摘要
阐述了特征参数准则的核心原理和预测流程,使用计算流体力学软件FLUENT数值模拟分析了某型航空发动机环形燃烧室的贫油熄火过程,提出了判断熄火的征兆——"M"型火焰及其产生原因.运用特征参数准则研究了不同进口气流速度、气流温度等关键参数对航空发动机燃烧室贫油熄火极限的作用规律.结果表明:贫油熄火油气比随进口气流速度的增加逐渐下降;当进口气流温度小于395K时,贫油熄火油气比随进口气流温度的增加逐渐降低;当进口气流温度超过395K后,贫油熄火极限基本不随进口气流温度的变化而改变.
Core principle and forecasting process of feature-parameter-criterion（FPC）were expounded firstly.A CFD software FLUENT was used to simulate the process of lean blowout（LBO）of an aero-engine annular combustor.＂M＂ flame was proposed as the portent of blowout and its cause was given.The effects of velocity and temperature of inlet air on the LBO limit of aero-engine combustor were discussed by use of FPC.The results show that lean blowout fuel air ratio decreases with the increase of velocity of inlet air.When temperature of inlet air is less than 395K,lean blowout fuel air ratio decreases with the increase of temperature of inlet air.And when temperature of inlet air is more than 395K,lean blowout fuel air ratio remains unchanged.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2014年第7期1631-1638,共8页
Journal of Aerospace Power
