Abstract
Two-dimensional numerical simulations on the two-phase rotating detonation wave of a stoichiometric ratio of the air-octane mixture by the discrete phase model are performed. The propagation process and stable flow field of the rotating detonation wave under nonpremixed and nonuniform injection conditions are analyzed. The effects of air injection total temperature and fuel injection inhomogeneity on the gas-liquid two-phase rotating detonation wave are investigated. The results show that under the same conditions, with the increase in the total temperature of air injection, the peak temperature, height, and propagation velocity of the detonation wave increase, but the peak pressure of the detonation wave decreases. The larger the jet spacing, the more pronounced the detonation wave is disturbed by the fuel jet. As the fuel jet spacing increases, the detonation wave propagation velocity decreases, but the peak temperature and peak pressure of the detonation wave increase. For the case of a jet spacing of 10 mm, the detonation wave cannot propagate when the air total temperature is 300 K, but the detonation wave can be stably propagated when the air total temperature is increased to 600 K. The stable propagation boundary of the rotating detonation wave with the combined action of the air total temperature and the jet spacing is obtained.
Highlights
Detonation is a high efficient way of premixed combustion heat, which has the thermodynamic advantage of energetic and fast propagation, and has received much attention in the field of aerospace propulsion
With a jet spacing of 10 mm, the detonation wave cannot propagate when the air total temperature is lower than 300 K, but the detonation wave can be stably propagated when the air total temperature is increased to 600 K
Numerical simulations on liquid octane and air two-phase detonation are performed to study the influence of the air injection total temperature of 300–800 K and the fuel injection spacing of 0–14 mm
Summary
Detonation is a high efficient way of premixed combustion heat, which has the thermodynamic advantage of energetic and fast propagation, and has received much attention in the field of aerospace propulsion. The propulsion system based on detonation includes three types: pulse detonation engine (PDE1–3), oblique detonation wave engine (ODE4), and rotating detonation engine (RDE5,6). Compared to the conventional constant pressure combustion, detonation combustion has the advantages of lower entropy increase and higher thermal cycle efficiency. Compared to the pulse detonation engine, RDE can continuously work and does not need repeated ignition naturally, which can solve the difficult problem of the high frequency repeating ignition of PDE. The RDE has a promising application in the field of aerospace, weaponry, navigation, and other thermal engineering areas, and they have attracted considerable attention in recent years. Some researchers from many countries, including Smirnov et al.,[7] Frolov et al.,[8] Hoke et al.,[9,10] Anand et al.,[11] Wolanski et al.,[12] Gaillard et al.,[13] Ma et al.,[14,15] Nakagami et al.,[16] Li et al.,[17] and Bluemner et al.,[18] have carried out related investigations
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