基于表面热膜的超高负荷低压涡轮叶栅附面层特性  

Experimental research on boundary layer behaviors of ultra-high-lift low-pressure turbine profile based on surface-mounted hot-film

作　　者：李伟[1,2] 朱俊强[1] 李钢[1] 徐燕骥[1] 

机构地区：[1]中国科学院工程热物理研究所,北京100190 [2]中国科学院研究生院,北京100190

出　　处：《航空动力学报》2011年第1期115-121,共7页Journal of Aerospace Power

基　　金：国家自然科学基金(50676095;50776086)

摘　　要：利用表面热膜测量了定常来流条件下某超高负荷后加载叶型吸力面附面层的分离流动,并与壁面静压实验结果进行了对比.结果表明,热膜用于超高负荷低压涡轮叶型附面层流动测量可靠性较高;热膜测得的准壁面剪切应力及相关统计参数能准确地判断附面层分离、再附着和转捩位置;在低雷诺数条件下,分离泡尺寸和转捩区长度随来流雷诺数的减小而增加.A hot-film experimental investigation on steady boundary layer separation behaviors of the suction surface of an ultra-high-lift low-pressure turbine profile was described,which was compared with loading distribution.The experimental results indicate that the surface-mounted hot-film is a reliable indicator of the position of separation bubble and transition for the ultra-high-lift low-pressure turbine blade.In the event of lower Reynolds numbers,the size of separation bubble and transitional regime increases under declining Reynolds numbers.

关 键 词：超高负荷 低压涡轮 分离泡 转捩 表面热膜 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]