摘要
航空发动机内空气冷却系统流通通道结构复杂。在各种复杂结构中,能有强烈换热过程的局部特征就是冲击换热。故以机匣环腔结构作为研究对象,在所研究的流动参数及结构参数范围内发现:相同冲击Re j下,随着冲击间距(H/d)的增大,冲击靶板上的温度分布更加均匀;当冲击孔角度(β)为90°时,冲击靶板面换热效果更佳;冲击孔周向角(α)越小,冲击靶板面的的整体温度水平越低,并且温度分布更为均匀;随着横流比(m c/m)的增大,冲击驻点的温度在逐渐降低,换热系数也在逐渐提高。
The structure of the air cooling system channel in the aeroengine is very complicated.Among various complex structures,the local feature with a strong heat exchange process is the impact heat transfer.Therefore,this paper considers the structure of the casing ring cavity as the research object,in the range of flow parameters and structural parameters studied,it is found that:the temperature distribution on the impact target plate is more uniform with the increase of the impact spacing(H/d)under the same impact Re;When the impact hole angle(β)is 90°,the heat exchange effect of the impact target surface is better;The smaller the circumferential angle(α)of the impingement hole,the lower the temperature level of the impact target surface and the more uniform temperature distribution;As the cross flow ratio(m c/m)increases,the temperature of the impact stagnation point gradually decreases,and the heat transfer coefficient also gradually increases.
作者
陈振华
崔成成
董奇
杨卫华
CHEN Zhenhua;CUI Chengcheng;DONG Qi;YANG Weihua(College of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;School of Energy and Environment,Southeast University,Nanjing 210016,China;China Aviation Powerplant Research Insititute,AVIC,Zhuzhou 412002,China)
出处
《重庆理工大学学报（自然科学）》
CAS
北大核心
2021年第4期182-193,共12页
Journal of Chongqing University of Technology：Natural Science
基金
国家自然科学基金项目(51276088)。
关键词
涡轮机匣
冲击间距
冲击孔角度
冲击孔周向角
横流比
turbine casing
impact spacing
impact angle
impact hole circumferential angle
cross flow ratio
