磁流体能量旁路超燃冲压发动机的混合 和燃烧性能数值研究

陈瑞锋; 魏志军; 王宁飞

磁流体能量旁路超燃冲压发动机的混合和燃烧性能数值研究

北京理工大学宇航学院, 北京 100081

基金项目: 国家自然科学基金(50906004)

计量
- 文章访问数: 2026
- HTML浏览量: 316
- PDF量: 568
- 被引次数: 0
出版历程
- 收稿日期: 2011-06-22
- 刊出日期: 2012-05-28

Numerical study of mixing and combustion performance for magnetohydrodynamic-bypass scramjet

School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China

摘要

摘要: 为了研究磁流体能量旁路超燃冲压发动机(AJAX)的混合燃烧性能,采用三维数值方法,分别对磁流体发电器作用区和化学反应区进行模拟.在其他条件不变的情况下,改变磁场强度和载荷因子从而改变燃烧室的入口条件,得到不同磁流体条件下的混合效率和燃烧效率.计算结果显示:随着磁场强度的增加和载荷因子的减小,混合效率都提高了,最多提高了11.4%,在热离解不明显的燃烧室前半段,燃烧效率也都有所提高;在燃烧室后半段,不出现热离解时燃烧效率最多提高6.5%,此时磁流体装置的引入可使燃烧室长度缩短25%,可降低飞行器的几何尺寸,减轻飞行器质量;出现热离解时,燃烧效率会有所降低甚至低于无磁流体作用时的情况,因此应尽量避免磁场强度过大或载荷因子过小引起燃烧室入口静温过高造成热离解降低燃烧效率.
- 磁流体发电器 /
- 隔离段 /
- 混合效率 /
- 燃烧效率 /
- 超燃冲压发动机
Abstract: In order to study the mixing and combustion performances of magnetohydrodynamic(MHD)-bypass scramjet(AJAX),the three-dimensional numerical methods were used for the MHD generator flow and the chemical reaction flow,respectly.The combustion entrance conditions were varied by altering the MHD conditions,the mixing efficiencies and combustion efficiencies were got.The results show that as the magnetic field strength increases or load factor decreases,the mixing efficiency is increase,the improved maximum value of mixing efficiency is 11.6%.In the front part of chamber where the thermal dissociation is not sensible,the combustion efficiency is increase;in the latter part of the chamber,while the thermal dissociation is no present,the combustion efficiency are increase,the improved maximum value of combustion efficiency is 6.5%,the combustion chamber is shorten by 25%,reduce the geometric sizes and mass of the vehicle;while the thermal dissociation is present,the combustion efficiency are reduced even lower than the no-MHD case,so it should try to avoid larger magnetic field strengths or smaller load factors to reduce the temperature of the combustion entrance,which cause the thermal dissociation reduce the combustion efficiency.
- magnetohydrodynamic generator /
- isolator /
- mixing efficiency /
- combustion efficiency /
- scramjet

HTML

参考文献(20)

[1]	Harsha P,Gur’janov E P.AJAX:new directions in hypersonic technology.AIAA-1996-4609,1996.
[2]	Fraishtadt V L,Kuranov A L,Sheikin E G.Use of MHD systems in hypersonic aircraft[J].Technical Physics,1998,43(11):1309-1313.
[3]	Kuranov A L,Sheikin E G.Magnetohydrodynamic control on hypersonic aircraft under “AJAX” concept[J].Journal of Spacecraft and Rockets,2003,40(2):174-182.
[4]	Sheikin E G,Kuranov A L.Scramjet with MHD bypass under ajax concept.AIAA-2004-1192,2004.
[5]	Park C,Bogdanoff D,Mehta U B.Theoretical performance of frictionless magnetohydrodynamic bypass scramjets[J].Journal of Propulsion and Power,2001,17(3):591-598.
[6]	Park C,Bogdanoff D,Mehta U B.Theoretical performance of a magnetohydrodynamic-bypass scramjet engine with nonequilibrium ionization[J].Journal of Propulsion and Power,2003,19(4):529-537.
[7]	Riggins D W.Analysis of the magnetohydrodynamic energy bypass engine for high-speed airbreathing propulsion[J].Journal of Propulsion and Power,2004,20(5):779-792.
[8]	Litchford R J,Cole J W,Bityurin V A,et al.Thermodynamic cycle analysis of magnetohydronamic-bypass hypersonic airbreathing engines[J].Journal of Propulsion and Power,2001,17(2):477-480.
[9]	Gaitonde D V.Magnetohydrodynamic energy-bypass procedure in a three-dimensional scramjet[J].Journal of Propulsion and Power,2006,22(3):498-510.
[10]	Bottini H,Bruno C,Czysz P A.Is the MHD scramjet really an advantage?.AIAA-2003-5046,2003.
[11]	Lee Chunnian,LU Haoyu.Quasi-one-dimensional parametric study for MHD Generator in MHD bypass scramjet system.AIAA-2007-644,2007.
[12]	郑小梅,徐大军,蔡国飙.MHD能量旁路超燃冲压发动机可行性分析[J].北京航空航天大学学报,2009,35(3):272-275. ZHENG Xiaomei,XU Dajun,CAI Guobiao.Feasibility study of MHD energy bypass scramjet[J].Journal of Beijing University of Aeronautics and Astronautics,2009,35(3):272-275.(in Chinese)
[13]	Dietiker J F,Hoffmann K A.Modified one-equation turbulence models for turbulent magnetohydrodnamic flows[J].Journal of Thermophysics and Heat Transfer,2003,17(4):509-520.
[14]	Kato H,Tannehill J C,Mehta U B.Numeical simulation of turbulent MHD flows using an iterative PNS algorithm.AIAA-2003-0326,2003.
[15]	Evan J S,Charles J S.Influence of chemical kinetics and unmixedness on burning in supersonic hydrogen flames[J].AIAA Journal,1980,18(2):188-193.
[16]	Mohieldin T O,Tiwari S N,Olynciw M J.Asymmetric flow-structures in dual mode scramjet combustor with significant upstream interaction.AIAA-2001-3296,2001.
[17]	Eklund D R,Northam G B.A numcrical study of the effects of geometry on the performance of a supersonic combustor //Proceedings of Aerospace Sciences Meeting and Exhibit.Reno:US National Research Coucil,1992:6-9.
[18]	Birzer C,Doolan C J.Quasi-one-dimensional model of hydrogen-fueled scramjet combustors[J].Journal of Propulsion and Power,2009,25(6):1220-1225.
[19]	Heiser W H,Pratt D T.Hypersonic airbreathing propulsion[M].Washinton D C:AIAA Education Series,1994:205-206.
[20]	刘陵,刘敬华,张榛,等.超音速燃烧与超音速燃烧冲压发动机[M].西安:西北工业大学出版社,1993.