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中南大学学报(英文版)

Journal of Central South University

Vol. 25    No. 3    March 2018

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Ignition characteristics and combustion performances of a LO2/GCH4 small thrust rocket engine
ZHANG Jia-qi(张家奇)1, 2, LI Qing-lian(李清廉)1, 2, SHEN Chi-bing(沈赤兵)1, 2

1. College of Aerospace Science and Engineering, National University of Defense Technology,Changsha 410073, China; 2. Science and Technology on Scramjet Laboratory, National University of Defense Technology,Changsha 410073, China

Abstract:A 500 N model engine filled with LO2/GCH4 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.

 

Key words: LO2/GCH4; small thrust rocket engine; ignition characteristic; combustion performance

中南大学学报(自然科学版)
  ISSN 1672-7207
CN 43-1426/N
ZDXZAC
中南大学学报(英文版)
  ISSN 2095-2899
CN 43-1516/TB
JCSTFT
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