Three-Dimensional Numerical Simulation of the Operation of an Experimental Hydrogen-Oxygen Rotating Detonation Engine

Abstract

Rotating Detonation Engines (RDEs) are a type of pressure-gain combustion system based on detonation waves traveling around a cylindrical combustion chamber igniting the fresh gases. Compared to classical combustors, detonative combustion potentially offers an increment in thermodynamic efficiency of the engine due to rapid heat release and lower entropy rise. The development of this technology could bring more compact and efficient combustors with applications to energy generation, air-breathing engines, and space propulsion.

The objective of the present work is to simulate the RDE tested at DLR Lampoldshausen. The engine is fed with a mixture of gaseous H2/O2. The experiment yielded data on detonation characteristics (number of waves, dominant frequencies and wave speed). The DLR TAU code is employed to run the simulations in an URANS approach. The numerical work aims to improve the understanding of the combustor dynamics, providing information about the detonation physics and flow field characteristics.

This article presents results for different operating points, providing insight about the number of waves, wave speed, rotating direction, and dominant frequencies. These results are also compared with the experimental data. Moreover, it lays a foundation for future RDE numerical studies employing the DLR TAU code.