摘要
为研究液氢/液氧发动机燃烧尾焰射流流动特点,采用耦合了Realizable k-ε湍流模型、液氢/液氧单步化学反应的N-S方程,化学反应速率采用湍流脉动机制和Arrhenius机制控制,运用PISO算法对液氢/液氧火箭发动机在地面发射阶段的燃烧尾焰射流流场进行了一体化仿真计算,得到了液氢/液氧发动机燃烧尾焰射流近场激波系结构,并与理论分析结果进行对比,证明了算法的有效性和正确性。分析了燃烧尾焰压力场的动态形成过程,捕捉到尾焰半球形冲击波的发展过程,并认为冲击波为正激波且进行匀速传播。获得了尾焰流场各项参数的分布情况,为开展燃烧尾焰射流的辐射计算提供数据基础。
To research the burning plume exhaust flow field of LH2/LOX rocket engine, the N-S equation is adopted, in which Realizable model and the LH2/LOX one-step chemical reaction are coupled. The chemical reaction rate is controlled by Eddy-Dissipation and Arrhenius Mechanism. The integration simulation calculation of the LH2/LOX rocket engine plume during the period of launch was performed with PISO algorithm, by which the shock wave system structure of the plume jet flow in the near field is acquired and compared with the theoretical analysis results. The effectiveness and correctness of this algorithm is proved. The dynamical forming process of the burning plume pressure field is analyzed, the developing process of the hemispheric impact wave has been gain, and it is considered that the impact wave is a normal shock wave and moves in the uniform velocity. The distribution of different parameters in the plume field has been acquired, which can provide a data foundation for the study on radiation of the plume jet flow.
出处
《火箭推进》
CAS
2015年第5期43-48,共6页
Journal of Rocket Propulsion
基金
国家自然科学基金(51206185
91441123)
关键词
尾焰
液氢/液氧火箭发动机
单步化学反应
冲击波
数值仿真
exhaust plume
LH2/LOX rocket engine
one-step chemical reaction
shock wave
numerical simulation
