基于气动斜坡/燃气发生器的超燃燃烧室实验  

Experiments of integrated aeroramp injector/gas-portfire in a supersonic combustion

作　　者：史新兴[1] 韦宝禧[2] 闫明磊[2] 徐旭[2] 李岩[3] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]北京航空航天大学宇航学院,北京100191 [3]北京机电工程研究所,北京100074

出　　处：《推进技术》2010年第5期549-554,共6页Journal of Propulsion Technology

摘　　要：为探索超燃冲压发动机燃烧室中的新的火焰稳定技术,提出了一种新型被动式燃料掺混增强技术—气动斜坡与燃气发生器组合燃料喷注技术,并在北航直联式超燃试验台对这种新型组合喷注器开展了超声速燃烧的试验研究。在模拟飞行马赫数5(燃烧室入口Ma=2),进行了冷流试验,获得了喷注器附近流场的纹影图像。本文设计了4种气动斜坡喷注单元,以乙烯为燃料,在约1kg/s试验气流中开展了多级喷注单元组合的超声速燃烧试验,在当量比0.78～1.22范围内实现了稳定的燃烧,经冲量分析法计算得到不同组合结构的燃烧效率为0.54～0.72。试验结果验证了这种新方案作为超然冲压发动机火焰稳定装置的可行性。The need for a new technology of flame stable to supersonic mixing flow has led to the development of many different styles of fuel injection. A novel integrated flush-wall aeroramp fuel injector/gas-portfire for supersonic combustion applications was developed and tested at direct-connected test rigs of Beijing University of Aeronautics and Astronautics. 4 different types of aerodynamic ramp injection panel were tested. Color schlieren visualization pictures were taken in the vicinity of the injectors to obtain a qualitative assessment of the injector flowfields. The stable combustion was obtained under the conditions such as flight Mach number 5 （combustor inlet Math number 2）, ethylene equivalence ratio 0.78 - 1.22 conditions in about 1 kg/s heated air flow. One-dimensional performance analysis of the test data indicated the combustion efficiencies were 0.54 - 0.72. It was concluded that this integrated aerodynamic ramp injector/gas-portfire for supersonic combustion is applicable.

关 键 词：气动斜坡 燃气发生器 超燃冲压发动机 超声速燃烧 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]