壁面嵌入式凹槽用于圆燃烧室的初步实验研究  

Preliminary experimental study of in-wall cavity applied to a circular combustor

作　　者：王洪亮 王铁军 任虎 WANG Hongliang;WANG Tiejun;REN Hu(Aerospace Technology Institute,CARDC,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心空天技术研究所,四川绵阳621000

出　　处：《推进技术》2025年第1期142-149,共8页Journal of Propulsion Technology

摘　　要：为了探索壁面嵌入式凹槽在圆截面燃烧室的适用性,在模拟来流马赫数6.5,燃烧室入口马赫数3.1,总温1660 K条件下,以液态煤油为燃料,开展了带壁面嵌入式凹槽的圆截面直连式燃烧室点火、燃烧实验,使用聚焦拍摄技术获得燃烧室内点火及火焰维持与传播等流场信息,分析了煤油当量比(ER)、凹槽扇角(θ)、煤油喷注位置变化对煤油点火、火焰维持及火焰传播的影响特性,与传统全圆周凹槽进行了对比。通过实验可以得到以下结论:(1)在壁面嵌入式凹槽底壁喷注煤油,不同θ及ER条件下均可点火,但点火及火焰维持能力有差异。(2)在壁面嵌入式凹槽上游喷注煤油时,不同θ条件下均可实现稳定燃烧。(3)相同θ条件下,从壁面嵌入式凹槽上游喷注时煤油燃烧效果更好。当前研究结果显示,壁面嵌入式凹槽应用于圆截面超声速燃烧室具有一定潜力,但还需要进行优化与改进并开展实验验证。Ignition and combustion experiments are conducted on a kerosene-fueled direct-connected combustor for free flow of Mach 6.5(combustor entrance Mach 3.1)and total temperature 1660 K to research the applicability of in-wall cavity in a circular cross-section combustor.The flow-field images of kerosene ignition,flame maintenance and propagation are obtained by focusing shoot,the effects of equivalent ratio(ER),fanshaped angle between two adjacent cavities(θ)and the kerosene ignition position on the flow-field are analyzed and compared with those of the combustor with traditional circular cavity.Conclusions can draw as follows:(1)Kerosene can be ignited at differentθand ER when injected from the bottom wall of the in-wall cavity with different flame maintenance.(2)Steady combustion are obtained for differentθwhen injected from the upstream wall of the in-wall cavity,but the variation ofθof this case has less influence on the kerosene combustion compared with those injected from the bottom wall of the in-wall cavity.(3)Combustion effect of kerosene is better when injecting from the upstream of the in-wall cavity with sameθ.The in-wall cavity has some application potential for circular cross-section combustor but optimization and improvement and experiment are needed for further study.

关 键 词：超声速燃烧室 壁面嵌入式凹槽 圆燃烧室 聚焦拍摄 点火 

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]