摘要
以某一高压涡轮导叶扇形叶栅为研究对象,通过数值和实验方法研究非轴对称端壁造型对涡轮叶栅内二次流的控制机制,分析出口马赫数增加对二次流损失特性的影响规律.结果表明:不同出口马赫数下,非轴对称端壁造型可有效降低总压损失,抑制周向二次流,削弱通道涡强度.出口总压损失系数和涡量随出口马赫数的变化而变化;出口马赫数为0.85时,改善效果最好,出口总压损失系数减小10.81%.
Taking a high pressure turbine guide blade sector cascade as the research object, numerical and experimental methods were used to study the control mechanism of the nonaxisymmetric endwall to the secondary flow in the cascade, and the influence of the increase of exit Mach number on the characteristics of secondary flow loss was analyzed. Research results show that the non-axisymmetric endwall can effectively affect the tangential secondary flow and the development of the passage vortices, resulting in the decrease of the total pressure loss and the change of the exit flow angles. The total pressure loss and the vorticity change with the exit Mach number, and the total pressure loss in the annular cascade with non-axisym- metric endwall reduces by 10.81% when the exit Mach num- ber is 0. 85.
出处
《大连海事大学学报》
CAS
CSCD
北大核心
2017年第4期67-73,共7页
Journal of Dalian Maritime University
基金
辽宁省高等学校创新团队支持计划资助项目(LT2015004)
中央高校基本科研业务费专项资金资助项目(3132016334)
关键词
涡轮
非轴对称端壁
马赫数
扇形叶栅
二次流
turbine
non-axisymmetric endwall
Mach number
sector cascade
secondary flow
