Computational Fluid Dynamic Optimization of an Experimental Rotating Detonation Rocket Engine Nozzle

Daniel E Paxson; Kenji Miki; H Douglas Perkins; Shaye Yungster

NASA NTRS · 20220006164

Computational Fluid Dynamic Optimization of an Experimental Rotating Detonation Rocket Engine Nozzle

Daniel E Paxson·Kenji Miki·H Douglas Perkins·Shaye Yungster

Abstract

A parametric optimization study is performed on the nozzle of a laboratory rotating detonation rocket engine (RDRE) using a three-dimensional computational fluid dynamic simulation. The primary optimization objective is maximum nozzle thrust. The basic nozzle configuration is a shrouded, truncated plug. The fluid in the RDRE chamber leading to the nozzle is choked at its exit so that its cyclic behavior is unaffected by any changes to the nozzle design. Optimization is performed for a single operating point. Parameters varied are the overall nozzle area expansion ratio and the fraction of the expansion area that is provided by the shroud. These two parameters indirectly affect the angle of the plug nozzle cone, and the bluff body area associated with its truncation. Nozzle thrust is evaluated as the difference between the thrust of the RDRE chamber-plus-nozzle combination and that of the chamber alone. The nozzle produces approximately 20% of the total engine thrust. The baseline nozzle is found to perform well, yielding 58.1% of the thrust calculated for a notional ideal RDRE nozzle which can instantaneously change shape to allow isentropic expansion of every fluid element. Optimization improves the performance, bringing the nozzle thrust to 70.0% of the notional ideal, and total engine thrust (chamber-plus-nozzle) to 94% of the ideal.

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Daniel E Paxson, Kenji Miki, H Douglas Perkins, Shaye Yungster. Computational Fluid Dynamic Optimization of an Experimental Rotating Detonation Rocket Engine Nozzle. https://ntrs.nasa.gov/citations/20220006164

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