摘要
为了探究单管燃烧室壁面开设光学观察窗与3维倾斜冷却孔对燃烧室冷态头部流场结构的影响规律,利用CFD软件对某型发动机单头部燃烧室结构及简化结构的流场特性进行数值计算,并利用粒子测速仪(PIV)对开设光学观察窗的单管燃烧室头部冷态流场进行了试验验证。结果表明:单管燃烧室冷态流场数值计算结果与PIV测量结果基本相同,验证了数值计算的准确性。燃烧室进口空气流量的增加不影响燃烧室回流区的大小;单管燃烧室壁面冷却孔的布置位置对冷态流场中心回流区几乎无影响;在单管燃烧室水平方向壁面上开设光学观察窗,对水平方向的回流区影响较大,而垂直平面上的回流区几乎不受影响。
In order to explore the influence of optical observation window and 3D inclined cooling hole on the cold flow field structure of the can-type combustor,flow field characteristics of the can-type combustor baseline structure and the simplified structure were numerically investigated by CFD software,and the Particle Image Velocimetry(PIV)was used to verify the cold flow field at the can-type combustor head with an optical observation window.The results show that the numerical results of the cold flow field in the can-type combustor are basically the same as those measured by PIV,which verifies the accuracy of the numerical calculation.The increase of the inlet air flow rate of the combustor does not affect the size of the recirculation zone of the combustor.The location of the cooling holes on the wall of the can-type combustor has little effect on the central recirculation zone of the cold flow field.As the optical observation window is set on the horizontal wall of the can-type combustor,the recirculation zone on the horizontal plane is greatly affected,while the vertical plane is almost unaffected.
作者
李伟
邸东
刘云鹏
陈登炳
颜应文
LI Wei;DI Dong;LIU Yun-peng;CHEN Deng-bing;YAN Ying-wen(College of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
出处
《航空发动机》
北大核心
2023年第1期103-108,共6页
Aeroengine
关键词
3旋流燃烧室
冷态流场
光学观测窗
粒子测速仪
冷却孔
回流区
航空发动机
triple swirl combustor
cold flow field
observation-window
Particle Image Velocimetry
cooling hole
recirculation zone
aeroengine
