离心力场下多孔介质中热驱动换热的实验  

Experimental Investigation on Thermo-Driving Heat Transfer in Porous Medium 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,江苏南京210016

出　　处：《航空动力学报》2006年第3期507-511,共5页Journal of Aerospace Power

基　　金：国家自然科学基金资助(50276027);国防基础科研基金资助(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,用实验的方法,模拟了离心力场下该新型冷却结构的热驱动换热现象,并与无多孔介质的情况进行了比较。实验结果表明:随着旋转速度、热流密度和冷气进口速度的增大,装有多孔介质的新型冷却结构的热驱动换热能力逐渐增强。同时实验研究发现,加入多孔介质后该新型冷却结构比未加多孔介质时具有更好的换热效果。Based on the research of turbine blade super cooling technique,experiments have been carried out to investigate the thermo-driving heat transfer phenomenon in a new cooling configuration filled with porous medium in a centrifugal force field. The heat transfer effectiveness of the new cooling configuration was compared to that of the configuration with no porous medium. The results show that the thermo-driving heat transfer effectiveness of the cooling configuration filled with porous medium can be enhanced by increasing the rotating speed, heat flux and cooling air speed. The heat transfer effectiveness of the new cooling configuration is strengthened with the installation of porous medium.

关 键 词：航空 航天推进系统 多孔介质 热驱动 封闭腔体 离心力 实验研究 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]