新型桨尖抑制旋翼跨声速特性的影响分析

发布时间：2018-03-03 20:30

本文选题：旋翼　切入点：新型桨尖　出处：《航空动力学报》2016年01期 　论文类型：期刊论文

【摘要】：为研究不同形式的新型桨尖在抑制旋翼跨声速特性方面的作用,开展了多种桨尖对旋翼局部流动及气动特性影响的数值分析研究.发展了基于高效嵌套网格方法的旋翼流场高精度CFD求解方法.在此基础上,详细分析了桨尖外形对旋翼桨叶跨声速区域激波强度、激波诱导气流分离、桨尖涡尾迹及气动性能的影响.数值结果表明:桨尖的后掠和上反在缓解旋翼跨声速特性方面的作用相对较小;桨尖前掠和下反能更有效地减少桨尖外端跨声速区域,降低该位置激波强度并缓解激波-附面层干扰诱导的气流分离;后掠桨尖在减小旋翼反扭矩方面的整体效果良好,直线前掠桨尖在大桨盘拉力状态能够更有效降低旋翼扭矩(直线前掠30°时,扭矩降低达12.3%),桨尖下反可以有效抑制桨尖涡强度(抛物下反30°时,桨尖涡强度降低50%),并加快桨尖涡尾迹的耗散.
[Abstract]:In order to study the role of different types of propeller tips in suppressing the transonic characteristics of rotor, Numerical analysis of the effects of various propeller tips on the local flow and aerodynamic characteristics of rotor is carried out. A high precision CFD method for solving rotor flow field based on efficient nested grid method is developed. The shock intensity and shock induced flow separation of rotor blade in transonic region are analyzed in detail. The numerical results show that the tip swept back and back have relatively little effect on the transonic characteristics of the rotor, and the tip forward and downward inversion can effectively reduce the transonic region of the outer tip of the propeller tip, the numerical results show that the tip of the propeller tip has relatively little effect on the transonic characteristics of the rotor rotor, and that the tip forward and downward sweep can reduce the transonic region of the rotor tip more effectively. Reducing the intensity of shock wave at this position and relieving the separation of airflow induced by shock wave and boundary layer interference, the swept back propeller tip has a good overall effect in reducing the reverse torque of rotor. Linear swept forward tip can reduce rotor torque more effectively in the condition of large propeller disc pull (when linear forward swept 30 掳, torque decreases by 12.3g), the tip vortex strength can be effectively suppressed under propeller tip (when parabolic reverse is 30 掳), The intensity of tip vortex is reduced by 50% and the dissipation of tip vortex wake is accelerated.
【作者单位】：南京航空航天大学航空宇航学院直升机旋翼动力学国家级重点实验室;
【基金】：国家自然科学基金(11272150) 江苏高校优势学科建设工程
【分类号】：V211.52

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