Work

Flow-field analysis and performance assessment of rotating detonation engines under different number of discrete inlet nozzles

Year: 2024

Type: article

Abstract: • RDE featuring different numbers of discrete inlet nozzles are numerically studied. • Effect of reactant non-uniformities on detonation combustion dynamics is analyzed. • RDE parameters such as detonation velocity, mass flow rate, and thrust are assessed. • RDE flow field structure and stability are affected by the number of inlet nozzles. This study explores in depth rotating detonation engines (RDEs) fueled by premixed stoichiometric hydrogen/air mixtures through two-dimensional numerical simulations including a detailed chemical kinetic mechanism. To model the spatial reactant non-uniformities observed in practical RDE combustors, the referred simulations incorporate different numbers of discrete inlet nozzles. The primary focus here is to analyze the influence of reactant non-uniformities on detonation combustion dynamics in RDEs. By systematically varying the number of reactant injection nozzles (from 15 to 240), while maintaining a constant total injection area, the study delves into how this variation influences the behavior of rotating detonation waves (RDWs) and the associated overall flow field structure. The numerical results obtained here reveal significant effects of the number of inlets employed on both RDE stability (self-sustaining detonation wave) and performance. RDE configurations with a lower number of inlets exhibit a detonation front with chaotic behavior (pressure oscillations) due to an increased amount of unburned gas ahead of the detonation wave. This chaotic behavior can lead to the flame extinguishing or decreasing in intensity, ultimately diminishing the engine's overall performance. Conversely, RDE configurations with a higher number of inlets feature smoother detonation propagations without chaotic transients, leading to more stable and reliable performance metrics. This study uses high-fidelity numerical techniques such as adaptive mesh refinement (AMR) and the PeleC compressible reacting flow solver. This comprehensive approach enables a thorough evaluation of critical RDE characteristics including detonation velocity, fuel mass flow rate, impulse, thrust, and reverse pressure waves under varying reactant injection conditions. The insights derived from the numerical simulations carried out here enhance the understanding of the fundamental processes governing the performance of RDE concepts.

Source: Applications in Energy and Combustion Science

DOI: 10.1016/j.jaecs.2024.100296

Authors: Sebastian Valencia, Andres Mendiburu, Luis Bravo, Prashant Khare, Cesar Celis

Institutions: Pontificia Universidad Católica del Perú, Universidade Federal do Rio Grande do Sul, DEVCOM Army Research Laboratory, United States Army Combat Capabilities Development Command, University of Cincinnati

Language: English

Topic: Combustion and Detonation Processes

Subfield: Aerospace Engineering

Field: Engineering

Domain: Physical Sciences

Open Access status: gold

Estimated APC paid: $2,000

Funders: National Science Foundation, Air Force Office of Scientific Research, Army Research Laboratory, DEVCOM Army Research Laboratory