剪刀式尾桨涡流干扰机理和气动特性研究

发布时间：2018-03-11 13:10

本文选题：直升机　切入点：剪刀式尾桨　出处：《力学学报》2016年04期 　论文类型：期刊论文

【摘要】：采用非常规剪刀式尾桨对直升机整体性能有着重要影响,关于其复杂流动干扰机理的研究尚处在发展之中.为了掌握剪刀式尾桨的流动干扰机理和参数影响规律,建立了适合于悬停状态下剪刀式尾桨干扰涡流场分析的计算流体力学(computational fluid dynamics,CFD)数值模拟方法.采用积分形式的Reynolds-averaged Navier-Stokes(RANS)方程作为旋翼流场求解控制方程,围绕旋翼流场的结构网格采用嵌套网格方法生成.在CFD方法验证基础之上,对悬停状态下两种不同构型剪刀式尾桨桨尖涡的涡核位置和强度的演变规律进行了定量分析,并对流场中桨尖涡与桨叶的贴近干扰、碰撞、破碎运动,同时准确捕捉了不同尺度涡之间的相互干扰、融合的过程进行了分析.进一步研究了剪刀角和轴间距参数对不同构型剪刀式尾桨气动特性的影响规律.计算结果表明,剪刀式尾桨流场中存在复杂的桨-涡干扰和涡-涡干扰现象,剪刀角和轴间距对剪刀式尾桨的气动特性有重要影响,L构型剪刀式尾桨气动性能整体优于U构型剪刀式尾桨.
[Abstract]:The use of non-conventional scissors tail impellers has an important effect on the overall performance of the helicopter, and the study on the mechanism of complex flow disturbance is still under development. A numerical simulation method of computational fluid dynamics (CFD) is established for the analysis of eddy current field of scissors tail propeller in hovering state. The integral Reynolds-averaged Navier-Stokes equations are used to solve the governing equations of rotor flow field. The structure mesh around rotor flow field is generated by nested grid method. Based on the verification of CFD method, the evolution law of vortex core position and strength of two different types of scissors tail propeller tip vortices in hovering state are quantitatively analyzed. In the flow field, the impeller tip vortex and the blade close to the interference, collision, fragmentation movement, and accurately capture the different scales of the interaction between vortices, The process of fusion is analyzed. The influence of the parameters of scissors angle and axial spacing on the aerodynamic characteristics of different configurations of scissors tail propeller is studied. There are complex phenomena of impeller vortex interference and vortex vortex disturbance in the flow field of scissors tail propeller. The angle of scissors and axial spacing have important influence on the aerodynamic characteristics of scissors tail impeller. The aerodynamic performance of scissors tail impeller with L configuration is better than that of U type scissors tail impeller on the whole.
【作者单位】：南京航空航天大学直升机旋翼动力学国家级重点实验室;
【基金】：国家自然科学基金资助项目(11272150)
【分类号】：V211.52

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