爆震波点火器管路传播过程数值模拟

为了进一步研究液体火箭发动机爆震波点火器的工作过程，结合实际试验发动机用爆震波点火器的工作条件，在混合比为3，初始氢氧混气压力为0．1MPa情况下，采用常用的两步显式MacCormak差分格式和有限速率化学反应动力模型，对爆震波点火器管路中爆震波的传播过程进行了数值模拟，研究了爆震波形成后在一维管路中传播特性及性能参数。从数值模拟结果来看，稳定传播的爆震波温度可达3500K，压力达到2MPa，其传播速度可达3430m／s，从爆震波形成到其传播到2m距离的出口，用时不到0．6ms。并与试验结果进行了对比分析，数值模拟结果和试验结果符合很好，为爆震波点火器的工程设计提供了理论依据。

Numerical simulation of detonation propagation in tube of detonation wave igniter

To investigate the process of detonation wave igniter of liquid rocket engine, one-dimensional reacting flow and finite reaction velocity model were used and the two-step explicit MacConnak scheme is adopted to numerically simulate the detonation wave propagation in the tube of the detonation wave igniter, with the factual experimental engine condition in which H2/O2 mixture ratio is about 3 and the initial pressure is 0.1MPa. The characteristics of detonation wave in a one-dimension tube with detonation wave formed were studied. The numerical results show that, the stable detonation wave has a high temperature of 3500K and high pressure of 2 MPa, and its propagation velocity is about 3430m/s. It costs less than 0. 6ms when the detonation wave arrives at the exit of a 2m-long tube. The numerical results agree well with experimental data and provide theoretical basis for engineering design of detonation wave igniter.