旋翼涡环状态非定常气动特性研究  

Investigation on unsteady aerodynamics of rotor in the vortex ring state

作　　者：赵磊[1] 王博[1] 王畅[2] 招启军[1] ZHAO Lei;WANG Bo;WANG Chang;ZHAO Qijun(National Key Laboratory of Helicopter Aeromechanics,NUAA,Nanjing 210016,China;China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]南京航空航天大学直升机动力学全国重点实验室,江苏南京210016 [2]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《飞行力学》2024年第3期1-5,共5页Flight Dynamics

基　　金：国家自然科学基金资助(12032012);重点实验室基金资助(61422202103);江苏高校优势学科建设工程资助项目。

摘　　要：旋翼涡环状态机理研究对直升机飞行安全具有重要意义。基于雷诺平均N-S控制方程,采用滑移网格技术和非结构网格建模,使用Spalart-Allmaras湍流模型,对直升机旋翼在不同下降率的垂直飞行中遭遇涡环状态进行了数值模拟研究。首先,验证了旋翼涡环状态的风洞试验数据;然后,在深度涡环状态下对旋翼进行了气动力分析,发现旋翼桨叶之间出现不同步的周期性变化现象;最后,对不同下降率下旋翼的气动力变化进行了对比。研究结果表明,涡环会导致旋翼叶片前段出现明显的拉力损失,而旋翼后段的拉力略微增加;该研究为了解旋翼遭遇涡环状态提供了一种分析思路,并对指导旋翼外形设计具有一定的实际意义。Research on the rationality of rotor in the vortex ring state is of significant importance for helicopter flight safety. Based on the Reynolds-averaged Navier-Stokes control equations, the sliding mesh technique, unstructured mesh modeling and the Spalart-Allmaras turbulence model, rotor encountering the vortex ring state in vertical flights with different descent rates was simulated. Firstly, the wind tunnel experimental data of the rotor in vortex ring states were verified. Then the aerodynamic parameters of the rotor in the deep vortex ring state were analyzed. It was found that the spanwise aerodynamic force between propellers has a non-synchronous periodic change. Finally, the rotor aerodynamic changes under different descent rates were compared. The research results show that the vortex ring will cause significant thrust loss at the front end of the rotor blade, while the thrust at the rear end of the rotor will increase slightly. An analytic idea is provided for the rotor encountering vortex ring state in this paper, which has certain practical significance for guiding the rotor shape design.

关 键 词：旋翼 涡环状态 垂直下降 CFD 

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]