直升机旋翼桨尖涡模拟和控制的CFD数值研究  

CFD simulation on the evolution and control of helicopter rotor tip vortices

作　　者：李擎 LI Qing(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》2022年第4期14-19,26,共7页Flight Dynamics

基　　金：江苏高校优势学科建设工程资助项目。

摘　　要：针对旋翼桨尖涡的生成演化问题,建立了一种基于CFD技术的数值模拟方法。首先,采用耦合k-ε湍流模型的雷诺平均N-S方程作为主控方程,搭配针对桨尖涡生成演化问题进行加密的运动嵌套网格进行计算,并以Caradonna-Tung旋翼模型为算例验证了该方法的可靠性。然后,采用该方法对桨尖涡的生成演化过程进行了研究,并开展了参数影响分析。最后,通过改变桨尖形状的方法,对桨尖涡被动控制方法进行了研究,并用CFD软件进行模拟验证。研究结果表明,桨尖涡的生成过程会随升力的增加而变得愈发激烈,桨尖涡的近场演化存在强烈的物理耗散现象;而桨尖涡的远场演化存在先收缩后扩张的现象,即存在收缩极限。所得结论对加深桨尖涡现象的理解具有一定意义。A numerical simulation method based on CFD technology was established to research the formation and evolution of blade tip vortex. Firstly, the simulation methods consists of the Reynolds time-averaged N-S equation coupled with the k-ε turbulence model as the control equation, and the encrypted overset mesh according to the characteristics of the blade tip vortex. The Caradonna-Tung model rotor is used as an example to verify the reliability of this method. Then, this method is used to study the mechanism of the generation and evolution of the blade tip vortex, and the parameter influence analysis is also carried out. Finally, this article gives a research on the passive control of tip vortex by using the geometry variation of blade tip, which is proved to be effective by using CFD simulation. The research results show that the generation process of the tip vortex will become more and more intense with the increase of lift;there is a strong physical dissipation phenomenon in the near-field evolution of the tip vortex. Furthermore, the far field evolution of tip vortex has the phenomenon of contraction first and then expansion, i.e., a contraction limit. The obtained conclusions have certain significance for deepening the understanding of the helicopter tip vortex phenomenon.

关 键 词：桨尖涡 旋翼 嵌套网格 CFD 流动控制 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]