大焓降静叶翘曲端壁流动控制研究  

Influence of Bump Endwalls on Cascade Flow of High-loading Stator Turbine Blade

作　　者：李长宝[1] 韩万金[2] 

机构地区：[1]哈尔滨汽轮机厂有限责任公司,哈尔滨150046 [2]哈尔滨工业大学能源科学与工程学院,哈尔滨150001

出　　处：《汽轮机技术》2016年第1期26-28,80,共4页Turbine Technology

摘　　要：以气动性能优良的尾缘正弯积迭的大焓降静叶为原型,采用5条具有控制点的B样条曲线作为沿流向的控制线设计翘曲端壁,研究翘曲端壁对端部的流动控制和探索翘曲端壁降低损失的机理。通过商业软件NUMECA数值研究了翘曲端壁对大焓降静压总压损失及根部载荷分布的影响,指出翘曲端壁可降低端部区域的横向压力梯度,削弱二次流强度,同时也增加摩擦损失,选择适合的翘曲型面并控制翘曲幅度在边界层以内可有效降低端部总压损失。Based on an aerodynamic-excellent high-loading stator turbine blade feathered with positive bending and the trailing edge stacking, the bump endwall surface samples were generated by 5 B-spline curves with 5 control points to investigate the influence of bump endwalls on cascade flow of high-loading stator turbine blade and the mechanism of bump endwalls on reducing total pressure losses. The numerical results by commercial software NUMECA showed that, the bump endwalls could lower the transverse pressure gradient near the endwall regions and weaken the secondary flow intensity, however,the friction loss would increased in the same time. So selecting the suitable bump endwall for the high-loading stator turbine cascade,whose warping range was in the boundary layer, can effectively reduce the total pressure loss near the endwall.

关 键 词：大焓降 静叶 翘曲端壁 流动控制 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]