Experimental and numerical study on multi-wavemodes of H2/O2rotating detonation combustor

H-2/O-2 are desirable propellants for rocket-based rotating detonation engines but are rarely reported. This report presents an experimental study on rotating detonations powered by H-2/O-2. A non-premixed three-dimensional numerical simulation was conducted via OpenFOAM-based code. The experimental results revealed more than five co-rotating detonation waves at various flow rates with a propagation speed below 2000 m/s. Furthermore, an adjustment stage was observed prior to the stabilization of the detonation in the N-wave mode. The wavenumber in the adjustment stage varied between N and N+1 when the flow rate was 153 g/s and between N-1 and N+1 at 186 g/s. The simulation results revealed that multiple waves and low filling heights characterized the flow field of the H-2/ O-2 rotating detonation. The severe deflagration of the contact surface led to new detonation waves at excessive filling heights. This supports further exploration of the potential application of H-2/O-2 propellants in rotating detonation rocket engines. (c) 2022 Hydrogen Energy Publications LLC. Published by Elsevier Ltd. All rights reserved.

Automated summary

This study presents an experimental investigation and numerical simulation of rotating detonations powered by H-2/O-2. Multiple co-rotating detonation waves and an adjustment stage were observed. The simulation results show that the flow field of H-2/O-2 rotating detonation is characterized by multiple waves and low filling heights, and new detonation waves occur at excessive filling heights.