Analysis of over/under tbcc inlet mode transition flow characteristic

被引：0
|
作者：
Liu J. [1 ]
Yuan H.-C. [1 ]
Guo R.-W. [1 ]
机构：
[1] Jiangsu Province Key Laboratory of Aerospace Power Systems, Nanjing University of Aeronautics and Astronautics, Nanjing
来源：
Yuhang Xuebao/Journal of Astronautics | 2016年 / 37卷 / 04期
关键词：
Air-breathing hypersonic propulsion system; Inlet mode transition; Shock oscillation; Turbine based combined cycle inlet; Unsteady numerical simulation;
D O I：
10.3873/j.issn.1000-1328.2016.04.012
中图分类号：
学科分类号：
摘要：
Unsteady flow characteristic exits during the turbine based combined cycle(TBCC) inlet mode transition. Thus, steady and unsteady numerical simulation methods are used to investigate the this flow fields in the present paper. The numerical results indicate the terminal shock oscillates in the TBCC inlet during the mode transition from turbojet mode to ramjet mode. And the terminal shock oscillation frequency is about 130 Hz. At the same time, the shock oscillation frequency is not affected by ramjet engine operation modes until the shock in ramjet flowpath is expelled to the front of the splitter. At the same operation condition of the engine, the frequency of shock oscillation increases as the rate of inlet mode transition is raised. The terminal shock oscillation phenomena occurred during TBCC inlet mode transition can be explained by subsonic wave propagation theory. © 2016, Editorial Dept. of JA. All right reserved.
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页码：461 / 469
页数：8
相关论文
共 25 条
  • [1] Tanatusgu N., Sato T., Balepin V.V., Et al., Development study on ATREX engine, (1996)
  • [2] Sato T., Kobayashi H., Tanatsugu N., Et al., Development study of the precooler of the ATREX engine, (2003)
  • [3] Steelant J., Achievements obtained for sustained hypersonic flight within the LAPCAT project, (2008)
  • [4] Mamplata C., Tang M., Technical approach to turbine-based combined cycle: FaCET, (2009)
  • [5] Walker S., Tang M., Mamplata C., TBCC propulsion for a Mach 6 hypersonic airplane, (2009)
  • [6] Ma H., Yuan J.-P., Fang Q., Dynamics analysis of air-breathing hypersonic vehicle, Journal of Astronautics, 28, 5, pp. 1100-1104, (2007)
  • [7] Chen M., Zhu Z.L., Zhu D.M., Et al., Performance analysis tool for turbine based combined cycle engine concept, Journal of Astronautics, 27, 5, pp. 854-859, (2006)
  • [8] Liu Z.-W., Wang Z.-X., Cai Y.-H., Et al., Numerical simulation of performance for turbine based combined cycle propulsion system, Journal of Propulsion Technology, 30, 1, pp. 1-6, (2009)
  • [9] Zhang H.-J., Liang D.-W., Guo R.-W., Study of flow characteristics for a variable geometry inlet on combined engine, Journal of Aerospace Power, 24, 10, pp. 2201-2207, (2009)
  • [10] Bilardo V.J., Curran F.M., Hunt J.L., Et al., The benefits of hypersonic airbreathing launch systems for access to apace, (2003)
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