摘要
为了研究主燃(MB)-涡轮叶间补燃(TIB)一体化燃烧室(M-TIB)中燃烧环二次射流角度对燃烧性能的影响,设计了3种燃烧环二次射流角度组合分别为40°&40°,45°&55°以及50°&50°的M-TIB模型。利用FLUENT软件的Realizable k-ε湍流模型、PDF燃烧模型和离散相模型对M-TIB的流动和燃烧进行数值模拟。研究结果表明:适当增大燃烧环二次射流角度,可以强化M-TIB内部气流的掺混,改善速度分布,提高出口速度,减少污染物排放。
In order to study the influence of air injection angle of combustion ring on combustion performance for Main Burner（MB）-Turbine Inter-Blade Burner（TIB） integration burner（shortly M-TIB）, three M-TIB models with the air injection angles of 40° 40°,45° 55° and 50° 50°were designed. The realizable k-ε turbulent model,PDF combustion model,and DPM model of FLUENT were used to simulate the turbulent flow and combustion of the burner. The results show that the methods of appropriately increasing the air injection angle of combustion ring can strengthen the blending of main flow and injection air in M-TIB,improve the distribution of velocity,increase the velocity of outlet, decrease the emission of pollutants.
出处
《航空发动机》
2016年第2期17-21,共5页
Aeroengine
基金
国家自然科学基金(51076064)资助
关键词
主燃-涡轮叶间一体化燃烧室
超紧凑燃烧
燃烧环
射流角度
燃烧特性
航空发动机
Main Burner-Turbine Inter-Blade Burner
Ultra-Compact Combustion
combustion ring
air injection angle
combustion performance
aeroengine
