富氧燃气发生器动态特性分析

刘上; 刘红军; 陈宏玉

富氧燃气发生器动态特性分析

航天推进技术研究院西安航天动力研究所,西安 710100

计量
- 文章访问数: 1551
- HTML浏览量: 134
- PDF量: 1296
- 被引次数: 0
出版历程
- 收稿日期: 2012-01-17
- 刊出日期: 2013-01-28

Analysis of oxidizer-rich preburner dynamic characteristics

Xi'an Aerospace Propulsion Institute, Academy of Aerospace Propulsion Technology,Xi'an 710100,China

摘要

摘要: 建立了描述富氧燃气发生器动态特性的线性化频域模型,以分析推进剂流量扰动对发生器室压的动态作用.通过与文献中试验数据对比,验证了模型和计算方法的合理性.在低频范围内采用考虑熵波的绝热流动模型,比较煤油和液氧流量扰动引起发生器压力振荡的频率响应,结果显示煤油流量扰动更易引起较大的熵波幅值.分析了燃烧温度与混合比关系的无量纲斜率、涡轮压比系数和燃烧时滞对发生器频率特性的影响规律.在很宽的频率范围内分析发生器的动态特性,需采用考虑声学效应的分布参数模型,既能在低频范围内涵盖绝热流动模型,又能反映气路的纵向声学振荡.
- 富氧燃气发生器 /
- 频率特性 /
- 流量扰动 /
- 熵波 /
- 声学效应
Abstract: The linearized frequency models for oxidizer-rich preburner were developed to analyze the preburner pressure dynamic response under the propellant flow rate disturbance.The validity of the models and calculation method were confirmed by comparing the results with the test data from references.Using the adiabatic flow model which considered entropy wave during the low frequency range,the frequency responses of preburner pressure under kerosene and liquid oxygen flow rate disturbance were compared respectively,and the result shows that kerosene flow rate disturbance causes higher entropy wave amplitude.The influence rules of the dimensionless slope of combustion temperature and mixture rate as well as pressure ratio of the turbo and combustion time lag on the preburner frequency characteristics were also analyzed.When the concerned frequency range is wide,the distributed parameter model considering the acoustic effect should be used,because the model not only contains the adiabatic flow model during the low frequency range,but also can reflect the longitudinal acoustic oscillation.
- oxidizer-rich preburner /
- frequency characteristics /
- flow rate disturbance /
- entropy wave /
- acoustics effect

HTML

参考文献(15)

[1]	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.
[2]	格列克曼.液体火箭发动机自动调节[M].顾明初,郁明桂,邱明煜,译.北京:宇航出版社,1995.
[3]	Holster J L.Analytical model for liquid rocket propellant feedline dynamics[J].Journal of Spacecraft,1973,11(3):180-187.
[4]	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 Zhengpeng.Frequency characteristic for liquid propellant staged combustion cycle rocket engine[J].Journal of Propulsion Technology,2000,21(1):5-7.(in Chinese)
[5]	陈琪锋,刘昆.基于分布参数线性化模型的分级燃烧循环液体火箭发动机频率特性计算[J].航空动力学报,2001,16(1):44-48. CHEN Qifeng,LIU Kun.Frequency characteristics computation of liquid rocket engine based on distributed parameter models[J].Journal of Aerospace Power,2001,16(1):44-48.(in Chinese)
[6]	李斌,杜大华.液氧/煤油补燃发动机低频频率特性研究[J].航空动力学报,2009,24(5):1187-1191. LI Bin,DU Dahua.Research on the low frequency characteristics of LOX/kerosene staged combustion cycle engine[J].Journal of Aerospace Power,2009,24(5):1187-1191.(in Chinese)
[7]	Osherov A,Natan B,Gany A.Analytical modeling of the gas generator frequency response in hybrid rocket boosters[J].Acta Astronautica,1997,39(8):589-598.
[8]	刘昆,张育林.液体火箭发动机燃烧室的一种分区模型[J].航空动力学报,2002,17(1):135-139. LIU Kun,ZHANG Yulin.An innovative partition model of liquid rocket engine combustion chambers[J].Journal of Aerospace Power,2002,17(1):135-139.(in Chinese)
[9]	吴宝元,葛李虎,谭永华,等.富氧预燃室高压缩尺试验研究[J].推进技术,2003,24(2):104-108. WU Baoyuan,GE Lihu,TAN Yonghua,et al.Experimental investigation of oxidizer-rich subscale preburner[J].Journal of Propulsion Technology,2003,24(2):104-108.(in Chinese)
[10]	Kim S H,Han Y M,Seo S,et al.Effects of LOX post recess on the combustion characteristics for bi-swirl coaxial injector .AIAA 2005-4445,2005.
[11]	Natanzon M S,Culick F.Combustion instability [M].Reston,US:AIAA,Inc.,1996.
[12]	曹泰岳.火箭发动机动力学[M].长沙:国防科技大学出版社,2004.
[13]	Culick F E C.Unsteady motions in combustion chambers for propulsion systems .AG-AVT-039,2006.
[14]	Duran I,Moreau S.Analytical and numerical study of the entropy wave generator experiment on indirect combustion noise .AIAA 2011-2829,2011.
[15]	Goh C S,Morgans A S.The effect of entropy wave dissipation and dispersion on thermoacoustic instability in a model combustor .AIAA 2011-2914,2011.