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基于脉冲燃烧风洞直连式试验平台,利用壁面压力测量和高速摄影等手段,研究了注油方式对超燃冲压发动机燃烧性能的影响.考察了不同油位单点注油时的注油特性,利用高速摄影揭示了各个油位的火焰发展历程.在产生有效推力及防止进气道不起动的限制下,确定了各个油位的贫油最低当量比、富油最高当量比.研究了第1油位、第2油位和其他油位组合注油时的耦合作用.以隔离段未扰动区域长度、燃烧室内推力、燃料比冲为指标,探寻了燃烧性能最佳的注油方式.试验获得的隔离段未扰动区域长度最大为149.6mm,燃烧室内推力最大为1 622.3N,燃料比冲最大为1 354.0s.
Based on the pulsed combustion wind tunnel direct-connect test platform, the influence of oil injection method on the combustion performance of scramjet was studied by the means of wall pressure measurement and high-speed photography.The injection characteristics of single-point oil injection with different oil levels were investigated, The flames of each oil level were revealed by the photography.The minimum lean ratio of the lean oil and the highest equivalence ratio of the rich oil at each oil level were determined under the restriction of effective thrust and preventing the intake air from starting up.The first oil level , The second oil level and other oil level combination of oil when the coupling effect.Under the undamped zone length of the isolation section, the thrust of the combustion chamber, the ratio of fuel as an indicator to explore the best combustion performance of the injection method. The maximum disturbance zone length is 149.6mm, the maximum thrust in the combustion chamber is 1 622.3N, and the maximum fuel specific impulse is 1 354.0s.