Ignition characteristics and combustion performances of a LO2/GCH4 small thrust rocket engine

• Published in: Journal of Central South University Vol. 25; no. 3; pp. 646 - 652
• Main Authors: Zhang, Jia-qi, Li, Qing-lian, Shen, Chi-bing
• Format: Journal Article
• Language: English
• Published: Changsha Central South University 01.03.2018; Springer Nature B.V
• Subjects: Combustion efficiency; Engineering; Flow velocity; Liquid oxygen; Low flow; Metallic Materials; Rocket engines; Rockets; Spark plugs; Spontaneous combustion; 燃烧性能; 小推力火箭发动机; 点火特性; LO; small thrust rocket engine; 液氧气甲烷; GCH; ignition characteristic; combustion performance
• ISSN: 2095-2899; 2227-5223
• DOI: 10.1007/s11771-018-3767-y

A 500 N model engine filled with LO 2 /GCH 4 was designed and manufactured. A series of ignition attempts were performed in it by both head spark plug and body spark plug. Results show that the engine can be ignited but the combustion cannot be sustained when head spark plug applied as the plug tip was set in the gaseous low-velocity zone with thin spray. This is mainly because flame from this zone cannot supply enough ignition energy for the whole chamber. However, reliable ignition and stable combustion can be achieved by body spark plug. As the O/F ratio increases from 2.61 to 3.49, chamber pressure increases from 0.474 to 0.925 MPa and combustion efficiency increases from 57.8% to 95.1%. This is determined by the injector configuration, which cannot produce the sufficiently breakup of the liquid oxygen on the low flow rate case.