|Table of Contents|

Combustion simulation and hot-fire test of GOX/GCH4 spark torch igniter(PDF)

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

Issue:
2022年04期
Page:
36-42
Research Field:
目次
Publishing date:

Info

Title:
Combustion simulation and hot-fire test of GOX/GCH4 spark torch igniter
Author(s):
ZHANG Feng;  YU Han;  SHANG Shuai;  HU Hongbo;  LIAN Junkai
(Science and Technology on Liquid Rocket Engine Laboratory, Xian Aerospace Propulsion Institute, Xian 710100, China)
Keywords:
spark torch igniter methane hot-fire test combustion simulation
PACS:
V435
DOI:
-
Abstract:
For reusable LOX/methane engines, the spark torch ignition is feasible.The combustion simulation and hot-fire tests were conducted for a GOX/GCH4 spark torch igniter.The simulation results agreed well with the theoretical results, when the mixture ratio is close to the equivalent mixture ratio, and their deviation increases significantly when the mixture ratio is rather fuel-rich.As mixture ratio increased, the thermal environment of the spark plug is deteriorating, which increases the risk that the spark plug will be burned.The hot-fire test results show that the igniter could achieve reliable ignition and stable operation performance within the range of mixing ratio 1.0-1.6, and the chamber pressure could reach the expected target.Meanwhile, the flame at the exit of the igniter has well stability and stiffness, which meets the design requirements of the combustor for igniter.

References:

[1] 孙宏明.液氧/甲烷发动机评述[J].火箭推进,2006,32(2):23-31.
SUN H M.Review of liquid oxygen/methane rocket engine[J].Journal of Rocket Propulsion,2006,32(2):23-31.
[2] HERNANDEZ R,MERCER S.Carbon deposition characteristics of LO2/HC propellants[C]//23rd Joint Propulsion Conference.Reston,Virginia:AIAA,1987.
[3] 张雪松.联合发射公司的新一代火箭[J].太空探索,2015(1):54-57.
[4] 禹天福,李亚裕.液氧/甲烷发动机的应用前景[J].航天制造技术,2007(2):1-4.
[5] PRECLIK D,HAGEMANN G,KNAB O,et al.LOX/hydrocarbon propellant trade considerations for future reusable liquid booster engines[C]//41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Reston,Virginia:AIAA,2005.
[6] IANNETTI A,GIRARD N,RAVIER N,et al.PROMETHEUS,a low cost LOX/CH4 engine prototype[C]//53rd AIAA/SAE/ASEE Joint Propulsion Conference.Reston,Virginia:AIAA,2017.
[7] KLEM M D,SMITH T D,WADEL M F,et al.Liquid oxygen/liquid methane propulsion and cryogenic advanced development[C]//The 62nd International Astronautical Congress 2011.Cape Town, South Africa:NASA,2011.
[8] 李文龙,李平,邹宇.烃类推进剂航天动力技术进展与展望未来[J].宇航学报,2015,36(3):243-252.
[9] 李斌,张小平,高玉闪.我国可重复使用液体火箭发动机发展的思考[J].火箭推进,2017,43(1):1-7.
LI B,ZHANG X P,GAO Y S.Consideration on development of reusable liquid rocket engine in China[J].Journal of Rocket Propulsion,2017,43(1):1-7.
[10] ROBINSON J W,STEPHENSON D D.Liquid oxygen/liquid methane ascent main engine technology development[C]//59th International Astronautical Congress 2008.Glasgow, Scotland:NASA,2008.
[11] REPAS G.Hydrogen-oxygen torch ignitor[R].NASA-T-M-106493,1994.
[12] BREISACHER K,AJMANI K.LOX/methane main engine igniter tests and modeling[C]//44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Reston,Virginia:AIAA,2008.
[13] 孙纪国,王剑虹.低温富燃火炬点火器研究[J].导弹与航天运载技术,1999(6):17-22.
[14] 孙纪国,王珏.高混合比火炬式电点火器试验研究[J].推进技术,2000,21(1):33-35.
[15] 刘巍,杨涛,胡建新,等.气氧/酒精火炬式电点火器试验[J].推进技术,2008,29(3):269-272.
[16] 邓维鑫,乐嘉陵,杨顺华,等.空气/煤油火炬点火器设计及试验[J].航空动力学报,2017,32(7):1554-1560.
[17] 董刚,黄鹰,陈义良.不同化学反应机理对甲烷射流湍流扩散火焰计算结果影响的研究[J].燃料化学学报,2000,28(1):49-54.
[18] 高玉闪,金平,蔡国飙.气氧/甲烷与气氢/气氧喷注器燃烧特性对比研究[J].推进技术,2013,34(6):775-780.
[19] 高玉闪,杜正刚,金平,等.气氧/甲烷同轴剪切喷注器燃烧特性数值模拟[J].火箭推进,2009,35(5):18-23.
GAO Y S,DU Z G,JIN P,et al.Numerical simulation on the combustion characteristic of shear coaxial GO2/GCH4 injector[J].Journal of Rocket Propulsion,2009,35(5):18-23.

Memo

Memo:
-
Last Update: 1900-01-01