航天推进技术研究院主办
HE Chuang,XING Lixiang,XU Haohai.Influence of gas drive pre-pressurized turbo-pump on frequency characteristics of liquid oxygen system in rocket engine[J].Journal of Rocket Propulsion,2021,47(01):76-82.
气驱预压涡轮泵对发动机液氧路频率特性影响
- Title:
- Influence of gas drive pre-pressurized turbo-pump on frequency characteristics of liquid oxygen system in rocket engine
- 文章编号:
- 1672-9374(2021)01-0076-07
- 关键词:
- 液氧/煤油补燃循环发动机; 预压涡轮泵; 频率特性; POGO; 传递矩阵
- Keywords:
- LOX/kerosene staged combustion cycle rocket engine; pre-pressurized turbo-pump; frequency characteristics; POGO; transmission matrix
- 分类号:
- V434.21
- 文献标志码:
- A
- 摘要:
- 液氧/煤油补燃循环发动机液氧路频率特性对于火箭POGO振动和发动机动力学特性具有重要的意义。以某型液氧/煤油补燃循环发动机氧路流体系统为研究对象,重点考虑气涡轮和泵动态特性的影响建立了系统线性化小偏差频域模型。应用复系数状态空间矩阵法计算了气涡轮压比、氧预压泵动态增益、燃气掺混段特性对系统频率特性的影响。研究结果表明:预压涡轮低压比状态下,系统响应幅值变大,预压涡轮压比对系统频率影响较小; 预压泵动态增益越大,系统频率越低,幅值越大; 燃气掺混段长度越大,系统频率越低,幅值越小。
- Abstract:
- The frequency characteristics of liquid oxygen system in the LOX/kerosene staged combustion cycle engine are of great significance to the vibration of rocket POGO and the engine dynamics. Based on the liquid oxygen system in a LOX/kerosene staged combustion cycle engine,a linearized small deviation frequency domain model was established by emphatically considering the influence of gas turbine and pump dynamic characteristics.The influence of the gas turbine pressure ratio, the dynamic gain of the oxygen pre-pressurized pump and the gas mixing section on the system frequency characteristics were calculated by using the complex coefficient state space matrix. The results show that under the low-pressure ratio condition of the preloaded turbine, the system response amplitude becomes larger, which has less influence on the system frequency.The higher the dynamic gain of the pressurized pump, the lower the system frequency and the larger the amplitude.The longer the gas mixing section, the lower the system frequency and the smaller the amplitude.
参考文献/References:
[1] HOLSTER J.Liquid rocket propellant feedline dynamics[C]//9th Propulsion Conference.Las Vegas,NV,Reston,Virigina: AIAA,1973.
[2] ORDONNEAU G.A new numerical method for pogo analysis[C]//30th Joint Propulsion Conference and Exhibit.Indianapolis,Reston,Virigina: AIAA,1994.
[3] 孙冰,魏鑫,池元成,等.液体运载火箭推进系统固有频率的通用化计算研究[J].导弹与航天运载技术,2009(1):38-40.
[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(2):12-18.
LIU S,LIU H J,WANG H Y.Frequency characteristic analysis for LOX feed system of oxidizer—rich preburner[J].Journal of Rocket Propulsion,2013,39(2):12-18.
[5] 陈琪锋, 刘昆, 张育林. 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.
[6] 荣克林,张建华,马道远,等.CZ—2F火箭POGO问题研究[C]//2007全国结构动力学学术研讨会论文集.南昌: 全国结构动力学学会,2007.
[7] 盛迪南.流体系统的动特性分析(矩阵法)[Z].1985.
[8] 秦澍纪.输送系统的动特性分析[Z].1985.
[9] 吴天城.推进剂输送管路系统的动态试验[Z].1985.
[10] 钱大馨.输送系统动态试验研究(水试)[Z].1985.
[11] 廖少英. POGO蓄压器变频降幅特性分析[J]. 上海航天,2002,19(1):32-35.
[12] 任辉,任革学,荣克林,等.液体火箭Pogo振动蓄压器非线性仿真研究[J].强度与环境,2006,33(3):1-6.
[13] 万屹仑,付欣毓,张黎辉,等.注气式蓄压器系统工作特性仿真分析[J]. 火箭推进,2018,44(3):37-42.
WAN Y L,FU X Y,ZHANG L H,et al.Simulation analysis on operating characteristics of gas-filled accumulator system[J]. Journal of Rocket Propulsion, 2018, 44(3):37-42.
[14] 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.
[15] 邢理想.闭式循环液体火箭发动机氧路低频动特性分析[D].西安:西安航天动力研究所,2009.
[16] 邢理想,杜大华,李斌.液氧/煤油补燃火箭发动机氧路低频动特性分析[J].火箭推进,2009,35(5):24-28.
XING L X,DU D H,LI B.Low frequency characteristics analysis of LOX / kerosene staged combustion cycle rocket engine[J].Journal of Rocket Propulsion,2009,35(5):24-28.
[17] 张淼,李斌,邢理想.基于燃气射流冷凝的氧路系统频率特性研究[J].航空学报,2020,41(2):142-151.
[18] 杜大华,张继桐.液压流体系统的频域特性分析[J].机床与液压,2006,34(10):86-88.
[19] BRENNEN C,ACOSTA A J.The dynamic transfer function for a cavitating inducer[J].Journal of Fluids Engineering,1976,98(2):182-191.
[20] BRENNEN C.Bubbly flow model for the dynamic characteristics of cavitating pumps[J].Journal of Fluid Mechanics,1978,89(2):223-240.
[21] 李斌,杜大华,张贵田,等.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.
[22] 格列克曼Б Ф.液体火箭发动机自动调节[M].顾明初,译.北京:宇航出版社,1995.
[23] 徐浩海,刘站国.液氧/煤油补燃发动机系统稳定性分析[J].火箭推进,2005,31(2):1-6.
XU H H,LIU Z G.System stability analysis of a LOX/kerosene staged combustion cycle engine[J].Journal of Rocket Propulsion,2005,31(2):1-6.
[24] 张黎辉,张振鹏.补燃循环液体火箭发动机系统的响应特性研究[J].航空动力学报,1999,14(4):425-428.
[25] 契万诺夫.液体火箭发动机工作过程的数学模拟[M].西安:西安航天动力研究所,2001.
相似文献/References:
[1]杜大华,黄金平,邢理想,等.液体火箭发动机泵动态特性水力试验研究[J].火箭推进,2013,39(03):50.
DU Da-hua,HUANG Jin-ping,XING Li-xiang,et al.Hydraulic test research on dynamic characteristics of oxygen pump of liquid rocket engine[J].Journal of Rocket Propulsion,2013,39(01):50.
[2]徐浩海,刘站国.液氧/煤油补燃发动机系统稳定性分析[J].火箭推进,2005,31(02):1.
Xu Haohai,Liu Zhanguo.System stability analysis of a LOX/kerosene staged combustion cycle engine[J].Journal of Rocket Propulsion,2005,31(01):1.
备注/Memo
收稿日期:2020-05-31
基金项目:国家自然科学基金(51775412)
作者简介:何闯(1996—),男,硕士,研究领域为液体火箭发动机系统仿真。