Experimental and numerical study on multi-wave modes of H2/O2 rotating detonation combustor

Abstract

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. • Rotating detonations powered by H 2 /O 2 at various flow rates were evaluated. • Multi-wave modes of H 2 /O 2 rotating detonations in a model engine were studied. • Demonstrate the formation of new detonation waves. • Results show potential of using H 2 /O 2 propellants in continuous detonation engines.