为了深入考察渐缩方式布置的三角对翼几何参数对半圆截面螺旋通道内流体流动特性与涡旋特性的影响，采用实验和数值模拟方法进行了研究。通道曲率δ在0.05~0.125之间，其中δ=0.067通道内三维速度场的模拟结果与激光多普勒测速仪测量结果吻合较好。结果表明，对翼诱导产生的纵向涡旋螺旋发展并强化离心涡旋，雷诺数Re越大，复合涡旋中心位置越靠近截面中心；当δ≥0.1时对翼后7.09~13.04倍翼高范围内会产生附加涡旋，且附加涡旋出现位置La/b值随着Re数和对翼长高比Γ值的增加而增大，随着δ和攻角?的增大而减小。复合纵向涡旋作用范围及其强度J值随着δ值和Γ值的增大而增大，J值最高可为单一螺旋通道的6.48倍，最大作用范围可达近20倍翼高。Γ值和无量纲厚度Δ对流动阻力f影响显著。

Experimental and numerical methods have been employed to study the influence of winglet pair geometry parameters on fluid flow and vortices characteristics in helical channels with semicircular cross section. The curvature ratios of helical channels are within the range of δ=0.05~0.125. Simulated data of three dimensional velocities have good agreements with those obtained by Laser Doppler velocimeter when δ=0.067. The results showed that the longitudinal vortices induced by the wing pair developed spirally along the main flow and strengthened the vortices produced by centrifugal force to a certain extent. The larger the Reynolds number was, the closer of the vortices were to the centerline of the cross section. There may be additional vortices in the range of 7.09~13.04 times of wing height behind the winglet pair when δ≥0.1. The value of La/b was used to indicate the occurrence position of the additional vortices. La/b value increased with the increasing of Reynolds number and the aspect ratio of the winglet, but it decreased with the increasing of curvature ratio and attack angle. As curvature ratio and the aspect ratio of the wing increasing, the strength of the combined longitudinal vortices would be enhanced and the affecting range of combined vortices in the helical channel became larger at the same time. The maximum strength of the combined longitudinal vortices was 6.48 times that of the smooth helical duct in the studied range. The longest affecting range of combined vortices reached the length of about 20 times the wing height in the helical channel. The aspect ratio of the wing and dimensionless thickness had significant impacts on flow resistance.