燃气涡轮弯叶片特性研究  

Application of Heat Transfer Design Process on the Turbine Vane

作　　者：卢平[1] 

机构地区：[1]东方汽轮机有限公司,德阳618000

出　　处：《汽轮机技术》2014年第2期119-122,共4页Turbine Technology

摘　　要：以燃气轮机涡轮第一级导叶为研究对象,借助数值模拟对涡轮导叶气动问题进行研究,针对于涡轮的工作特点,进行了多方案计算及对比,研究了不同弯扭叶片设计参数对涡轮叶栅气动性能的影响。结果表明:根部采用-15°弯角,即正弯15°,采用0.4弯高,即采用大弯高可以有效地降低端壁处低能流体的聚集,从而有效地降低横向二次流,采用上述弯叶片计算得到总压损失系数有所降低。Based on first stage turbine vane of turbo engines for a research,study the aerodynamic problem of turbine vane by numerical simulation. For the working characteristics of the turbine,multiple parameters of bowled and twisted blades are simulated and compared to approach the aerodynamic influence. The result shows that： bowl angle -15° （positive bowl angle 15°） and bowl high 0.4,which means large bowl and high,can effectively decrease the gather of low energy fluid at the end wall ,thus reduce the crosswise secondary flow. The simulation show the total pressure loss of the blade mentioned above is lower than origin bowled blade.

关 键 词：涡轮 气动 弯扭叶片 横向二次流 损失 

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]