液体火箭发动机非稳态燃烧过程对其稳定性的影响
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摘要
基于模型分析了由非稳态燃烧过程引起的不稳定热释放这一激励源项对稳定性的影响,探讨了相应的激励机理。采用小扰动分析方法,将一维层流预混火焰燃烧模型方程分解为稳态和非稳态两类控制方程,建立了线性增长率中燃烧释热项的计算方法,获得了温度及释热量的空间分布,探讨了初始温度及比热比变化对其影响规律。结果表明:采用高能推进剂的燃烧系统具有相对较低的稳定性,而对于同一种推进剂,比热比的增加会导致稳定性对频率的敏感程度增加,且具有明显的频率选择性。
Based on theoretical model,the effect of unstable combustion heat release induced by unsteady combustion process,the most important source term of exciting on combustion stability and its triggering mechanism were analyzed and discussed.Then one dimensional premixed laminar flame model was separated into stable and unstable forms by the small perturbation analysis way,and the calculating method for heat release term in linear growth rate was built.With the distributions of temperature and heat release in space,the effects of varying initial temperature and specific heat ratio on this term were investigated.It is indicated that the combustion system using energetic propellants with low initial temperature always behaves more stably.For the same kind of propellant,increasing the specific ratio will make stability more sensitive to frequency,which will be more clearly for some frequency range.
Based on theoretical model,the effect of unstable combustion heat release induced by unsteady combustion process,the most important source term of exciting on combustion stability and its triggering mechanism were analyzed and discussed.Then one dimensional premixed laminar flame model was separated into stable and unstable forms by the small perturbation analysis way,and the calculating method for heat release term in linear growth rate was built.With the distributions of temperature and heat release in space,the effects of varying initial temperature and specific heat ratio on this term were investigated.It is indicated that the combustion system using energetic propellants with low initial temperature always behaves more stably.For the same kind of propellant,increasing the specific ratio will make stability more sensitive to frequency,which will be more clearly for some frequency range.
引文
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[20]杨甫江,郭志辉,曾宇晖.贫燃预混旋流火焰热声特性研究[J].航空动力学报,2014,29(12):2854-2861.YANG Fujiang,GUO Zhihui,ZENG Yuhui.Study on thermoacoustic characteristic of lean premixed swirling flames[J].Journal of Aerospace Power,2014,29(12):2854-2861.(in Chinese)
[21]谢法,张珊珊,蒋洪德.入口流动参数脉动对燃气轮机燃烧室燃烧不稳定的影响[J].航空动力学报,2015,30(7):1561-1565.XIE Fa,ZHANG Shanshan,JIANG Hongde.Effects of inlet flow parameters oscillation on combustion instability of gas turbine combustor[J].Journal of Aerospace Power,2015,30(7):1561-1565.(in Chinese)
[2]李磊,孙晓峰.一种基于谱方法的三维热声不稳定模型[J].航空动力学报,2011,26(5):1017-1024.LI Lei,SUN Xiaofeng.Three dimensional thermo-acoustic instability model based on spectral method[J].Journal of Aerospace Power,2011,26(5):1017-1024.(in Chinese)
[3]付宇,郭志辉,杨甫江,等.基于经验模态分解的燃烧不稳定性分析[J].航空动力学报,2016,31(3):623-630.FU Yu,GUO Zhihui,YANG Fujiang,et al.Analysis on combustion instability based on empirical mode decomposition[J].Journal of Aerospace Power,2016,31(3):623-630.(in Chinese)
[4]张澄宇,李磊,孙晓峰.加力燃烧室热声振荡纵向传播特性及控制[J].航空动力学报,2010,25(2):278-283.ZHANG Chengyu,LI Lei,SUN Xiaofeng.Thermaoacoustic oscillating calculation of longitudinal equivalence frequency and stability in aero engine afterburner[J].Journal of Aerospace Power,2010,25(2):278-283.(in Chinese)
[5]CROCCO L,CHENG S I.Theory of combustion instability in liquid propellant rocket motors[M].London:ButterWorths Ltd,1956.
[6]MUSS J A,NGUYEN T V,JOHNSON C W.User's manual for rocket combustor interactive design(ROCCID)and analysis computer program:VolumeⅠuser manual[R].NASA-CR-187109,1990.
[7]MUSS J A,NGUYEN T V,JOHNSON C W.User's manual for rocket combustor interactive design(ROCCID)and analysis computer program:VolumeⅡappendixes A-K[R].NASA-CR-187110,1990.
[8]CULICK F E C.Nonlinear behavior of acoustic waves in combustion chambers[R].NASA-CR-149367,1983.
[9]CULICK F E C.Nonlinear growth and limiting amplitude of acoustic oscillations in combustion chambers[J].Journal of Combustion Science and Technology,1971,3(1):1-16.
[10]LIEUWEN T.Online combustor stability margin assessment using dynamic pressure data[J].Journal of Engineering for Gas Turbines and Power,2005,127(4):478-482.
[11]KIRCHHOFF G.Vorlesungen uber mathematische physik:mechanik[M].Leibzig,Germany:[s.n.],1883.
[12]HART R W,MCCLURE F T.Theory of acoustic instability in solid propellant rocket combustion[J].Symposium(Internation)on Combustion,1965,10(1):1047-1065.
[13]MORFEY C L.Acoustic energy in non-uniform flows[J].Journal of Sound and Vibrations,1971,14(4):159-169.
[14]MYERS M K.Transport of energy by disturbances in arbitrary steady flows[J].Journal of Fluid Mechanics,1991,226(3):383-400.
[15]FLANDRO G A,JACOB E J.Finite amplitude waves in liquid rocket combustion chambers[R].AIAA-2008-1003,2008.
[16]汪广旭,付秀文,石晓波,等.燃烧室非线性压力振荡及其产生机理研究[J].火箭推进,2016,429(2):29-34.WANG Guangxu,FU Xiuwen,SHI Xiaobo,et al.Study on nonlinear pressure oscillation and its mechanism in combustion chamber[J].Journal of Rocket Propulsion,2016,429(2):29-34.(in Chinese)
[17]FLANDRO G A,FISCHBACH S R.Effects of wave incidence on combustion instability driving mechanisms[R].AIAA-2007-5807,2007.
[18]TIEN J S.Oscillatory burning of solid propellant including gas phase time lag combustion[J].Journal of Science and Technology,1972,20(5):47-54.
[19]STEPHEN R T.An introduction to combustion concepts and applications[M].2nd ed.Boston:McGraw-Hill Education,2015.
[20]杨甫江,郭志辉,曾宇晖.贫燃预混旋流火焰热声特性研究[J].航空动力学报,2014,29(12):2854-2861.YANG Fujiang,GUO Zhihui,ZENG Yuhui.Study on thermoacoustic characteristic of lean premixed swirling flames[J].Journal of Aerospace Power,2014,29(12):2854-2861.(in Chinese)
[21]谢法,张珊珊,蒋洪德.入口流动参数脉动对燃气轮机燃烧室燃烧不稳定的影响[J].航空动力学报,2015,30(7):1561-1565.XIE Fa,ZHANG Shanshan,JIANG Hongde.Effects of inlet flow parameters oscillation on combustion instability of gas turbine combustor[J].Journal of Aerospace Power,2015,30(7):1561-1565.(in Chinese)