发动机泵后管路-汽蚀管系统水力激振试验

刘上; 张兴军; 程晓辉; 赵瑞国; 吕鹏翾; 张琳; 付幼明; 杨唱; 孙冰; 方杰

doi:10.13224/j.cnki.jasp.2018.12.028

发动机泵后管路-汽蚀管系统水力激振试验

doi: 10.13224/j.cnki.jasp.2018.12.028

1.
中国航天科技集团有限公司西安航天动力研究所液体火箭发动机技术重点实验室，西安 710100
2.
北京航空航天大学宇航学院，北京 100191

计量
- 文章访问数: 562
- HTML浏览量: 3
- PDF量: 389
- 被引次数: 0
出版历程
- 收稿日期: 2017-09-21
- 刊出日期: 2018-12-28

Experiment for hydraulic vibration onrocket engine feed pipe-Venturi tube system after pump

摘要

摘要: 为了研究火箭发动机泵后管路-汽蚀管系统动力学特性，开展水力激振试验。在汽蚀管下游引入水力激振信号，测量供应管路和推力室头腔的脉动压力，建立描述系统动力学特性的传递函数。结果表明:该系统主要表现出1阶谐振特征，高阶谐振峰不明显。在谐振频率下，汽蚀管出口至氧主阀之间管路上脉动压力的幅值整体较高，脉动压力幅值沿流向逐步增大；经过氧主阀后，压力振荡幅值沿流向快速降低。发现了压力脉动通过此汽蚀管向上游传播的现象：即使汽蚀管处于汽蚀状态，仍存在部分压力脉动通过汽蚀管逆向传播至上游管路；而汽蚀管对整个管路仍然起到了明显的隔振效果。在过大的汽蚀裕度下，汽蚀管出口由声学闭端边界逐渐向声学开端边界转变。
- 汽蚀管 /
- 供应管路 /
- 水力激振 /
- 谐振频率 /
- 响应幅值
Abstract: In order to investigate the dynamical characteristics of the feed pipe - Venturi tube system after pump in a liquid rocket engine, hydraulic vibration experiment were conducted. By generating hydraulic vibration signal after Venturi tube, the pressure fluctuation data at the feed pipes and the thrust chamber manifold were measured, and the transfer function for disturbing this system dynamics was established. The test results indicated that the first resonant response was the main characteristics for the feed system, and the high order resonant peak was unobvious. At the resonant frequency, the pressure oscillation amplitudes were quite high between Venturi tube and main valve, and increased along the flow direction before main valve, but decreased after main valve. A phenomenon of pressure fluctuation transmitting upstream through Venturi tube was discovered. Even the Venturi tube was under the cavitation condition, partial pressure fluctuation could transmit upstream through it, while the Venturi tube also had an evident insulated effect for the whole feed pipe. When the cavitation allowance of Venturi tube was excessively big, the Venturi tube outlet condition was changed from acoustic closed boundary to acoustic open boundary.
- Venturi tube /
- feed pipe /
- hydraulic vibration /
- resonant frequency /
- response amplitude

HTML

参考文献(17)

[1]	任汉芬,刘国球,朱宁昌，等.液体火箭发动机原理［M］.北京:中国宇航出版社,2005.
[2]	HARRJE D T,REARDON F H.液体推进剂火箭发动机不稳定燃烧［M］.朱宁昌,张宝炯,译.北京:国防工业出版社，1980.
[3]	刘上,刘红军,陈建华,等.富氧燃气发生器-供应系统耦合稳定性研究［J］.推进技术,2013,34(11):1448-1458.LIU Shang,LIU Hongjun,CHEN Jianhua,et al.Investigation on oxidizer-rich preburner feed system coupled stability［J］.Journal of Propulsion Technology,2013,34(11):1448-1458.(in Chinese)
[4]	刘上,刘红军,王海燕.富氧燃气发生器液氧供应系统频率特性分析［J］.火箭推进,2013,39(4):12-18.LIU Shang,LIU Hongjun,WANG Haiyan.Frequency characteristic analysis for LOX feed system of oxidizer-rich preburner［J］.Journal of Rocket Propulsion,2013,39(2):12-18.(in Chinese)
[5]	刘上,刘红军,孙宏明,等.液体火箭发动机中频耦合振荡初步研究［J］.推进技术,2013,34(1):101-108.LIU Shang,LIU Hongjun,SUN Hongming,et al.Preliminary study of medium frequency coupled oscillation in liquid rocket engine［J］.Journal of Propulsion Technology,2013,34(1):101-108.(in Chinese)
[6]	张黎辉，张振鹏.补燃循环液体火箭发动机输送系统的频率特性［J］.推进技术,2000,21(1):5-7.ZHANG Lihui,ZHANG Zhenpeng.Frequency characteristic for liquid propellant staged combustion cycle rocket engine［J］.Journal of Propulsion Technology,2000,21(1):5-7.(in Chinese)
[7]	KAHN D R,SCHUMAN M D,HUNTING J K,et al.Orbital maneuvering engine feed system coupled stability investigation［R］.NASA CR-144409,1975.
[8]	丁猛,吴继平,梁剑寒,等.文氏管在煤油燃料超燃冲压发动机中的应用［J］.推进技术,2005,26(1):16-19.DING Meng,WU Jiping,LIANG Jianhan,et al.Application of control technology based on Venturi in kerosene fueled scramjet［J］.Journal of Propulsion Technology,2005,26(1):16-19.(in Chinese)
[9]	沈赤兵,吴继平.可调汽蚀文氏管试验研究［J］.推进技术,2004,25(5):473-476.SHEN Chibing,WU Jiping.Experimental investigation on the controllable cavitating Venturi［J］.Journal of Propulsion Technology,2004,25(5):473-476.(in Chinese)
[10]	张小斌,曹萧丽,邱利民,等.液氧文氏管汽蚀特性计算流体力学研究［J］.化工学报,2009,60(7):1638-1643.ZHANG Xiaobin,CAO Xiaoli,QIU Limin,et al.CFD study on cavitation of liquid oxygen in Venturi［J］.Journal of the Chemical Industry and Engineering Society of China,2009,60(7):1638-1643.(in Chinese)
[11]	朱子勇,刘红彤,孙万民.汽蚀文氏管内部空穴两相流动数值计算与试验比较［J］.导弹与航天运载技术,2014 (1):75-81.ZHU Ziyong,LIU Hongtong,SUN Wanmin.Comparison between the numerical simulation and test result for two-phase flow in the internal cavity of cavitating Venturi［J］.Missiles and Space Vehicles,2014(1):75-81.(in Chinese)
[12]	赵东方,朱佳凯,徐璐,等.文氏管中低温流体汽蚀过程可视化实验研究［J］.低温工程,2015(6):56-61.ZHAO Dongfang,ZHU Jiakai,XU Lu,et al.Visualization experiment of cavitating flow of cryogenic fluid in Venturi tube［J］.Cryogenics,2015(6):56-61.(in Chinese)
[13]	赵东方.液氮文氏管空化动态特性可视化实验研究［D］.杭州:浙江大学,2016. ZHAO Dongfang.Experimental observation on dynamic characteristic of liquid nitrogen cavitaion in Venturi tube［D］.Hangzhou:Zhejiang University,2016.(in Chinese)
[14]	BAZAROV V,LEE E,LINEBERRY D,et al.Pulsator designs for liquid rocket injector research［R］.AIAA-2007-5156,2007.
[15]	BALASUBRAMANYAM M S,CHEN C,BAZAROV V.Numerical studies on frequency response to mass flow rate variations in a hydromechanical pulsator［R］.AIAA-2009-4956,2009.
[16]	KHIL T,KIM S,CHO S,et al.Quantifying the variation of the mass flow rate generated in a simplex swirl injector by pressure fluctuation［R］.AIAA-2008-4849,2008.
[17]	FU Qingfei,YANG Lijun,WANG Xiangdong.Theoretical and experimental study of the dynamics of a liquid swirl injector［J］.Journal of Propulsion and Power,2010,26(1):94-101.