Experimental Study on Combustion Modes in a Supersonic Combustor

Survey on the mode transition technique in combined cycle propulsion systems

“…Bao et al [1] have also found that different combustor modes occur with different equivalence ratio through the analysis of the pressure distribution along the combustor. Masumoto et al [42] have successfully proposed a simple model to predict the minimum combustor length for the supersonic or dualmode combustion, and four operating modes have been observed, namely non-ignition, weak, supersonic and dual-mode combustion [27,28].…”

Experimental study on Dynamic Characteristics of Combustion Mode Transition

“…Scramjet mode combustion zone appeared only in the cavity; in contrast, the spread of the ramjet mode combustion is significantly larger than the former. Ryou et al [10] investigated the effect of combustor length and total temperature on combustion modes, and suggested the minimum combustor length to attain the supersonic or dual-mode combustion.…”

Influence of Plasma on the Combustion Mode in a Scramjet

“…Traditional passive flame stabilization methods (such as cavity and plate flame stabilization) stabilize a flame in a vortex structure to achieve the purpose of stable combustion, which is dominated by supersonic inflow and formed passively. The interaction between the instability of the inflow and the combustion affects the flame structure [7][8][9][10][11]. Especially in the process of acceleration, it has been pointed out that the combustor inlet flow acceleration will lead to the transition of the flame mode [12,13].…”