Thrust and flow field characterization of Rotating Detonation Engines using detailed numerical simulations

Rotating Detonation Engines (RDE) operate on continuous detonation-based thermodynamic cycles to achieve increased efficiency over the traditional Brayton cycle. A typical RDE design involves an annular cylinder, into which a fuel-air mixture is injected axially and consumed by a rotating detonation wave, while the burnt mixture is expelled to produce thrust. In this work, we report on detailed numerical simulations of an unrolled 2D RDE, operating on a stoichiometric H₂-air mixture. Results from two codes are reported, where the conservation equations are solved using Piecewise Parabolic Method (FLASH¹) and discontinuous-Galerkin method (JENRE²). In addition to varying the numerics, effect of reaction chemistry was also examined, by performing simulations with an induction time model, a 1-step reaction mechanism, and a detailed (9-species, 19-step) reaction mechanism³. We also report on several quantities of interest including the detonation wave height, thrust, and specific impulse as the ratio of the injector pressure to the ambient pressure is varied.

¹B. Fryxell et al., Astrophys. J., Suppl. Ser. 131, 273 (2000).
²D. Schwer, A. Corrigan & K. Kailasanath, AIAA SciTech, 52nd Aerospace Sciences Meeting, (2014).
³M.A. Mueller et al., Int. J. Chem. Kinet., 31, 113 (1999).