摘要
在涵道螺旋桨的设计过程中,由于涵道与螺旋桨之间相互干扰问题的复杂性,桨盘处的诱导速度难以确定,导致涵道螺旋桨的设计难度相比孤立螺旋桨显著增大。建立了涵道螺旋桨的动量理论模型,推导了涵道螺旋桨的桨盘推力占总推力的比值k与桨盘处诱导速度的对应关系,并基于计算流体力学(CFD)仿真分析揭示了悬停和前飞状态下k值的变化规律。对于给定的涵道构型,相关规律具体表现为:在悬停状态下,k值几乎不随螺旋桨转速变化,基本保持为常数;而在前飞状态下,k值与涵道螺旋桨的推力系数之间存在线性关系,且该线性关系与转速和来流风速等工况参数无关,这十分有利于建立关于k值的工程模型,在此基础上还进一步探讨和揭示了叶片数不同涵道螺旋桨的k值统一规律。以上研究丰富了对涵道螺旋桨的理论认知,并对涵道螺旋桨设计理论的完善具有参考价值。
The design of ducted propellers is much more challenging than that of isolated propellers,as the complex⁃ity of the interference between the duct and the propeller makes it difficult to determine the induced velocity at the pro⁃peller.In the present study,a momentum model of ducted propellers is established.Based on the model,the ratio of the propeller thrust to the total thrust of ducted propellers,denoted as k,is analyzed,and its relationship with the in⁃duced velocity at the propeller is obtained.Furthermore,the variation law of k in the hovering and forward flight states is revealed by numerical analysis based on Computational Fluid Dynamics(CFD)simulations.For a given duct con⁃figuration,the following variation law of k is found:in the hovering state,k hardly varies with the change of the propel⁃ler’s rotational speed;in the forward flight state,the k value and the thrust coefficient of the ducted propeller show a linear relationship.The linear relationship is independent of both the rotational speed and the incoming wind velocity,which is very beneficial for establishing an engineering model about the value of k.In addition,the uniform law of k val⁃ues for ducted propellers with different number of blades is revealed.The present study enriches the theoretical under⁃standings about ducted propellers and has potential values for application in the ducted propeller design.
作者
李旭东
钟伟
王震
王同光
李金龙
LI Xudong;ZHONG Wei;WANG Zhen;WANG Tongguang;LI Jinlong(Jiangsu Key Laboratory of Hi-Tech Research for Wind Turbine Design,College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Nanjing Xunli Aviation Technology Co.,Ltd.,Nanjing 211113,China;Tianchang Xingzhou Aeronautical Technology Co.,Ltd.,Tianchang 239300,China)
出处
《航空学报》
北大核心
2025年第4期130-149,共20页
Acta Aeronautica et Astronautica Sinica
基金
国家重点研发计划(2022YFE0207000)。
