磁控进气道的临界焓提取率研究与数值验证

陈瑞锋; 魏志军; 王宁飞

磁控进气道的临界焓提取率研究与数值验证

北京理工大学宇航学院,北京 100081

计量
- 文章访问数: 1537
- HTML浏览量: 0
- PDF量: 25
- 被引次数: 0
出版历程
- 收稿日期: 2010-10-22
- 修回日期: 2011-05-16
- 刊出日期: 2011-08-28

Study on critical enthalpy extraction ratio and numerical validation for magnetohydrodynamic inlet

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

摘要

摘要: 为保证磁控进气道工作于起动状态,提出了临界焓提取率的概念,采用涡轮喷气发动机的模型对磁控进气道进行类比分析,推导得到了磁控进气道在临界起动状态下的模型.最后通过数值验算,磁控进气道的临界状态模型与数值结果符合较好,误差小于5.7%,可为磁控进气道的设计提供参考.
- 磁控进气道 /
- 临界焓提取率 /
- 起动状态 /
- 超燃冲压发动机 /
- 涡轮喷气发动机
Abstract: To ensure that the magnetohydrodynamic (MHD) inlet works in starting state,the concept of critical enthalpy extraction ratio was proposed for the MHD inlet.The quasi-one-dimensional model for the critical enthalpy extraction ratio state of MHD inlet was analyzed using the turbojet engine model,the variable cross-section pipe flow theory and the expressions of modified polytropic efficiencies.By comparison of this model with the computational fluid dynamics (CFD) method,the results show that this model fits good,and the error is less than 5.7%,thus providing a reference for design of the MHD inlet.
- magnetohydrodynamic inlet /
- critical enthalpy extraction ratio /
- start state /
- scramjet /
- turbojet engine

HTML

参考文献(18)

[1]	Gurijanov E P,Harsha P T.AJAX-new directions in hypersonic technology.Norfolk,VA:7th International Space Planes and Hypersonic Systems and Technologies Conference,1996.
[2]	Park C,Bogdanoff D,Mehta U B.Theoretical performance of frictionless magneto hydrodynamic bypass scramjets[J].Journal of Propulsion and Power,2001,17(3):591-598.
[3]	Macheret S O,Shneider M N,Miles R B.Optimum performance of electron beam driven magnetohydrodynamic generators for scramjet inlet control[J].AIAA Journal,2007,45(9):2157-2163.
[4]	Shneider M N,Macheret S O,Miles R B.Analysis of magnetohy drodynamic control of scramjet inlets[J].AIAA Journal,2004,42(11):2303-2310.
[5]	Sheikin E G,Kuranov A L.Scramjet with MHD controlled inlet.AIAA 2005-3223,2005.
[6]	Deb P,Agarwal R K.Numerical study of MHD-bypass scramjet inlets with finite rate chemistry.AIAA 2001-794,2001.
[7]	LV Haoyu,Lee C H,DONG Haitao,et al.Numerical analysis and optimization of three-dimensional MHD controlled inlets.AIAA 2008-1390,2008.
[8]	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)
[9]	鲍文,常军涛,牛文玉,等.超燃冲压发动机磁控进气道设计影响因素分析[J].航空动力学报,2005,20(3):368-372. BAO Wen,CHANG Juntao,NIU Wenyu,et al.Influence factor analysis of the MHD controlled scram jet inlet design[J].Journal of Aerospace Power,2005,20(3):368-372.(in Chinese)
[10]	Heiser W H,Pratt,D T.Hypersonic air-breathing propulsion[M].Washington,DC:AIAA Education Series,1994.
[11]	Van Wie D M,Kwok F T,Walsh R F.Starting characteristics of supersonic inlets.Lake Buena Vista,FL:ASME,SAE,and ASEE,Joint Propulsion Conference and Exhibit,1996.
[12]	梁德旺,袁化成,张晓嘉.影响高超声速进气道起动能力的因素分析[J].宇航学报,2006,27(4):714-719. LIANG Dewang,YUAN Huacheng,ZHANG Xiaojia.Research on the effects of start ability of hypersonic inlet[J].Journal of Astronautics,2006,27(4):714-719.(in Chinese)
[13]	Oates G C.Aerothermodynamics of gas turbine and rocket propulsion[M].Reston:AIAA Education Series,1997.
[14]	Rosa R J.磁流体发电[M].南京工学院磁流体发电科研组译.北京:科学出版社,1975.
[15]	居滋象,吕友昌,荆伯弘.开环磁流体发电[M].北京:北京工业大学出版社,1998.
[16]	Dietiker J,Hoffmann K A.Modified one-equation turbulence models for turbulent magnetohydrodnamic flows[J].Journal of Thermophysics and Heat Transfer,2003,17(4):509-520.
[17]	Kato H,Tannehill J C,Mehta U B.Numeical simulation of turbulent MHD flows using an iterative PNS algorithm.Reno,Nevada,USA:41st Aerospace Sciences Meeting and Exhibit,2003.
[18]	TCowling T G.电磁流体力学[M].唐戈,郭均,译.北京:科学出版社,1960.