Formation and Evolution of the Numerical Air-Breathing Rotating Detonation Fueled by C12H23

Abstract

ABSTRACT Conducting an in-depth study of the characteristics of a two-phase rotating detonation combustor is crucial for developing a new type of air-breathing engine that can be used for wide-range flight. This study established the first full-process air-breathing two-phase rotating detonation numerical combustor, based on published experimental data, using the Euler-Lagrangian method to simulate the complete process of fuel injection, breaking, evaporation, blending, and combustion. The simulation model analyzed the cold flow and the combustion flow field after detonation ignition, providing insight into the interaction mechanism between the two-phase detonation wave and fuel. The simulation results showed that the secondary heat release after the detonation wave was caused by the secondary combustion of unburned droplets. The working frequency of the detonation combustor was found to be 2301 Hz, and the propagation speed was 1228.89 m/s. Compared to the experiment, the simulation showed a deviation of approximately 19.5% in terms of frequency and detonation wave propagation velocity. When the Sauter-mean diameter of the droplets D 32 was around 25 μm, the combustor was able to operate stably. The thrust generated by the engine was approximately 1009 N, and the fuel-specific impulse was about 1767.5 s. These findings have significant theoretical value in designing a two-phase air-breathing rotating detonation combustor and engine.