摘要
对氢/氧气-气和气-液同轴剪切式单喷注器进行了燃烧流动的仿真研究.采用带化学反应的湍流Navier-Stokes方程和颗粒轨道模型描述发动机内部喷雾两相燃烧流动过程,气相化学反应速率都由Ar-rhenius公式计算.对典型气-气燃烧和气-液燃烧仿真结果进行了比较,结果表明气-气燃烧完成长度相对气-液燃烧更长;并进行了同轴喷注器关键参数对两种燃烧流场的影响的仿真和分析比较,得到喷注流量和动量比均为影响两类型喷注器燃烧流场的关键因素,且这两因素对燃烧完成长度的影响趋势是完全相同的,而喷注速度对两类型喷注器燃烧流场影响程度都较小.
Single-element shear-coaxial GH2/GO2 and GH2/LOX injectors were numerically simulated.Two-phase turbulent combustion process of GH2/LOX was simulated with chemical Navier-Stokes equations and discrete particle model.Chemical reaction was calculated with Arrhenius formulation.GH2/GO2 and GH2/LOX combustion flowfields and the influences of some key design parameters on two types of fields were obtained.The combustion completion length of GH2/GO2 injector is longer.The injection flowrate and momentum ratio are key parameters for the both types of injectors,and the influence tendencies of these two parameters are the same.The injection velocity is less influential to both types of injectors.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第6期1401-1406,共6页
Journal of Aerospace Power
基金
国家高技术基金项目(2007AA702*)
关键词
气-气燃烧
气-液燃烧
喷雾燃烧
全流量补燃循环
数值仿真
gas-gas combustion
spray combustion
gas liquid combustion
full flow stage combustion（FFSC） cycle
numerical simulation
