Abstract
Abstract : The objective of this research was to improve understanding of the mechanisms by which flow, mixing and combustion processes are coupled to acoustic fields in liquid-propellant rocket motors. Particular attention was focused on analyses of amplification mechanisms coupled with finite-rate chemical reactions by use of numerical and analytical methods. Special attention was focused on LOX/GH2 systems and suggested a possible explanation of threshold phenomena found in liquid-propellant rockets. Reduced chemistry was developed for describing LOX combustion in GH2. and approaches towards explaining droplet burning-time minima in the transcritical regime were completed. The results can be helpful in improving knowledge of combustion mechanisms and combustion instability in liquid-propellant rocket motors at high pressures.
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