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http://dx.doi.org/10.5139/JKSAS.2004.32.4.061

Experimental study of combustion stability assessment of injector  

Seo, Seong-Hyeon (한국항공우주연구원)
Lee, Kwang-Jin (한국항공우주연구원)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.32, no.4, 2004 , pp. 61-66 More about this Journal
Abstract
The objective of the present study is to develop methodology for the assessment of combustion stability of liquid rocket injectors. To simulate actual combustion occurring inside of a thrust chamber, a fullscale injector has been employed in the study, which bums gaseous oxygen and mixture of methane and propane. The main idea of the experiment is that the mixing mechanism is considered as a dominant factor significantly affecting combustion instability in a fullscale thrust chamber. A single split triplet injector has been used with an open-end cylindrical combustion chamber. The characteristics revealed by excited dynamic pressures in gaseous combustion show degrees of relative acoustic damping depending on operating conditions. Upon test results, the direct comparison between various types of injectors can be realized for the selection of the best design among prospective injectors.
Keywords
Combustion Stability; Subscale Test; Liquid Rocket; Acoustic Damping; Injector;
Citations & Related Records
Times Cited By KSCI : 1  (Citation Analysis)
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