叶尖小翼周向最宽位置对高负荷压气机级特性影响的研究

Effects of widest circumferential position of tip winglet on high load compressor stage performance

关键词:  高负荷压气机  叶尖小翼  级特性  稳定工作裕度  数值研究

Key words:  High-load compressor  Tip winglet  Stage performance  Stable operating margin  Numerical study

摘要:

针对叶尖小翼扩稳技术，采用数值方法在改变叶尖小翼宽度的基础上，考虑了叶尖小翼几何形状的周向最宽位置对高负荷压气机级性能的影响。研究结果表明，叶尖小翼宽度越大且最宽位置靠近叶片两端时，压气机级的稳定工作裕度的提升越明显。叶尖小翼宽度为2.0倍叶顶宽度时，且周向最宽位置位于转子前缘25%轴向弦长时，叶尖小翼最多使叶顶泄漏流的质量流量减少了7.66%，提升了压气机级通道内流体的轴向速度，抑制了转子及静子叶片叶表的分离情况，从而延缓了压气机级的失速，压气机级的稳定工作裕度提升了29.18%。

Abstract:

For the tip winglet expansion technology， on the basis of changing the tip winglet width， the numerical calculation method is adopted to consider the effects of the widest circumferential position of tip winglet geometry on high-load compressor stage performance. The research results show that when the width is larger and the widest position of the tip winglet is closer to both ends of the blade， the stable operating margin of the compressor stage is improved more significantly. When the width of tip winglet is double the tip width， and the widest circumferential position of the tip winglet is located at 25% chord length of the rotor leading edge， the tip winglet reduces the tip leakage flow mass flow by 7.66% at most and increases the axial velocity of the fluid in the compressor stage passage. The separation of the rotor blade and stator vane surfaces is suppressed， thus delaying the stall of the compressor stage， and the stable operating margin of the compressor stage increases by 29.18%.