横截面形状对超声速磁流体发生器性能的影响

doi:10.7527/S1000-6893.2015.0045

流体力学与飞行力学

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横截面形状对超声速磁流体发生器性能的影响

吕浩宇¹, 甄华萍², 李椿萱³, 张义宁⁴

1. 北京航空航天大学宇航学院, 北京 100191;
2. 北京航天长征飞行器研究所, 北京 100076;
3. 北京航空航天大学航空科学与工程学院, 北京 100191;
4. 北京动力机械研究所激光推进及其应用国家重点实验室, 北京 100074

收稿日期:2014-12-19 修回日期:2015-02-09 出版日期:2015-11-15 发布日期:2015-03-20
通讯作者: 吕浩宇,Tel.:010-82339026,E-mail:lvhy@buaa.edu.cn E-mail:lvhy@buaa.edu.cn
作者简介:吕浩宇,男,博士,副教授。主要研究方向:磁流体动力学在飞行器设计中的应用。Tel:010-82339026,E-mail:lvhy@buaa.edu.cn;甄华萍,女,博士,工程师。主要研究方向:高超声速飞行器设计及数值模拟。Tel:010-88645431,E-mail:tracypp16@163.com;李椿萱,男,博士,教授,博士生导师。主要研究方向:高超声速飞行器设计及数值模拟。Tel:010-82317011,E-mail:lichx@buaa.edu.cn;张义宁,男,博士,副研究员。主要研究方向:燃烧学及爆震推进技术。Tel:010-88534691,E-mail:yining_pde@nuaa.edu.cn
基金资助:
国家自然科学基金(11372028);中央高校基本科研业务费专项资金

Influence of cross-sectional shape on the performance of supersonic magnetohydrodynamic generator

LYU Haoyu¹, ZHEN Huaping², LEE Chunhian³, ZHANG Yining⁴

1. School of Astronautics, Beihang University, Beijing 100191, China;
2. Beijing Institute of Space Long March Vehicle, Beijing 100076, China;
3. School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China;
4. National Key Lab of Laser Propulsion and the Application, Beijing Institute of Power Machinery, Beijing 100074, China

Received:2014-12-19 Revised:2015-02-09 Online:2015-11-15 Published:2015-03-20
Supported by:
National Natural Science Foundation of China (11372028);Fundamental Research Funds for the Central Universities

摘要/Abstract

摘要：

通过三维数值模拟研究了不同横截面形状的磁流体(MHD)发生器的热、电磁流动特性,发生器入口采用超声速来流条件,旨在应用于磁流体旁路超燃冲压发动机推进系统。数值模拟采用低磁雷诺数下磁流体五方程模型,通过熵条件格式和超松弛迭代(SOR)法联合算法分别求解Navier-Stokes方程组和电势方程。研究表明在电极壁面上电场、电流以及洛伦兹力等电磁场参数呈周期性变化,由于电极端点效应,电磁场参数在电极端点出现周期性的极值,而在管道中心电极端点效应对电流影响并不大,沿着流向电流保持连续变化。对不同管道横截面形状的发生器的数值模拟表明:由于涡电流和二次流效应的影响,形状参数较小的发生器焦耳热较为严重,二次流较弱;而形状参数较大的发生器焦耳热较小,二次流增强。因此,当形状参数α=0.8时可获得较好的焓提取率和电效率。

关键词: 高超声速飞行器, 磁流体发生器, 数值模拟, 横截面形状, 形状参数

Abstract:

Three-dimensional numerical simulations were performed to study the thermal and electromagnetic fluid characteristics of supersonic magnetohydrodynamic (MHD) generator under the influence of inlet cross-sectional shape, which tends to be applied to improv the performance of propulsion system of scramjet. A joint numerical procedure, composed of an entropy conditioned scheme for solving the non-homogeneous Navier-Stokes equations and an successioe over relaxation (SOR) method for solving the elliptic equation governing the electrical potential, was used in this paper. Numerical results indicate that the electromagnetic parameters, such as electric field, electric current density and Lorentz force etc., vary periodically along the electrode wall. The extreme values of the electromagnetic parameters are located at the edges of the electrodes. Due to the influence of width between the electrode pair, the subsequent current eddies and secondary flow on the cross-section substantially affect the performance of MHD generator. In case of small cross-sectional shape parameter, severe Joule heating and weak secondary flow are induced in the MHD generator, and vice versa in case of high shape parameter. Consequently, when the cross-sectional shape parameter α is 0.8, the enthalpy extraction ratio and electric efficiency of MHD generator are considerable.

Key words: hypersonic vehicle, magnetohydrodynamic generator, numerical simulation, cross-sectional shape, shape parameter

中图分类号:

V211.1⁺2

吕浩宇, 甄华萍, 李椿萱, 张义宁. 横截面形状对超声速磁流体发生器性能的影响[J]. 航空学报, 2015, 36(11): 3549-3556.

LYU Haoyu, ZHEN Huaping, LEE Chunhian, ZHANG Yining. Influence of cross-sectional shape on the performance of supersonic magnetohydrodynamic generator[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(11): 3549-3556.

参考文献

[1] Gurijanov E P, Harsha P T. AJAX:new directions in hypersonic technology, AIAA-1996-4609[R]. Reston:AIAA,1996.
[2] Lineberry J T, Begg L L, Castro J H, et al. Scramjet driven MHD power demonstration-HVEPS program, AIAA-2006-3080[R]. Reston:AIAA, 2006.
[3] Nikodijevic D D, Stamenkovic Z M, Zivkovic D S, et al. Active control of flow and heat transfer in boundary layer on the porous body of arbitrary shape[J]. Thermal Science, 2012, 16(S2):S295-S309.
[4] Murray R C, Zaidi S H, Carraro M R, et al. Magnetohydrodynamic power generation using externally ionized, cold, supersonic air as working fluid[J]. AIAA Journal, 2006, 44(1):119-127.
[5] Lee C H, Lu H Y. Quasi-one-dimensional parametric study for MHD generator in MHD bypass scramjet system, AIAA-2007-0644[R]. Reston:AIAA, 2007.
[6] Chen G, Zhang J B, Lee C H. Numerical simulation of external MHD generator on board reentry vehicles[J]. Journal of Beijing University of Aeronautics and Astronautics, 2010, 36(2):135-139(in Chinese).陈刚,张劲柏,李椿萱.再入飞行器表面磁流体发电装置数值模拟[J].北京航空航天大学学报, 2010, 36(2):135-139.
[7] He M S, Yang W J, Zheng X M, et al. Viscosity effect of hypersonic inlet based on magnetohydrodynamic control[J]. Journal of Aerospace Power, 2013, 28(2):365-371(in Chinese).何淼生,杨文将,郑小梅,等.基于磁流体控制的高超声速进气道黏性效应[J].航空动力学报, 2013, 28(2):365-371.
[8] Li Y W, Li Y H, Lu H Y, et al. Preliminary experimental investigation on MHD power generation using seeded supersonic argon flow as working fluid[J]. Chinese Journal of Aeronautics, 2011, 23(12):701-708.
[9] Zhu T, Li Y H, Zhang B L, et al. Transient acceleration system of magnetoplasmadynamic supersonic airstream and its experimental research[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(8):1375-1383(in Chinese).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.
[10] Lu H Y, Lee C H, Dong H T, et al. Hall effects in three-dimensional MHD generator[J]. Chinese Journal of Theoretical and Applied Mechanics, 2008, 40(3):306-314(in Chinese).吕浩宇,李椿萱,董海涛,等. Hall效应对三维磁流体发生器的影响[J].力学学报, 2008, 40(3):306-314.
[11] Zhang K P, Tian Z Y, Feng D H, et al. Numerical study of acceleration/deceleration control of three dimensional magnetohydrodynamic flow in channel[J]. Acta Aerodynamics Sinica, 2009, 27(4):474-479(in Chinese).张康平,田正雨,冯定华,等.三维磁流体动力学管道流动加减速控制数值研究[J].空气动力学报, 2009, 27(4):474-479.
[12] Lu H Y, Lee C H, Dong H T. Characterization of the three-dimensional supersonic flow for the MHD generator[J]. Science in China Series G:Physics, Mechanics & Astronomy, 2009, 52(4):534-545.
[13] Ohkuma H, Takahashi T, Fujino T, et al. Performance prediction of scramjet driven DCW MHD generator with three-dimensional analysis, AIAA-2008-4333[R]. Reston:AIAA, 2008.
[14] Tamada Y, Niwa N, Takahashi T, et al. Influence of cross-sectional shape on generator performance and electromagnetic fluid phenomena of DCW-MHD generators for hypersonic airplanes, AIAA-2013-2891[R]. Reston:AIAA,2013.
[15] Chen Z, Zhang J B, Lee C H. Direct numerical simulation of the turbulent MHD channel flow at low magnetic Reynolds number for electric correlation characteristics[J]. Science in China Series G:Physics, Mechanics & Astronomy, 2010, 53(10):1901-1913.
[16] Lu H Y, Lee C H. Influence of Hall effects on characteristics of magnetohydrodynamic converging channel[J]. Chinese Science Bulletin, 2010, 55(14):1454-1460.

E-mail：hkxb@buaa.edu.cn

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横截面形状对超声速磁流体发生器性能的影响

Influence of cross-sectional shape on the performance of supersonic magnetohydrodynamic generator

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