尾缘弯折角对涡轮叶片气动性能的影响  

The Impact of Trailing Edge Angle on the Aerodynamics of Steam Turbine Blades

作　　者：刘剑 王开拓 陈禹 陈亚 张鑫 LIU Jian;WANG Kai-tuo;CHEN Yu;CHEN Ya;ZHANG Xin(China Chang Jiang Energy Corporation,Wuhan 430081,China)

机构地区：[1]中国长江动力集团有限公司汽轮机研究所,武汉430081

出　　处：《汽轮机技术》2023年第5期355-357,366,共4页Turbine Technology

摘　　要：设计了6组具有不同尾缘弯折角的小焓降涡轮叶片,并对叶片的气动性能进行了研究,结果表明:尾缘弯折角增大使叶片的载荷后移,叶片斜切部分扩压流动加剧,导致叶片尾缘处边界层分离,但扩压段的后移及横向压力梯度的减小,减缓了二次流的发展;尾缘弯折角减小使叶片的载荷前移,横向压力梯度增大促进了二次流的发展,但载荷的前移,减小了叶片斜切部分扩压的程度,叶片尾缘处没有发生边界层分离。最终确定当尾缘弯折角等于4.22°时,即叶型3的总压损失最小。This paper investigates the aerodynamics of six steam turbine blades with different trailing edge angles,the enthalpy drop of which is low.The result shows that large trailing angel pushes the blade loading to the downstream direction,and raises the diffusivity of the flow in the inclination region.It leads to flow separation in the trailing edge.However,the rearward diffusion region and the decreasing lateral pressure gradient restrain the development of secondary flow.On the contrary,small trailing angle moves the loading area forward and increases the lateral pressure gradient,which consequently develops the secondary flow.From another aspect,the forward loading section decreases the diffusion level of the flow at the inclination area.Thus,no boundary flow separation is observed around the trailing edge.When the trailing angle is set to 4.22 degree,the third blade profile,the smallest total pressure loss is adopted.

关 键 词：尾缘弯折角 小焓降 后加载叶型 涡轮叶片 

分 类 号：TK263.3[动力工程及工程热物理—动力机械及工程]