Rotating Detonation Combustion Characteristics of Kerosene-Fueled Wide-Area Scramjets

Abstract

Through the method of three-dimensional numerical simulation, the rotating detonation combustion characteristics of kerosene-fueled scramjets in the range of Ma＝3~7 were studied. In the flight condition of Ma=3, due to the poor effect of fuel atomization and evaporation, the detonation combustion of kerosene fuel cannot be realized. In the flight conditions of Ma＝4, 5, 6, with the increase of Mach number, the number of wave heads increases gradually, which are single-wave, three-wave, and five-wave modes, respectively. However, the propagation speed gradually decreases. In the scramjet mode, the liquid fuel has a good effect of atomization and evaporation. Nevertheless, kerosene vapor remains in the flow field to varying degrees and is discharged from the combustion chamber without participating in the reaction. In the flight condition of Ma＝7, the flow field will burn in a stationary detonation mode because the incoming flow is close to CJ velocity.

Keywords

• kerosene
• wide-area scramjet
• rotating detonation
• combustion characteristics