摘要
为了将串列叶栅更好地应用于高负荷核心压气机后面级,通过直列叶栅的方法,引入高度倾斜的附面层来流条件,对采用串列叶栅作为核心压气机后面级的静子进行变间隙数值模拟研究。比较低展弦比串列叶栅不同间隙、不同附面层来流条件的叶栅整体性能、尖部载荷及叶尖泄漏涡的发展情况。结果表明:随着间隙增大,叶尖区域堵塞加强,损失加大;倾斜附面层来流,低叶展总压损失得到明显改善;小间隙时叶尖产生两个间隙泄漏涡,前叶泄漏涡在叶栅通道中部消失,后叶泄漏涡在近前缘产生;随着间隙增大,泄漏涡绕卷起始点后移。
In order to improve the application of tandem cascade, to nlake it better apply to high load core compressor, the rear stages＇ clearance effects of high pressure compressor with tandem stator are captured. A redesign of a high-turning tandem cascade is studied in the manner of linear cascade with different clearance sizes. The cascade performances, tip loading and the development trajectory of leakage vortex are compared with collateral inlet boundary layer and skewed inlet boundary layer. The results show that the tip region blockage is burdened and total pressure loss is sharpened with the clearance increasing. With the skewed inlet boundary lay er, the pressure loss is decreased clearly at the low span. Two leakage vortexes are captured near the tip region with 2% span clearance. The front blade＇s leakage vortex vanishes in the passage, and the second leakage vortex emerges near the leading edge of rear blade. With the clearance increasing, the roll up point moves down- stream.
出处
《航空工程进展》
2013年第4期443-449,共7页
Advances in Aeronautical Science and Engineering
基金
国家自然科学基金(51236006)
关键词
轴流压气机
高压压气机
大弯角静子
串列叶栅
间隙效应
axial compressor
high pressure compressor
high-turning stator
tandem cascade
clearance effects
