摘要
对具有 3.6 %相对叶顶间隙涡轮叶栅的三维流场进行了实验和数值模拟 ,分析了大间隙涡轮叶栅流道内的涡系结构。结果表明在叶顶间隙内部和上半叶展出现了复杂的分离涡系 ,在上半叶展存在叶顶泄漏涡、上通道涡、吸力侧脱落涡、压力侧叶顶脱落涡和被泄漏流吹向下游的尾缘涡系的相互作用。
Flow visualizations on wall surface and numerical simulations of flow structure with turbine cascade with large tip clearance were carried out. Based on the experiential results and with the aid of numerical simulations, detailed flow structures within a typical turbine cascade were discussed. The detailed information of the flow fields near the wall surface, in the tip clearance, and especially, around the trailing edge is shown in the present study. In the up-half-span region, the flow becomes very complex due to the existence of the tip clearance. There are interactions among those vortices such as leakage vortex, up passage vortex, shed vortices on the pressure and suction sides, and trailing edge vortices. In the low-half-span, the flow fields near the region formed by the trailing edge and the endwall are also very complex. There are 3 saddle points in company with 6 separation lines and 2 nodal points represent the trailing edge vortices on the wall surface near those regions.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2002年第4期392-398,共7页
Journal of Aerospace Power
基金
国家自然科学基金资助项目 ( 5 0 10 6 0 0 2 )
哈尔滨工业大学校基金资助项目 ( HIT.20 0 0 .74)
关键词
涡轮叶栅
间隙
流场结构
尾缘涡
turbine cascade
tip clearance
flow structure
