弯-掠叶片对压气机叶栅端壁流动的控制作用  

Effect of blade sweeping-curving on the endwall flow field of compressor cascade

作　　者：宋彦萍[1] 刘振德[1] 赵桂杰[1] 王仲奇[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001

出　　处：《推进技术》2004年第4期338-342,共5页Journal of Propulsion Technology

基　　金：国家自然科学基金项目(50236020);国家"九七三"基金项目(G1999022307)。

摘　　要：利用数值和实验方法对气动弯掠在压气机叶栅中的作用机理进行了研究。结果表明,相对于网格数目和网格类型,进、出口边界条件和湍流模型对计算和实验结果吻合的影响要大。叶片前掠改变了叶栅的三维压力场,使得低能流体重新分配。正弯与前掠的结合进一步加强了这种控制作用,为叶片设计提供了一个自由度。Both numerical and experimental investigations were carried out to study the effect of aerodynamic sweeping-curving on the endwall flow field of compressor cascade. The precision of the numerical simulation depends on the inlet and outlet boundary conditions as well as the turbulence model more than the grid refinement level and the grid type. The 3-D flow field is changed completely in a forward-swept compressor cascade, which makes the low energy fluid redistribute in the flow passage. The blade both with positively curving and forward sweeping further strengthens this kind of effect, providing a freedom to the blade design.

关 键 词：压气机叶片 压气机叶栅 湍流模型 自由度 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]