近壁流向涡对多排孔的模拟与实验研究  

Simulation and Experimental Study of Near Wall Flow Vortex on Multiple Rows of Holes

作　　者：王佳男 Jianan Wang(School of Energy and Power Engineering,University of Shanghai for Science and Technology,Shanghai)

机构地区：[1]上海理工大学能源与动力工程学院,上海

出　　处：《建模与仿真》2024年第3期2381-2395,共15页Modeling and Simulation

摘　　要：通过模拟叶栅研究二次流对端区多排扇形孔的影响,并在平板气膜实验台上安装涡流发生器生成流向涡,模拟叶栅端区二次流对壁面气膜冷却的作用,研究流向涡强度对多排扇形孔冷效的影响。结果表明:当涡流强度增加,流向涡对气膜冷效的影响和气膜偏斜程度增加。气膜的叠加效应可以提高第二排和第三排气膜冷却效率,弥补流向涡造成后排气膜冷却效率的降低。进气角会影响叶栅通道涡强度,导致端壁气膜发生变形,冷效分布发生改变。边界层会造成二次流强度减弱,导致压力面侧的气膜冷效得到增强。By simulating the effect of secondary flow on multiple rows of fan-shaped holes in the end wall region of the blade cascade,and installing a vortex generator on a flat film experimental platform to generate flow direction vortices,the effect of secondary flow on wall film cooling in the end region of the blade cascade is simulated,and the influence of flow direction vortex intensity on the cooling efficiency of multiple rows of fan-shaped holes is studied.The results indicate that as the intensity of vortices increases,the influence of flow vortices on film cooling efficiency and the degree of film skewness increase.The superposition effect of gas film can improve the cooling efficiency of the second and third rows,and compensate for the decrease in cooling efficiency of the rear row film caused by flow vortices. The inlet angle can affect the vortex strength of the blade passage, causing deformation of the end wall air film and a change in the distribution of cooling efficiency. The boundary layer can cause a decrease in the intensity of secondary flow, resulting in an enhanced cooling effect of the gas film on the pressure surface side.

关 键 词：二次流 扇形孔 气膜冷效 涡流强度 

分 类 号：G63[文化科学—教育学]