计入桨叶结构弹性的新型桨尖旋翼流场数值模拟研究
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摘要
弹性旋翼流场的数值模拟是直升机空气动力学领域具有挑战性的研究课题。本文开展了适用于弹性旋翼的动态网格变形方法和嵌套网格系统、桨叶结构有限元分析建模以及旋翼流场模拟等研究,发展了与该网格系统对应的基于RANS方程的旋翼流场数值求解方法和程序,并针对直升机弹性旋翼流场进行了数值计算与分析,同时,开展了新型桨尖弹性旋翼流场的数值模拟。主要工作包括以下方面:
作为背景和前提,本文概述了旋翼计算流体力学(CFD)、桨叶结构分析、弹性桨叶旋翼流场模拟以及新型桨尖旋翼流场模拟等研究方面的国内外现状,指出了现有研究中存在的不足,以及开展弹性旋翼、新型桨尖弹性旋翼的流场数值模拟的重要意义,提出了本文拟采用的研究方法和内容。
为了更好地模拟桨叶的弹性运动,基于改进的弹簧模拟方法,建立了一个针对桨叶贴体网格的动态变形方法,该方法适合于弹性旋翼流场的CFD求解。针对旋翼瞬态流场、桨尖涡运动的特点,本文生成了由用于模拟桨叶近场气动力环境的贴体网格和用于捕捉桨尖涡运动信息的流场背景网格组成的动态嵌套网格系统。给出了一种搜索网格信息的高效方法,以减小在时变的旋翼流场模拟中嵌套信息搜索的成本。基于中等变形梁理论和哈密尔顿原理,建立了一个旋翼动力学的有限元分析模型。该模型中,推导了桨叶运动的偏微分控制方程,并采用改进的Newmark-beta方法对桨叶运动方程进行求解。此外,还在该桨叶结构分析模型中耦合了旋翼系统的配平计算,以得到更切合实际的桨叶结构响应。
在嵌套网格的基础上,应用RANS方程,本文又发展了旋翼流场的CFD分析方法和计算模型。该方法将高阶逆风格式和通量差分裂格式相结合对旋翼流场进行空间离散,采用基于Krylov子空间迭代的无矩阵形式LU-SGS隐式方法进行时间积分,以有效提高旋翼CFD模拟的计算效率。结合所建立的弹性桨叶结构分析模型,在Partitioned方法的基础上,本文还给出了弹性旋翼流场耦合的求解策略。在此基础上,进一步建立了弹性旋翼流场的数值模拟方法。然后,以不同旋翼为算例,进行了刚性和弹性旋翼流场的数值模拟方法的验证计算。
为了适合于新型桨尖的研究,本文在所建立的弹性旋翼流场分析模型的基础上,又进一步拓展建立了适合于形状线性变化的新型桨尖弹性旋翼流场模拟的方法。应用该方法,着重针对悬停状态下后掠、尖削、下反及其组合形状的新型桨尖弹性旋翼进行了流场数值计算,研究了弹性对新型桨尖旋翼流场的影响,同时探究了桨尖外形参数对桨叶表面气动载荷的影响规律。
Elastic rotor flowfield numerical simulation is a challenging subject in the field of Helicopter Aerodynamics. The dynamic grid deforming approach and overset grid system for elastic rotors, the blade structural finite-element analyzing modeling, and the rotor flowfield simulation are investigated in this thesis. A solving method and the corresponding code for rotor flowfield are developed based on the RANS equations and the grid system, and based on the method, the elastic rotor flowfield of helicopters is computed and analyzed. Meanwhile, the elastic rotor flowfield with new blade tips is also simulated. The major contributions of the author’s research work are as follows:
As the background of present work, the research and development in the field of the rotor Computational Fluid Dynamics, blade structural analysis, flowfield simulation for elastic-blade rotors as well as flowfield simulation for new blade-tip rotors are briefly reviewed. The difficulties in the current research are pointed out, and the significance of modeling elastic rotor flowfield, including new blade-tip rotor flowfield is then described. In addition, the methodology used in the present research is briefly introduced.
In order to model blade elastic movement, on the basis of modified spring simulation approach, the thesis establishes a method of blade body-fitted grid dynamic deformation wich is suitable for the flowfield solution of elastic rotor. According to the characteristics of rotor transient flowfield and the blade-tip vortex movement, a dynamic overset grid system, which is composed of a body-fitted grid used for simulating the blade aerodynamic circumstance in the near field and a background grid for capturing the movement of tip vortice, is constructed. Also, an efficient method for grid information search is given to reduce the searching cost. Based on the Hamilton’s principle and the beam theory of small strain and moderate deformation, a finite-element analysis model for rotor blade dynamics is established. In this model, the partial differential gorverning equation on blade movement is derived, and the equation is discretized and then solved by applying the improved implicit Newmark-beta method. Furthermore, a trim algorithm for the rotor system is coupled into the blade structural analysis for impoving the solution of blade structural response.
Based on the overset grid, a CFD analyzing method for rotor flowfield is developed with the application of RANS equations. In this method, the high-order upwind scheme is combined with the flux-difference splitting scheme to discretize the rotor flowfield spatially. Then, the equation is integrated in the time domain with the matrix-free LU-SGS implicit scheme of Krylov subspace iteration, so as to improve the computational efficiency of rotor CFD simulation. With the help of‘Partitioned’method, the coupled solving strategy for the elastic rotor flowfield is also provided, by combining the elastic blade structural analysis. On this basis, the elastic rotor flowfield simulation is further carried out. Afterwards, the present rigid and elastic rotor flowfield simulation methods are validated by comparing with available reference results for different rotor cases.
To study new blade-tip rotors, the author expands the above work to simulate flowfield of the elastic rotor with linear-changed blade tips, and a corresponding method is developed. The computations on the elastic rotor flowfield in hover with sweep, tapered, anhedral and combined shapes are performed by the use of the method, and the influence of elasticity on the rotor flowfield with new blade tips is analysed. From the analyses, the conclusions about how the tip shape parameters affect the blade surface airloading are drawn.
作为背景和前提,本文概述了旋翼计算流体力学(CFD)、桨叶结构分析、弹性桨叶旋翼流场模拟以及新型桨尖旋翼流场模拟等研究方面的国内外现状,指出了现有研究中存在的不足,以及开展弹性旋翼、新型桨尖弹性旋翼的流场数值模拟的重要意义,提出了本文拟采用的研究方法和内容。
为了更好地模拟桨叶的弹性运动,基于改进的弹簧模拟方法,建立了一个针对桨叶贴体网格的动态变形方法,该方法适合于弹性旋翼流场的CFD求解。针对旋翼瞬态流场、桨尖涡运动的特点,本文生成了由用于模拟桨叶近场气动力环境的贴体网格和用于捕捉桨尖涡运动信息的流场背景网格组成的动态嵌套网格系统。给出了一种搜索网格信息的高效方法,以减小在时变的旋翼流场模拟中嵌套信息搜索的成本。基于中等变形梁理论和哈密尔顿原理,建立了一个旋翼动力学的有限元分析模型。该模型中,推导了桨叶运动的偏微分控制方程,并采用改进的Newmark-beta方法对桨叶运动方程进行求解。此外,还在该桨叶结构分析模型中耦合了旋翼系统的配平计算,以得到更切合实际的桨叶结构响应。
在嵌套网格的基础上,应用RANS方程,本文又发展了旋翼流场的CFD分析方法和计算模型。该方法将高阶逆风格式和通量差分裂格式相结合对旋翼流场进行空间离散,采用基于Krylov子空间迭代的无矩阵形式LU-SGS隐式方法进行时间积分,以有效提高旋翼CFD模拟的计算效率。结合所建立的弹性桨叶结构分析模型,在Partitioned方法的基础上,本文还给出了弹性旋翼流场耦合的求解策略。在此基础上,进一步建立了弹性旋翼流场的数值模拟方法。然后,以不同旋翼为算例,进行了刚性和弹性旋翼流场的数值模拟方法的验证计算。
为了适合于新型桨尖的研究,本文在所建立的弹性旋翼流场分析模型的基础上,又进一步拓展建立了适合于形状线性变化的新型桨尖弹性旋翼流场模拟的方法。应用该方法,着重针对悬停状态下后掠、尖削、下反及其组合形状的新型桨尖弹性旋翼进行了流场数值计算,研究了弹性对新型桨尖旋翼流场的影响,同时探究了桨尖外形参数对桨叶表面气动载荷的影响规律。
Elastic rotor flowfield numerical simulation is a challenging subject in the field of Helicopter Aerodynamics. The dynamic grid deforming approach and overset grid system for elastic rotors, the blade structural finite-element analyzing modeling, and the rotor flowfield simulation are investigated in this thesis. A solving method and the corresponding code for rotor flowfield are developed based on the RANS equations and the grid system, and based on the method, the elastic rotor flowfield of helicopters is computed and analyzed. Meanwhile, the elastic rotor flowfield with new blade tips is also simulated. The major contributions of the author’s research work are as follows:
As the background of present work, the research and development in the field of the rotor Computational Fluid Dynamics, blade structural analysis, flowfield simulation for elastic-blade rotors as well as flowfield simulation for new blade-tip rotors are briefly reviewed. The difficulties in the current research are pointed out, and the significance of modeling elastic rotor flowfield, including new blade-tip rotor flowfield is then described. In addition, the methodology used in the present research is briefly introduced.
In order to model blade elastic movement, on the basis of modified spring simulation approach, the thesis establishes a method of blade body-fitted grid dynamic deformation wich is suitable for the flowfield solution of elastic rotor. According to the characteristics of rotor transient flowfield and the blade-tip vortex movement, a dynamic overset grid system, which is composed of a body-fitted grid used for simulating the blade aerodynamic circumstance in the near field and a background grid for capturing the movement of tip vortice, is constructed. Also, an efficient method for grid information search is given to reduce the searching cost. Based on the Hamilton’s principle and the beam theory of small strain and moderate deformation, a finite-element analysis model for rotor blade dynamics is established. In this model, the partial differential gorverning equation on blade movement is derived, and the equation is discretized and then solved by applying the improved implicit Newmark-beta method. Furthermore, a trim algorithm for the rotor system is coupled into the blade structural analysis for impoving the solution of blade structural response.
Based on the overset grid, a CFD analyzing method for rotor flowfield is developed with the application of RANS equations. In this method, the high-order upwind scheme is combined with the flux-difference splitting scheme to discretize the rotor flowfield spatially. Then, the equation is integrated in the time domain with the matrix-free LU-SGS implicit scheme of Krylov subspace iteration, so as to improve the computational efficiency of rotor CFD simulation. With the help of‘Partitioned’method, the coupled solving strategy for the elastic rotor flowfield is also provided, by combining the elastic blade structural analysis. On this basis, the elastic rotor flowfield simulation is further carried out. Afterwards, the present rigid and elastic rotor flowfield simulation methods are validated by comparing with available reference results for different rotor cases.
To study new blade-tip rotors, the author expands the above work to simulate flowfield of the elastic rotor with linear-changed blade tips, and a corresponding method is developed. The computations on the elastic rotor flowfield in hover with sweep, tapered, anhedral and combined shapes are performed by the use of the method, and the influence of elasticity on the rotor flowfield with new blade tips is analysed. From the analyses, the conclusions about how the tip shape parameters affect the blade surface airloading are drawn.
引文
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