieces are lower than 1 150 K. |
| |
| Keywords: | aerospace propulsion system aero-engine main combustor impingement cooling effusion cooling |
| 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 |
