縦渦導入型燃料噴射ストラットの超音速混合燃焼実験(第1報) : スクラムジェット燃焼器における超音速縦渦列の効果

概要

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Effects of streamwise vortices on enhancement of supersonic mixing and combustion are examined in a scramjet combustor whose main flow is a Mach 2.45 vitiation air stream with a total temperature of 2200K. The fuel injector strut called “Alternating-Wedge Strut (AW-Strut)” is used to generate streamwise vortices and to inject hydrogen fuel into their core region. For comparison, a generic strut, “MO-Strut,” without streamwise vortex generation is also examined. Direct visualization of flame shows rapid formation of streamwise vortices and ignition/combustion within the vortices already upstream of the strut trailing edge. Wall pressure measurements along the combustor show that for the case of AW-Strut the wall pressure rise due to combustion is almost twice that of the MO-Strut case. Gas sampling at the combustor exit demonstrates that much more uniform fuel/air mixing is obtained for the case of AW-Strut. The present results verify the phenomenal performance of the supersonic streamwise vortices for enhancement of supersonic mixing and combustion.
社団法人日本航空宇宙学会の論文
2002-04-05