NUMERICAL INVESTIGATION OF STRUT LIQUID INJECTION UNDER HYPERSONIC FLOW

The detonation in the oblique detonation engine combustion chamber is premixed combustion. Fuel premixing in the engine inlet is the prerequisite and key to the operation of the oblique detonation engine. Most research focused on gas phase fuels, but there are fewer studies on liquid fuels for applications. The interaction between hypersonic flow and liquid is a complex physical flow process. There are many influencing parameters of gas-liquid interaction, making the research more complex. This paper uses numerical simulation methods to solve the two-dimensional compressible Reynolds time-averaged Navier-Stokes (RANS) equation, combined with the CLSVOF (coupled level set and volume of fluid) phase interface capture method. The interaction model between hypersonic incoming flow and liquid jet is considered. The influence of the incoming Mach number, jet angle and velocity on liquid fragmentation, transport and mixing was systematically studied. The results show that under the action of hypersonic flow, the liquid column moves in the flow direction affected by the pressure gradient. The liquid phase has five evolving forms: liquid column, continuous liquid film, liquid filament shape, liquid block shape and gas-liquid mixed layer. The angle and velocity of the jet have an impact on the characteristics of the liquid continuous film and the breakup distance. This in turn affects the downstream liquid distribution and shear layer disturbance. The inflow Mach number affects the normal height of the downstream liquid distribution through the pressure gradient. Through parameters analysis, the liquid penetration depth is directly proportional to the total pressure loss. Changing the jet angle is a more effective way to increase penetration depth and improve engine performance.