摘要
设计了适用于某驻涡燃烧室模型的喷油杆,对该喷油杆进行了冷态雾化试验,在不同的气液比、不同的气体和液体压力下研究了喷油杆的雾化性能.通过计算流体动力学(CFD)方法对驻涡燃烧室进行了冷态和热态的数值模拟,得到了燃烧室内部的速度场、温度场和质量分数分布.计算结果表明:该燃烧室设计合理,结构紧凑,燃料燃烧充分,凹腔试验件的壁温分布较为理想.得到了总压损失和出口温度分布的变化规律:燃烧室的总压损失略偏大,出口温度分布较为均匀.并对出口温度分布的规律进行了试验验证,研究结果可以为驻涡燃烧室的工程应用提供参考.
A fuel injector was designed for a certain type of trapped vortex combustor. Then, experiments were conducted to check its atomizing performance under various conditions, including different gas to liquid ratios, gas pressures and liquid pressures. The cold and hot simulations of the combustor were conducted to study the performance, and the velocity field, the temperature field and mass fraction distribution of the combustor were obtained. The simulation results show that the combustor is reasonably designed with compact structure and high combustion efficiency. The wall temperature distribution of the cavity is ideal. The changing regularity of the pressure loss and the outlet temperature distribution were obtained by numerical simulation and experimental research. The total pressure loss of the combustor is a bit larger and the temperature distribution of outlet is uniform. The results can provide relevent reference for the engineering application of the trapped vortex combustor.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2013年第5期1134-1141,共8页
Journal of Aerospace Power
关键词
驻涡燃烧室
燃烧性能
出口温度分布
凹腔
数值模拟
trapped vortex combustor
combustion performanceoutlet temperature distribution
cavity
numerical simulation
