Fundamental analysis and modeling of spray-detonation dynamics with application to rotating detonation engines

Theoretical studies have shown that, when compared to traditional chemical rocket engines, rotating detonation rocket engines (RDREs) offer the potential for achieving higher propulsion efficiencies, smaller engine volumes, and the omission of turbopumps from high-thrust propulsion systems. A realization of these gains would result in higher specific thrust and decreases in required propellant mass, system complexity, and cost for spacefaring missions. For rocket applications, the development of liquid-fueled RDREs, which offer high volumetric energy density, is critical. Attempts have been made to numerically and experimentally characterize liquid- fuel RDREs, but little has been done to evaluate the spray-detonation dynamics or how mixture stratification impacts combustion and large-scale physical processes in these systems. Research successfully isolating these effects could enhance understanding of the coupling between droplet breakup, evaporation, mixing, turbulence, and spray-detonation interaction in RDREs and aid in the development of models for use in future studies. Therefore, research is proposed to develop improved fundamental understanding and physics-based models of spray-detonation combustion dynamics with application to RDREs. The proposed research seeks to address this problem by (1) performing and studying direct numerical simulation) of spray-detonation configurations to isolate and model the impact of droplet-laden flows on detonation dynamics and stability, and (2) applying improved spray-detonation closure models to large eddy simulation of an RDRE and comparing against experimental data for validation. If successful, the models and insights derived will make numerical and theoretical study of liquid-fueled RDREs increasingly feasible, accelerating progress towards realizable detonation-driven propulsion systems.

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