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Advisor(s)
Abstract(s)
Pressure and temperature increase in combustion chambers of Liquid Rocket Engines (LRE’s), while enhancing injection and combustion efficiencies, leads to both fuels and oxidizers to exceed their critical point conditions, reaching the domain of supercritical fluid flows. For these conditions, it is well known that the flow exhibits a quantitative gas jet-like behavior, and therefore may be described successfully with a relatively straightforward approach developed for incompressible but variable density flows. The present paper presents the application of a RANS method as a valid cost-effective flow description method. Experimental conditions are selected, consisting of both ends of the Widom line, in gas-like and liquid-like configurations, dominated over by mechanical and thermal breakup processes, respectively. This is evaluated by assessing the suitable boundary conditions for an accurate and physical representation of the injection processes. In this sense, it is concluded an isothermal injector configuration is the one allowing for an accurate representation of both mechanical and thermal disintegration processes in supercritical conditions.
Description
Keywords
Supercritical Widom line Gas-like Liquid-like Liquid Rocket Engines RANS method
Citation
Publisher
American Institute of Aeronautics and Astronautics Inc, AIAA