扩张型双喉道喷管的流动特性和起动方法

额日其太; 邓双国; 李家军

扩张型双喉道喷管的流动特性和起动方法

北京航空航天大学能源与动力工程学院, 北京 100191

详细信息

作者简介:
额日其太(1970-),男,内蒙古兴安盟人,副研究员,eriqitai@buaa.edu.cn.

中图分类号: V 231.3
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出版历程
- 收稿日期: 2010-01-08
- 网络出版日期: 2011-03-31

Flow characteristic and starting method for divergent dual throat nozzle

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

摘要

摘要: 利用数值模拟方法,对二元扩张型双喉道喷管的流动特性和起动方法进行了研究.结果表明:扩张型双喉道喷管内会出现正激波系,产生了很大的总压损失,使第2喉道壅塞,喷管不能起动.在低落压比条件下,喉道注气可以形成大的分离区,使激波强度减弱、喷管可以起动;在大落压比条件下,喉道注气不能形成大的分离区,喷管不能起动.扩张段注气可以在喷管内形成大的分离区,使正激波转变成斜激波系,减小了总压损失,使第2喉道流通能力增强、喷管起动.
- 喷管 /
- 射流 /
- 起动
Abstract: The flow characteristic and starting method of two-dimensional divergent dual throat nozzle were studied numerically. The results show that there will be normal shock waves in the divergent zone of the dual throat nozzle, which result in great loss in total pressure and choke at the second throat, thus the nozzle can not start. In the condition of low nozzle pressure ratio, a large separation region, which weakens the shock waves, can be formed by injection in the throat, and the nozzle can start; in the condition of high nozzle pressure ratio, a large separation region will not be formed. A large separation region in the nozzle can be generated by injecting in the divergent, thus the oblique shock is formed instead of the normal shock, the total pressure loss decreases, and the nozzle can start.
- nozzles /
- fluidics /
- starting

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参考文献(1)

[1] 吴雄,张为华,王中伟.气体二次喷射推力向量控制数值仿真[J].北京航空航天大学学报,2007,33(1):43-45 Wu Xiong,Zhang Weihua,Wang Zhongwei.Numerical simulation of secondary gas injecting for thrust vector control[J].Journal of Beijing University of Aeronautics and Astronautics,2007,33(1): 43-45 (in Chinese) [2] 罗静,王强,额日其太. 两种流体控制矢量喷管内流场计算及分析[J].北京航空航天大学学报,2004,30(7):597- 601 Luo Jing,Wang Qiang,Eriqitai.Computational analysis of two fluidic thrust-vectoring concepts on nozzle flow field[J].Journal of Beijing University of Aeronautics and Astronautics,2004, 30(7):597-601(in Chinese) [3] Eriqitai,Wang Qiang.Computational investigation of dual throat fluidic thrust vectoring nozzle .2006-ISJPPE-6017,2006 [4] Flamm J D,Deeret K A,Mason M L,et al.Design enhancements of the two-dimensional dual throat fluidic thrust vectoring nozzle concept .AIAA 2006-3701,2006 [5] 汪明生,杨平.双喉道推力矢量喷管的内流特性研究[J].推进技术,2008,29(5): 566-572 Wang Mingsheng,Yang Ping.Study of dual throat nozzle internal flow characteristic[J].Journal of Propulsion Technology,2008,29(5): 566-572 (in Chinese) [6] 谭慧俊,陈智.二元双喉道射流推力矢量喷管的数值模拟研究[J].航空动力学报,2007,22 (10): 1678-1684 Tan Huijun,Chen Zhi.A computational study of 2-D dual throat fluidic thrust vectoring nozzles[J].Journal of Aerospace Power,2007,22 (10): 1678-1684 (in Chinese) [7] Deere K A,Flamm J D,Berrier B L,et al.Computational study of an axisymmetric dual throat fluidic thrust vectoring nozzle for a supersonic aircraft application .AIAA 2007-5085,2007 [8] Flamm J D,Deere K A,Mason M L,et al. Experimental study of an axisymmetric dual throat fluidic thrust vectoring nozzle for supersonic aircraft application .AIAA 2007-5084,2007

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