Geometric Effects of Liquid Rocket Engine Pintle Injectors in Supercritical CombustionGeometric Effects of Liquid Rocket Engine Pintle Injectors in Supercritical Combustion

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The effects of the total momentum ratio (TMR) and blockage factor (BF) of pintle injectors with nine combinations in the supercritical combustion condition were studied experimentally. Oxidizer-centered pintle injectors with discrete two-row orifices were considered. The combustion test conditions using liquid oxygen and Jet A-1 as propellants were a combustion pressure of 70 bar and an OFR of 2.45. The decrease in the TMR with the fuel momentum growth enhanced characteristic velocity efficiency. The BF determined by the aspect ratio of the second row orifice contributed to the characteristic velocity efficiency change. However, the BF effect on the efficiency was not as significant as the TMR in the supercritical conditions. Furthermore, TMR affected the BF effect on the characteristic velocity efficiency by limiting the effective collision area between the two propellants in the second row orifices. Chugging was the most dominant in combustion pressure fluctuation modes and weakly correlated with the TMR and BF. In the supercritical combustion of pintle injector discrete orifice configuration, an increase in TMR reduced the combustion perturbation ratio slightly.
Publisher
SPRINGER
Issue Date
2022-11
Language
English
Article Type
Article
Citation

INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES, v.23, no.5, pp.941 - 952

ISSN
2093-274X
DOI
10.1007/s42405-022-00489-w
URI
http://hdl.handle.net/10203/301033
Appears in Collection
AE-Journal Papers(저널논문)
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