摘要
对液氧 煤油液体火箭发动机的预燃室进行三维湍流流动与燃烧过程的数值模拟。流动采用圆柱坐标系中的三维N S方程组 ,并用k ε双方程湍流模型闭合 ,用同位网格和SIMPLE算法求解 ,源项进行线性化处理以便于收敛 ;离散后的方程采用SIP法求解 ;燃烧采用单步快速不可逆化学反应 ;喷注单元和预燃室头部的喷雾可以考虑液滴颗粒轨道模型 (PSIC)。针对液氧 煤油液体火箭发动机的预燃室建立了耦合计算软件 ,通过考核算例获得燃气流场。
The numerical simulation of 3 D turbulent flow and combustion process was carried out for a pre burner of liquid rocket engine using liquid oxygen /kerosene as propellant.3 D N S equations with k ε equations in the cylindrical coordinate system and SIMPLE method were employed to describe and solve the turbulent flow of the pre burner. The source terms were treated by linearization for more quickly converging. The numerical solution of the algebraic equations system after separation was implemented by the Stone's Strongly Implicit Procedure (SIP). One step fast non reversible chemical reactions were employed in combustion. The software of coupled computation for the pre burner was developed with the reasonable detail reasonable distribution of gas parameters obtained by examination, such as flow, fraction concentration and temperature fields.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2002年第2期121-125,共5页
Journal of Propulsion Technology
基金
国家"八六三"基金资助项目 ( 863 2 3 3 2 )
关键词
液体推进剂
火箭发动机
预燃室
湍流模型
三维流
数值仿真
Liquid propellant rocket engine
Precombustion chamber
Turbulence model
Three dimensional flow
Numerical simulation
