Rotating Detonation Engines (RDE) are considered as a promising concept for power-generation and propulsion systems. In recent years, many studies have shown a growing interest in this technology, particularly for space applications. Based on a self-sustaining detonation process, RDE deliver a continuous thrust and takes advantage of pressure gain combustion. Thus meaning RDE could offer a higher specific impulse or reduce the chamber inlet pressure, with consequent size reduction or complete elimination of turbopump systems, compared to conventional liquid rocket engines. In addition, RDE chambers can be compactly designed and adapted to an aerospike nozzle suitable for both atmospheric and vacuum operations.

To predict the performance improvements of RDE, numerical approaches are necessary. However, during a preliminary development phase, high-fidelity CFD simulations can be complex and time consuming. Therefore, there is a need to develop rapid and reasonably accurate assessment tools for engine pre-design and large parametric studies.

The goal of this article is to present a new computer-based tool, called DETOne. The different models will be described and assumptions discussed. Furthermore, RDE calculations will be proposed as well as comparisons with CFD simulations and experimental results. The program architecture is based on a set of order-reduced models describing the different phenomenon involved within a RDE chamber, such as injection, generation of a reactant layer, detonation and expansion of the burnt gases towards the nozzle exit. As primary assumptions, engine steady-state operations and typical flow-field patterns are considered. This consists in (i) a triangular refilling zone where fresh reactants are continuously injected (ii) a transversal detonation front and a post-detonation region where injection is blocked (iii) an oblique shock wave anchored at a triple point (iv) and a curved slip-line corresponding to the shear layer between the burnt gases.

Basically, the numerical methodology uses a 1D chemical kinetics solver to assess the Chapman-Jouguet proprieties and the detonation velocity. In addition, an iterative process is carried out to predict the angles of oblique shock waves and of slip-lines through a Prandtl-Meyer function. In parallel, a MOC (Method Of Characteristics) is applied to reconstruct the 2D flow-field within the RDE chamber.

The present model has highlighted its ability to reproduce the main flow features, such as temperature and pressure profiles. Comparisons with results from literature have shown good agreements. Finally, this tool could be used to perform a launch system analysis and to pre-design a RDE demonstrator.