冲压增程炮弹发动机补燃室内流场分析  

Analysis on Flow Field in Secondary Combustion Chamber for Ramjet Assisted Range Projectile

作　　者：张磊[1] 周长省[1] 鞠玉涛[1] 

机构地区：[1]南京理工大学机械工程学院,南京210094

出　　处：《系统仿真学报》2008年第20期5480-5483,5488,共5页Journal of System Simulation

摘　　要：采用标准k-ε二方程模型和有限速率/涡团耗散模型对冲压增程炮弹冲压发动机补燃室流场进行了三维数值模拟研究和进行了冲压发动机联管实验。得出了反应物和产物组分、温度等发动机参数的变化趋势,实验研究获得温度和压强随时间变化曲线。结果表明:由于燃气侧喷发动机特殊结构,具有两处扩散火焰峰面,并对压强、温度、成分分布有重要影响。温度和压强随时间的变化曲线相吻合,证实所设计的冲压发动机能正常工作。The flow field in secondary combustion chamber for the ramjet assisted range projectile was numerically simulated by using the standard k-εtwo equation turbulent model and FR/EDC model. The ramjet union experiment was studied. The variation trend of reactant and resultant species,temperature and so on was obtained. The temperature response curve and pressure variation curve were gained in ramjet engine union experiment. The results indicate that it has effect on distribution of temperature,pressure and mass fraction of species that the gas combustion in ramjet has two diffusion flame peaks. It is proved that the gas dual-injection ramjet can work normally,as temperature response curve is consistent with thrust variation curve.

关 键 词：冲压发动机 补燃室 数值模拟 联管实验 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]