厚液膜敞口型离心喷嘴自激振荡特性试验

doi:10.7527/S1000-6893.2018.22189

流体力学与飞行力学

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厚液膜敞口型离心喷嘴自激振荡特性试验

薛帅杰^1,2, 刘红军^1,2, 洪流^1,2, 陈鹏飞^1,2

1. 西安航天动力研究所, 西安 710100;
2. 液体火箭发动机技术重点实验室, 西安 710100

收稿日期:2018-04-11 修回日期:2018-05-04 出版日期:2018-09-15 发布日期:2018-06-21
通讯作者: 薛帅杰 E-mail:xueshuaijie@163.com
基金资助:
国家"973"计划（613239010102）

Test on self-excited oscillation characteristics of an open-end swirl injector with thick liquid film

XUE Shuaijie^1,2, LIU Hongjun^1,2, HONG Liu^1,2, CHEN Pengfei^1,2

1. Xi'an Aerospace Propulsion Institute, Xi'an 710100, China;
2. Key Laboratory of Science and Technology on Liquid Rocket Engine, Xi'an 710100, China

Received:2018-04-11 Revised:2018-05-04 Online:2018-09-15 Published:2018-06-21
Supported by:
National Basic Research Program of China (613239010102)

摘要/Abstract

摘要： 为了解补燃循环液氧煤油发动机预燃室煤油离心喷嘴的自激振荡特性，在大气环境下开展了厚液膜敞口型离心喷嘴自激振荡特性试验研究。无外加激励条件下，使用水作为工作介质，通过增加喷嘴长度的方法实现了敞口型离心喷嘴旋流腔液膜增厚和内流过程持续自激振荡。采用脉动压力传感器和高速相机记录了喷前压力、旋流腔气涡和喷注雾化的振荡特性。研究发现：喷嘴自激振荡过程中，旋流腔气涡周期性地"间断"和"贯通"，气涡"间断"时喷注过程具有显著的Klystron效应；喷前压力、旋流腔气涡和喷注雾化过程的振荡频率接近且不同喷注压降条件下振荡频率基本保持在10~45 Hz之间，喷注压降对振荡过程的影响较小，喷前压力相对振荡峰值与其振荡频率显著相关；喷嘴的自激振荡过程可能由旋流腔内的液膜流动过程和气涡流动过程的耦合作用主导。

关键词: 敞口型离心喷嘴, 厚液膜, 气涡, 雾化, 自激振荡, Klystron效应

Abstract: To understand the self-excited oscillation characteristics of the kerosene swirl injector in the pre-burner of staged combustion LO_x/kerosene rocket engine, self-excited oscillation in the open-end swirl injector has been investigated experimentally in the atmospheric environment using water as the working fluid. Sustained self-excited oscillation of the internal flow process was spontaneously generated in an open-end swirl injector with long swirl chamber and thick liquid film. The fluctuations of the pressure before injecting, the gas core in the swirl chamber and the spray process were detected by a dynamic pressure sensor and a high-speed camera. It is found that the gas core in the swirl chamber became disconnected periodically when self-excited oscillation was generated, and the Klystron effect of spray was induced when the gas core was disconnected. The fluctuation frequencies of the pressure, the gas core and the spray were close to each other under the same working condition, and were limited in the range from 10 to 45 Hz with different injection pressure drops. The pressure drop of the injector had unremarkable impact on the fluctuation process. There is a significant correlation between the relative amplitude of dynamic pressure and the fluctuation frequency. The self-excited oscillation of the injector may be induced by interaction of the gas core with the film in the swirl chamber.

Key words: open-end swirl injector, thick liquid film, gas core, spray, self-excited oscillation, Klystron effect

中图分类号:

V434.3

薛帅杰, 刘红军, 洪流, 陈鹏飞. 厚液膜敞口型离心喷嘴自激振荡特性试验[J]. 航空学报, 2018, 39(9): 122189-122198.

XUE Shuaijie, LIU Hongjun, HONG Liu, CHEN Pengfei. Test on self-excited oscillation characteristics of an open-end swirl injector with thick liquid film[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(9): 122189-122198.

参考文献

[1] BAZAROV B. 液体喷嘴动力学[M]. 任汉芬, 孙纪国, 译. 北京:中国宇航出版社, 1997:1-5. BAZAROV B. Dynamics of liquid injector[M]. REN H F, SUN J G, translated. Beijing:China Astronautic Publishing House, 1997:1-5(in Chinese).
[2] BAZAROV B, YANG V. Liquid-propellant rocket engine injector dynamics[J]. Journal of Propulsion and Power, 1998, 14(5):797-806.
[3] ISMAILOV M, HEISTER S. Dynamic response of rocket swirl injectors, Part I-Wave reflection and resonance[J]. Journal of Power and Propulsion, 2011, 27(2):402-411.
[4] ISMAILOV M, HEISTER S. Dynamic response of rocket swirl Injectors, Part Ⅱ-Nonlinear dynamic response[J]. Journal of Power and Propulsion, 2011, 27(2):412-421.
[5] AHN B, ISMAILOV M, HEISTER S. Experimental study swirl injector dynamic response using a hydromechanical pulsator[J]. Journal of Propulsion and Power, 2012, 28(3):585-595.
[6] KHIL T, CHUNG Y, BAZAROV V, et al. Dynamic characteristics of simplex swirl injector in low frequency range[J]. Journal of Propulsion and Power, 2012, 28(2):323-333.
[7] HARRJE D T, REARDON F H. Liquid propellant rocket combustion instability:NASA SP-194[R]. Washington, D.C.:NASA, 1972.
[8] 杨立军, 富庆飞, 王永涛, 等. 多排切向通道敞口型离心喷嘴的动态特性研究[J]. 宇航学报, 2006, 27(5):865-870. YANG L J, FU Q F, WANG Y T, et al. Investigation of dynamic of multi-row tangential channel opened swirl injector[J]. Journal of Astronautics, 2006, 27(5):865-870(in Chinese).
[9] 杨立军, 张向阳, 葛明和. 敞口型离心喷嘴动力学特性理论分析[J]. 推进技术, 2006, 27(6):497-499. YANG L J, ZHANG X Y, GE M H. Theoretical analysis of dynamics of open swirl injector[J]. Journal of Propulsion Technology, 2006, 27(6):497-499(in Chinese).
[10] FU Q F, YANG L J, QU Y Y, et al. Geometrical effects on the fluid dynamics of an open-end swirl injector[J]. Journal of Propulsion and Power, 2011, 27(5):929-936.
[11] 富庆飞, 杨立军, 屈元元, 等. 敞口型液体离心喷嘴动态特性数值模型[J]. 航空动力学报, 2010, 25(9):2132-2138. FU Q F, YANG L J, QU Y Y, et al. Numerical simulation of dynamic characteristics of an open-end swirl injector[J]. Journal of Aerospace Power, 2010, 25(9):2132-2138(in Chinese).
[12] CHUNG Y, KIM H, JEONG S, et al. Dynamic characteristics of open-type swirl injector with varying geometry[J]. Journal of Propulsion and Power, 2016, 32(3):583-591.
[13] 张贵田. 高压补燃液氧煤油发动机[M]. 北京:国防工业出版社, 2005:145-150. ZHANG G T. High pressure staged combustion LO_x/kerosene rocket engine[M]. Beijing:National Defense Industry Press, 2005:145-150(in Chinese).
[14] KENNY R, HULKA J, MOSER M, el al. Effect of chamber backpressure on swirl injector fluid mechanics[J]. Journal of Propulsion and Power, 2009, 25(4):902-913.
[15] 陈晨, 杨样, 高宏力, 等. 敞口式离心喷嘴内部及近喷口区域的流动特性[J]. 航空动力学报, 2016, 31(12):2988-2995. CHEN C, YANG Y, GAO H L, et al. Flow field in and near the open-end swirl injector[J]. Journal of Aerospace Power, 2016, 31(12):2988-2995(in Chinese).
[16] 丁文镜. 自激振动[M]. 北京:清华大学出版社, 2009:2-10. DING W J. Self-excited vibration[M]. Beijing:Tsinghua University Press, 2009:2-10(in Chinese).
[17] BAYVEL L, ORZECHOWSKI Z. Liquid atomization[M]. Milton Park:Taylor & Francis, 1993:252-266.
[18] 张新桥. 基于离心式喷嘴的多组分燃料喷雾燃烧过程研究[D]. 长沙:国防科技大学, 2016:24-32. ZHANG X Q. Research on spray combustion of multi-component fuel based on swirl injector[D]. Changsha:National University of Defense Technology, 2016:24-32(in Chinese).
[19] MOON S, SERIE E, BAE C. Liquid film thickness inside the high pressure swirl injectors:Real scale measurement and evaluation of analytical equations[J]. Experimental Thermal and Fluid Science, 2010, 34(2):113-121.
[20] 吴孟达, 李兵, 王文浩. 高等工程数学[M]. 北京:科学出版社, 2009:187-203. WU M D, LI B, WANG W H. Advanced engineering mathematics[M]. Beijing:Science Press, 2009:187-203(in Chinese).
[21] 王凯, 杨国华, 李鹏飞, 等. 离心式喷嘴内部流动过程数值仿真分析[J]. 火箭推进, 2016, 42(4):14-20. WANG K, YANG G H, LI P F, et al. Numerical simulation of internal flow process in pressure swirl injector[J]. Journal of Rocket Propulsion, 2016, 42(4):14-20(in Chinese).
[22] 陈晓东, 刘宇, 杨威迦. 液体离心喷嘴中的静态表面波[J]. 推进技术, 2010, 31(1):42-46. CHEN X D, LIU Y, YANG V J. Stationary surface wave in liquid swirl injector[J]. Journal of Propulsion Techno-logy, 2010, 31(1):42-46(in Chinese).

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厚液膜敞口型离心喷嘴自激振荡特性试验

Test on self-excited oscillation characteristics of an open-end swirl injector with thick liquid film

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