摘要
为了研究超燃冲压发动机燃烧室内液体燃料雾化掺混特性,确定影响雾化的关键因素以实现高效燃烧,在超燃冷态雾化实验平台,以纹影法为主,同时辅助以平面激光诱导荧光（PLIF）技术和基于向前散射原理的颗粒直径测量技术,分别对横向射流航空煤油RP-3和水在超声速气流中的流场波系结构、射流穿透深度和诱导弓形激波强度等进行了实验研究,并对射流雾化掺混特性进行了数理分析.结果表明：定义的无量纲参数能够定性分析两种液体横向射流在超音速流场中的变化规律,并得到与实验结果一致的结论;在动压比1.0-3.3范围内,射流穿透深度和诱导弓形激波强度随着动压比和射流速度的增加而增加;表面张力和黏度对超声速射流掺混有重要影响.
In order to study the atomization mixing characteristics of liquid fuel in scramjet combustor as well as determine the key factors influencing the atomization so as to realize efficient combustion,the flow field structure of the shock wave,jet penetration and induced bow shock strength of liquid jet aviation kerosene RP-3 and water in supersonic flow were experimentally studied respectively by mainly using the schlieren method,assisted with planar laser induced fluorescence（ PLIF） technology and particle diameter measurement technology in supersonic combustion cold spray experiment platform. And jet atomization mixing characteristics were mathematically analyzed. It is demonstrated that defined dimensionless parameters could qualitative analyze variation trend associated with both two kinds of liquid jet in supersonic cross flow,and the conclusion is consistent with the experimental result. Within the scope of the dynamic pressure ratio of 1. 0- 3. 3,the jet penetration and induced bow shock strength increases with the increase of dynamic pressure ratio and jet velocity. Surface tension and viscosity have important effects on the supersonic jet mixing.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2015年第12期2356-2362,共7页
Journal of Beijing University of Aeronautics and Astronautics
