超声速串列静叶设计  

Design of supersonic tandem stator

作　　者：曹志鹏[1] 尹红顺[1] 周拜豪[1] 余华蔚[1] 

机构地区：[1]中国燃气涡轮研究院,成都610500

出　　处：《燃气涡轮试验与研究》2015年第2期1-6,共6页Gas Turbine Experiment and Research

基　　金：航空基金(2013ZB24005;2011ZB24002)

摘　　要：高压比单级风扇静叶进口全超声,气流转折角大于50°,常规单排静叶难以达到这样高的负荷水平,采用串列静叶结构是一种有效的技术手段。针对进口超声的基元叶型,采用灵活控制中线形状的基元叶型设计方法,优化叶型前缘激波结构,降低激波、附面层干扰引起的损失。在级环境下,对分别采用新方法和定制叶型方法设计的串列静叶进行详细的性能对比,三维数值模拟结果显示:应用新方法设计的高负荷串列静叶,可降低激波损失,优化叶排通道内的激波结构,有效控制尾迹分离,改善叶片排间的流动匹配,提高串列风扇性能。The inlet flow of stator for high pressure ratio fan was supersonic and the flow turning angle was bigger than 50 degree. The tandem stator was used to achieve the loading lever, which could not be done by the conventional stator. The supersonic elementary blade was designed by the flexible control method of camber line shape, which could optimize the shock wave structure, decrease the loss caused by shock-boundary interaction. Detail comparisons of performance between new methods and customizing blade profile methods were carried out in stage environments. The numerical simulation results indicated the high loading tandem stator, which created by advanced blade design techniques decreased the shock wave loss, optimized the shock structure, controlled the wakes separation, improved the flow matching and increased the tandem fan performance.

关 键 词：航空发动机 串列静叶 基元叶型 高负荷 激波结构 流动匹配 

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]