| Transonic Instability in Entrance Part of Mixing Chamber of High-Speed Ejector |
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| 作者姓名： | Vaclav Dvorak Pavel Safarik |
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| 作者单位： | Technical University of Liberec，Faculty of Mechanical Engineering，Division of Power Engineering，Halkova 6，461 17 Liberec，Czech Republic Ph.D，Czech Technical University in Prague，Faculty of Mechanical Engineering，207- Institute of Fluid Dynamics and Power Engineering，Division of Fluid Dynamics and Thermodynamics. Technicka 4，166 07 Praha 6，Czech Republic |
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| 摘 要： | Introduction The research of flow structure in the entrance part of the mixing chamber of two-dimensional supersonic ejector1,2] shows, how this structure depends both on stagnation pressure ratio of streams p01/p023] and on back pressure ratio pb/p02 4]. It was found out that the structure of shock waves is not stable, but it oscillates less or more. For the high back pressure ratio a terminal shock wave is in the mixing chamber and due to this shock wave the mixing processes change quali…
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| 关 键 词： | 跨音速流动 不稳定性 混频 震动波 排除器 |
| 收稿时间： | 20 June 2005 |
Transonic instability in entrance part of mixing chamber of high-speed ejector |
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| Vaclav Dvorak,Pavel Safarik.Transonic Instability in Entrance Part of Mixing Chamber of High-Speed Ejector[J].Journal of Thermal Science,2005,14(3):258-263,271. |
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| Authors: | Vaclav Dvorak Pavel Safarik |
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| Affiliation: | (1) Faculty of Mechanical Engineering, Division of Power Engineering, Technical University of Liberec, Halkova 6, 461 17 Liberec, Czech Republic;(2) Faculty of Mechanical Engineering, 207 - Institute of Fluid Dynamics and Power Engineering, Division of Fluid Dynamics and Thermodynamics, Czech Technical University in Prague, Technicka 4, 166 07 Praha 6, Czech Republic |
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| Abstract: | The paper deals with experimental and numerical study of flow structure in two-dimensional model of supersonic ejector. Schlieren pictures of flow structure were taken, static pressure distributions on side wall were measured and Fluent software to calculate the flow structure in supersonic ejector was used. For certain region of back pressure ratio pb/p02 and stagnation pressure ratio of both streams p01/p02 the terminal shock wave is close to the trailing edge of the primary flow nozzle and a transonic instability occurs. The instability causes the movement of position of boundary layer separation, the structure of shock waves changes and all flow structure oscillates. The movie of these regimes during schlieren experiments was taken and relevant numerical modelling was performed. |
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| Keywords: | transonic instability ejector shock waves |
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