中文摘要：

用 supercritical 煤油的二阶段的注射的超声的模型燃烧室试验性地与约 1,750 K 的停滞温度在两马赫 2.5 和 3.0 模型燃烧室被调查。约 760 K 的 Supercritical 煤油在 0.5 鈥 ?.46 的全面等价比率范围被准备并且注射。在双人脚踏车的二个综合 injector/flameholder 洞模块被用来便于燃料空气混合和稳定的燃烧。为在一个在上游的地点的单个阶段的燃料注射，边界层分离能与由于过多的本地热版本增加燃料等价比率宣传进隔离乾，这被发现， in turns 它改变了入口气流条件。移动燃料注射到一个进一步下游的地点能减轻这个问题，当它将由于更短的燃料住处时间在燃烧效率导致减少时。与二阶段的燃料注射，全面燃烧室表演被显示被改善，没有边界层分离的在上游的繁殖，以燃料富人条件的煤油注射能被到达进隔离乾。而且，入口马赫的效果数并且在燃烧性能上驾驶氢也被学习。关键词超声的燃烧 - 上演注射 - 燃烧效率 - Supercritical 煤油工程被中国的国家自然科学基础支持(10672169， 10621202 ) 。

英文摘要：

Supersonic model combustors using two-stage injections of supercritical kerosene were experimentally investigated in both Mach 2.5 and 3.0 model combustors with stagnation temperatures of approximately 1,750 K. Supercritical kerosene of approximately 760 K was prepared and injected in the overall equivalence ratio range of 0.5-1.46. Two pairs of integrated injector/flameholder cavity modules in tandem were used to facilitate fuel-air mixing and stable combustion. For single-stage fuel injection at an upstream location, it was found that the boundary layer separation could propagate into the isolator with increasing fuel equivalence ratio due to excessive local heat release, which in turns changed the entry airflow conditions. Moving the fuel injection to a further downstream location could alleviate the problem, while it would result in a decrease in combustion efficiency due to shorter fuel residence time. With two-stage fuel injections the overall combustor performance was shown to be improved and kerosene injections at fuel rich conditions could be reached without the upstream propagation of the boundary layer separation into the isolator. Furthermore, effects of the entry Mach number and pilot hydrogen on combustion performance were also studied.