前缘涡度对压气机叶栅性能的影响
Effect of Leading Edge Tubercles on Compressor Cascade Performance
摘要：
锯齿是对翼型前缘的改进，其形式为钝的波浪状锯齿。关于孤立翼型上结节效应的几项研究表明，结节在过失速状态下具有有益的效果，因为它可以减少阻力，增加升力，从而延迟失速。延迟失速的前景对于燃气轮机中的轴向压缩机的设计者特别有吸引力，因为这导致具有更高负载的设计，并且因此导致具有更少级数的更高压力升高。本文对NACA 65209翼型叶栅进行了不同结节形状的实验研究。在出口平面上使用五孔探针进行测量，以比较叶栅性能参数。此外，在叶片表面附近进行热线测量，以了解靠近结节区域的流动性质。叶栅端壁上的油流可视化显示了通过有和没有结节的叶片通道的流动。对于所考虑的叶栅，发现最佳性能叶片组的估计失速角从未修改叶片的6.0°增加到8.6°。在轴流压气机叶片上应用这种结构，可以有效地抑制轴流压气机的失速，扩大轴流压气机的工作范围。
英文摘要：
Tubercles are modifications to the leading edge of an airfoil in the form of blunt wave-like serrations. Several studies on the effect of tubercles on isolated airfoils have shown a beneficial effect in the post-stall regime, as reduced drag and increased lift, leading to a delay of stall. The prospect of delaying stall is particularly attractive to designers of axial compressors in gas turbines, as this leads to designs with higher loading and therefore higher pressure rise with fewer number of stages. In the present study, experiments were performed on a cascade of airfoils with NACA 65209 profile with different tubercle geometries. The measurements were made over an exit plane using a five-hole probe to compare the cascade performance parameters. Additionally, hot-wire measurements were taken near the blade surface to understand the nature of the flow in the region close to the tubercles. Oil-flow visualization on the cascade end wall reveal the flow through the passage of blades with and without tubercles. For the cascade considered, the estimated stall angle for the best performing set of blades is found to increase up to 8.6° from that of the unmodified blade of 6.0°. Application of such structures in axial compressor blades may well lead to suppression of stall in axial compressors and extend the operating range.
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