Effect of mixing on the Combustion Performance of H2O2/Kerosene Gas-liquid Rotating Detonation

Improving mixing effect to achieve high-intensity rotating detonation is a key research direction in rotating detonation rocket engine technology. The H2O2/kerosene gas-liquid rotating detonation was investigated through theoretical analysis and the three-dimensional numerical simulation method. The influence of relative angle and mass flow rate on the performance of gas-liquid rotating detonation was studied. The results show that the combustor based on H2O2 decomposition gas/kerosene can achieve 97.33% of the theoretical specific impulse of the conventional combustor using only 11% of the characteristic length. When the penetration depth (wd) of the mixing ratio 7 isoline at 20 mm downstream of the injection point exceeds 40%, and the relative angle is acute, the detonation performance can reach a higher level. Within the relative angle range of 90° to about 30°, reducing the relative angle not only improves circumferential mixing but also promotes concentrated energy release of detonation, thereby enhancing the intensity of the detonation. However, excessively small relative angles result in insufficient radial penetration of kerosene jets, leading to detonation wave decoupling. For a given combustor, parasitic deflagration dominates performance under high mass flow rate conditions, while kerosene jet penetration depth dominates under low mass flow rate conditions. This study reveals the influence mechanisms of relative angle and flow rate on gas-liquid rotating detonation, providing significant value for combustor optimization.