带小翼肋条的涡轮叶尖泄漏流场的数值模拟  

Numerical Simulation on Tip Leakage Flow of Turbine Blade with Suction-side Winglet Ribs

作　　者：蔡晋[1] 陈波[2] 闫雪[1] 李伟[3] 陶华[1] 

机构地区：[1]西北工业大学现代设计与集成制造技术教育部重点实验室,西安710072 [2]空军雷达学院基础部,武汉430019 [3]西北工业大学动力与能源学院,西安710072

出　　处：《动力工程学报》2010年第12期919-925,共7页Journal of Chinese Society of Power Engineering

摘　　要：对叶尖吸力面带小翼肋条的某一轴流转子叶尖间隙泄漏流场进行了数值研究,分析了在不同肋条宽度下泄漏流场细节,并对涡轮效率进行了计算.结果表明:涡轮叶尖单吸力边小翼肋条总体上减小叶尖表面压差,使得吸力面后半部分泄漏流速度减小,从而减小泄漏流动损失,但会增大通道内流动损失,使涡轮转子效率下降;小翼肋条宽度有一个最佳值,小间隙下增大肋条宽度使得涡轮转子效率降低,大间隙下增大肋条宽度却使得涡轮转子效率提高;吸力边小翼肋条改变了叶尖吸力边附近的流场,对压力边附近泄漏流动结构影响不大.Numerical simulation was carried to tip leakage flow of an axial turbine blade with suction-side winglet ribs,while the influence of rib width on the leakage flow field analyzed and the turbine efficiency calculated.Results show the suction-side winglet rib may reduce pressure difference on the tip surface,which makes the leakage flow rate at latter part of suction side reduced,resulting in lowered leakage flow loss;however,the passage flow loss may be increased,leading to reduced rotor efficiency.For the width of winglet rib,there exists an optimal value;and with the rise of rib width,the rotor efficiency decreases for a tight tip clearance,but increases for a loose tip clearance.The winglet rib at suction side changes the flow field at suction side,but affects little on the flow structure near the pressure side.

关 键 词：叶尖间隙高度 泄漏涡 被动控制 数值模拟 

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]