Combustion instabilities remain a major problem in most applications of combustion chambers. Instabilities have been seen with the three major liquid rocket engine injector types: impinging jets, shear coaxial and swirl coaxial. The specificities of the flow field and any hydrodynamic instabilities are of interest in explaining the appearance of combustion instabilities. This paper provides an overview of the phenomena that come into play in combustion and hydrodynamic instabilities and general guidelines concerning the design of liquid rocket engine injectors. Finally, it is primarily concerned with summarizing various studies that clarify the impact of injector design on spray and flow field development, both non-reacting and reacting experiments, as well as computational analyses. A critical review of these investigations informed the lay-out of a swirl injector design parameter study.
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