隔板对燃烧室声学特性的影响

李丹琳; 田原; 孙纪国

隔板对燃烧室声学特性的影响

中国航天科技集团公司北京航天动力研究所主推进发动机设计部, 北京 100076

计量
- 文章访问数: 1734
- HTML浏览量: 167
- PDF量: 469
- 被引次数: 0
出版历程
- 收稿日期: 2011-04-13
- 修回日期: 2011-10-08
- 刊出日期: 2012-03-28

Effects of baffle on combustion acoustic characteristics of liquid rocket engine

Main Propulsion Division, Beijing Aerospace Propulsion Institute, China Aerospace Science and Technology Corporation, Beijing 100076, China

摘要

摘要: 为了研究液体火箭发动机燃烧室出现的横向一阶切向燃烧不稳定,通过冷态声学试验和理论算例的计算,研究了不同参数的隔板装置对一阶切向声学频率及阻尼特性的影响,结果表明:增加轴向隔板长度和径向隔板数目均会降低一阶切向声学频率,同时增强声阻尼效果;喷嘴式隔板产生的声阻尼效果,比典型直板形状的隔板要好得多,隔板喷嘴最佳间隙在0.1~0.4mm,采用最佳隔板喷嘴间隙能够在较短的轴向隔板长度上得到较高的阻尼能力,从而改善冷却问题.
- 声学频率 /
- 阻尼特性 /
- 隔板 /
- 声学试验 /
- 燃烧不稳定性
Abstract: Cold acoustic tests have been performed to elucidate the effect of baffle on the damping characteristics of the first-tangential acoustic mode in a liquid rocket engine.Different kinds of baffle parameters were researched by acoustic tests.The results agree well with the theory typical example and show that when increasing the axial baffle length and the radial baffle number,the acoustic frequency of the first-tangential acoustic mode decreases and the acoustic damping capacity increases.Injector-forming baffles have some advantages over the typical straight baffles in acoustic damping capability;an optimal acoustic damping capacitance has been achieved in 0.1~0.4mm;axial baffle length can be reduced by using the optimal baffle gap,providing a possible solution of thermal cooling problems.
- acoustic frequency /
- damping characteristics /
- baffle /
- acoustic test /
- combustion instability

HTML

参考文献(12)

[1]	哈杰,里尔登.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.
[2]	Kim H J,Lee K J,Choi H S,et al.An experimental study on acoustic damping enhancement by the gap of baffled injectors.AIAA 2005-4446,2005.
[3]	Kim S K,Kim H J,Woo S S.Acoustic stability analysis of liquid propellant rocket combustion chambers[J].AIAA 2004-4142,2004.
[4]	Walter E,Indranil D R.The effect of a baffle on acoustic radation directivity.AIAA 1998-2250,1998.
[5]	郭志辉,王帅,李磊,等.贫燃预混旋流火焰燃烧不稳定性的实验[J].航空动力学报,2009,24(12):2637-2642. GUO Zhihui,WANG Shuai,LI Lei,et al.Experimental study on combustion instability of lean premixed swirl flame[J].Journal of Aerospace Power,2009,24(12):2637-2642.(in Chinese)
[6]	聂万胜,庄逢辰.喷雾特性对液体火箭发动机燃烧稳定性的影响[J].推进技术,2000,21(3):56-59. NIE Wansheng,ZHUANG Fengchen.Effect of spray characteristic on the liquid rocket combustion stability[J].Journal of Propulsion Technology,2000,21(3):56-59.(in Chinese)
[7]	周进,胡小平,黄玉辉,等.液体火箭发动机气液同轴式喷嘴声学特性的试验研究[J].推进技术,1996,17(4):37-41. ZHOU Jin,HU Xiaoping,HUANG Yuhui,et al.An experimental study on acoustic characteristics of gas-liquid coaxial injector of liquid rocket engine[J].Journal of Propulsion Technology,1996,17(4):37-41.(in Chinese)
[8]	赵震,郭志辉,黄勇.模型燃烧室低频不稳定燃烧的初步探讨[J].航空动力学报,2003,18(6):803-807. ZHAO Zhen,GUO Zhihui,HUANG Yong.A preliminary investigation of low-frequency combustion instability in a modal combustor[J].Journal of Aerospace Power,2003,18(6):803-807.(in Chinese)
[9]	黄玉辉,周进,胡小平,等.气液同轴式喷嘴自激振荡的试验现象和声学模型及对火箭发动机不稳定燃烧的影响[J].声学学报,1998,23(5):459-465. HUANG Yuhui,ZHOU Jin,HU Xiaoping,et al.Experiment and acoustic model for the self-oscillation of coaxial swirl injector and its influence to combustion of liguid rocket engine[J].Acta Acoustics,1998,23(5):459-465.(in Chinese)
[10]	刘卫东,王振国,周进,等.液体火箭发动机径向不稳定燃烧数值分析模型[J].推进技术,1997,18(6):5-9. LIU Weidong,WANG Zhenguo,ZHOU Jin,et al.Numerical analysis model of radul combustion instability in liquid propellant rocke engine[J].Journal of Propulsion Technology,1997,18(6):5-9.(in Chinese)
[11]	张蒙正,张志涛,郁锋,等.液体火箭发动机单喷注器燃烧室声学特性模拟实验原理及实现[J].声学技术,2007,26(2):268-272. ZHANG Mengzheng,ZHANG Zhitao,YU Feng,et al.Principle and design of simulation test for acoustic characteristics of liquid rocket engine chamber with a single injector[J].Technical Acoustics,2007,26(2):268-272.(in Chinese)
[12]	樊晓波,王敏庆,盛美萍.隔板应用于发动机燃烧室不稳定燃烧抑制中的二维数值计算分析[J].机械科学与技术,2007,26(9):1118-1121. FAN Xiaobo,WANG Minqing,SHENG Meiping.Two-dimensional numerical analysis of applying baffles to restraining the combustion instability in a marine engine[J].Mechanical Science and Technology for Aerospace Engineering,2007,26(9):1118-1121.(in Chinese)