Schlieren and PLIF Measurements of Liquid Fuel Injection in Mach 2 Supersonic Crossflow
Structures of liquid-fuel injection in supersonic crossflow is studied experimentally.Schemes of flush-wall injector and aviation kerosene are selected.The conditions of the supersonic freestream are kept constant (total pressure is 0.5MPa,total temperature is 500K and Mach number is 2) and the diameter of the injector is fixed as 0.5mm,while seven scenarios of injection angle and three scenarios of injection driven pressure are discussed.Both methods of schlieren and planar laser induced fluorescence (PLIF) techniques are implemented to obtain the visual images of the liquid-fuel injection.The penetration height of fuel is analyzed quantitatively with the aid of Photoshop and Origin.The results serve not only the future computational simulation but also combined scheme of flush-wall injector and other combustor configurations.
supersonic crossflow flush-wall injector liquid-fuel injection schlieren planar laser induced fluorescence (PLIF) penetration height
Hui Yang Feng Li Baigang Sun Dandan Tian Yaoying Song Dapeng Guo Xianzhi Gao
School of Jet Propulsion,Beihang University,Beijing,China School of Jet Propulsion,Beihang University,Beijing,China;Aviation University of Air Force,Changchun Tianjin University of Finance and Economics,Tianjin,China
国际会议
沈阳
英文
701-705
2012-07-27（万方平台首次上网日期，不代表论文的发表时间）