离心力场下多孔介质的不同孔隙率对热驱动换热影响的研究  

Effect of different porosity on thermally driven heat transfer in a centrifugal force field

作　　者：夏婕[1] 常海萍[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》2006年第6期972-977,共6页Journal of Aerospace Power

基　　金：国家自然科学基金资助项目(50276027);国防基础科研资助项目(J1400D001)

摘　　要：以涡轮叶片新型超级冷却技术的研究为背景,在具有冷却通道的新型冷却结构中加入多孔介质,采用实验与数值模拟相结合的方法研究了不同孔隙率条件下,新型冷却结构的热驱动换热规律,实验和计算结果基本一致。研究结果表明不同孔隙率条件下,该新型冷却结构具有相同的换热规律:随着旋转速度、热流密度和冷气进口速度的增大,该结构的热驱动换热能力逐渐增强。同时实验研究发现,随着孔隙率的增大,热驱动换热效果降低。Based on the background of the turbine blade super-cooling technology, porous medium was installed in a new kind of cooling configuration with cooling tunnels. Experinvest with d gate the thermally driven heat fferent porosity in a centrifugal force field. The results of experiments are basically consistent with that of the numerical simnlallons. Study shows that the heat transfer processes of the new cooling configuration are identical under different porosity. The thermally driven heat transfer of the cooling con figuration filled with porous medium can be enhanced by increasing rotating speed, heat flux and cooling air speed. At the same time, the heat transfer effect is weakened with the increase of the porosity.

关 键 词：航空、航天推进系统 多孔介质 孔隙率 热驱动 

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]