多喷嘴氢氧燃烧二元加热器设计与仿真

田亮; 陈超群; 徐旭; 宋冈霖; 张岩

多喷嘴氢氧燃烧二元加热器设计与仿真

田亮¹,
陈超群¹,
徐旭¹,
宋冈霖^1,2,
张岩³

1.
北京航空航天大学宇航学院, 北京 100191
2.
中国西昌卫星发射中心发射测试站, 四川西昌 615608
3.
南阳理工学院土木工程系, 河南南阳 473300

计量
- 文章访问数: 1421
- HTML浏览量: 1
- PDF量: 1044
- 被引次数: 0
出版历程
- 收稿日期: 2012-07-13
- 刊出日期: 2013-07-28

Design and numerical simulation of two-dimensional oxygen-hydrogen heater with multiply jet

1.
School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
2.
China Xichang Satellite Launch Center, Xichang Sichuan 615608, China
3.
Department of Civil Engineering, Nanyang Institute of Technology, Nanyang Henan 473300, China

摘要

摘要: 为了获得均匀的喷管出口参数,设计了两种喷注形式的多喷嘴氢氧燃烧二元加热器和一个拉瓦尔喷管,利用CFD仿真软件对其进行了流场计算,研究了同一工况下不同喷注器构型、速度比和喷嘴压降对喷管出口均匀度的影响.结果表明:喷注器构型对出口气流的均匀程度影响不大,它主要影响喷注器的温度;氢气与空氧混气的速度比越低,出口均匀性越好,空氧混气喷嘴的压降越低,出口均匀性越好;拉瓦尔喷管收缩比对出口均匀性有很大影响,设计时应尽量使两方向收缩比相近.
- 加热器 /
- 均匀性 /
- 速度比 /
- 氧喷嘴压降 /
- 收缩比
Abstract: For generating uniform air flow at Laval nozzle outlet,the influences of the form,velocity ratio and pressure drop of the injection was studied.An air heater with two forms of injection and a Laval nozzle were designed,then FLUENT was used to simulate the combustion and flow filed.The result show that:there is little influence from the form of the injection,which mainly influences the temperature of the injector;the lower velocity rate and oxygen drop of the jet means the more uniform of nozzle outlet and approximative contraction ratio in two directions is better for the outlet.
- heater /
- uniformity /
- velocity ratio /
- oxygen pressure drop /
- contraction ratio

HTML

参考文献(15)

[1]	Curran E T.Scramjet engines:the first forty years[J].Journal of Propulsion and Power,2001,17(6):1138-1148.
[2]	王树声.论超燃冲压发动机试验研究及其试验设备[J].推进技术,1988,9(1):12-17. WANG Shusheng.On experimental studies of scramjet and its test facilities[J].Journal of Propulsion Technology,1988,9(1):12-17.(in Chinese)
[3]	张新宇,陈立红,顾洪斌,等.超燃冲压模型发动机实验设备与实验技术[J].力学进展,2003,33(4):491-498. ZHANG Xinyu,CHEN Lihong,GU Hongbin,et al.Progress in study on test facility and experimental technique for model scramjet[J].Advances In Mechanics,2003,33(4):491-498.(in Chinese)
[4]	Sarisin M N,Ulas A.Investigation of combustion control in the vitiator of a connected pipe setup for ramjet applications [R].Reno Nevada:Aerospace Sciences Meeting And Exhibit,2006.
[5]	Dunsworth L C,Reed G J.Ramjet engine testing and simulation techniques [R].Las Vegas:Joint Propulsion Conference,1978.
[6]	Peter H C,Chu C,Marksberry L,et al.High temperature storage heater technology for hypersonic wind tunnels and propulsion test tacilities [R].Capua,Italy:International Space Planes And Hypersonics Systems And Technolo,2005.
[7]	Andrews E H,Torrelce M G,Anderson G Y,et al.Langley Mach 4 scramjet test facility [R].Virginia:NASA Technical Memorandum,86277,1985.
[8]	李龙飞,王延涛,杨伟东,等.超声速燃烧地面试验的蓄热式加热器及其关键技术[J].火箭推进,2012,38(2):16-19. LI Longfei,WANG Yantao,YANG Weidong,et al.Thermal energy storage heater and its key technologies for supersonic combustion ground test facilities[J].Journal of Rocket Propulsion,2012,38(2):16-19.(in Chinese)
[9]	沈赤兵,刘友朋,吴海燕.一种空气加热器的三维流场数值仿真[J].国防科技大学学报,2011,33(1):17-20. SHEN Chibing,LIU Youpeng,WU Haiyan.Numerical simulation of three-dimension flow field in an air-heater[J].Journal of National University of Defense Technology,2011,33(1):17-20.(in Chinese)
[10]	杨阳,刘伟雄,乐嘉陵,等.直连式脉冲燃烧高温风洞的设计[J].西南交通大学学报,2008,43(3):387-391. YANG Yang,LIU Weixiong,LE Jialing,et al.Design of direct-connect impulse combustion wind tunnel[J].Journal of Southwest Jiaotong University,2008,43(3):387-391.(in Chinese)
[11]	李小平,葛李虎,栾希亭.加热器在冲压发动机试验技术中的应用研究[J].火箭推进,2007,33(3):14-19. LI Xiaoping,GE Lihu,LUAN Xiting.Applications of gas generator in ramjet direct-connect test facility[J].Journal of Rocket Propulsion,2007,33(3):14-19.(in Chinese)
[12]	陈超群,韦宝禧,章成亮,等.超燃试验用加热器三维粘性流场数值模拟[J].北京航空航天大学学报,2009,35(5):591-595. CHEN Chaoqun,WEI Baoxi,ZHANG Chengliang,et al.Numerical simulation of three dimension viscous flow of combustion-heater used for scramjet test[J].Journal of Beijing University of Aeronautics and Astronautics,2009,35(5):591-595.(in Chinese)
[13]	王辽,徐旭.超燃冲压发动机地面试验氢燃烧加热器流场数值模拟[J].航空动力学报,2008,23(8):1397-1402. WANG Liao,XU Xu.Numerical investigation of hydrogen combustion-heater for scramjet ground test[J].Journal of Aerospace Power,2008,23(8):1397-1402.(in Chinese)
[14]	杜正刚,高玉闪,李茂,等.同轴双剪切气-气喷嘴数值模拟[J].航空动力学报,2010,25(4):829-834. DU Zhenggang,GAO Yushan,LI Mao,et al.Numerical simulation of shear dual-coaxial gas-gas injector[J].Journal of Aerospace Power,2010,25(4):829-834.(in Chinese)
[15]	伍荣林,王振羽.风洞设计原理[M].北京:北京航空学院出版社,1985.