MCGA-assisted ignition process and flame propagation of a scramjet at Mach 2.0

Abstract

The ignition process and flame propagation with ethylene fuel in cavity-stabilized scramjet by a Multi-Channel Gliding Arc (MCGA) at Mach 2.0 were investigated. Effects of equivalence ratios on the MCGA-assisted ignition process and flame propagation of the scramjet were recorded by two high-speed cameras from different view angles. The discharge characteristics of MCGA are also collected synchronously with the high-speed cameras. The distributions of temperature, velocity, and equivalence ratios in non-reactive flows of the cavity were simulated by Reynolds Averaged Navier-Stokes (RANS) model. The results show that MCGA can achieve reliable ignition with the Global Equivalence Ratios (GER) between 0.06 and 0.17. The ignition process is composed of flame kernel generation, flame development, and stable combustion. The time from flame kernel generation to the establishment of global flame decreases as GER decreases from 0.17 to 0.08. In the streamwise direction, the flame first develops to the Cavity Leading Edge (CLE) because of the influence of the cavity recirculation zone and then uplifts into the cavity shear layer, and finally develops to the Cavity Trailing Edge (CTE). In the spanwise direction, the flame width is less than 50% of the width of the cavity before developing to CLE and begins to develop towards the two sides of the combustor after reaching CLE, which is affected by the angular recirculation zone on both sides of CLE. The ignition processes by MCGA in the scramjet combustor are significantly affected by local distributions of equivalence ratios and velocity in the cavity.