高位预旋进气转静盘腔换热实验  

Experimental study on heat transfer in rotor-stator cavity with high-positioned pre-swirl inflow

作　　者：王锁芳[1] 朱强华[1] 栾海峰[1] 张羽[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2007年第8期1216-1221,共6页Journal of Aerospace Power

摘　　要：将某型发动机的涡轮盘腔结构简化成高位预旋进气的转静盘腔模型,结合热色液晶先进测温显示技术,通过实验的方法研究了转静盘间距、进气流量、旋转雷诺数以及旋流比等参数的变化对冷气降温效果和转盘换热效果的影响.实验结果表明:高位预旋进气对转盘外缘的冷却效果较好,转盘上的温度分布呈现为同心圆形状;随着旋转雷诺数和转静盘间距的增大或者进气流量的减小,冷气的总温降减小,气流对转盘的换热效果变差.A turbine disc-cavity cooling configuration of an aero-engine was simplified to a rotor-stator cavity model with high-positioned pre-swirl nozzle. The influences of rotor-stator gap,cooling air flux,rotational Reynolds number and swirl ratio on the drop of cooling air temperature and heat transfer on the rotor were experimentally investigated by using advanced temperature measurement technology of the thermochromic liquid crystal. The experimental results indicate that, the high-positioned pre-swirling inflow yields outstanding cooling effect on the rotor fringe, and the temperature of the rotor is distributed in the shape of concentric circle;the drop of cooling air temperature diminishes with the increase of rotational Reynolds number and rotor-stator gap,or with the decrease of cooling air flux,meanwhile, the cooling effect on the rotor becomes worse.

关 键 词：航空、航天推进系统 预旋 转静盘腔 换热 实验 热色液晶 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]