Experimental and Numerical Studies on Fuel Injection and Combustion of Solid-Liquid Rocket Ramjet
In order to study the process of liquid fuel injection and combustion of Solid-Liquid Rocket Ramjet, a subscale test is conducted. Weak combustion effect is obtained according to the wall pressure of the test engine. Some three-dimensional numerical simulations about the experimental engine on the experimental operation condition are conducted to investigate the weak combustion effect. In the simulations, fuel mixture, evaporation and combustion are included, the liquid fuel droplets are tracked by solving Lagrangian equations of motion and transport for the life histories of individual droplet groups, and single-step reaction system is applied. It is indicated that the combustion efficiency is greatly affected by liquid fuel injector positions. When fuel injectors are imposed close to the air inlets, the strong air inlet stream can take liquid fuel into the center region of the chamber, but its momentum along the chamber shortens the residence time of fuel droplets. When fuel injectors are located in the front of the chamber head, the vortex caused by fuelrich gas of gas generator contributes to transverse motion of the fuel droplets which promotes the droplets to evaporate and combust.
Solid-Liquid Rocket Ramjet fuel injection subscale test numerical simulation combustion efficiency
Lin Zhen Yang Wenjiang Qin Lizi Liu Yu
School of Astronautics.Beijing University of Aeronautics and Astronautics, Beijing 100191, China School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China School of Astronautics,Beijing University of Aeronautics and Astronautics, Beijing 100191, China
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
1180-1183
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）