Study on Total Pressure Loss and Flow Field Structure of Double Vortex Combustor

摘要

Experimental and numerical analysis have been conducted to investigate the flow field structure and total pressure loss of the double vortex combustor. The combustor is used as interstage turbine burner and uses evaporating tubes as fuel injection device. The experimental results indicate that mach number of inlet is the most important influence factors. At the same mach number, the mainstream temperature and fuel flow rate has little influence on the total pressure loss. Under the same condition of flow parameters, the structure size of cavity has influence on the total pressure loss. Streamline diagrams are showing the connection between total pressure loss and flow field structure. Obtained results can be used for structural optimization of vortex combustor.