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首页> 外文期刊>Chinese journal of aeronautics >Experimental Study on the Aerodynamic Performance of Swept-Curved Blade
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Experimental Study on the Aerodynamic Performance of Swept-Curved Blade

机译：后掠叶片气动性能的实验研究

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摘要

Compared with a straight blade, a unique compressor blade integrated forward-swept and positive-curved stacking line is studied experimentally. Aerodynamic parameters of the two cascades are measured by a five-hole probe at different positions and ink trace flow visualization is conducted on blade surfaces. The result shows that the swept-curved cascade has lower endwall loss and higher midspan loss as compared with the straight cascade. However, lower loss is accompanied with lower diffusion factor. Opposite 'C' shape static pressure distribution is established on the suction surface of the swept-curved blade, which is helpful for avoiding the accumulation of low energy fluid in the endwall corner region. Anyhow the studies support the conclusion that the swept-curved blade conduces to not only the reduction of overall loss but also the improvement of stable operation in the endwall corner region.
机译：与直叶片相比，实验研究了一条独特的集成了前掠式和正弯曲式堆叠线的压缩机叶片。两个叶栅的空气动力学参数通过一个五孔探针在不同位置进行测量，并在刀片表面上进行墨迹流可视化。结果表明，与直式叶栅相比，弯曲弯曲的叶栅具有较低的端壁损耗和较高的中跨损耗。然而，较低的损耗伴随较低的扩散因子。在后掠曲线叶片的吸力表面上建立了相反的“ C”形静压分布，这有助于避免低能流体在端壁拐角区域积聚。无论如何，这些研究支持这样的结论，即后掠弯曲的叶片不仅有助于减少整体损失，而且还可以改善端壁拐角区域的稳定运行。

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