亚声速真空管道磁浮系统气动热特性研究

宋嘉源; 李田; 张晓涵; 张继业; 张卫华

doi:10.7638/kqdlxxb-2021.0227

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亚声速真空管道磁浮系统气动热特性研究

专栏——高速列车空气动力学研究 | 更新时间：2026-05-28

- 亚声速真空管道磁浮系统气动热特性研究
- Research on aerodynamic and thermal characteristics of subsonic evacuated tube maglev system
- 空气动力学学报 2022年40卷第2期页码：115-121
- 作者机构：
  
  西南交通大学牵引动力国家重点实验室,成都,610031
- 作者简介：
  
  宋嘉源（1999-），男，四川乐山人，硕士生，研究方向：空气动力学. E-mail：478901854@qq.com
  李田*，副研究员，硕士生导师，研究方向：空气动力学. E-mail：litian2008@home.swjtu.edu.cn
- 基金信息：
  
  四川省科技计划（2019YJ0227）;中国博士后科学基金（2019M663550）
- DOI：10.7638/kqdlxxb-2021.0227
  中图分类号： U171
- 纸质出版：2022
- 稿件说明：
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宋嘉源, 李田, 张晓涵, 等. 亚声速真空管道磁浮系统气动热特性研究[J]. 空气动力学学报, 2022, 40(2): 115−121.

SONG Jiayuan, LI Tian, ZHANG Xiaohan, et al. Research on aerodynamic and thermal characteristics of subsonic evacuated tube maglev system[J]. 2022, 40(2): 115-121.
宋嘉源, 李田, 张晓涵, 等. 亚声速真空管道磁浮系统气动热特性研究[J]. 空气动力学学报, 2022, 40(2): 115−121. DOI： 10.7638/kqdlxxb-2021.0227

SONG Jiayuan, LI Tian, ZHANG Xiaohan, et al. Research on aerodynamic and thermal characteristics of subsonic evacuated tube maglev system[J]. 2022, 40(2): 115-121. DOI： 10.7638/kqdlxxb-2021.0227.

摘要

为解决真空管道磁浮系统气动热问题，研究管道内气动热分布特性至关重要。以某高速磁浮列车为研究对象，基于Sutherland黏性公式及SST

k-ω

湍流模型，数值仿真了三维可压缩亚声速真空管道磁浮系统的气动特性及气动热效应，考虑的阻塞比范围为0.1～0.4、列车运行速度为600～1000 km/h，研究了列车表面温度分布、列车尾部温度分布及管道激波的传播规律。研究结果表明：不同工况下头车与中间车表面温度变化呈缓慢下降趋势，由于尾部激波产生而造成尾车表面温度上升明显，且升高幅值随速度与阻塞比增大而增加。在壅塞状态下，尾车鼻尖处最高温度与阻塞比及速度基本呈线性关系。尾车流线型顶部与悬浮间隙处均有激波产生，管道内激波具有典型的三维特性和周期性，在轨道与管道表面之间反射的激波簇形成尾部低温与列车后方高低温交替特性。

Abstract

The aerodynamic thermal effect is important for the design of evacuated tube maglev system. Based on Sutherland viscosity equation and SST

k-ω

turbulence model

the aerodynamic characteristics and aerodynamic thermal effect of three-dimensional compressible subsonic evacuated tube maglev system are numerically simulated. The blockage ratio ranges from 0.1 to 0.4 and the train running speed ranges from 600 km/h to 1000 km/h. The results show that the variation of the surface temperature of the head car and the middle car is similar under different conditions. The surface temperature of the tail car increases obviously due to t

he generation of rear shock waves

and the amplitude increases with the increment of speed and blockage ratio. Under the condition of choke

the maximum temperature at nose of the tail car is basically linear relationship with the blockage ratio and speed. Shock waves are generated at the streamline of the tail car and the suspension gap. The shock wave in the tube has typical three-dimensional characteristics and periodicity. The shock wave cluster reflected between the track and the tube forms the characteristics of low temperature at the tail and alternating temperature behind the train.

关键词

Keywords

references

SHEN Z Y. On developing high-speed evacuated tube transportation in China[J]. Journal of Southwest Jiaotong University, 2005, 40(2): 133-137. (in Chinese)

MUSK E. Hyperloop Alpha[R]. SpaceX, 2013, 13-14

MAO M L, JIANG D W, DENG X G. Study of hybrid scheme for the prediction of aerodynamic heat transfer-rate in hypersonic laminar flow[J]. Acta Aerodynamica Sinica, 2009, 27(3): 275-280. (in Chinese)

GENG X R, GUI Y W, WANG A L. Study on aerothermo dynamic performance of mini-protuberance submerged in hypersonic flows[J]. Acta Aerodynamica Sinica, 2006, 24(2): 265-268. (in Chinese)

ZHANG J B, LI H M, WANG J B, et al. Numerical analysis of the temperature field of vacuum tube maglev train[J]. Chinese Journal of Vacuum Science and Technology, 2021, 41(5): 448-455. (in Chinese)

ZHANG J B, LI H M, WANG J B, et al. Simulation analysis and research on thermal effect of maglev train in low vacuum tube[J]. China Railway, 2020(11): 100-106. (in Chinese)

KIM T K, KIM K H, KWON H B. Aerodynamic characteristics of a tube train[J]. Journal of Wind Engineering and Industrial Aerodynamics, 2011, 99(12): 1187-1196. DOI:10.1016/j.jweia.2011.09.001

CHOI J K, KIM K H. Effects of nose shape and tunnel cross-sectional area on aerodynamic drag of train traveling in tunnels[J]. Tunnelling and Underground Space Technology, 2014, 41: 62-73. DOI:10.1016/j.tust.2013.11.012

LIU J L, ZHANG J Y, ZHANG W H. Analysis of aerodynamic characteristics of high-speed trains in the evacuated tube[J]. Journal of Mechanical Engineering, 2013, 49(22): 137-143. (in Chinese)

ZHOU P, LI T, ZHANG J Y, et al. Research on shock wave trains generated by the hyper train in the evacuated tube[J]. Journal of Mechanical Engineering, 2020, 56(2): 86-97. (in Chinese)

ZHOU P, LI T, ZHANG J Y, et al. Aerothermal effect generated by hyper train in the evacuated tube[J]. Journal of Mechanical Engineering, 2020, 56(8): 190-199. (in Chinese)

ZHOU P, ZHANG J Y, LI T, et al. Numerical study on wave phenomena produced by the super high-speed evacuated tube maglev train[J]. Journal of Wind Engineering and Industrial Aerodynamics, 2019, 190: 61-70. DOI:10.1016/j.jweia.2019.04.003

NIU J Q, SUI Y, YU Q J, et al. Numerical study on the impact of Mach number on the coupling effect of aerodynamic heating and aerodynamic pressure caused by a tube train[J]. Journal of Wind Engineering and Industrial Aerodynamics, 2019, 190: 100-111. DOI:10.1016/j.jweia.2019.04.001

ZHANG X H, LI T, ZHANG J Y, et al. Aerodynamic choked flow and shock wave phenomena of subsonic evacuated tube train[J]. Journal of Mechanical Engineering, 2021, 57(4): 182-190. (in Chinese)

ZHANG X H, JIANG Y, LI T. Effect of streamlined nose length on the aerodynamic performance of a 800 km/h evacuated tube train[J]. Fluid Dynamics Materials Processing, 2020, 16(1): 67-76. DOI:10.32604/fdmp.2020.07776

JIA W G, DONG C G, ZHOU Y, et al. Study of thermal-pressure coupling effect in the evacuated tube transportation system on blocking ratio[J]. Journal of Engineering Thermophysics, 2013, 34(9): 1745-1748. (in Chinese)

ZHOU Y, LIU H L, LIU Y J, et al. Simulation of entropy layer in evacuated tube transport at supersonic speed[J]. Chinese Journal of Vacuum Science and Technology, 2014, 34(8): 775-780. (in Chinese)

林建忠. 流体力学[M]. 清华大学出版社, 2013

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