进口气流冲角对环形叶栅端壁气膜冷却效率的影响  

The Influence of Incidence Angle on the Endwall Film Cooling Effectiveness of the Annular Cascade

作　　者：戴斌[1] 刘庆龙[1] 戴韧[1] 

机构地区：[1]上海理工大学能源与动力工程学院,上海200093

出　　处：《燃气轮机技术》2010年第2期43-47,共5页Gas Turbine Technology

基　　金：上海市重点学科建设项目:J50501

摘　　要：进口气流冲角变化会改变端壁横向压力梯度致使端壁气膜冷却气体覆盖发生变化。本文在环形叶栅端壁30%、60%、90%轴向弦长处和距前缘-10%轴向弦长端壁处布置单排圆柱形气膜冷却孔,运用CFD方法在吹风比为1.0条件下对来流冲角为10°、0°和-15°时端壁气膜冷却效率进行对比分析。结果显示冲角由正值到负值,压力面和吸力面一侧两支马蹄涡夹裹冷却气膜主体向压力面偏移,致使吸力面一侧端壁未冷却区域扩大,压力面一侧端壁未冷却区域缩小。吸力面一侧端壁气膜冷却效率沿流向逐渐提升,并在流道中、下游完全冷却覆盖端壁,而压力面一侧端壁一直未能获得冷却气膜覆盖。The variation of incidence angle brings on the different pressure distribution and variation of film cooling coverage on end-wall. This study sets cylinder holes at 30,60,90 and - 10 percent axial chord of endwall, analyzes endwall film cooling effectiveness through CFD method when the incidence angle is 10 deg, 0 deg and - 15 deg under blowing ratio 1.0. The result shows that with the change of incidence angle from positive to negative, pressure and suction side horse vortex entrain the main body of cooling gas ＇to pres- sure side, leading to endwaU near the pressure side without cooling coverage area is shrunken and endwall near the suction side without cooling coverage area is expanded. Along streamwise, suction side endwall film cooling effectiveness is risen, and achieves enough cooling coverage at the middle and down stream, but endwall near the pressure side has no cooling coverage.

关 键 词：叶栅冲角 端壁 气膜冷却效率 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]