氢氧火炬式电点火器燃烧流动分析
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摘要
为研究氢氧火炬式电点火器工况范围广、燃烧流场复杂的特性,采用CFD数值仿真方法,对不同氢氧喷注距离、混合比以及背压对点火器内燃烧流动及热防护的影响进行了研究。结果表明:氢氧喷注距离的缩短有利于点火器头部及火花塞热防护,但会造成点火器身部内壁温度升高;混合比过高将直接导致火花塞及氧喷嘴烧蚀,需结合点火能量优化设计;流量不变,点火器背压升高对燃烧及热防护影响不大。
The hydrogen-oxygen torch igniter operates in wide conditions of pressure and mixture ratio, which results in complicated combustion phenomenon. The influence of hydrogen-oxygen injection distance, mixture ratio and back pressure on igniter combustion and thermal protection are studied by CFD numerical simulation methods. Results reveal that shorter hydrogen-oxygen injection distance is helpful to protect the igniter head and spark plug, while the temperature of igniter chamber wall rises. High mixture ratio results in spark plug and oxygen injector erosion, which should be selected combining with the ignition energy. The back pressure has negligible effects on the igniter combustion and thermal protection with the same mass flow.
The hydrogen-oxygen torch igniter operates in wide conditions of pressure and mixture ratio, which results in complicated combustion phenomenon. The influence of hydrogen-oxygen injection distance, mixture ratio and back pressure on igniter combustion and thermal protection are studied by CFD numerical simulation methods. Results reveal that shorter hydrogen-oxygen injection distance is helpful to protect the igniter head and spark plug, while the temperature of igniter chamber wall rises. High mixture ratio results in spark plug and oxygen injector erosion, which should be selected combining with the ignition energy. The back pressure has negligible effects on the igniter combustion and thermal protection with the same mass flow.
引文
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[7]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(1):34-36.Sun Jiguo,Wang Jue.Experimental study on high mixture ratio torch ignitor[J].Journal of Propulsion Technology,2000(1):34-36.
[8]郭田莉,孙慧娟.氢氧火炬式电点火系统研究[J].战术导弹技术,2015(3):55-59.Guo Tianli,Sun Huijuan.Research on torch ignition system of LOX/LH2engine[J].Tactical Missile Technology,2015(3):55-59.
[9]郭田莉,孙慧娟.火炬式电点火系统点火能量的正交试验研究[J].导弹与航天运载技术,2016(2):90-93,96.Guo Tianli,Sun Huijuan.Orthogonal testing study on ignition energy of a torch ignition system[J].Missiles and Space Vehicles,2016(2):90-93,96.
[2]Liang P Y.Modeling of SSME fuel preburner ASI[R].N92-32259,1992.
[3]Dexter C R,McCay T D.Space shuttle main engine fuel preburner augmented spark igniter shutdown detonations[R].AIAA-86-1445,1986.
[4]俞世宏.国外氢氧发动机的火舌点火器[J].国外导弹与宇航,1983(09):25-29.Yu Shihong.Torch igniters of foreign hydrogen and oxygen engines[J].Foreign Missiles and Astronautics,1983(09):25-29.
[5]吴宏斌.国外氢氧火箭发动机的火药点火器和电点火器[J].导弹与航天运载技术,1994(5):32-42.Wu Hongbin.Pyrotechnic igniters and electrical spark igniters for LOX/LH2 rocket engines[J].Missiles and Space Vehicles,1994(5):32-42.
[6]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.Sun Jiguo,Wang Jianhong.Study on cryogenic fuel-rich spark igniter[J].Missiles and Space Vehicles,1999(6):17-22.
[7]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(1):34-36.Sun Jiguo,Wang Jue.Experimental study on high mixture ratio torch ignitor[J].Journal of Propulsion Technology,2000(1):34-36.
[8]郭田莉,孙慧娟.氢氧火炬式电点火系统研究[J].战术导弹技术,2015(3):55-59.Guo Tianli,Sun Huijuan.Research on torch ignition system of LOX/LH2engine[J].Tactical Missile Technology,2015(3):55-59.
[9]郭田莉,孙慧娟.火炬式电点火系统点火能量的正交试验研究[J].导弹与航天运载技术,2016(2):90-93,96.Guo Tianli,Sun Huijuan.Orthogonal testing study on ignition energy of a torch ignition system[J].Missiles and Space Vehicles,2016(2):90-93,96.