航天推进技术研究院主办
[1]刘昌国,陈锐达,刘 犇,等.小推力空间液体火箭发动机夹气启动特性[J].火箭推进,2021,47(03):8-15.
LIU Changguo,CHEN Ruida,LIU Ben,et al.Start-up characteristics of low-thrust space liquid rocket engine with entrained gas[J].Journal of Rocket Propulsion,2021,47(03):8-15.
点击复制
LIU Changguo,CHEN Ruida,LIU Ben,et al.Start-up characteristics of low-thrust space liquid rocket engine with entrained gas[J].Journal of Rocket Propulsion,2021,47(03):8-15.
小推力空间液体火箭发动机夹气启动特性
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
47
期数:
2021年03期
页码:
8-15
栏目:
研究与设计
出版日期:
2021-06-30
- Title:
- Start-up characteristics of low-thrust space liquid rocket engine with entrained gas
- 文章编号:
- 1672-9374(2021)03-0008-08
- Keywords:
- gas entrainment; start-up process; injector; atomization; cut-off
- 分类号:
- V434.3
- 文献标志码:
- A
- 摘要:
- 为了探究供应管路夹气对液体火箭发动机启动过程的影响,利用彩色高速相机捕捉了双组元150 N发动机直流互击式喷注器雾化特征,对比了夹气和不夹气状态下喷雾场的启动过程,并在高空模拟热试车台进行了国内首次小推力空间液体火箭发动机夹气启动验证试验,采用氮气对真空舱内推进剂供应管路吹除后直接进行推进剂充填并点火。结果表明,夹气状态下的喷注器喷雾场空间分布上主要集中于中心轴线区域,局部区域雾化效果增强,液滴直径减小,雾化锥角增大; 夹气雾化充分发展时,中心主射流起始段和边区射流局部出现断流,空间整体分布均匀性较差。高空模拟热试车条件下,夹气没有对发动机启动过程造成持续性振荡,点火推力峰有增大的趋势,发动机其他性能、温度、振动等测量参数以及开关机过程没有发生显著变化。但是,夹气一定程度上增加了发动机启动过程的复杂性和不确定性因素,工程上需要引起足够重视,强烈建议热试车时增加3 s预点火程序,排出推进剂充填后发动机控制阀前可能产生的气泡,确认发动机启动无异常后再继续后续点火程序。
- Abstract:
- In order to explore the effect of gas entrainment in the supply pipelines during the liquid rocket engine start-up process,the atomization characteristics of 150 N bipropellant engine impinging injector were captured by the color high-speed camera.The start-up processes of spray field under the gas-entrained and non-gas-entrained states were compared.The first domestic verification test of low-thrust space liquid rocket engine start-up with entrained gas was carried out in the high altitude simulation hot fire test bench.The propellant supply pipelines in the vacuum cabin were directly filled after nitrogen blowing,and then the engine was ignited.The results show that the injector spray field distribution with gas entrainment is mainly concentrated in the central axis area,and the local area atomization effect is enhanced.In addition,the droplet diameter decreases and the atomization cone angle increases.When the atomization with gas entrainment is fully developed,the initial section of the central main jet and the side jets will be locally cut off,and the overall distribution uniformity of the injector spray field is poor.Under the hot fire test conditions,there is no continuous oscillation during the engine start-up process due to the gas entrainment,the engine ignition thrust peak tends to increase,and other measurement parameters including performance,temperature,vibration and start-up and shutdown process of the engine do not change significantly.However,the gas entrainment may increase the complexity and uncertainly of the engine start-up process,and enough attention needs to be paid in engineering application.It's strongly recommended to add a 3-second pre-ignition program during the hot fire test to discharge the bubbles before the control valves after propellant filling,and to continue the subsequent ignition procedure of the engine after confirming that there is no abnormality during the start-up process.
参考文献/References:
[1] 杨立军,富庆飞.液体火箭发动机推力室设计[M].北京: 北京航空航天大学出版社,2013.
[2] 刘昌国,施浙杭,陈锐达,等.液体射流撞击液膜振荡行为的实验研究[J].推进技术,2019,40(12): 2748-2754.
[3] 李佳楠,费俊,杨伟东,等.直流互击式喷注单元雾化特性准直接数值模拟[J].推进技术,2016,37(4): 713-725.
[4] 刘晓伟,胡伟,曹晶,等.鲁泊数和孔径比对直流互击式喷注器性能的影响[J].火箭推进,2010,36(3): 24-27.LIU X W,HU W,CAO J,et al.Effects of Rupe number and ratio of injection orifice diameter on unlike impinging injector performance[J].Journal of Rocket Propulsion,2010,36(3): 24-27.
[5] 郑刚,聂万胜,何博,等.撞击角对撞击式喷嘴雾化特性影响研究[J].推进技术,2015,36(4): 608-613.
[6] NEWHOUSE C W,FOOTE J F.Apollo SM-LM RCS engine development program summary report[R].NASA CR-101930,1969.
[7] 俞肇铭.R4-D双组元姿控发动机的研制(五): 气体混入,推力振荡[J].现代防御技术,1982,10(6): 41-60.
[8] 孙冰,张建伟.火箭发动机热防护技术[M].北京: 北京航空航天大学出版社,2016.
[9] TRAINER D.Effects of flow pattern on the breakup length of circular air-assisted water jets[J].Atomization and Sprays,2018,28(9): 763-777.
[10] TRAINER D.Breakup length and liquid splatter characteristics of air-assisted water jets[J].International Journal of Multiphase Flow,2016,81: 77-87.
[11] SUN C H,NING Z,LV M,et al.Time-frequency analysis of acoustic and unsteadiness evaluation in effervescent sprays[J].Chemical Engineering Science,2015,127: 115-125.
[12] KONSTANTINOV D,MARSH R,BOWEN P J,et al.Effervescent atomization for industrial energy-technology review[J].Atomization and Sprays,2010,20(6): 525-552.
[13] 岳连捷,俞刚.气泡雾化喷嘴液雾特性[J].推进技术,2003,24(4): 348-352.
[14] 孙春华.气泡雾化喷射中气液两相作用及射流喷雾的研究[D].北京: 北京交通大学,2017.
[15] 孙春华,宁智,乔信起,等.气泡雾化喷嘴泡状流出口喷雾脉动特征[J].化工学报,2018,69(10): 4253-4260.
[16] MORRELL G.Rocket thrust variation with foamed liquid propellants[R].NACA RM E56K27,1957.
[17] CASIANO M J,HULKA J R,YANG V.Liquid-propellant rocket engine throttling: a comprehensive review[J].Journal of Propulsion and Power,2010,26(5): 897-923.
[18] 薛帅杰,刘红军,陈鹏飞,等.注气离心喷嘴喷注过程稳定性试验[J].航空学报,2019,40(7): 122697.
[19] 陈坚,李建中,袁丽,等.雾化特性对喷雾燃烧点火过程的影响[J].推进技术,2017,38(6): 1318-1326.
[20] 聂万胜,庄逢辰.喷雾特性对液体火箭发动机燃烧稳定性的影响[J].推进技术,2000,21(3): 56-59.
相似文献/References:
[1]杨建文,胡锦华,石晓波.发动机/扩压器不同安装方案对高模试车启动过程的影响[J].火箭推进,2022,48(01):53.
YANG Jianwen,HU Jinhua,SHI Xiaobo.Effect of different engine/diffuser installation schemes on start-up process in high attitude test[J].Journal of Rocket Propulsion,2022,48(03):53.
备注/Memo
收稿日期：2020-07-01; 修回日期:2020-12-14
作者简介：刘昌国(1976—),男,博士生,研究领域为空间液体火箭发动机。
通信作者：于达仁(1966—),男,教授,研究领域为等离子推进、高超声速推进与控制。
更新日期/Last Update:
1900-01-01