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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 characteristics of liquid fuel atomization and blending in the combustion chamber of scramjet and determine the key factors affecting the atomization in order to achieve high efficiency combustion, Induced fluorescence (PLIF) and particle diameter measurement based on the forward scattering principle, respectively, the horizontal jet jet fuel kerosene RP-3 and water in the supersonic airflow flow field structure, jet penetration depth and induced bow shock intensity Etc. The experimental results show that the defined dimensionless parameters can qualitatively analyze the variation of the two transverse jets in the supersonic flow field and obtain the experimental results Conclusions: The jet penetration depth and induced bow shock intensities increase with the increase of dynamic pressure ratio and jet velocity at the dynamic pressure ratio of 1.0-3.3. The surface tension and viscosity have an important influence on supersonic jet mixing.