抽吸气对高负荷跨声双级风扇裕度影响的数值研究  

Numerical Research on the Influence of Boundary Layer Suction on the Stall Margin of a High Loading Transonic Two-Stage Fan

作　　者：白尨 金海良[1] 金东海[1] 桂幸民[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《燃气涡轮试验与研究》2012年第2期12-17,共6页Gas Turbine Experiment and Research

基　　金：国家自然科学基金(50736007;51006005);"凡舟"青年基金(20100401)

摘　　要：采用数值模拟方法,研究了叶片吸力面开缝抽气方案对某高负荷跨声双级风扇性能和稳定工作范围的影响,分析了开缝位置及大小对抽吸气效果的影响。结果表明:通过静子叶片吸力面边界层抽气,可将边界层分离区的分离流引出,抑制或推迟边界层分离,减小因边界层分离带来的损失,从而改善风扇/压气机的气动性能,提高其稳定工作裕度;抽吸气效果与缝隙位置及大小等因素有关,风扇/压气机设计中应用抽吸气技术时须综合考虑以上各种因素的影响。The numerical simulation method was adopted to investigate how the technique of boundary lay- er suction on the vane suction side affected the performance and stall margin of a high loading transonic two-stage fan. The influences of the location and width of slot on the effects of boundary layer suction were analyzed. The results indicated that the boundary layer suction on the stator vane can eliminate the separa- tion flow in the range of boundary layer separation and prevent or postpone the boundary layer separation to improve the aerodynamic performance of the fans/compressors and broaden their stall margin. The effects of boundary layer suction are related to the location and width of the slot. All the factors should be taken into account when the technique of boundary layer suction is adopted in the design of fan/compressor.

关 键 词：高负荷 跨声速 风扇 边界层抽气 数值模拟 裕度 

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]