| 中心锥冷却对喷管腔体红外辐射的抑制作用数值分析 |
| |
| 引用本文： | 张勃,吉洪湖,张宗斌,罗明东,林兰之.中心锥冷却对喷管腔体红外辐射的抑制作用数值分析[J].航空动力学报,2012,27(3):560-565. |
| |
| 作者姓名： | 张勃 吉洪湖 张宗斌 罗明东 林兰之 |
| |
| 作者单位： | 南京航空航天大学 能源与动力学院, 南京 210016;南京航空航天大学 能源与动力学院, 南京 210016;成都飞机设计研究所 总体设计部, 成都 610041;成都飞机设计研究所 总体设计部, 成都 610041;南京航空航天大学 能源与动力学院, 南京 210016 |
| |
| 摘 要： | 航空发动机高温部件是发动机3~5μm上的重要红外辐射之一,对高温部件之一的中心锥的红外抑制技术进行了数值研究.在中心锥前端布置气膜缝槽,缝槽几何参数经过优化设计,将部分外涵低温气流经过支板引入中心锥,对支板和锥体壁面形成冲击冷却,在锥体前端形成气膜覆盖,使得支板与中心锥壁面得到了有效冷却,两者平均温度分别降低21.1%和46.2%,冷却气量约为外涵流量的1.6%.喷管腔体3~5μm波段上红外辐射得到有效抑制,喷管正后方红外辐射相比原型喷管降低30%,0°~45°范围内红外辐射则明显降低.
|
| 关 键 词： | 红外抑制 喷管腔体 中心锥 气膜冷却 冲击冷却 |
| 收稿时间： | 2011/4/19 0:00:00 |
| 修稿时间： | 2011/8/29 0:00:00 |
Numerical investigation of thermal radiation characteristics of nozzle cavities with center cone cooled |
| |
| ZHANG Bo,JI Hong-hu,ZHANG Zong-bin,LUO Ming-dong and LIN Lan-zhi.Numerical investigation of thermal radiation characteristics of nozzle cavities with center cone cooled[J].Journal of Aerospace Power,2012,27(3):560-565. |
| |
| Authors: | ZHANG Bo JI Hong-hu ZHANG Zong-bin LUO Ming-dong and LIN Lan-zhi |
| |
| Institution: | College of Power and Energy, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Power and Energy, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;System Engineering Department, Chengdu Institute of Aircraft Designing, Chengdou 610041, China;System Engineering Department, Chengdu Institute of Aircraft Designing, Chengdou 610041, China;College of Power and Energy, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
| |
| Abstract: | Numerical investigation was performed on the infrared suppress characteristics of the nozzles with and without cone cooled.In the former,cone and blade were cooled by secondary channel gas,and the temperatures of blade and cone walls were effectively decreased by 21.1% and 46.2% respectively,using only 1.6% of the secondary gas.The radiation of nozzle cavity in 3-5 μm was suppressed effectively,the radiation in the small view angle range from behind the nozzle decreased obviously,and the radiation decreased by 30% from straight behind the nozzle compared to the nozzle without cone cooling. |
| |
| Keywords: | infrared suppressing nozzle cavity cone film cooling impinging cooling |
| 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 |
|
