Pulsed Schileren System and Its Application to Visualization of Flow-Field in a Supersonic Combustor

Journal of Propulsion Technology ›› 2013, Vol. 34 ›› Issue (1): 42-46.

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Pulsed Schileren System and Its Application to Visualization of Flow-Field in a Supersonic Combustor

Key Laboratory of High Temperature Gas Dynamics/Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China;Key Laboratory of High Temperature Gas Dynamics/Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China;Key Laboratory of High Temperature Gas Dynamics/Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China;Key Laboratory of High Temperature Gas Dynamics/Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China

Published:2021-08-15

脉冲纹影技术及其在超声速燃烧室流场显示中的应用

袁越明,杨猛,张泰昌,范学军

中国科学院力学研究所/高温气体动力学国家重点实验室,北京 100190;中国科学院力学研究所/高温气体动力学国家重点实验室,北京 100190;中国科学院力学研究所/高温气体动力学国家重点实验室,北京 100190;中国科学院力学研究所/高温气体动力学国家重点实验室,北京 100190

作者简介:袁越明(1983—),男,助理研究员,研究领域为超声速燃烧实验与测量技术。E-mial:yuanym@imech.ac.cn
基金资助:
国家自然基金重大研究计划重点支持项目(91016005);国家自然基金创新群体项目(10621202)。

Abstract

Abstract: The flow-field in the supersonic combustor has the characteristics of high speed, high temperature, high background radiation, and so on. Thus,the visualization of flow-field in a supersonic combustor is difficult. According to above characteristics, a pulsed schlieren system was developed, and a short exposure time was chosen to freeze the flow-field. On the other hand, compared to the electric flash energy, the background radiation could be ignorable during the exposure time. Thereby, the effect of background radiation is eliminated effectively. The pulsed schlieren system is used to study the flow-field structures during the combustion process of supercritical kerosene in a Mach number 3.0 supersonic flow. Schlieren images clearly show flow-field structures and their evolutionary process.

Key words: Schlieren; Supersonic combustion; Supercritical kerosene;Flow-Field visualization

摘要： 超声速燃烧室内部流场具有流速快、温度高、背景光辐射强等特点,其流场显示较为困难。为此设计了一套脉冲纹影系统,该系统通过缩短曝光时间来冻结流场；另一方面,利用脉冲火花光源在短曝光时间内脉冲放电能量远高于燃烧室背景辐射能量的特点,有效消除了燃烧室背景辐射的影响。利用该系统对马赫数3.0的超临界煤油燃烧流场结构进行研究,得到了超临界煤油燃烧过程的清晰流场结构图像及其演化过程。

关键词: 脉冲纹影;超声速燃烧;超临界煤油;流场显示 

袁越明,杨猛,张泰昌,范学军. 脉冲纹影技术及其在超声速燃烧室流场显示中的应用[J]. 推进技术, 2013, 34(1): 42-46.

References

[1] Aguilera C, Pang B,Yu K H.Fin-Guided Liquid-Feul injection ito March 2.1 Airflow[R].AIAA 2011-5763.
[2] Chae-Hyoung Kim,In-Seuck Jeung.Effect of Fuel Injection Locations with Hyper Mixer in Supersonic Combustion[R].AIAA 2011-5830.
[3] Jan Martinze Schranmm, Sebastian Karl,Klaus Hnnemann.Ground Testing of the HyShot II Scramjet Configuration in HEG[R].AIAA 2008-2547.
[4] Fan Xuejun,Yu Gong,Li Jianguo, et al.Investigation of Vaporized Kerosene Injection and Combustion in a Supersonic Model Combustion[J].Journal of Propulsion and Power, 6,2(1).
[5] Lavante E Von,Zeitz D,Kallenberg M.Numerical Simulation of Supersonic Airflow with Transverse Hydrogen Injection[J].Journal of Propulsion and Power,1,7(6).
[6] Kondo A, Sakaue S, Arai T.Fluctuation of Mass Flux and Concentration on Supersonic Mixing using Streamwise Vortices[R].AIAA 2008-2535.
[7] Chae Hyoung Kim, Eunju Jeong, Jeong-Woo Kim, et al.Mixing and Penetration Studies of Transverse Jet into a Supersonic Crossflow[R].AIAA 2007-5420.
[8] Bonanos Aristides M, Bergthorson Jeffrey M,Dimotakis Paul E.Molecular Mixing and Flowfield Measurements in an Expansion-Ramp Combustion:Supersonic Flow[R].AIAA 2007-5417.
[9] Tomoaki KitagawaIgnition, Atsushi Moriwaki, Kenichi Takita, et al.Characteristics of Methane and Hydrogen Using a Plasma Torch in Supersonic Flow[J].Journal of Propulsion and Power, 3,9(5).
[10] Koichi Murakami, Aya Nishikawa, Kenichi Takita, et al.Ignition Characteristics of Hydrocarbon Fuels by Plasma Torch in Supersonic Flow[R].AIAA 2003-6939.
[11] Jinkwan Song, Chanyeon Jung, Jeongjae Hwang, et al.An Experimental Study on the Flame Dynamics with V-Gutter Typer Flameholder in the Model Combustor[R].AIAA 2011-6126.
[12] Sergey Leonov,Dmitry Yaeantsev.Eeperiments on Electrically Controlled Flameholding on a Plane Wall in Supersonic Airflow[J].Journal of Propulsion and Power,9,5(2).
[13] Rasmussen Chadwick C,Driscoll James F.Characteristics of Cavity-Stabilized Flames in a Supersonic Flow[J].Journal of Propulsion and Power,5,1(4).
[14] Estruch D, Lawson N J,MacManus D G, et al.Measurement of Shock Wave Unsteadiness using a High-Speed Schlieren System and Digital Image Processing[J].Review of Scentific Instruments,2008,9,8.
[15] Sugiyama H,Tsujiguchi Y,Honma T.Structure and Oscillation Phenomena of Pseudo-Shock Wave in a Straight Square Duct at Mach2 and 4[R].AIAA 2008-2646.
[16] Tsuyoshi Kumasaka, Noritaka Ichikawa, Goro Masuya, et al.Influence of Combustion on Behavior of Pesudo-Shock Wave[R].AIAA 2003-6912.
[17] Ferry F J Schrijer, Fulvio Scarano,Bas W van Oudheusden.Experiments on Hypersonic Boundary Layer Separation and Reattachment on a Blunted Cone-Flare using Quantitative InfraRed Thermography[R].AIAA 2003-6967.
[18] Pan Yu, Tan Jian-Guo,Liang Jian-Han, et al.Experimental Investigation of Combustion Mechanisms of Kerosene-Fueled Scramjet Engines with Double-Cavity Flameholders[J].Acta Mechanica Sinica, 1,7(6).
[19] Pan Yu, Lei Jing, Tan Jianguo, et al.Experimental Investigation on the Combustion Oscillation in a Model Scramjet Engine[R].ISABE 2011-1528.
[20] Liepmann H W.Elements of Gasdynamics[M].New York:John Wiley & Sons.Inc, 1957.
[21] Fan X J, Zhong F Q, Yu G,et al.Catalytic Cracking and Heat Sink Capacity of Aviation Kerosene under Supercritical Conditions[J].Journal of Propulsion and Power,9,5(6).
[22] 范学军, 俞刚.超临界煤油超声速燃烧特性实验[J].推进技术, 6,7 (1).(FAN Xue-jun,YU Gang.Experiments on Supersonic Combustion of Supercritical Kerosene[J].Journal of Propulsion Technology,6,7(1).)

Pulsed Schileren System and Its Application to Visualization of Flow-Field in a Supersonic Combustor

脉冲纹影技术及其在超声速燃烧室流场显示中的应用

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