关键词: 突扩型燃烧室;高超音速冲压喷气发动机;航天飞机主发动机;复合式发动机;氢燃料;性能分析

Abstract: In this paper, the combustion performance of dump combustor in ramjet engine for aerospaceplane was discussed. The ramjet characteristics using liquid hydrogen was calculated and analysed in edtail. The results show that the ramjet performance meet the demand of aerospaceplane on propulsion system in the range of Ma= 1. 50-6. 00 and H = 40km. The calculated results for dump and normal combustors were compared. At low altitude and small Ma number, the results show that the performance of dump combustor is better than normal combustor. That is, the thrust is increased and the resistance of overflow is decreased. At higher altitude and Ma number, the differences in performance are very small. The problem of flow matching is partially solved.

Key words: Hypersonic ramjet;Space shuttle main engine;compound engine;Hydrogen fuel;performance analysis