Mohammedniyasdeen NEJAAMTHEEN, Jeong-Yeol CHOI

DOI Number: N/A

Conference number: HiSST-2025-252

This study presents a numerical analysis of the initial flow-field characteristics of a Disk-shaped Rotating Detonation Rocket Engine (DiskRDE) using a non-premixed ethylene/oxygen mixture. The primary objective is to explore the flow dynamics and combustion characteristics within a compact and efficient propulsion system suitable for upper-stage rockets. Numerical simulations were conducted using a density-based, compressible turbulent reactive solver. The results reveal the progression of the detonation process through five distinct stages, from ignition to limit cycle detonative mode. Instantaneous and spatiotemporal contours of pressure, temperature, pressure gradient, and mixture fraction provide detailed insights into the detonation wave’s behavior, including the complex interactions of primary and secondary wavefronts, as well as the formation of rarefaction and transverse
waves. The study highlights the role of combustion dynamics in stabilizing the detonation process, offering valuable information for optimizing the performance of DiskRDEs. The validation of the numerical results against experimental data demonstrates the reliability of the computational framework, confirming its potential for future design improvements.

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In Categories: 1.Events, 1.HiSST 2025, Propulsion Systems & Components
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