小推力气氧气甲烷火箭发动机点火过程观测

doi:10.7527/S1000-6893.2023.28876

Abstract

Abstract:

Ignition process in the reaction control thruster fueled by gaseous oxygen and gaseous methane is experimentally observed with high-speed photography. The effects of the spark plug type， recess of the high-voltage plug， and mixture ratio on the ignition process are studied. The results show that the start-up process of the engine includes two sections， ignition process and transition process. The ignition process involves six phases in turn： spark formation， fire core formation， fire core grow-up， filling， fluctuation， and stable flame. However， during the transition process， with the increase of the fuel flow rate， the mixture ratio decreases to the stable condition. Experimental studies show that with enough spark energy， the flame is primarily controlled by the mixture ratio， and the range of the mixed ratio 2.01-18.3 has been validated. On the other hand， the duration from spark to stable flame is determined by the instantaneous mixture ratio at the spark time. In conclusion， the effect of the spark plug type does not play a significant role， while long recess of the spark plug always produces long duration of fire core propagation and short grow-up duration.

Key words: ignition, flame propagation upstream, spark plug, recess, mixture ratio

CLC Number:

V434

Qiyu ZHOU, Jiaqi ZHANG. Observation on ignition process in small rocket thruster fueled by gaseous oxygen and gaseous methane[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(8): 128876-128876.

Figures/Tables 18

Fig.1

Fig.2

Table 1

Fig.3

Fig.4

Table 2

Fig.5

Fig.6

Fig.7

Table 3

Fig.8

Fig.9

Fig.10

Table 4

Fig.11

Fig.12

Fig.13

Fig.14

References 22

1	HURLBERT E A， UENO H， ALEXANDER L， et al. International space exploration coordination group assessment of technology gaps for LOx/methane propulsion systems for the global exploration roadmap： AIAA-2016-5280 ［R］. Reston： AIAA， 2016.
2	KLEM M， SMITH T， WADEL M， et al. Liquid oxygen/liquid methane propulsion and cryogenic advanced development［C］∥ IAC，2011.
3	潘一力，周海清，吉林，等. 液氧/液甲烷姿控发动机点火技术研究［J］. 火箭推进， 2019， 45（4）： 16-25.
	PAN Y L， ZHOU H Q， JI L， et al. Study on ignition technology of LO_X/LCH₄ attitude control engine［J］. Journal of Rocket Propulsion， 2019， 45（4）： 16-25 （in Chinese）.
4	曹亚文，李斌，王飞，等. 高背压等离子点火器及其液体燃料点火特性实验研究［J］. 推进技术， 2021， 42（7）： 1570-1580.
	CAO Y W， LI B， WANG F， et al. Experiment researches of high back pressure plasma ignitor and liquid fuel ignition characteristics［J］. Journal of Propulsion Technology， 2021， 42（7）： 1570-1580 （in Chinese）.
5	ROCKETDYNE. Space shuttle main engine orientation ［M］.Washington，D.C.：NASA，1998.
6	PRATT & WHITNEY. RL10 ignition limits test for Shuttle Centaur：NASA-CR-183199［R］. Washington，D.C.：NASA， 1987.
7	中国航天工业总公司《世界导弹与航天发动机大全》编辑委员会. 世界导弹与航天发动机大全［M］. 北京：军事科学出版社， 1999.
	China Aerospace Industry Corporation， “World Missile and Space Engine” Editorial Committee. An encyclopedia of world missile and space engines［M］. Beijing： Military Science Publishing House， 1999 （in Chinese）.
8	SANCHEZ L E， CHAPARRO J， TORRES S， et al. Development and testing of a O2/CH4 torch igniter for propulsion systems： AIAA-2016-4975 ［R］.Reston：AIAA， 2016.
9	ZHANG J Q， LI Q L， SHEN C B. Ignition characteristics and combustion performances of a LO2/GCH₄ small thrust rocket engine［J］. Journal of Central South University， 2018， 25（3）： 646-652.
10	SCHNEIDER S， JOHN J， ZOECKLER J. Design， fabrication， and test of a LOX/LCH₄ RCS igniter at NASA： AIAA-2007-5442 ［R］. Reston：AIAA， 2007.
11	BREISACHER K， AJMANI K. LOX/methane main engine igniter tests and modeling： AIAA-2008-4757 ［R］. Reston：AIAA， 2008.
12	FRENKEN G， VERMEULEN E， BOUQUET F， et al. Development status of the ignition system for vinci： AIAA-2002-4330 ［R］. Reston：AIAA， 2002.
13	王艳，方杰，杨进慧，等. 氢氧火炬点火器低压燃烧流动仿真研究［J］. 航空动力学报， 2021， 36（11）： 2344-2352.
	WANG Y， FANG J， YANG J H， et al. Simulation study on combustion flow in low-pressure condition of hydrogen-oxygen torch ignitor［J］. Journal of Aerospace Power， 2021， 36（11）： 2344-2352 （in Chinese）.
14	张锋，于涵，尚帅，等. 气氧/气甲烷火炬式电点火器燃烧仿真与热试［J］. 火箭推进， 2022， 48（4）： 36-42.
	ZHANG F， YU H， SHANG S， et al. Combustion simulation and hot-fire test of GOX/GCH₄ spark torch igniter［J］. Journal of Rocket Propulsion， 2022， 48（4）： 36-42 （in Chinese）.
15	ROBINSON P J， VEITH E M， HURLBERT E A， et al. 445 N （100-lbf） LO₂/LCH₄ reaction control engine technology development for future space vehicles［J］. Acta Astronautica， 2010， 66（5-6）： 836-843.
16	MOREHEAD R L， ATWELL M J， MELCHER J C， et al. Cold helium pressurization for liquid oxygen/liquid methane propulsion systems： Fully-integrated initial hot-fire test results： AIAA-2016-4682 ［R］.Reston： AIAA， 2016.
17	MANFLETTI C. Low ambient pressure injection and consequences on ignition of liquid rocket engines： AIAA-2012-4131 ［R］. Reston： AIAA， 2012.
18	MANFLETTI C. Laser ignition of a research 200N RCS LO _x /GH2 and LO _x /GCH₄ engine： AIAA-2012-4132 ［R］.Reston：AIAA， 2012.
19	MANFLETTI C. Laser ignition of an experimental cryogenic reaction and control thruster： Ignition energies［J］. Journal of Propulsion and Power， 2014， 30（4）： 952-961.
20	BÖRNER M， MANFLETTI C， HARDI J， et al. Laser ignition of a multi-injector LOX/methane combustor［J］. CEAS Space Journal， 2018， 10（2）： 273-286.
21	CONTE D， BUDZYN D， BURGOYNE H， et al. Innovative Mars Global International Exploration （IMaGInE） mission： AIAA-2016-5596 ［R］. Reston： AIAA， 2016.
22	黄代民，覃欣欣，徐伟巍. 湍流状态下甲烷爆炸极限实验研究［J］. 电气防爆， 2020（3）： 39-42.
	HUANG D M， QIN X X， XU W W. Experimental study on methane explosion limit in turbulent state［J］. Electric Explosion Protection， 2020（3）： 39-42 （in Chinese）.

序号	参数	数值
1	燃烧室压力P_c/MPa	0.2
2	氧气喷前压力P_o/MPa	0.7
3	甲烷气喷前压力P_f/MPa	0.7
4	氧气流量 M_o/（g·s^-1）	3.9
5	甲烷气流量 M_f/（g·s^-1）	2.6
6	混合比 MR （M_o/M_f）	1.5
7	喉径D_t/mm	8
8	特征长度L^*/mm	190

序号	参数	数值
1	氧孔数目-孔径/mm	2-∅1.2
2	甲烷数目-孔径/mm	2-∅0.9
3	火花塞外径/mm	6
4	火花塞孔内径/mm	8

试验编号	M_f /（g·s^-1）	M_o /（g·s^-1）	R_s/mm	MR	火花塞	火焰
1	2.69	3.81	0.5	1.42	1	熄灭
2	1.78	3.59	0.5	2.02	1	正常
3	1.61	3.79	0.5	2.35	1	正常
4	2.65	4.02	8.0	1.52	2	熄灭
5	1.76	3.53	8.0	2.01	2	正常
6	1.66	4.03	0.5	2.43	2	正常
7	1.66	4.02	3.0	2.42	2	正常
8	1.66	4.02	5.5	2.42	2	正常
9	1.67	4.03	8.0	2.41	2	正常

编号	参数	火花	第1次回传	火焰稳定	燃烧稳定
1	试验6-t/ms	7 084.76	7 084.95	7 085.4	7 140
2	试验6-P_f/MPa		0.147		0.863
3	试验6-M_f/（g·s^-1）		0.24		1.51
4	试验6-MR		16.8		2.67
5	试验4-t/ms	7 080.95	7 081.21	7 081.9	7 132.2
6	试验4-P_f/MPa		0.157		1.31
7	试验4- M_f/（g·s^-1）		0.27		2.3
8	试验4-MR		14.9		1.75

[1]	Xiao BAI, Pengjin CAO, Qinglian LI, Peng CHENG. Generation and transmission mechanisms of disturbance inside injector during self-pulsation [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(4): 126523-126523.
[2]	Jianjun WU, Zejun HU, Zhicheng HE, Yu ZHANG, Yang OU, Zhengxue MA, Qinhui PENG, Yuxuan ZHONG. Research progress of electrically controlled solid propulsion technology [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(15): 528716-528716.
[3]	Mingbo SUN, Jiajian ZHU, Tiangang LUO, Qinyuan LI, Yifu TIAN, Minggang WAN, Yongchao SUN. Research progress of unsteady supersonic combustion controlled by electric excitation technology [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(15): 528787-528787.
[4]	Zejun HU, Yunchao FENG, Zhicheng HE, Zhixun XIA, Mingtai LI. Ignition and combustion characteristics of micro-sized aluminum particles in H₂O and O₂ [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(15): 528866-528866.
[5]	Pengjin CAO, Xiao BAI, Peng CHENG, Qinglian LI. Effect of operating parameters on self-pulsation characteristics of gas-liquid swirl coaxial injectors [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(15): 528770-528770.
[6]	ZHAO Minghao, WANG Ke, WANG Zhicheng, ZHU Yiyuan, YU Xiaodong, FAN Wei. Effects of ignition on initiation characteristics of hollow rotating detonation combustor [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 124870-124870.
[7]	XIA Yizhi, WANG Yong, HONG Liu, YANG Weidong, CHEN Hongyu. Experiment on ignition and flame of gelled hypergolic bipropellants [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(1): 123254-123254.
[8]	ZHOU Daiying, ZHANG Ying, FENG Jian. Estimation of target precession frequency based on time-domain difference of sequential HRRPs [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(S1): 722183-722183.
[9]	TIAN Jichao, SONG Qiang, HONG Gang, ZHANG Ran. Solutions for impact zone safety issue of conventional rockets [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(S1): 722302-722302.
[10]	YAO Shiyong, MIN Changwan. Effects of opening diameter on measurement of recessed pressure transducers [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(12): 122029-122029.
[11]	LI Yingkun, HAN Junli, CHEN Xiong, ZHOU Changsheng, GONG Lunkun. Numerical simulation of the ignition transient of dual pulse motor based on multi-physics coupling [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(4): 120409-120409.
[12]	XU Can, MA Hu, LI Jian, DENG Li, YU Ling. Propagation property of flame and pressure wave in rotating detonation engine [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(10): 121226-121226.
[13]	CHEN Qian, ZHANG Huiqiang, WANG Bing, ZHOU Weijiang, YANG Yunjun. Research progress of combustion in supersonic mixing layers [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(1): 20036-020036.
[14]	WANG Qiuxiao, HUANG Dongxin, MENG Hua. Numerical simulation of CH₄-LO_<i>x non-premixed turbulent combustion at supercritical pressures [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(7): 2132-2143.
[15]	MIAO Shikun, ZHOU Jin, LIN Zhiyong. Propagation characteristics of detonation wave influenced by wall suction [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(3): 854-864.

Observation on ignition process in small rocket thruster fueled by gaseous oxygen and gaseous methane

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 18

References 22

Related Articles 15

Recommended Articles

Metrics

Comments