摘要
叶顶间隙二次流在高压涡轮总损失中占据了较大比重.针对某型航空发动机的结构特点,研究了涡轮叶顶间隙结构对性能影响的机理.计算结果和实验数据吻合的较好.流场细节分析表明:在叶顶间隙流通面积相同情况下,台阶型、渐缩型间隙优于直线型,凸/凹型间隙效率最低;渐缩型间隙在叶片前半轴弦受到上通道涡的抑制,减少了叶顶间隙泄漏涡的强度和范围;凸型间隙在叶片前缘引起了流动分离,凹型间隙存在一高速区,增加了二次流损失.
The secondary flow loss plays a main part in the total loss of high pressure turbine s(HPT).Based on the structure of one type aero-engine,this paper is focused on mechanic of the tip clearance structure,which influences the turbine characteristics.Numerical results agree well with the experiment data.The detailed information of the flow fields shows that,with the same tip clearance flow area,the step and shrink tip clearance shape perform better than line tip clearance shape,while the groove and bulge shap...
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2009年第5期1096-1100,共5页
Journal of Aerospace Power
关键词
叶顶间隙
航空发动机
高压涡轮
二次流
数值分析
tip clearance
aero-engine
high pressure turbine
secondary flow
numerical analysis
