Block structured adaptive mesh refinement for rotor flows

XIAO Zhongyun; GUO Yongheng; ZHANG Lu; CUI Xingda

doi:10.7638/kqdlxxb-2021.0255

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Block structured adaptive mesh refinement for rotor flows

更新时间：2026-05-28

- Block structured adaptive mesh refinement for rotor flows
- Vol. 40, Issue 5, Pages: 158-165(2022)
- 作者机构：
  
  中国空气动力研究与发展中心,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2021.0255
  CLC： V211.3
- Published：2022
- 稿件说明：
移动端阅览
肖中云, 郭永恒, 张露, 等. 旋翼流动的块结构化网格自适应方法[J]. 空气动力学学报, 2022, 40(5): 158−165.

XIAO Zhongyun, GUO Yongheng, ZHANG Lu, et al. Block structured adaptive mesh refinement for rotor flows[J]. 2022, 40(5): 158-165.
肖中云, 郭永恒, 张露, 等. 旋翼流动的块结构化网格自适应方法[J]. 空气动力学学报, 2022, 40(5): 158−165. DOI： 10.7638/kqdlxxb-2021.0255

XIAO Zhongyun, GUO Yongheng, ZHANG Lu, et al. Block structured adaptive mesh refinement for rotor flows[J]. 2022, 40(5): 158-165. DOI： 10.7638/kqdlxxb-2021.0255.

摘要

从旋翼的旋转运动和旋涡环绕流场特点出发，探讨了流场计算中的双网格建模方法，即采用结构化贴体网格随桨叶一起运动，采用背景网格的自适应加密模拟旋涡的空间演化。发展了块结构化的背景笛卡尔网格生成方法，网格以块为单位进行加密或稀疏变化，所有网格块的网格维数相同，采用八叉树数据结构和空间填充Z曲线进行管理，满足自适应加密和并行分区的需求。采用该方法对UH-60A旋翼进行了网格建模，在以桨叶贴体网格为输入的前提下自动生成了初始笛卡尔背景网格，同时针对旋翼的悬停和前飞状态流场，分别采用Landgrebe和Beddoes尾迹模型为网格加密提供线索。在此基础上对空间背景网格进行了自适应加密，最大允许网格加密层次为9层，桨尖涡目标区域的网格尺度为0.01倍弦长。结果表明，当前笛卡尔自适应网格方法足够灵活，能够根据桨尖涡位置变化进行网格加密或稀疏操作，自适应网格加密受最大加密层次、目标加密区域的大小和目标区域的网格间距等因素决定。本文的自适应方法具有网格调整效率高的特点，在提高非定常桨尖涡模拟精度方面有一定的应用前景。

Abstract

Focusing on the rotating motion and vortex flow of rotors

a dual grid modelling method is discussed

in which body fitted moving structured grids are used to capture the boundary layer flow and background grids with adaptive mesh refinement (AMR) are used for the blade tip vortex flow. A method of generating block structured Cartesian grids is developed

in which the grid refinement or coarsening is performed on blocks with identical grid dimensions. All Cartesian blocks are organized by the octree data structure and spatial filling Z curves

which meets the requirements of adaptive refinement and parallel partition. The dual grid method is applied for the UH-60A rotor simulation. The initial Cartesian background grid is automatically generated with the body fitted blade grid as the input. For rotor flows in hovering and forward flight conditions

the Landgrebe and Beddoes wake models are introduced respectively to adaptively refine the background grids. The maximum allowed number of grid layer is 9 and the grid spacing for the tip vortex filament in the target area is 1% of the chord length. Results show that the present Cartesian grid adaptive method is able to flexibly refine or coarsen grids for the blade tip vortex by controlling the maximum refinement level

the size and grid spacing of the target refinement area for the vortex capturing. The present AMR method is highly efficient in grid adjustment

and shows convincing prospects in improving the simulation accuracy of unsteady blade tip vortices.

关键词

Keywords

references

JOHNSON W. Milestones in rotorcraft aeromechanics[R ] . NASA/TP-2011-215971, 2011. https://rotorcraft.arc.nasa.gov/Johnson_TP-2011-215971_final.pdf

PULLIAM T H, JESPESEN D C. Large scale aerodynamic calculation on Pleiades[R ] . NAS-09-004, 2009. https://www.nas.nasa.gov/assets/pdf/techreports/2009/nas-09-004.pdf

HARIHARAN N S, EGOLF T A, SANKAR L N. Simulation of rotor in hover: Current state and challenges[C]//52nd Aerospace Sciences Meeting, 2014. AIAA 2014-0041. doi: 10.2514/6.2014-0041

ABRAS J, HARIHARAN N S, NARDUCCI R P. Wake breakdown of high-fidelity simulations of a rotor in hover[C]//AIAA Scitech 2019 Forum, San Diego, California. Reston, Virginia: AIAA, 2019. doi: 10.2514/6.2019-0593

TANG Z G, CHEN H, BI L, et al. Numerical simulation of supersonic viscous flow based on adaptive Cartesian grid[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(5): 121697. (in Chinese)

SANG S H, SUN Z H, CHEN R L, et al. Computing flows around rotor by using time-depended adaptive grid based on unstructured-Cartesian overset mesh system[J]. Journal of Nanjing University of Aeronautics Astronautics, 2018, 50(4): 528-535. (in Chinese)

DUBEY A, ALMGREN A, BELL J, et al. A survey of high level frameworks in block-structured adaptive mesh refinement packages[J]. Journal of Parallel and Distributed Computing, 2014, 74(12): 3217-3227. DOI:10.1016/j.jpdc.2014.07.001

KIRK B S, PETERSON J W, STOGNER R H, et al. libMesh: a C++ library for parallel adaptive mesh refinement/coarsening simulations[J]. Engineering With Computers, 2006, 22(3-4): 237-254. DOI:10.1007/s00366-006-0049-3

BURSTEDDE C, WILCOX L C, GHATTAS O. p4est: scalable algorithms for parallel adaptive mesh refinement on forests of octrees[J]. SIAM Journal on Scientific Computing, 2011, 33(3): 1103-1133. DOI:10.1137/100791634

CO LELLA P, GRAVES D T. Chombo software package for AMR applications design document[R ] . Lawrence Berkeley National Laboratory Deposit Manage, 2013. https://crd.lbl.gov/assets/pubs_presos/chomboDesign.pdf

MACNEICE P, OLSON K M, MOBARRY C, et al. PARAMESH: a parallel adaptive mesh refinement community toolkit[J]. Computer Physics Communications, 2000, 126(3): 330-354. DOI: 10.1016/S0010-4655(99)00501-9

WISSINK A M, HORNUNG R D, KOHN S R, et al. Large scale parallel structured AMR calculations using the SAMRAI framework[C]//SC '01: Proceedings of the 2001 ACM/IEEE Conference on Supercomputing, Denver, CO, USA. IEEE, 2001: 22. doi: 10.1145/582034.582040

JI H, LIEN F S, YEE E. Parallel adaptive mesh refinement combined with additive multigrid for the efficient solution of the Poisson equation[J]. ISRN Applied Mathematics, 2012, 2012: 1-24. DOI:10.5402/2012/246491

KAMKAR S J, WISSINK A M, JAMESON A, et al. Feature-driven cartesian adaptive mesh refinement in the helios code[C ] //48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, Orlando, Florida, 2010. AIAA 2010-171. http://aero-comlab.stanford.edu/Papers/AIAA-2010-171-748.pdf

LIU C Q. Liutex-third generation of vortex definition and identification methods[J]. Acta Aerodynamica Sinica, 2020, 38(3): 413-431, 478. (in Chinese)

BEDDOES T S. A wake model for high resolution airloads[C ] //Proceedings of the 2 nd international conference on basic rotorcraft research, Triangle Park, USA, 1985.

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Study on aerodynamic interference between helicopter hovering rotor and plateau complex terrain

Numerical analysis of aerodynamic characteristics and mechanisms of a rotor in cross-medium flight

Dynamic stall characteristics of a rotor airfoil under coupled pitching-plunging motions

Modeling and research of aerodynamic interference mechanisms for aerial-aquatic rotorcraft approaching the water surface

The analysis on rotor aeroelastic loads characteristic in high speed condition

Related Author

Xing Miaomiao

Gao Zhongpu

Li Guoqiang

Zhang Wei

WANG Xiao

GAO Shicai

LI Guoqiang

WU Jiaqiang

Related Institution

School of Aeronautics, Northwestern Polytechnical University, Xi'an

Low Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang

School of Aeronautics and Astronautics, Southwest University of Science and Technology, Mianyang

National Key Laboratory of Helicopter Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing

State Key Laboratory of Aerodynamics, Mianyang

AI问答

⁰