狭长出口弯曲混合管一体化红外抑制器红外特性分析  

Research on Infrared Suppressor Characteristics of Integrating the Fuselage Utilizing Nozzle Ejection

作　　者：唐正府[1] 张靖周[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《燃气涡轮试验与研究》2007年第2期37-40,共4页Gas Turbine Experiment and Research

基　　金：武器装备预研基金资助项目(51410040304HK0201)

摘　　要：将发动机热端部件-弯曲混合管埋入尾机身模型内部并引入旋翼下洗气流与热排气强迫混合,这是一种新型的一体化红外抑制器结构。通过数值模拟和实验分析比较了波瓣喷管与旋翼下洗的混合流场,并且获得了不同旋翼下洗气流作用下模型壁面的红外辐射光谱。结果表明:在弯曲混合管出口存在低压区,使得周围冷却气流在压差的驱动下被不断吸入混合;模型的红外辐射主要以8～14μm波段的红外辐射为主,随着旋翼下洗气流速度的增加,模型的红外辐射强度逐渐降低。A new configuration of infrared suppressor embedding the hot components into the back of the fuselage was presented, which ejected the ambient air into core flux utilizing lobed nozzle at the same time entrained the downwash to forced mixing. Infrared radiation spectrum of the model wall was achieved at the different downwash velocity, and mixing flow field was compared by numerical computation with experimental data. The results showed that cool air was pumped into mixing because of the lower pressure region at the exit of the curved mixing duct; infrared radiation mainly come from the wave band of 8-14 μm, and infrared spectral radiant intensity was reduced by increasing the rotor downwash velocity.

关 键 词：隐身技术 波瓣喷管 弯曲混合管 红外抑制器 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]