首页 | 本学科首页   官方微博 | 高级检索  
     

高超声速等截面磁流体发电机性能研究
引用本文:黄浩,黄护林,张义宁,刘振德. 高超声速等截面磁流体发电机性能研究[J]. 航空动力学报, 2013, 28(3): 573-582
作者姓名:黄浩  黄护林  张义宁  刘振德
作者单位:1.南京航空航天大学 高新技术研究院,南京 210016
基金项目:高超声速冲压发动机技术重点实验室基金(20110101010);江苏高校优势学科建设工程资助
摘    要:采用三维低磁雷诺数磁流体动力学五方程模型,对等截面管道法拉第型分段电极磁流体发电机内的流动进行数值模拟,研究了负载系数、磁场强度、电极-绝缘壁宽度比对发电通道性能的影响.结果表明:当负载系数为0.50时电功率密度达到最大,并且随着负载系数的增大发生器的减速能力降低;当磁场强度为8T时,500mm的管道长度即可将来流马赫数从6降低到3以下,温度保持在800K以下,并且每立方米的管道发电量能够达到兆瓦级的水平. 

关 键 词:高超声速   等截面管道   磁流体(MHD)发电机   分段电极   三维模型
收稿时间:2012-04-04

Performance investigation of hypersonic rectangular MHD generator
HUANG Hao,HUANG HU-lin,ZHANG Yi-ning and LIU Zhen-de. Performance investigation of hypersonic rectangular MHD generator[J]. Journal of Aerospace Power, 2013, 28(3): 573-582
Authors:HUANG Hao  HUANG HU-lin  ZHANG Yi-ning  LIU Zhen-de
Affiliation:1.Academy of Frontier Science, Nanjing university of Aeronautics and Astronautics, Nanjing 210016, China2.Science and Technology on Scramjet Laboratory, The 31st Reserch Institute, China Aerospace Science and Industry Corporation, Beijing 100074, China
Abstract:Three dimensional magnetohydrodynamics (MHD) five-equation model associated with low magnetic Reynolds assumption was used to simulate the flow phenomenon for a rectangular Faraday type MHD generator with segmented electrode,and the effects of load factors,intensity of magnetic field and the width of the electrodes on the performance of the generator were investigated.The results show that,the electrical power density reached its maximum value when the loading factor is 0.50,and with the increase of the load factor,the slowing capacity of the generator is reduced.At the magnetic field strength of 8T,the 500mm long generator can reduce the Mach number from 6 to 3 below,the temperature could be kept below 800K,and power generation can reach the amount of megawatt-scale of per cubic meter of the duct.
Keywords:hypersonic  rectangular duct  magnetohydrodynamics(MHD) generator  segmented electrode  three-dimensional model
本文献已被 万方数据 等数据库收录!
点击此处可从《航空动力学报》浏览原始摘要信息
点击此处可从《航空动力学报》下载全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号