加力燃烧室NO_x排放生成规律试验分析  

Experimental analysis on NO_x generation and emission distribution off aviation afterburners

作　　者：王琦[1] 胡筱敏[1] 

机构地区：[1]东北大学资源与土木学院,沈阳110819

出　　处：《北京航空航天大学学报》2012年第8期1005-1009,共5页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家自然科学基金重点资助项目(69735101);国家自然科学基金资助项目(30170270)

摘　　要：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.An afterburners was designed to get aviation engine extra thrust, but higher inlet temperature will generate higher NO. emission. One V style structure test facilities was adopted as an afterburners flow fields stabilizer, the section concentration of different NO. and 02 emission from the afterburners were analyzed in condition of inlet T 600 ℃ to outlet T 600 - 1 200 ℃ , the test was fulfilled at 4 experimental conditions of same flux and flow fields. The results show that the chamber combustion is of ＂higher temperature, rich oxy- gen, poor fuel＂ characteristics, most Oxygen consumption in an afterburner chamber is contributed to generate CO2 and in the emission temperature scope of 800 - 1 200 ℃, the NO thermal generation is restrained and af- fected by incomplete combustion product CO evidently.

关 键 词：NOX排放 加力燃烧室 断面浓度分布 生成抑制 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]