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.
Numerical investigation was performed on the infrared suppress characteris- tics 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 de- creased by 21.1% and 46.2% respectively, using only 1.6% of the secondary gas. The ra- diation of nozzle cavity in 3~5/~m 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.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2012年第3期560-565,共6页
Journal of Aerospace Power
关键词
红外抑制
喷管腔体
中心锥
气膜冷却
冲击冷却
infrared suppressing
nozzle cavity
cone
film cooling
impinging cooling
