摘要
利用Fluent软件,采用经过PIV试验验证过的Realized k-ε湍流模型,对中心分级燃烧室的燃烧流场进行数值模拟,计算确定出回流区大小、温度分布及特征截面。使用特征截面特征参数法及其判定准则,对该中心分级燃烧室贫油熄火极限进行预测,并对熄火过程火焰形状的成因进行分析。结果表明:随着油气比的降低,回流区温度降低且长宽尺度增大,贫油熄火时的油气比为0.005 83且火焰呈M型,与相关试验测试结果一致。
By using Fluent software, realized k-ε turbulence model verified by PIV test was selected for numerical simulation of combustion flow field, and the size of the recirculation zone, temperature distribu-tion and the feature section were calculated. Using the characteristic parameter of feature section method, the lean blow-out limit of concentric staged combustor was predicted and the causes of the flame shape were analyzed. The results show that with the decrease of fuel-air ratio, the temperature of recirculation zone reduces but length and width increase gradually, fuel-air ratio reaches 0.00583 and flame appears M pattern. The numerical results are good agreement with the experimental results.
出处
《燃气涡轮试验与研究》
北大核心
2016年第2期1-6,共6页
Gas Turbine Experiment and Research
基金
国家自然科学基金(51476106)
辽宁省自然科学基金(2015020639)
关键词
航空发动机
中心分级燃烧室
贫油熄火极限
油气比
特征截面
回流区
aero-engine
concentric staged combustor
lean blow-out limit
fuel-air ratio
feature section
recirculation zone
