论文部分内容阅读
采用计算流体力学的方法,对氢氧火箭发动机推力室的起动过程进行了数值仿真。起动的非定常过程由双时间步方法模拟,燃烧过程由稳态层流火焰面模型模拟,火焰面建库采用6组分8步反应的化学动力学模型。按照地面试车时序进行推力室起动过程仿真,获得了起动过程的建压曲线以及详细的流场建立过程。结果表明,经过点火瞬间压力松弛控制的稳态层流火焰面模型可用于火箭发动机的点火过程动态仿真,仿真得到的压力曲线与试车曲线相比符合良好。
Computational fluid dynamics (CFD) method is used to simulate the starting process of the rocket engine thrust chamber. The unsteady process of starting is simulated by a two-time step method. The combustion process is modeled by a steady-state laminar flame model. The flame surface is constructed using a six-component, eight-step reaction kinetic model. According to the sequence of test run on the ground, the start-up process of thrust chamber was simulated and the pressure-build curve of start-up process and the establishment of detailed flow field were obtained. The results show that steady-state laminar flame surface model controlled by pressure relaxation at ignition moment can be used to simulate the ignition process of rocket engine. The simulated pressure curve is in good agreement with the test curve.