富氧预燃室试验启动过程研究

汪小卫; 金平; 俞南嘉; 蔡国飙

富氧预燃室试验启动过程研究

北京航空航天大学宇航学院, 北京 100083

基金项目: 国家863基金资助项目(2005AA22040)

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出版历程
- 收稿日期: 2006-11-28
- 修回日期: 2007-03-20
- 刊出日期: 2007-12-28

Start-up experimental research on oxidizer-rich preburner

School of Astronautics, Beijing University of Aeronautics and Astrnautics, Beijing 100083, China

摘要

摘要: 为开展全流量补燃循环发动机富氧预燃室试验研究,对其试验启动过程进行了设计,阐述了试验条件下的富氧预燃室启动过程的特点,选择了非传统的富燃点火启动模式.对该预燃室启动过程动态特性进行仿真研究和热试车试验,计算与试验结果吻合良好,多次试验结果表明在小流量富氧预燃室上应用富燃点火启动点火可靠性高、试验稳定可靠,无任何烧蚀现象.启动方案的研究和仿真为预燃室的试验打下基础,并为今后该类型发动机动态过程研究提供参考.
- 航空、航天推进系统 /
- 富氧预燃室 /
- 启动过程 /
- 动态数学模型 /
- 仿真
Abstract: In order to develop oxidizer-rich preburner technology of full-flow staged combustion cycle engine(FFSC),this paper planned the start-up experiment for an H₂/O₂ ox-rich preburner,and described their characteristics under test conditions.And,a fuel-rich ignition start-up mode was selected.The simulation study and test run of preburner show that,the calculated results match the test results,demonstrating that fuel-rich ignition for small flux ox-rich preburners is reliable and steady without any burning.This research and simulation lay a firm basis for future test and study of similar preburners.
- aerospace propulsion system /
- ox-rich preburner /
- start-up /
- dynamic model /
- simulation

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参考文献(10)

[1]	Davis J A,Campbell R L.Advantages of a full-flow staged combustion cycle engine system[R].AIAA97-3318,Tokyo Japan,1997.
[2]	Jones J M,Nichols J T,Boyce W D,et al.Integrated powerhead demonstration:full flow cycle development[R].Air Force Research Lab 4 DracoEdwards AFB,Aerojet PO Box 13222 Sacramento,William F.Sack,Boeing Defence & Space Group 6633 Canoga Ave Canoga Park,AFRL-PR-ED-TP-1998-003.
[3]	Farhangi S,Hunt K,Tuegel L,et al,Oxidizer-rich preburner for advanced rocket engine application[R].Rockwell International,Rocketdyne Division,Canoga Park,California 91303,AIAA 94-3260.
[4]	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.ZHANG Xiaoping,DING Fengnian.Starting process of oxidizer-rich staged combustion rocket engine[J].Journal of Propulsion Technology,2004,25(1):82-85.
[5]	刘红军,张恩昭,董锡鉴.补燃循环发动机启动特性仿真研究[J].推进技术,1999,20(3):5-9.LIU Hongjun,ZHANG Enzhao,DONG Xijian.Start-up simulation of a liquid propellant staged combustion rocket engine[J],Journal of Propulsion Technology,1999,20(3):5-9.
[6]	邢继发.世界导弹与航天发动机大全[M].北京:军事科学出版社,1999:115-122,152-158,162-163.
[7]	张育林,刘昆,程谋森.液体火箭发动机动力学理论与应用[M].北京:科学出版社,2005.
[8]	黄敏超,王新建,王楠.补燃循环液体火箭发动机启动过程的模块化仿真[J].推进技术,2001,22(2):101-103.HUANG Minchao,WANG Xinjian,WANG Nan.Modular simulation on the start process for staged combustion cycle liquid propellant rocket engine[J].Journal of Propulsion Technology,2001,22(2):101-103.
[9]	戴佳,黄敏超,沈赤兵,等.双组元液体推进系统启动过程时序分析[J].火箭推进,2006,32(2):16-22.DAI jia,HUANG Minchao,SHEN Chibing,et al,Startup process timing analysis of liquid bipropellant pressure-fed propulsion system[J].Journal of Rocket Propulsion[J],2006,32(2):16-22.
[10]	陆启韶.常微分方程的定性方法和分叉[M].北京:北京航空航天大学出版社,1989.