中心锥冷却对喷管腔体红外辐射的抑制作用数值分析

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

1.
南京航空航天大学能源与动力学院, 南京 210016
2.
成都飞机设计研究所总体设计部, 成都 610041

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出版历程
- 收稿日期: 2011-04-19
- 修回日期: 2011-08-29
- 刊出日期: 2012-03-28

Numerical investigation of thermal radiation characteristics of nozzle cavities with center cone cooled

1.
College of Power and Energy, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
System Engineering Department, Chengdu Institute of Aircraft Designing, Chengdou 610041, China

摘要

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.
- 红外抑制 /
- 喷管腔体 /
- 中心锥 /
- 气膜冷却 /
- 冲击冷却
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 3~5μm 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.
- infrared suppressing /
- nozzle cavity /
- cone /
- film cooling /
- impinging cooling

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参考文献(13)

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