|Table of Contents|

Start-up characteristics of low-thrust space liquid rocket engine with entrained gas(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2021年03期
Page:
8-15
Research Field:
研究与设计
Publishing date:

Info

Title:
Start-up characteristics of low-thrust space liquid rocket engine with entrained gas
Author(s):
LIU Changguo123CHEN Ruida23LIU Ben23XU Hui23YU Daren1
1.School of Energy,Harbin Institute of Technology,Harbin 150001,China; 2.Shanghai Institute of Space Propulsion,Shanghai 201112,China; 3.Shanghai Engineering Research Center of Space Engine,Shanghai 201112,China
Keywords:
gas entrainment start-up process injector atomization cut-off
PACS:
V434.3
DOI:
-
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.

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.

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