为了对比安装涡流恢复导叶与单排螺旋桨气动性能和气动噪声的差异，采用数值模拟的方法研究了安装六种不同间距涡流恢复导叶和单排螺旋桨的气动力及气动噪声。研究结果表明：在起飞状态，级间距Δx=0.27的工况下，安装涡流恢复导叶使得推力系数增加6.4%，效率增加6.7%。随着间距的增大，前级叶片的桨尖涡、尾迹涡等涡系结构在通过后级叶片时破碎并向下游传播，且强度逐渐减小。噪声强度随着级间距的增加而逐渐减小，最大级间距涡流恢复导叶的噪声与最小级间距涡流恢复导叶噪声相比降低5.7 dB，噪声下降幅度随级间距的增加逐渐减缓，存在级间距最优位置使得推力增加最大，噪声强度适中。

In order to compare the aerodynamic and acoustic performance difference between the swirl recovery vane installed at different axial distances and the single propeller， aerodynamic force and aerodynamic noise of six different swirl recovery vanes and single propeller are calculated by numerical simulation. The results show that in the take off condition，with stage spacing Δx=0.27，it can be seen that the thrust coefficient increases by 6.4% and the efficiency increases by 6.7% after installing the swirl recovery vanes. With the increase of the spacing， the tip vortices，wake vortices and other vortices structures of the front blades are broken and propagate downstream when passing through the rear blades，and the strength gradually decreases. The noise intensity decreases gradually with the increase of stage spacing，and the noise of the maximum stage spacing swirl recovery vanes is 5.7 dB lower than that of the minimum stage spacing swirl recovery vanes and the decreasing amplitude of noise intensity gradually slows down with the increase of stage spacing，and there is an optimal position of stage spacing to maximize the thrust increase and moderate noise intensity.

V211.3

国家自然科学基金（12102451）。