圆孔喷嘴形成气动喉部的定常数值研究

谢侃; 刘宇; 王一白

圆孔喷嘴形成气动喉部的定常数值研究

北京航空航天大学宇航学院,北京 100191

基金项目: 航天科技创新基金(CASC200903)

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出版历程
- 收稿日期: 2010-03-02
- 修回日期: 2010-04-25
- 刊出日期: 2011-04-28

Steady numerical study of aerodynamic throat formed by round injectors

School of Astronautics, Beijing University of Aeronautics and Astronautics,Beijing 100191,China

摘要

摘要: 对固体火箭发动机上由圆孔喷嘴喷入二次流所形成的气动喉部进行了三维数值模拟.考察了圆孔喷嘴形成气动喉部的典型三维流动特征和喷嘴流量特性.研究了不同喷嘴面积比、喷嘴个数、喷射角度、喷嘴构型及主要喷管参数对气动喉部调节喉部面积能力的影响.结果表明在相同的喷嘴面积比下,增加喷嘴个数、采用逆向喷射或选用收缩喷嘴构型都能显著提高气动喉部的扼流性能.
- 圆孔喷嘴 /
- 固体火箭发动机 /
- 气动喉部 /
- 二次流 /
- 数值模拟
Abstract: A three-dimensional (3-D) numerical simulation of aerodynamic throat formed by secondary flow from round injectors,which was applied to solid propellant rocket motors,was performed in this paper.The typical 3-D flow structure and mass flow character of round injectors were reviewed.The influence of different injector area ratios,injector numbers,injection angles,injector types and major nozzle parameter were studied.The results show that the mass control performance of aerodynamic throat can be obviously improved by increasing injector numbers,applying reverse injection or convergence injector type at the same injector area ratio.
- round injector /
- solid rocket motor /
- aerodynamic throat /
- secondary flow /

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参考文献(12)

[1]	李娟,李江,王毅林,等.喉栓式变推力发动机性能研究[J].固体火箭技术,2007,30(6):505-509. LI Juan, LI Jiang,WANG Yilin,et al.Study on performance of pintle controlled thrust solid rocket motor[J].Journal of Solid Rocket Technology,2007,30(6):505-509.(in Chinese)
[2]	McArdle J G.Internal characteristics and performance of an aerodynamically controlled,variable discharge convergent nozzle .NACA TN4312,1958.
[3]	McAulay J E.Cold-air investigation of three variable-throat-area convergent-divergent nozzles .NASA TM X-42,1958.
[4]	Catt J A,Miller D N,Giuliano V J.A static investigation of fixed-geometry nozzle using fluidic injection for throat-area control .AIAA 95-2604,1995.
[5]	Miller D N,Yagle P J,Bender E E,et al.A computational investigation of pulsed injection into a confined,expanding crossflow .AIAA 2001-3026,2001.
[6]	Miller N,Yagle P J,Hamstra J W.Fludic throat skewing for thrust vectoring in fixed-geometry nozzles .AIAA 99-0365,1999.
[7]	Vakili A D,Sauerwein S C.Pulsed injection applied to nozzle internal flow control .AIAA 99-1002,1999.
[8]	Yagle P J,Miller D N,Bender E E,et al.A computational investigation of pulsed ejection . AIAA 2002-3278,2002.
[9]	Williams R G,Vittal B R.Fluidic thrust vectoring and throat control exhaust nozzle .AIAA 2002-4060,2002.
[10]	Glenn D E.Predicting performance of candidates to replace Halon 2402(Freon 114B2) in the Minuteman Ⅲ Second Stage LITVC system .AIAA 92-3558,1992.
[11]	谢侃,刘宇,任军学,等.两相流环缝塞式喷管理想型面的设计方法[J].固体火箭技术,2007,30(3):223-228. XIE Kan,LIU Yu,REN Junxue,et al.An ideal method for the two-phase ring plug nozzle design[J].Journal of Solid Rocket Technology,2007,30(3):223-228.(in Chinese)
[12]	谢侃,刘宇,王一白.固体火箭发动机气动喉部的两相流数值模拟[J].推进技术,2010,31(1):56-60. XIE Kan,LIU Yu,WANG Yibai.Simulation for two-phase flow aerodynamic throat of solid rocket motors[J].Journal of Propulsion Technology,2010,31(1):56-60.(in Chinese)