航天推进技术研究院主办
[1]孙永奇,李宝荣,杨建文.上面级发动机推力室喷管延伸段气膜冷却研究[J].火箭推进,2013,39(04):13-18.
SUN Yong-qi,LI Bao-rong,YANG Jian-wen.Research on gas film cooling at nozzle extension section of thrust chamber for upper stage engine[J].Journal of Rocket Propulsion,2013,39(04):13-18.
点击复制
SUN Yong-qi,LI Bao-rong,YANG Jian-wen.Research on gas film cooling at nozzle extension section of thrust chamber for upper stage engine[J].Journal of Rocket Propulsion,2013,39(04):13-18.
上面级发动机推力室喷管延伸段气膜冷却研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
39
期数:
2013年04期
页码:
13-18
栏目:
研究与设计
出版日期:
2013-08-30
- Title:
- Research on gas film cooling at nozzle extension section of thrust chamber for upper stage engine
- 文章编号:
- 1672-9374(2013)04-0013-06
- Keywords:
- liquid rocket engine; thrust chamber; nozzle extension section; gas
- 分类号:
- V434-34
- 文献标志码:
- A
- 摘要:
- 上面级发动机采用四氧化二氮/偏二甲肼为推进剂，将涡轮排气引入推力室喷管气膜冷却喷管延伸段。仿真计算和热试车表明：推力室主燃气与涡轮排气压力在同一截面处相等，涡轮排气沿喷管延伸段壁面流动形成紧贴喷管壁面的气膜，对主燃气无扰动，对喷管延伸段起到冷却保护作用。推力室喷管延伸段传热计算值和热试车延伸段温度测量值吻合，排气集合器内压力基本均匀，满足工程应用需要。
- Abstract:
- Nitrogen tetroxide (N2O4)/unsymmetrical dimethylhydrazine (UDMH) is adopted as propellant of the upper stage engine. The turbine exhaust gas is imported into the nozzle extension section of thrust chamber to form low temperature gas film. The simulation calculation and the ground hot-firing test were performed to validate the cooling method. The results show that the pressure of the main gas from the thrust chamber is equal with that of the turbine exhaust gas, and the gas film formed by the turbine exhaust gas which flows along the nozzle extension section and appresses with the inner wall of the nozzle has no perturbation to the main gas, and protects the nozzle extension section from high temperature. The value of heat-transfer calculation of the nozzle extension section of thrust chamber coincides with that of temperature detection during the ground hot-firing test. The pressure in the exhaust gas collector is basically uniform. It satisfied the requirements of a project.
相似文献/References:
[1]郑 伟,李护林,陈新红.激光快速成形技术在液体动力领域的应用前景[J].火箭推进,2015,41(06):1.
ZHENG Wei,LI Hulin,CHEN Xinhong.Application prospect of laser rapid prototyping
technology in the field of liquid power[J].Journal of Rocket Propulsion,2015,41(04):1.
[2]郭 敬,宋晶晶,孔凡超.发动机推进剂增压输送系统建模仿真技术综述[J].火箭推进,2015,41(05):1.
GUO Jing,SONG Jingjing,KONG Fanchao.Overview of modeling and simulation technology
for propellant pressurization feed system
of liquid rocket engine[J].Journal of Rocket Propulsion,2015,41(04):1.
[3]于 康,谢荣华,陈晓江.表面张力贮箱电子束焊接工艺研究[J].火箭推进,2015,41(05):89.
YU Kang,XIE Ronghua,CHEN Xiaojiang.Study on electron beam welding process
for surface tension tank[J].Journal of Rocket Propulsion,2015,41(04):89.
[4]刘中华,苏 晨,汪军安,等.气路膜片设计研究[J].火箭推进,2015,41(05):95.
LIU Zhonghua,SU Chen,WANG Junan,et al.Design and study of pneumatic diaphragm in gas circuit[J].Journal of Rocket Propulsion,2015,41(04):95.
[5]薛 薇,蔡震宇,曹红娟,等.基于可视化平台的液氢/液氧火箭发动机核心部件质量计算[J].火箭推进,2015,41(04):61.
XUE wei,CAI Zhenyu,CAO Hongjuan,et al.Mass calculation of key assembly units in
LH2/ LOX rocket engine based on visual interface[J].Journal of Rocket Propulsion,2015,41(04):61.
[6]穆朋刚,童 飞,蒲光荣,等.温度对贮箱增压系统的影响分析[J].火箭推进,2015,41(04):74.
MU Penggang,TONG Fei,PU Guangrong,et al.Influence of temperature on tank pressurization system[J].Journal of Rocket Propulsion,2015,41(04):74.
[7]高朝辉,刘 宇,肖 肖,等.垂直着陆重复使用运载火箭对动力技术的挑战[J].火箭推进,2015,41(03):1.
GAO Zhao-hui,LIU Yu,et al.Challenge to propulsion technology for vertical
landing reusable launch vehicle[J].Journal of Rocket Propulsion,2015,41(04):1.
[8]申智帅,等.气动增压器技术及其在空间推进系统的应用[J].火箭推进,2015,41(03):15.
SHEN Zhi-shuai,RUAN Hai-jun,et al.Pneumopump technology and its application
in space propulsion system[J].Journal of Rocket Propulsion,2015,41(04):15.
[9]周 伟.某膨胀循环发动机推力室冷却结构流场仿真分析[J].火箭推进,2015,41(02):63.
ZHOU Wei.Flow field simulation analysis of cooling configuration
in thrust chamber of an expander cycle engine[J].Journal of Rocket Propulsion,2015,41(04):63.
[10]张 翔,徐洪平,安雪岩,等.液体火箭发动机稳态运行故障
数据聚类分析研究0[J].火箭推进,2015,41(02):118.
ZHANG Xiang,XU Hong-ping,AN Xue-yan,et al.Clustering analysis for fault data in steady process of
liquid propellant rocket engine[J].Journal of Rocket Propulsion,2015,41(04):118.
[11]杜大华,吴静杰,段捷.液体火箭发动机推力室极限承载能力研究[J].火箭推进,2010,36(05):40.
DU Da-hua,WU Jing-jie,DUAN Jie.Analysis of loading limit of the LRE thrust chamber[J].Journal of Rocket Propulsion,2010,36(04):40.
[12]吕发正,吴海波,杨永红,等.液氧牒油高压推力室液膜冷却环局部过热分析[J].火箭推进,2009,35(03):11.
Lti Fazhen9,Wu Haib0,Yang Yonghon9,et al.Investigation on local overheating of the film cooling ring
for LOX／kerosene high pressure chamber[J].Journal of Rocket Propulsion,2009,35(04):11.
[13]张峰,刘伟强.层板发汗冷却在液体火箭发动机中的应用与发展综述[J].火箭推进,2007,33(06):43.
Zhang Feng,Liu Weiqiang.Application and development of platelet transpiration cooling technology in LRE[J].Journal of Rocket Propulsion,2007,33(04):43.
[14]栾叶君,孙纪国,田昌义,等.氢氧推力室再生冷却内壁故障分析[J].火箭推进,2006,32(05):17.
Luan Yejun,Sun Jiguo,Tian Changyi,et al.Failure analysis on regeneratively cooled wall of a hydrogen-oxygen thrust chamber[J].Journal of Rocket Propulsion,2006,32(04):17.
[15]王新建.冷气模拟推力室研究[J].火箭推进,2004,(05):22.
Wang Xinjian.Simulation Study on Cold Gas Thruster[J].Journal of Rocket Propulsion,2004,(04):22.
备注/Memo
收稿日期：2012-10-１３；修回日期：2012-12-06
基金项目：国家863项目（2007AA705302)
作者简介：孙永奇（1976—），男，硕士，研究领域为液体火箭发动机推力室设计
更新日期/Last Update:
1900-01-01