针栓式变推力火箭发动机内流场数值仿真研究

Numerical Simulation of Inner Flow Field of a Pintle Injector Variable Thrust Rocket Engine

发动机推力室的工作过程直接影响到发动机的性能,在设计过程中,从理论上分析推力室内的燃烧流动过程具有非常重要。通过数值仿真,可以大大缩短发动机的研制和改进设计周期,减少研制经费。针对自燃推进剂针栓式变推力液体火箭发动机燃烧与流动的特点,借助CFD计算软件FLUENT,采用标准k-ε湍流模型及有限速率化学反应模型,对采用针栓式喷注器的变推力液体火箭发动机的推力室喷雾燃烧过程进行了数值仿真。计算结果得到了压强分布,温度分布,生成物的摩尔分数分布,粒子轨迹分布、流强、混合比分布以及流动马赫数分布等,并对流场结构和影响发动机性能的喷注器参数进行了分析。数值计算结果可为变推力发动机喷注器和推力室的设计和优化提供参考。

The performance of rocket engine is affected by working process of thrust chamber. Theory analysis on working process of thrust chamber is of great significance. The development and design cycle and cost of rocket engine can be cut down greatly with the support of numerical simulation. In view of the traits of combustion and flow of self - ignition propellant and with the support of powerful calculational ability of computer and Fluent of CFD software, an integrative simulation research of the pintle variable thrust liquid propellant rocket engine was developed. Numerical simulation of spray combustion flow field of a variable thrust rocket engine with flux - oriented injector was done. The distributions of pressure, temperature, molar fraction of product, flow Mach number, mixed ratio and flow intensity were attained. By comparing the calculational results, the effects of structure parameters and working condition etc. on whole performance of variable thrust rocket engine were analysed. The results also provided theoretic ref- erences and valuable information for the design and optimization of future variable thrust rocket engine.