超声速串列静叶积叠优化分析  

Stacking Optimization Analysis of Supersonic Tandem Stator

作　　者：曹志鹏[1] 王永明[1] 尹红顺[1] 安利平[1] 

机构地区：[1]中国燃气涡轮研究院,四川成都610500

出　　处：《航空科学技术》2015年第5期81-88,共8页Aeronautical Science & Technology

基　　金：航空科学基金(2013ZB24005;2011ZB24002)~~

摘　　要：在进口超声速、气流转折角大的高负荷条件下,静叶通道中激波强度高,激波、附面层干扰引起的损失大,且静叶中三维流动引起的径向载荷分布不均匀,易产生角区分离。叶片积叠优化是提高风扇性能的一项有效技术。采用数值模拟的方式研究了不同积叠形式对优化串列静叶沿展向激波结构,改善叶排间流动匹配的作用。三维流动对比分析可以得出:高负荷串列静叶采用正弓形积叠,叶片展向载荷分布合理,静叶端壁角区分离损失减小,前后叶片排流动匹配较好,风扇性能进一步提高。In the high loading conditions of supersonic inlet flow and big turning angle, high loss is caused by the interaction of strong shock and boundary layer in ifelds of the stator passage, the non-uniform distributions of radial loadings caused by three-dimensional lfow could bring the corner separation. Optimization of blade stacking techniques could improve the fan performance obviously. This paper carried out affect analysis of the different stacking line on optimizing the radial shock structure and improving the lfow match between blade rows by numerical simulation. The comparisons of three dimensional lfow numerical results showed：positive bowed blade optimized the radial loadings, reduced the corner separation loss of stator end wall, and improved the lfow matching, increased the fan performance.

关 键 词：串列静叶 超声速 积叠优化 角区分离 弓形静叶 流动匹配 高压比风扇 

分 类 号：V235.13[航空宇航科学与技术—航空宇航推进理论与工程]