航天推进技术研究院主办
[1]李 程,杨永强,徐浩海,等.500 t级液氧煤油补燃发动机起动过程仿真研究[J].火箭推进,2014,40(06):1-6.
LI Cheng,YANG Yong-qiang,XU Hao-hai,et al.Numerical simulation of start-up process for 500 t thrust LOX/kerosene staged combustion cycle rocket engine[J].Journal of Rocket Propulsion,2014,40(06):1-6.
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LI Cheng,YANG Yong-qiang,XU Hao-hai,et al.Numerical simulation of start-up process for 500 t thrust LOX/kerosene staged combustion cycle rocket engine[J].Journal of Rocket Propulsion,2014,40(06):1-6.
500 t级液氧煤油补燃发动机起动过程仿真研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
40
期数:
2014年06期
页码:
1-6
栏目:
专论与综述
出版日期:
2014-12-29
- Title:
- Numerical simulation of start-up process for 500 t thrust LOX/kerosene staged combustion cycle rocket engine
- Keywords:
- LOX/kerosene rocket engine; dual-thrust chamber; staged combustion cycle; start-up; numerical simulation
- 分类号:
- V434-34
- 文献标志码:
- A
- 摘要:
- 500 t级液氧煤油补燃发动机是我国首台采用双推力室方案、自身分级起动方式的重型液体火箭发动机。结合重型发动机特点建立了描述发动机起动过程的数学模型，通过数值仿真分析了影响发动机起动特性的主要因素，确定了发动机的起动方案。研究结果表明：液氧主阀和发生器燃料阀打开时差应确保发生器点火在氧头腔充满后进行；流量调节器的转初级起始时间应早于推力室建压时间；燃料节流阀转大流量应在发动机起动受控段进行。
- Abstract:
- 500 t thrust LOX/kerosene staged combustion cycle engine is the first liquid propellant rocket engine with dual-thrust chamber system in China. The mathematical model of describing the start-up process of engine was developed based on the characteristics of the heavy-duty engine. The sensitive parameters affecting start-up characteristic of engine were analyzed by means of numerical simulation, so a reasonable start-up scheme of the engine was determined. The research results reveal that the gas generator (GG) should not ignite before the mixing head cavity of the GG has been filled with liquid oxygen, the ignition of the combustion chamber (CC) should lag behind the rise of the temperature of the GG, and the throttle valve should be released to the main passage after start-up of the engine is under control.
参考文献/References:
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[2]DURTESTE Stephane. A transient model of the VINCI cryogenic upper stage rocket engine, AIAA 2007-5531[R]. USA: AIAA, 2007.
[3]BELYAEV E N, CHVANOV V K, CHERVAKOV V V. The outflow of a two-phase gas-liquid mixture from the mixing head of a gas generator when starting a liquid- propellant rocket engine[J]. High Temperature, 2005, 43(3): 446-451.
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[5]张小平. 补燃循环发动机起动过程仿真研究[J]. 火箭推进, 2003, 29(3): 18-21.
[6]杨永强, 刘红军, 徐浩海, 等. 补燃循环发动机强迫起动研究[J]. 火箭推进, 2011, 37(2): 14-18.
[7]陈宏玉, 刘红军. 补燃循环发动机推力调节过程建模与仿真研究[J]. 火箭推进, 2014, 40(1): 18-24.
[8]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.
[9]徐浩海, 刘站国. 补燃循环发动机起动过程涡轮功率控制[J]. 火箭推进, 2006, 32(4): 10-14.
[10]张小平, 丁丰年. 富氧补燃循环发动机启动过程[J]. 推进技术, 2004, 25(1): 82-85.
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备注/Memo
收稿日期：2014-08-13；修回日期：2014-08-29 基金项目：中国航天科技集团公司支撑项目（2012JY02） 作者简介：李程（1987—），男，硕士研究生，研究领域为液体火箭发动机系统仿真
更新日期/Last Update:
1900-01-01