超燃冲压发动机燃气取样探针设计与试验验证

Design and experimental verification of gas sampling probe for scramjet engine

燃气取样探针作为超燃冲压发动机燃气分析系统的关键部件,决定了超声速环境中燃气取样的代表性。根据超燃冲压发动机试验条件,基于燃气取样探针理论分析,利用结构设计和流场分析相结合的方式,完成了一支6点取样探针的设计,并在燃气发生器出口超声速环境下开展了校核试验。流场分析表明探针内部结构能够实现化学反应冻结。空气校核试验测量的氧气含量与理论值吻合,偏差小于1%;燃料校核试验测量了燃气发生器出口超声速气流中的氧气、一氧化碳和二氧化碳,其结果在一定程度上反映了燃烧室流场的空间分布。预估燃气发生器的燃烧效率约为83%。

As a key component for scramjet engine gas analysis system,gas sampling probe determines the sampling characteristics of supersonic environment.According to the scramjet engine experimental conditions,based on the theoretical analysis of the gas sampling probe,combining the structural design and probe flow field analysis,a 6-point sampling probe design was completed and the gas generator exit verification test at supersonic condition was carried out.Flow field analysis shows that the internal flow field of the probe can achieve chemical reaction freezing.The O2 percentage of the air calibration experiment is consistent with the theoretical value,and the deviation is less than 1%.The O2,CO and CO2 of the gas generator exit flow are measured respectively,and the results reflect the distribution of combustor flow filed to some extent.Combustion efficiency of the gas generator is approximately 83%.