附面层抽吸对高负荷跨音风扇转子性能的影响  

Effects of Boundary Layer Suction on the Performance of High-load Transonic Fan Rotor

作　　者：黄建[1] 刘波[1] 赵鹏程[1] 曹志远[1] 

机构地区：[1]西北工业大学 动力与能源学院,西安710072

出　　处：《航空工程进展》2012年第3期338-343,共6页Advances in Aeronautical Science and Engineering

基　　金：国家自然科学基金(50976093)

摘　　要：针对高负荷跨音速压气机存在强激波及严重的激波与附面层干扰,以某高负荷跨音风扇转子为研究对象,采用数值方法研究了吸力面不同抽吸位置对风扇转子性能的影响。结果表明:高负荷跨音风扇转子存在激波和逆压梯度引起的附面层分离,合理的抽吸位置既能有效的削弱激波与附面层干扰,又能控制尾缘分离,使通道激波后移,扩大流道高马赫数范围;通道内三维激波范围的扩大会带来转子稳定裕度的负面影响。In high-load transonic compressor, there is always strong shockwave as well as its interaction with boundary layer. A high-load transonic fan rotor is investigated through numerical simulation to explore the in- fluence of different aspirated position on the fan rotor performance. The results show that shockwave and ad- verse pressure gradient in high-load rotor passage will cause boundary layer separation. Reasonable aspirated po- sition can effectively weaken the interference between shockwave and boundary layer, and also control the trai- ling edge separation, make passage shockwave moving toward outlet, enlarge the work range at high Mach number~ the expansion of the three dimensional shockwave in the channel will bring negative effect on rotor stall margin.

关 键 词：跨音风扇 激波 附面层吸气 涡轮风扇发动机 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]