新型桨尖弹性旋翼气动特性的Navier-Stokes方程数值模拟
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摘要
直升机弹性旋翼流场和气动特性的数值计算是直升机空气动力学领域具有挑战性的研究课题。本文开展了适用于计入桨叶弹性变形运动的旋翼运动嵌套网格生成方法和高效贡献单元搜索策略、旋翼流场数值模拟以及桨叶动力学分析方法等研究,发展了与该网格系统对应的基于Navier-Stokes方程的旋翼非定常流场的数值计算方法和程序。分别针对直升机刚性/弹性旋翼的流场和气动特性进行了数值模拟与分析,同时,开展了新型桨尖对弹性旋翼气动特性的影响研究。主要工作包括以下几个方面:
作为前提和背景,本文首先阐述了论文的研究目的,并对直升机旋翼气动特性计算、桨叶结构动力学分析、新型桨尖弹性旋翼气动特性研究等的国内外现状进行了概述,指出了现有研究中存在的不足及难点,提出了本文拟采用的研究方法和内容。
针对旋翼桨叶多种复杂运动和旋翼流场求解的特点,首先建立了一套用于旋翼粘性流场模拟的结构运动嵌套网格生成方法。为了更好地模拟贴体网格随桨叶在背景网格中的运动和弹性变形,给出了一个基于改进的弹簧模拟方法的桨叶网格变形方法,以适用于弹性旋翼流场的求解。同时,建立了一种新的与该网格系统相对应的高效嵌套网格洞边界确定和贡献单元搜索的策略。
基于所建立的嵌套网格系统,本文又发展了一套适合于悬停、前飞状态旋翼流场与气动特性数值计算的方法及程序。在求解N-S方程时,空间方向上采用低数值耗散的Roe格式并结合三阶逆风格式(MUSCL),以减少旋翼尾迹数值耗散、提高计算精度。时间方向则使用双时间方法来模拟前飞流场的非定常变化过程。另一方面,依据Hamilton原理和中等变形梁理论,建立了一个基于有限元方法的适合于新型桨尖旋翼桨叶动力学分析的模型,并在该模型中耦合了旋翼配平分析。
结合所建立的旋翼流场求解方法和弹性桨叶结构分析模型,本文还提出了一个弹性旋翼流场/结构弱耦合求解的策略,建立了一个用于弹性旋翼悬停和前飞气动特性计算的模型。应用该耦合求解器,着重针对UH-60A直升机旋翼、7A旋翼及SA349/2直升机旋翼等不同外形桨叶,分别进行了刚性和弹性旋翼流场和气动特性的数值计算,并验证了方法的有效性。
最后,应用所建立的弹性旋翼气动特性计算方法,着重进行了后掠、尖削、下反及其组合形状的新型桨尖弹性旋翼在悬停和前飞状态下的旋翼性能与气动特性计算,分析了不同桨尖形状对弹性旋翼性能和气动特性的影响,得出了对旋翼设计有实际指导意义的结论。
The numerical computation of flowfields and aerodynamic characteristics for helicopter elastic rotors is a highly challenging subject in the field of Helicopter Aerodynamics. The moving-embedded grid methodology with actual blade elastic deformation and a corresponding effective donor-element searching strategy, the rotor flowfield numerical simulation method, and the blade dynamic analysis approach have been investigated in this thesis. By employing the moving-embedded grid and Navier-Stokes equations, a high-accuracy numerical method and code is developed to simulate the helicopter rotor unsteady flowfield. The flowfield and aerodynamic characteristics for rigid/elastic rotors are computed and analyzed. Meanwhile, the effects of blade-tip shape on rotor aerodynamics of elastic rotor are also simulated. The major contributions of the author’s research work are as follows: As the background of present work, the objectives of the research are firstly described. The research and development in the field of calculation of rotor aerodynamic characteristics, blade structural analysis, and aerodynamic calculation for elastic rotors with new tip are briefly reviewed. The difficulties in the current research are also pointed out. In addition, the methods used in the present research are briefly introduced.
Aiming at the simulation of the complex rotor flowfield in which there are many blade movements, a structured moving-embedded grid method has been firstly developed in the thesis. At the same time, in order to model blade body-fitted grid movement and elastic deformation, a mesh deformation approach based on the modified spring analogy is presented, which is suitable for the flowfield numerical simulation of elastic rotors. Then, an efficient method for hole-cutting and donor searching of overset grids is given.
Based on the developed moving-embedded grid system, a numerical method and solver is developed to solve the flowflied and aerodynamic characteristics of helicopter rotors in hover and forward flight. For the solution of N-S equations, both the low dissipation Roe scheme and the third-order upwind scheme (MUSCL) are employed, which can reduce the false dissipation of the rotor wake vorticity effectively. Also, the dual-time stepping method is used for simulating the unsteady phenomenon in helicopter flowfield. Meanwhile, based on the Hamilton’s principle and the moderate-deformation beam theory, a finite-element analysis model for the rotor with new blade tips is established, a trim algorithm for the rotor system is also coupled into the blade structural analysis.
By combining the rotor flowfield analysis with the elastic-blade structural analysis, the flowfield/structure loose coupled solving algorithm for the elastic rotor aerodynamic characteristics is presented. Base on this, the flowfield and aerodynamic characteristics of rigid and elastic rotors have been calculated on UH-60A rotor, 7A rotor and SA349/2 rotor respectively, and the capability of this method is demonstrated by comparing with available experimental data.
Finally, the rotor performance and aerodynamic characteristics of elastic blades in hover and forward flight with such new blade tips as swept, tapered, anhedral and combined shapes are calculated by the method developed, and the influence of different blade-tip shapes on elastic rotor performance and aerodynamic characteristics is analysed. Some meaningful conclusions for rotor design are also drawn.
作为前提和背景,本文首先阐述了论文的研究目的,并对直升机旋翼气动特性计算、桨叶结构动力学分析、新型桨尖弹性旋翼气动特性研究等的国内外现状进行了概述,指出了现有研究中存在的不足及难点,提出了本文拟采用的研究方法和内容。
针对旋翼桨叶多种复杂运动和旋翼流场求解的特点,首先建立了一套用于旋翼粘性流场模拟的结构运动嵌套网格生成方法。为了更好地模拟贴体网格随桨叶在背景网格中的运动和弹性变形,给出了一个基于改进的弹簧模拟方法的桨叶网格变形方法,以适用于弹性旋翼流场的求解。同时,建立了一种新的与该网格系统相对应的高效嵌套网格洞边界确定和贡献单元搜索的策略。
基于所建立的嵌套网格系统,本文又发展了一套适合于悬停、前飞状态旋翼流场与气动特性数值计算的方法及程序。在求解N-S方程时,空间方向上采用低数值耗散的Roe格式并结合三阶逆风格式(MUSCL),以减少旋翼尾迹数值耗散、提高计算精度。时间方向则使用双时间方法来模拟前飞流场的非定常变化过程。另一方面,依据Hamilton原理和中等变形梁理论,建立了一个基于有限元方法的适合于新型桨尖旋翼桨叶动力学分析的模型,并在该模型中耦合了旋翼配平分析。
结合所建立的旋翼流场求解方法和弹性桨叶结构分析模型,本文还提出了一个弹性旋翼流场/结构弱耦合求解的策略,建立了一个用于弹性旋翼悬停和前飞气动特性计算的模型。应用该耦合求解器,着重针对UH-60A直升机旋翼、7A旋翼及SA349/2直升机旋翼等不同外形桨叶,分别进行了刚性和弹性旋翼流场和气动特性的数值计算,并验证了方法的有效性。
最后,应用所建立的弹性旋翼气动特性计算方法,着重进行了后掠、尖削、下反及其组合形状的新型桨尖弹性旋翼在悬停和前飞状态下的旋翼性能与气动特性计算,分析了不同桨尖形状对弹性旋翼性能和气动特性的影响,得出了对旋翼设计有实际指导意义的结论。
The numerical computation of flowfields and aerodynamic characteristics for helicopter elastic rotors is a highly challenging subject in the field of Helicopter Aerodynamics. The moving-embedded grid methodology with actual blade elastic deformation and a corresponding effective donor-element searching strategy, the rotor flowfield numerical simulation method, and the blade dynamic analysis approach have been investigated in this thesis. By employing the moving-embedded grid and Navier-Stokes equations, a high-accuracy numerical method and code is developed to simulate the helicopter rotor unsteady flowfield. The flowfield and aerodynamic characteristics for rigid/elastic rotors are computed and analyzed. Meanwhile, the effects of blade-tip shape on rotor aerodynamics of elastic rotor are also simulated. The major contributions of the author’s research work are as follows: As the background of present work, the objectives of the research are firstly described. The research and development in the field of calculation of rotor aerodynamic characteristics, blade structural analysis, and aerodynamic calculation for elastic rotors with new tip are briefly reviewed. The difficulties in the current research are also pointed out. In addition, the methods used in the present research are briefly introduced.
Aiming at the simulation of the complex rotor flowfield in which there are many blade movements, a structured moving-embedded grid method has been firstly developed in the thesis. At the same time, in order to model blade body-fitted grid movement and elastic deformation, a mesh deformation approach based on the modified spring analogy is presented, which is suitable for the flowfield numerical simulation of elastic rotors. Then, an efficient method for hole-cutting and donor searching of overset grids is given.
Based on the developed moving-embedded grid system, a numerical method and solver is developed to solve the flowflied and aerodynamic characteristics of helicopter rotors in hover and forward flight. For the solution of N-S equations, both the low dissipation Roe scheme and the third-order upwind scheme (MUSCL) are employed, which can reduce the false dissipation of the rotor wake vorticity effectively. Also, the dual-time stepping method is used for simulating the unsteady phenomenon in helicopter flowfield. Meanwhile, based on the Hamilton’s principle and the moderate-deformation beam theory, a finite-element analysis model for the rotor with new blade tips is established, a trim algorithm for the rotor system is also coupled into the blade structural analysis.
By combining the rotor flowfield analysis with the elastic-blade structural analysis, the flowfield/structure loose coupled solving algorithm for the elastic rotor aerodynamic characteristics is presented. Base on this, the flowfield and aerodynamic characteristics of rigid and elastic rotors have been calculated on UH-60A rotor, 7A rotor and SA349/2 rotor respectively, and the capability of this method is demonstrated by comparing with available experimental data.
Finally, the rotor performance and aerodynamic characteristics of elastic blades in hover and forward flight with such new blade tips as swept, tapered, anhedral and combined shapes are calculated by the method developed, and the influence of different blade-tip shapes on elastic rotor performance and aerodynamic characteristics is analysed. Some meaningful conclusions for rotor design are also drawn.
引文
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