High Temperature MHD Technology System Design and Commissioning Experiments

Journal of Propulsion Technology ›› 2015, Vol. 36 ›› Issue (5): 774-779.

Previous Articles Next Articles

High Temperature MHD Technology System Design and Commissioning Experiments

Plasma-Dynamic Laboratory，Air Force Engineering University，Xi’an 710038，China,Plasma-Dynamic Laboratory，Air Force Engineering University，Xi’an 710038，China,Plasma-Dynamic Laboratory，Air Force Engineering University，Xi’an 710038，China,Plasma-Dynamic Laboratory，Air Force Engineering University，Xi’an 710038，China,Plasma-Dynamic Laboratory，Air Force Engineering University，Xi’an 710038，China,Plasma-Dynamic Laboratory，Air Force Engineering University，Xi’an 710038，China and The 95903th Unit of PLA，Wuhan 430331，China

Published:2021-08-15

高温磁流体动力技术实验系统设计与调试

高　岭¹,李益文¹,张百灵¹,阳鹏宇¹,樊　昊¹,段成铎¹,向波罗²

空军工程大学等离子体动力学重点实验室，陕西西安 710038,空军工程大学等离子体动力学重点实验室，陕西西安 710038,空军工程大学等离子体动力学重点实验室，陕西西安 710038,空军工程大学等离子体动力学重点实验室，陕西西安 710038,空军工程大学等离子体动力学重点实验室，陕西西安 710038,空军工程大学等离子体动力学重点实验室，陕西西安 710038,中国人民解放军 95903部队，湖北武汉 430331

作者简介:高　岭(1988—)，男，硕士生，研究领域为高超声速飞行器推进技术。E-mail:kgdlinggao@126.com 通讯作者:李益文(1983—)，男，讲师，研究领域为航空推进技术。
基金资助:
国家自然科学基金(51306207；11372352)；陕西省自然科学基金(2013JQ1016)。

Abstract

Abstract: In order to carry out high temperature magnetohydrodynamic(MHD) technology such as MHD power generation，MHD acceleration and MHD flow control，a MHD technology experimental system based on high temperature combustion chamber was developed. The basic element，design idea and operation of the high temperature MHD technology experimental system were introduced. With aviation kerosene and oxygen，the combustion chamber can reach a maximum temperature of 3256K. Then a conductive fluid in which the conductivity is 11.6S/m is acquired by adding auxiliary ionization K2CO3. Finally，through acceleration in the nozzle，the conductive fluid is transformed into a supersonic conductive fluid with Mach number 1.5. Pilot run of the system achieved stable operation for more than 15s，showing that the system is capable of conducting high temperature MHD experiments with a longer time frame.

Key words: Hypersonic；Thermal ionization；MHD；Plasma

摘要： 为了开展高温磁流体功率提取、磁流体加速、磁流体流动控制等磁流体动力技术实验，研制了基于高温燃气发生器的磁流体动力技术实验系统。介绍了高温磁流体动力技术实验系统的基本组成，设计思想及运行情况。燃气发生器采用航空煤油和气氧燃烧，产生最高温度可达3256K的高温燃气，通过添加辅助电离种子K2CO3，可以得到电导率为11.6S/m的导电流体；高温燃气经喷管的加速，在出口得到马赫数1.5的超声速导电流体；实验系统调试实现了15s以上稳定运行，表明具备了开展较长时间高温磁流体动力实验的能力。

关键词: 高超声速；热电离；磁流体；等离子体

GAO Ling¹,LI Yi-wen¹,ZHANG Bai-ling¹,YANG Peng-yu¹,FAN Hao¹,DUAN Cheng-duo¹,XIANG Bo-luO². High Temperature MHD Technology System Design and Commissioning Experiments[J]. Journal of Propulsion Technology, 2015, 36(5): 774-779.

高　岭,李益文,张百灵,阳鹏宇,樊　昊,段成铎,向波罗. 高温磁流体动力技术实验系统设计与调试[J]. 推进技术, 2015, 36(5): 774-779.

References

[1] Chapman J, Schmidt H, Ruoff R, et al. Flight Weight Magnets for Space Application Using Carbon Nanotubes[R]. AIAA 2003-0330.
[2] 刘鉴民. 磁流体发电[M].北京: 机械工业出版社,1984.
[3] Lineberry J T, Begg L L, Castro J H, et al. HVEPS Scramjet-Driven MHD Power Demonstration Test Results[R]. AIAA 2007-3880.
[4] Moeller T, Robert Rhodes, Lineberry J T, et al. HVEPS Combustion Driven MHD Power Demonstration Tests[R]. AIAA 2008-4097.
[5] 李益文, 李应红, 张百灵, 等. 基于激波风洞的超声速磁流体动力技术实验系统[J]. 航空学报, 2011, 32(6): 1015-1024.
[6] Bobashev S V, Erofeev A V, Lapushkina T A, et al. Air Plasma Produced by Gas Discharge in Supersonic MHD Channel[R]. AIAA 2006-1373.
[7] 郑小梅, 吕浩宇, 徐大军. 等二维超然冲压发动机磁控进气道的数值模拟[J].推进技术, 2010, 31(1):12-17. (ZHENG Xiao-mei, LV Hao-yu, XU Da-jun, et al.Numerical Simulation of a Two-Dimensional Scramjet MHD Controlled Inlet[J]. Journal of Propulsion Technology, 2010, 31(1):12-17.)
[8] Borghi C A, Carraro M R, Cristofolini A, et al. Magnetohydrodynamic Interaction in the Shock Layer of a Wedge in a Hypersonic Flow[J]. IEEE Transactions On Plasma Science, 2006, 34(5): 2450-246.
[9] Nishihara M, Rich J W, Lempert W R, et al. Low-Temperature M=3 Flow Deceleration by Lorentz Force[R]. AIAA 2006-1004.
[10] 罗莎 R J. 磁流体发电[M].北京: 科学出版社出版社.1975.
[11] 李应红, 李益文, 苏长兵. 高超声速磁流体-涡轮联合发动机[C]. 桂林: 中国航空学会第十届发动机软科学学术讨论会论文集, 2010.
[12] 赵青, 刘述章, 童洪辉. 等离子体技术及应用[M].北京: 国防工业出版社, 2009.
[13] LI Yiwen, LI Yinghong, LU Haoyu, et al. Preliminary Experimental Investigation on MHD Power Generation Using Seeded Supersonic Argon Flow as Working Fluid[J]. Chinese Journal of Aeronautics, 2011, 24(12): 701-708.
[14] 李益文, 李应红, 张百灵, 等. 超声速气流磁流体加速初步实验研究[J]. 力学学报, 2012, 44(2): 238-244.
[15] 杨昌琪, 何学农, 周适. 对角线磁流体发电机[M].北京: 科学出版社, 1981.
[16] 张也影. 流体力学[M].北京: 高等教育出版社, 2010.
[17] 朱涛, 李应红, 张百灵, 等. 磁激等离子体超声速气流的瞬态加速系统及其实验研究[J]. 航空学报, 2012, 33(8):1375-1383.(编辑:梅瑛)　　　　　　　　　　　　　*　收稿日期:2014-04-23；修订日期:2014-06-30。基金项目:国家自然科学基金(51306207；11372352)；陕西省自然科学基金(2013JQ1016)。作者简介:高岭(1988—),男,硕士生,研究领域为高超声速飞行器推进技术。E-mail:kgdlinggao@126.com 通讯作者:李益文(1983—),男,讲师,研究领域为航空推进技术。E-mail:Lee_yiwen@163.com

High Temperature MHD Technology System Design and Commissioning Experiments

高温磁流体动力技术实验系统设计与调试

PDF

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 0

Recommended Articles

Metrics

Comments