Progress in research on mixing techniques for transverse injection flow fields in supersonic crossflows  

作　　者：Wei HUANG Li YAN 

机构地区：[1]Science and Technology on Scramjet Laboratory, National University of Defense Technology

出　　处：《Journal of Zhejiang University-Science A(Applied Physics & Engineering)》2013年第8期554-564,共11页浙江大学学报（英文版）A辑（应用物理与工程）

基　　金：supported by the Science Foundation of National University of Defense Technology (No. JC11-01-02);the Hunan Provincial Natural Science Foundation of China (No.12jj4047)

摘　　要：The transverse injection flow field has an important impact on the flowpath design of scramjet engines. At present a combination of the transverse injection scheme and any other flame holder has been widely employed in hypersonic propulsion systems to promote the mixing process between the fuel and the supersonic freestream; combustion efficiency has been improved thereby, as well as engine thrust. Research on mixing techniques for the transverse injection flow field is summarized from four aspects, namely the jet-to-crossflow pressure ratio, the geometric configuration of the injection port, the number of injection ports, and the injection angle. In conclusion, urgent investigations of mixing techniques of the transverse injection flow field are pro- posed, especiaUy data mining in the quantitative analytical results for transverse injection flow field, based on results from multi-objective design optimization theory.The transverse injection flow field has an important impact on the flowpath design of scramjet engines. At present a combination of the transverse injection scheme and any other flame holder has been widely employed in hypersonic propulsion systems to promote the mixing process between the fuel and the supersonic freestream; combustion efficiency has been improved thereby, as well as engine thrust. Research on mixing techniques for the transverse injection flow field is summarized from four aspects, namely the jet-to-crossflow pressure ratio, the geometric configuration of the injection port, the number of injection ports, and the injection angle. In conclusion, urgent investigations of mixing techniques of the transverse injection flow field are proposed, especially data mining in the quantitative analytical results for transverse injection flow field, based on results from multi-objective design optimization theory.

关 键 词：Aerospace propulsion system Transverse injection MIXING Supersonic crossflow 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]