悬停旋翼桨尖涡吹气控制的数值模拟

发布时间：2018-03-16 17:14

本文选题：旋翼　切入点：桨尖涡　出处：《南京航空航天大学学报》2016年02期 　论文类型：期刊论文

【摘要】：开槽桨尖是减弱旋翼桨尖涡强度的一种被动流动控制手段。旋翼桨尖涡由于涡量高度集中在一个很小的区域范围内,数值计算容易受到网格分布和数值耗散的影响,导致涡量耗散过快,不利于对旋翼尾迹涡开展研究。针对这一问题,文中采用重叠网格局部加密和湍流模型旋转修正等方法,获得了悬停旋翼的高分辨率桨尖涡流场。采用该方法,对比研究了Caradonna-Tung旋翼基本外形和开槽桨尖外形在悬停状态下的空间旋涡流场,从涡量分布、旋涡特征速度等方面研究了开槽桨尖控制桨尖涡强度的流动机理,比较了4种不同开槽方式对控制效果的影响,以及对旋翼悬停性能的影响。结果表明,开槽桨尖能够有效减弱桨尖涡的强度,但同时会对旋翼拉力和扭矩产生一定的负面影响。
[Abstract]:The slotted propeller tip is a passive flow control method to reduce the vortex intensity of rotor tip. The tip vortex of rotor rotor is easily affected by the grid distribution and numerical dissipation because the vortex height is concentrated in a very small region. The vorticity dissipation is too fast, which is not conducive to the study of rotor wake vortices. In order to solve this problem, some methods such as overlapping mesh local encryption and turbulence model rotation correction are used in this paper. The swirl field of high resolution propeller tip of hovering rotor is obtained. By using this method, the spatial vortex flow field of Caradonna-Tung rotor is compared with that of slotted rotor tip in hovering state. The flow mechanism of slotted propeller tip controlling tip vortex strength is studied in terms of vortex characteristic velocity. The effects of four different grooving modes on the control effect and the hovering performance of rotor are compared. The slotted tip can effectively reduce the strength of the tip vortex, but it will have some negative effects on the rotor tension and torque at the same time.
【作者单位】：中国空气动力研究与发展中心计算空气动力研究所;
【基金】：国家自然科学基金(11572341)资助项目
【分类号】：V211

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