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为了探索RBCC(Rocket Based Combined Cycle)亚燃模态条件下掺混燃烧性能,对多种工况进行了数值计算。对比分析了各工况下的燃烧室压力、掺混反应效率、总压损失等参数来分析燃烧室内部特性的变化。从数值模拟的研究中可以发现:由于RBCC亚燃模态的特点,一次火箭高温羽流,使得喷注的燃料能够有效地雾化蒸发,通过支板的混合增强作用能有效地提高煤油燃料的掺混能力,凹腔又适当的延长了煤油在燃烧室的停留时间,形成有效的火焰稳定区域,两种有效的火焰稳定方式的结合能实现液体燃料稳定有效的燃烧,而且双凹腔前后组合也能提高燃料的掺混燃烧能力。从计算中还可以发现,合理地布置支板与凹腔的相对位置能提高燃料的掺混反应效率,实现燃料的充分燃烧,并对燃烧性能提高有明显的帮助。
In order to explore the mixed combustion performance under the RBCC (Rocket Based Combined Cycle) sub-combustion mode, a variety of operating conditions were numerically calculated. The combustion chamber pressure, mixing reaction efficiency, total pressure loss and other parameters were analyzed to analyze the changes of the internal characteristics of the combustion chamber. From the numerical simulation, it can be found that due to the characteristics of the RBCC sub-combustion mode, a rocket’s high-temperature plume enables the injected fuel to atomize and evaporate effectively. The mixing enhancement of the support plate can effectively increase the kerosene fuel Blending cavity, and the cavity is appropriate to extend the kerosene residence time in the combustion chamber, the formation of an effective flame stability zone, the combination of two effective flame stabilization can be stable and effective liquid fuel combustion, and dual-cavity front and rear combination It also improves the blending and fueling ability of the fuel. It can also be found from the calculation that a reasonable arrangement of the relative positions of the support plate and the cavity can improve the efficiency of the fuel blending reaction, achieve full combustion of the fuel, and obviously help to improve the combustion performance.