尾迹作用下不同负荷分布叶型边界层发展研究  

INVESTIGATION OF BOUNDARY LAYER DEVELOPMENT FOR DIFFERENT LOADING DISTRIBUTION CONSIDERING WAKE EFFECT

作　　者：杨琳[1] 邹正平[1] 李维[2] 秦代斌 

机构地区：[1]北京航空航天大学能源与动力工程学院,航空发动机气动热力重点实验室,北京100083 [2]株洲航空动力研究所,湖南株洲412002 [3]中国燃气轮机研究院,四川江油621703

出　　处：《工程热物理学报》2006年第5期751-753,共3页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.50206001;No.50546013);航空基础科学基金项目资助(No.03C51030)

摘　　要：利用数值模拟手段研究了非定常来流条件下负荷分布形式对边界层发展的影响,探讨了适合低雷诺数条件下低压涡轮的负荷分布形式。结果表明,后加载形式在较低雷诺数情况下有利于控制边界层发展,并且尾缘处的分离能够有效地被上游尾迹抑制,与前加载和均匀加载叶型相比,其气动损失最小。当雷诺数降到很低时,仅靠尾迹的作用难以有效抑止分离。结果还显示:在同样条件下,尾迹强度增大有利于控制边界层的分离。Effect of loading distribution on boundary layer development with unsteady inflow condition was investigated by numerical simulation, in order to find out the adapted loading distribution for low pressure turbines working at low Reynolds number. The results show that at low Reynolds number the aft loading distribution is of avail to control boundary layer development and the separation near trailing edge can be suppressed by upstream wake, so the losses are minimum compared with forward and uniform loading distribution. When Reynolds number decrease to a very low level, separation can hardly be suppressed only by wake. The results also show that at the same condition stronger wake has more ability to suppress separation.

关 键 词：数值模拟 负荷分布 边界层 非定常 雷诺数 尾迹 

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]