三维造型对高负荷跨声风扇静子的影响分析  

Analysis of three-dimensional blading influence on highly loaded transonic fan stator

作　　者：徐朋飞[1] 刘宝杰[1] 赵斌[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机气动热力国防科技重点实验室,北京100191

出　　处：《航空动力学报》2012年第3期674-681,共8页Journal of Aerospace Power

摘　　要：以负荷系数高达0.42的跨声风扇进口级为背景,利用三维数值模拟手段,研究了叶片三维气动造型技术对高负荷跨声风扇静子气动性能的影响,并深入地分析了其影响机理.结果表明:由于激波在静子叶根有垂直于轮毂端壁的趋势,因此前掠造型对于激波/端壁附面层所主导的静子角区分离的控制效果并不明显;相比之下,正弯静子通过加入叶片力使得角区中的低速流体向叶中发生径向迁移,显著地改善了静子的性能;而复合弯掠进一步提高了静子的性能,说明单纯使用前掠造型收效不佳,需要配合正弯造型才能达到最佳效果.Under the background of highly loaded transonic inlet fan stage, which pro- duces loading coefficient of 0.42, three-dimensional （3-D） blading influence on transonic stator aerodynamic performance was analyzed as well as its mechanism with numerical simu lation technology. The result indicates that the forward sweep is not effective to control the corner separation conducted by shock/endwall boundary layer interaction because of the trend that the shock always tends to remain perpendicular to the endwall. Positive bow mod- ifies the stator performance obviously through adding the blade force to migrate the low speed corner fluid toward to mid-span. Sweep/bow composition improves the stator per- formance further, illustrating that the benefit from pure forward sweep is limited and for ward sweep can attain optimum effect when combining the positive bow.

关 键 词：掠形 弯形 静子 跨声风扇 高负荷 

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]