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 MacCormak 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 0.1 MPa. 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 3500 K and high pressure of 2 MPa, and its propagation velocity is about 3430 m/s. It costs less than 0.6 ms when the detonation wave arrives at the exit of a 2 m-long tube. The numerical results agree well with experimental data and provide theoretical basis for engineering design of detonation wave igniter.