涵道风扇布局参数对其气动特性的影响研究  

Investigations of the layout parameter influence on the aerodynamic characteristics of ducted fan

作　　者：胡瑞 曹宸恺 赵国庆[1] 招启军[1] HU Rui;CAO Chenkai;ZHAO Guoqing;ZHAO Qijun(National Key Laboratory of Rotorcraft Aeromechanics,NUAA,Nanjing 210016,China)

机构地区：[1]南京航空航天大学直升机旋翼动力学国家级重点实验室,江苏南京210016

出　　处：《飞行力学》2023年第3期7-12,共6页Flight Dynamics

基　　金：国家自然科学基金资助(12072156,12032012)。

摘　　要：基于Navier-Stokes方程开展了不同气动布局参数下的涵道风扇非定常气动特性数值模拟研究。首先,结合滑移网格方法建立了适用于涵道风扇流场求解的数值模拟方法,并基于NASA涵道风扇试验模型开展了气动性能计算验证。随后,基于所建立的CFD方法开展了涵道风扇气动布局参数对其气动特性的影响研究,揭示了悬停状态下桨尖间隙和桨盘/涵道轴向相对位置对涵道风扇流场与气动性能的影响规律。结果表明:较大的桨尖间隙对桨尖涡的抑制作用减弱,导致涵道风扇的气动性能大幅降低,同时,桨尖涡强度的增加极大地改变了桨叶尖部的压强分布;当桨盘由基准位置向涵道出口方向移动时,涵道内的诱导速度分布发生改变,涵道唇口处气流速度降低,唇口的负压峰值下降,导致涵道拉力减小,当桨盘位置由基准位置向涵道入口移动时,桨尖涡的卷起对唇口处流动的影响加剧,导致涵道拉力明显降低。Based on the Navier-Stokes equations,the numerical simulations of unsteady aerodynamic characteristics of ducted fan with different aerodynamic layout parameters are carried out.Firstly,numerical methods for the flowfield of ducted fans were established coupled with the sliding mesh method,and the aerodynamic performance was verified based on the NASA ducted fan test model.Then,the influence of the aerodynamic layout parameters of the ducted fans on its aerodynamic characteristics was studied based on the established CFD method,and the influences of the blade tip clearance and the axial relative position between the rotor disk and the duct on the flowfield and aer-odynamic performance of the ducted fan in hover was revealed.The results show that the suppression effect of large tip clearance on the tip vortex is weakened,leading to a significant reduction in the aerodynamic performance of the ducted fans.Meanwhile,the tip vortex is enhanced and greatly changes the pressure distribution at the blade tip.As the rotor disk moves from the baseline position to the duct outlet,the distribution of induced velocity in the duct is mainly affected where the flow velocity and the peak negative pressure at the duct lip decreases,causing the reduction of the duct thrust.However,as the rotor disk moves towards the duct inlet,the roll-up of the tip vortex has an enhanced impact on the flow at the lip,resulting in a significant reduction in the duct thrust.

关 键 词：涵道风扇 桨尖间隙 桨盘/涵道相对位置 气动性能 CFD方法 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]