液氢突扩燃烧冲压发动机性能

COMBUSTION PERFORMANCE OF DUMP CMOBUSTOR IN RAMJET ENGINE USING LIQUID HYDROGEN FUEL

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

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

摘要:

对航天飞机用液氢突扩燃烧冲压发动机性能进行了比较详细的计算及分析。研究的工作范围为Ma=1.50～6.50、高度变化范围为H=0～40km。并把计算结果与等截面液氢冲压发动机性能进行了比较。计算结果表明,在低空低马赫数时突扩燃烧冲压发动机性能较为优越,而在高空高马赫数时性能基本没有变化。航天飞机使用突扩燃烧室冲压发动机在低空低马赫数时可以部分解决流量匹配问题,还可提高发动机推力、减少溢流阻力。燃烧室结构也较简单。

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.