Numerical study on the flow and combustion characteristics of an advanced vortex combustor fueled by liquid aviation kerosene

To explore the feasibility of using liquid aviation kerosene in an advanced vortex combustor, a comprehensive numerical simulation is conducted to investigate the effects of blockage ratio, fuel injection position, and fuel/air jet momentum flux ratio on the flow and combustion characteristics in this study. The results indicate that as the blockage ratio increases, the vortex structures within the cavity become more stable, leading to an increased combustion efficiency, a more uniform outlet temperature distribution, and decreased CO emissions. The effect of fuel jet position on the overall performance of advanced vortex combustors is minor. As the fuel jet position increases, the total pressure recovery coefficient decreases slightly, while the combustion efficiency and outlet temperature distribution improve marginally. This is because the increased mixing distance between the fuel and mainstream. As the fuel/air jet momentum flux ratio increases, the total pressure recovery coefficient decreases while the combustion efficiency increases. Interestingly, the outlet temperature distribution factor exhibits a trend of first increasing and then decreasing. When the blockage ratio is 0.6, the fuel je position is 30 mm, and the fuel/air jet momentum flux ratio is 163.43, the overall performance of the advanced vortex combustor reaches its optimum. These findings are of great significance for the design and optimization of the advanced vortex combustor fueled by liquid aviation kerosene.