二次气射流角对涡轮叶间燃烧室的影响研究  

Influence of Secondary Air Injection Angle on Inter-blade Turbine Burner

作　　者：莫妲[1] 唐豪[2] 李明[2] 张超[2] 郑海飞[2] 

机构地区：[1]中航工业沈阳发动机设计研究所,沈阳110015 [2]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空发动机》2012年第5期18-21,50,共5页Aeroengine

基　　金：国家自然科学基金(51076064)资助

摘　　要：为研究二次气射流角对涡轮叶间燃烧室的影响,设计了3种带有不同二次气射流角的涡轮叶间燃烧室模型,利用FLUENT软件的Realizable k-ε湍流模型、PDF燃烧模型、DO辐射模型和离散相模型对燃烧室的流动和燃烧进行数值模拟。结果表明:涡轮叶间燃烧室具有高效率(99.2%)的特点,增大二次气射流角可使切向动量分量增加、油滴蒸发变慢、出口温度场分布不均匀、总压损失增加。To study the influence of angle for secondary air injection on Inter-stage Turbine Burner （ITB）, three ITB models with different air injection angle were designed. The turbulent flow and combustion of the burner were simulated by the Realizable k-E turbulent model, PDF combustion model and DO radiation model and DPM model of FLUENT software. The results show that ITB is of high combustion efficiency （99.2%）. The increasing air injection angle can lead to the increase of circumferential momentum, the decrease of fuel evaporation velocity, the increase of outlet temperature distubution uneveness and the increase of total pressure loss.

关 键 词：涡轮级间燃烧室 超紧凑燃烧 涡轮内燃烧 二次气射流角 燃气涡轮发动机 燃烧性能 

分 类 号：TK423.2[动力工程及工程热物理—动力机械及工程]