Experimental and numerical studies on combusion character of solid-liquid rocket ramjet

Solid-Liquid Rocket Ramjet (SLRR) uses both solid and liquid fuels. It has been interested in for its steady combustion character without using a flame stabilizer. The high-temperature gas jet from solid-propellant gas generator of SLRR can work as duty flame for air/liquid fuel combustion at the same time. To attain high combustion efficiency at design and off-design conditions, the experiment and numerical simulation were conducted to learn combustion process in the chamber, focusing on mix and evaporation. The experimental data was also used to value the accuracy of CFD. In numerical simulation, the alcohol droplets were tracked by solving Lagrangian equations of motion and transport for the life histories of individual droplet groups; and single-step reaction system was applied. The research of varying mass flow rate of alcohol fuel indicates that SLRR has a wide boundary of flame out. By varying alcohol injection parameters, it is found that high combustion efficiency can be attained at design and fuel-rich conditions when alcohol injectors are imposed close to the air inlets; when injectors are imposed far away from air inlets, a better combustion can be attained at fuel-poor conditions. By applying inverse injection means with a proper injection angle, combustion efficiency can be increased in use of droplets-vortex interaction in the head region.