气喷嘴和声腔对燃烧室声学特性的影响
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摘要
为了掌握气喷嘴和声腔对燃烧室声学特性的影响规律以及解释声学实验中出现的切向频率分化现象的内在机理,采用声学有限元方法(FEM)并在单喷嘴声学模拟实验验证的基础上,从固有频率和声压分布角度分析了气喷嘴长度、声腔长度和节流嘴直径对燃烧室声学特性的影响规律,利用声压分布成功地解释了实验中出现的频率分化现象。结果表明:当燃烧室某阶切向振型频率与喷嘴1阶纵向振型频率相等时,喷嘴由于共振将切向振型声压幅值极值点附近的能量转移到喷嘴中,改变了燃烧室原切向振型的声压分布,因此在声学实验中产生切向频率分化现象;气喷嘴长度与节流嘴直径之间存在着耦合关系,在液氧煤油补燃发动机喷嘴设计阶段可进行组合参数匹配优化。
In order to obtain the influence of gas-liquid nozzle and acoustic resonators on the acoustic characteristics of combustion chamber and explain the mechanism of tangential frequency differentiation in acoustic experiments,a model combustion chamber with cylindrical tubes was investigated by acoustic finite element method(FEM).The analysis results were verified by the experiment of a single injector chamber.On this basis,the influence rules of gas nozzle,orifice and resonators on acoustic frequency were established in terms of the frequency and sound pressure distribution.The phenomenon of frequency differentiation was explained by the sound pressure distribution results.Results showed that the energy of tangential mode transferred into the gas nozzle and changed the original mode of combustion chamber,when the frequency of first order longitudinal mode of gas nozzle or resonator was equal to that of the tangential mode of combustor,and the phenomenon of frequency differentiation in tangential modes emerged in acoustic experiments.The coupling relationship between gas nozzle length and diameter of orifice was discovered,enabling to make combinatorial parameter optimization during rocket engine design.
In order to obtain the influence of gas-liquid nozzle and acoustic resonators on the acoustic characteristics of combustion chamber and explain the mechanism of tangential frequency differentiation in acoustic experiments,a model combustion chamber with cylindrical tubes was investigated by acoustic finite element method(FEM).The analysis results were verified by the experiment of a single injector chamber.On this basis,the influence rules of gas nozzle,orifice and resonators on acoustic frequency were established in terms of the frequency and sound pressure distribution.The phenomenon of frequency differentiation was explained by the sound pressure distribution results.Results showed that the energy of tangential mode transferred into the gas nozzle and changed the original mode of combustion chamber,when the frequency of first order longitudinal mode of gas nozzle or resonator was equal to that of the tangential mode of combustor,and the phenomenon of frequency differentiation in tangential modes emerged in acoustic experiments.The coupling relationship between gas nozzle length and diameter of orifice was discovered,enabling to make combinatorial parameter optimization during rocket engine design.
引文
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[19]张蒙正.高频燃烧不稳定性全尺寸头部燃烧室低压燃烧模拟实验的原理及实现[J].试验与技术管理,2008,25(10):38-41.ZHANG Mengzheng.Principle and realization ofhigh frequency combustion instabilities simulation tests of full size chamber[J].Experiment Technology and Management,2008,25(10):38-41.(in Chinese)
[20]张蒙正,张志涛,杨国华,等.燃烧室声学特性模拟实验及应用[J].试验与技术管理,2007,24(8):39-42.ZHANG Mengzheng,ZHANG Zhitao,YANG Guohua,et al.Simulation test and application of chamber acoustic characteristics[J].Experiment Technology and Management,2007,24(8):39-42.(in Chinese)
[2]赵文涛,周进,聂万胜,等,.液体火箭发动机燃烧不稳定性分析与热释放声放大机理[J].国防科技大学学报,1997,19(2):10-14.ZHAO Wentao,ZHOU Jin,NIE Wansheng,et al.Combustion instability of the liquid rocket engine and the mechanism of sound amplification by heat release[J].Journal of National University of Defense Technology,1997,19(2):10-14.(in Chinese)
[3]洪鑫,程惠尔.液体火箭发动机燃烧室波动过程数值分析[J].推进技术,1999,20(2):5-8.HONG Xin,CHENG Huier.Numerical analysis of acoustical wave motion in combustion chamber of liquid rocket engine[J].Journal of Propulsion Technology,1999,20(2):5-8.(in Chinese)
[4]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.
[5]李龙飞,陈建华,刘站国.大推力液氧煤油补燃发动机高频燃烧不稳定性的控制方法[J].导弹与航天运载技术,2011(3):16-19.LI Longfei,CHEN Jianhua,LIU Zhanguo.Control techniques of high frequency combustion instability for high thrust LOX/kerosene staged combustion cycle engine[J].Mission and Space Vehicles,2011(3):16-19.(in Chinese)
[6]李龙飞,陈建华,刘站国.增强大推力火箭发动机燃烧稳定性裕度的方法[J].火箭推进,2014,40(5):8-13.LI Longfei,CHEN Jianhua,LIU Zhanguo.Method to enhance combustion stability margin of high thrust rocket engine[J].Journal of Rocket Propulsion,2014,40(5):8-13.(in Chinese)
[7]POWELL E A,ZINN B T.The prediction of nonlinear three-dimensional combustion instability in liquid rockets with conventional nozzles[R].NASA CR-121279,1974.
[8]王枫,李龙飞,张贵田.喷嘴结构对液氧煤油火箭发动机高频燃烧不稳定性的影响[J].实验力学,2012,27(2):178-182.WANG Feng,LI Longfei,ZHANG Guitian.Influence of geometrical structure of coaxial injector on high-frequency combustion instability for staged combustion LOX/kerosene rocket engine[J].Journal of Experimental Mechanics,2012,27(2):178-182.(in Chinese)
[9]李龙飞,陈建华,周立新,等.补燃循环火箭发动机气液同轴式喷嘴声学特性研究[J].火箭推进,2004,30(6):5-10.LI Longfei,CHEN Jianhua,ZHOU Lixin,et al.Investigation on acoustic characteristics of gas-liquid coaxial injector of staged combustion rocket engine[J].Journal of Rocket Propulsion,2004,30(6):5-10.(in Chinese)
[10]薛帅杰,洪流,杨伟东.声学扰动对燃烧室声学特性的影响[J].推进技术,2016,37(2):201-208.XUE Shuaijie,HONG Liu,YANG Weidong.Effects of acoustic excitation on acoustic characteristics for combustor[J].Journal of Propulsion Technology,2016,37(2):201-208.(in Chinese)
[11]谭永华.中国重型运载火箭动力系统研究[J].火箭推进,2011,37(1):1-6.TAN Yonghua.Research on power system of heavy launch vehicle in China[J].Journal of Rocket Propulsion,2011,37(1):1-6.(in Chinese)
[12]SMITH R,XIA G,ANDERSON W A,et al.Computational simulations of the effect of chamber diameter on singleelement rocket combustor instability[R].AIAA 2008-5250,2008.
[13]王治军,常新龙,田干,等.液体火箭发动机推力室设计[M].北京:国防工业出版社,2014.
[14]胡伟,李平.双组元轨控发动机声腔技术方案及试验验证[J].火箭推进,2006,32(5):7-11.HU Wei,LI Ping.The acoustic cavity technique options and test validation of the bipropellant orbit control rocket engine[J].Journal of Rocket Propulsion,2006,32(5):7-11.(in Chinese)
[15]聂万胜,庄逢辰,张光中.液体火箭发动机中声腔抑制不稳定燃烧声学分析[J].应用声学,2001,20(4):35-39.NIE Wansheng,ZHUANG Fengchen,ZHANG Guangzhong.Acoustic analysis of resonators for combustion instability suppression in liquid rocket engines[J].Applied Acoustics,2001,20(4):35-39.(in Chinese)
[16]聂万胜,庄逢辰.声腔应用于液体火箭发动机不稳定燃烧抑制中的特性研究[J].国防科技大学学报,1998,20(2):12-16.NIE Wansheng,ZHUANG Fengchen.The study of characteristics of resonators used in liquid rocket engines combustion stabilities suppression[J].Journal of National University of Defense Technology,1998,20(2):12-16.(in Chinese)
[17]严宇,王延涛,李佳明,等.有声腔燃烧室的声学特性实验[J].航空动力学报,2016,31(7):1785-1791.YAN Yu,WANG Yantao,LI Jiaming,et al.Experiment on acoustic characteristic of combustion chamber with acoustic resonators[J].Journal of Aerospace Power,2016,31(7):1785-1791.(in Chinese)
[18]王枫,李龙飞,张贵田.液氧煤油补燃发动机喷注器高频燃烧不稳定性的试验研究[J].宇航学报,2012,33(2):260-264.WANG Feng,LI Longfei,ZHANG Guitian.Experimental study on high frequency combustion instability with coaxial injector of staged combustion LOX/kerosene rocket engine[J].Journal of Astronautics,2012,33(2):260-264.(in Chinese)
[19]张蒙正.高频燃烧不稳定性全尺寸头部燃烧室低压燃烧模拟实验的原理及实现[J].试验与技术管理,2008,25(10):38-41.ZHANG Mengzheng.Principle and realization ofhigh frequency combustion instabilities simulation tests of full size chamber[J].Experiment Technology and Management,2008,25(10):38-41.(in Chinese)
[20]张蒙正,张志涛,杨国华,等.燃烧室声学特性模拟实验及应用[J].试验与技术管理,2007,24(8):39-42.ZHANG Mengzheng,ZHANG Zhitao,YANG Guohua,et al.Simulation test and application of chamber acoustic characteristics[J].Experiment Technology and Management,2007,24(8):39-42.(in Chinese)