脊状表面翼型叶片减阻机理研究  

Study on Drag-reduction Mechanism of Riblet Surface on Aerofoil Blade of Centrifugal Fan

作　　者：吴正人[1] 郝晓飞[1] 戎瑞[1] 王松岭[1] 

机构地区：[1]华北电力大学电站设备状态监测与控制教育部重点实验室,保定市071003

出　　处：《系统仿真学报》2014年第6期1355-1361,共7页Journal of System Simulation

基　　金：河北省自然科学基金资助项目(E2012502016);中央高校基本科研业务费专项资金资助项目(12QN39)

摘　　要：利用Fluent软件,对G4-73型离心风机翼型叶片脊状表面的减阻特性进行了数值模拟研究,并分析了其减阻效果及减阻机理。结果表明:脊状结构在风机翼型表面具有较好的减阻效果,脊状结构尺寸s=0.1mm时的减阻效果较好,最大减阻率为9.65%。脊状结构沟槽内部形成的稳定的二次涡,能显著减小黏性阻力。相比于光滑表面,脊状结构表面总体剪切应力明显减小,反映了翼型表面脊状结构的减阻效果。同时,沟槽间隔的存在一方面使得部分区域剪切应力明显增大,另一方面能够避免沟槽内涡旋的相互干扰,故推测存在最优沟槽间距在避免涡旋相互干扰的同时使得壁面剪切应力最小。所得研究结果可为工程实际中风机叶片的优化改型及性能改善提供参考依据。The drag reduction characteristics of riblet structure on aerofoil blade of the G4-73 centrifugal fan were numerically simulated with Fluent. Then the effect and the mechanism of drag reduction were investigated ulteriorly. The results are as follows： Riblet structure has a good drag reduction effect on the blade. The best drag reduction effect has been gotten with riblet width s=0.1mm, with the greatest drag reduction efficiency of 9.65%. The stable secondary vortex formed within the groove of the riblet structure could reduce the viscous resistance significantly. Compared to the smooth surface, the overall shear stress of the riblet surface is significantly reduced, reflecting the drag reduction effect of the riblet structure on the airfoil surface. Meanwhile, the existence of the interval between grooves makes the shear stress of some regions increased obviously, and it could avoid the mutual interference between vortexes within the groove at the same time. So it is speculated that there would be an optimal interval which could avoid the mutual interference and make the shear stress minimum as well.

关 键 词：离心风机 脊状结构 减阻 涡旋 数值模拟 

分 类 号：TH4[机械工程—机械制造及自动化] O355[理学—流体力学]