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)

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