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不同掠型扩压叶栅壁面静压分布特性研究
Experimental Investigation of Surface Static Pressure Distributions in Different Swept Compressor Cascades
【摘要】 实验研究了不同掠型叶片组成的平面扩压叶栅壁面静压分布。结果表明,前掠叶栅流道中横向压力梯度减弱,型面压力沿叶展呈反"C"型,有利于减弱角区低能流体堆积,但中径处损失将有所增加;弯掠叶片强化了上述趋势,其降低端部损失和延缓角区分离的能力更强,具有深入研究的必要。
【Abstract】 The experimental study of static pressure distribution on the surfaces of rectangular compressor cascades with different swept blades shows the forward swept cascade weakens the cross pressure gradient in the flow passage,establishes opposite "C" type pressure distribution along the blade height,which helps reduce the accumulation of low energy fluid in the suction corner region,but increases the loss near the midspan.The forward swept-positive curved cascade,compared to the forward swept cascade,further strengthens the capacity of reducing the loss near the endwall and delaying corner stall.
【Key words】 aerospace propulsion system; cascade experiment; static pressure distribution; swept blade; curved blade;
- 【文献出处】 航空动力学报 ,Journal of Aerospace Power , 编辑部邮箱 ,2004年02期
- 【分类号】V231.3
- 【被引频次】6
- 【下载频次】161