Development and Analysis of a Gaseous Hydrogen-Oxygen Rotating Detonation Combustor

Abstract: Theory suggests that more efficient rocket propulsion can possibly be achievedby utilizing a pressure-gain detonative combustion process instead of conventional deflagration combustion. To demonstrate this, rotating detonation engines that sustain one or several detonation waves in an annular enclosure havebeen a subject of research for decades. A detonation wave multiplicity modelthat accounts for transient injection effects in an annular enclosure was derivedand coupled with existing design guidelines to methodically size a rotatingdetonation engine for combustion dynamics research. An annular combustion chamber assembly was designed, manufactured and integrated to a testbench. Four hot-fire tests were performed using a hydrogen-oxygen mixturewith mean total mass flow rates of 35-40 g s−1to study the efficacy of initiatinga detonation with a spark plug and to verify the integrity of the design. Highfrequency pressure sensors recorded an oscillating pressure peak of 2-3 bar.Co-rotating combustion waves were observed in the optical data from one ofthe tests, but the low recorded pressure peaks indicate that they were possiblyweak detonations, only achieving 57 % of the theoretical detonation velocity.