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从燃烧特性和对机体冷却的必要性等方面考虑,液氢是比较理想的可将机体加速到高超声速的燃料,但因其燃料箱太大,实际应用有困难。而采用航空燃料,其燃烧特性和冷却性能方面也存在问题。本研究采用单成分碳氢燃料在超燃冲压发动机燃烧室模型中进行了燃烧试验,以了解其基本燃烧特性为目的,对喷气燃料中含量多的正烷烃,按其含碳数从7到16分成5组进行了燃烧试验,比较了每种燃料的自发点火性和保焰性,介绍了试验方法及结果。
From the combustion characteristics and the necessity of cooling the body and other considerations, the liquid hydrogen is ideal for the body to accelerate to hypersonic fuel, but because of its fuel tank is too large, practical difficulties. The use of aviation fuel, its combustion characteristics and cooling performance there are problems. In this study, a single-component hydrocarbon fuel combustion test was carried out in a scramjet combustion chamber model to understand the basic combustion characteristics of n-alkanes with high content in jet fuel. According to their carbon content from 7 to 16 The combustion test was divided into five groups, the spontaneous ignitability and flame retardancy of each fuel were compared, and the test methods and results were introduced.