航天推进剂废气废液燃烧处理实验

Experimental on combustion of space propellant useless gas and liquid

针对航天生产试验现场有毒推进剂废气废液的无害化处理,设计了一种火箭煤油/空气燃烧处理装置,通过富燃/富氧高温燃气处理硝基类氧化剂/肼类燃料的废气废液。基于该燃烧处理装置,分别进行了燃烧器性能调试以及N2O4与甲基肼的废气与废液处理实验。实验结果表明,燃烧装置在两种基本工作模态下,燃气温度小于1200℃,燃烧高效、稳定;N2O4在处理流量0~20g/s时,排放物中NOx浓度最高为25ppm,燃气温度小于1200℃;在甲基肼处理流量<6g/s时,排放物中VOC浓度小于0.05ppm,NOx浓度小于2.0ppm,其中燃气最高温度随甲基肼流量增加不断增大,最高达1300℃。该燃烧处理装置可实现对有毒航天推进剂高效、彻底的处理,废气排放符合相关标准要求。

In order to realize harmless dipose of toxic propellant useless liquid and gas in aerospace production test site, a rocket kerosene/air combustion dipose device was designed to deal with the useless gas and liquid, and experiments of nitro oxidant or hydrazine dipose by fuel-rich or oxygen-rich high-temperature gas were carried out,respectively.The experimental results show that the combustor operated efficiently and stablely under the two basic working mode, and the gas temperature is less than 1 200 ℃.And the highest concentration of NOx in the emissions is 25 ppm when the mass flow rate of N2O4 in the range of 0~20 g/s, the gas temperature is less than 1 200 ℃ at the same time.When the mass flow rate of methylhydrazine in the range of 0~6 g/s, the VOC concentration in the emissions is <0.05 ppm, and the NOx concentration is less than 2.0 ppm, the temperature of gas increases with the mass flow rate of methylhydrazine continuously, the maximum value is up to 1 300 ℃.Therefore, dipose of toxic propellant by the combustion device is efficient and complete,and exhaust emission meets relevant standards.