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实现航空发动机大推力通常采用加力燃烧室设计,燃烧室进气温度升高会同步导致排放尾气中NOx浓度提高.采用典型加力燃烧室主稳定器的V型结构试验件,测试加力燃烧前后(进口600℃,出口600～1200℃)燃烧室排放断面的NOx浓度分布,通过相同流场4种试验工况的NOx生成浓度组分和氧含量变化分析,验证了加力燃烧室NOx生成以热力型NO为主的“高温、富氧、贫油”燃烧特性.结果表明加力燃烧室燃烧过程中消耗的氧含量大多贡献于CO2增量,在800～1000℃燃气排放温度范围内,不完全燃烧产物CO对NO的热力生成有明显抑制作用.
To achieve aero-engine thrust generally use afterburner design, the combustion chamber inlet temperature will be synchronized to lead to the exhaust emission of NOx concentration increased.Using a typical afterburner main stabilizer V-shaped structural test pieces, test afterburning The NOx concentration distribution in the discharge section of the combustion chamber before and after the inlet (600 ℃, exit of 600 ~ 1200 ℃) was analyzed. The analysis of the change of NOx concentration and oxygen content in the four test conditions in the same flow field validated the afterburning NOx formation The results show that most of the oxygen content in the combustion process of afterburner contributes to the increase of CO2, and at 800 ~ 1000 ℃ gas emission temperature range Within the incomplete combustion products of CO on the thermal generation of NO significantly inhibited.