Computational Study of Reactants Mixing in a Rotating Detonation Combustor Using Compressible RANS

Weiß, S.; Bohon, Myles D.; Paschereit, Christian Oliver; Gutmark, Ephraim

doi:10.1007/s10494-019-00097-x

Cited by 11 publications

(3 citation statements)

References 32 publications

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“…for the mass flow rate _ m of H 2 limited by the stoichiometric proportion with the locally available O 2 , with respect to the greater of the mass flow rate of H 2 or its stoichiometric value defined by the locally available O 2 . The first observation is consistent with other numerical and experimental findings from (Weiss et al, 2020;Prakash et al, 2021;Sato et al, 2021;Athmanathan et al, 2022;Pal et al, 2023). More details about the SI injection element can be found in the previously referenced publications by Gaillard et al (2019).…”

Section: Injection Element Of Semi-impingement Typesupporting

confidence: 89%

Rotating detonation combustors for propulsion: Some fundamental, numerical and experimental aspects

Naour¹,

Davidenko

Gaillard

et al. 2023

Front. Aerosp. Eng.

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Propulsion systems based on the constant-pressure combustion process have reached maturity in terms of performance, which is close to its theoretical limit. Technological breakthroughs are needed to develop more efficient transportation systems that meet today’s demands for reduced environmental impact and increased performance. The Rotating Detonation Engine (RDE), a specific implementation of the detonation process, appears today as a promising candidate due to its high thermal efficiency, wide operating Mach range, short combustion time and, thus, high compactness. Following the first proofs of concept presented in the 1960s, the last decade has seen a significant increase in laboratory demonstrators with different fuels, injection techniques, operating conditions, dimensions and geometric configurations. Recently, two flight tests of rocket-type RDEs have been reported in Japan and Poland, supervized by Professors Kasahara (Nagoya University) and Wolanski (Warsaw University), respectively. Engineering approaches are now required to design industrial systems whose missions impose efficiency and reliability constraints. The latter may render ineffective the simplified solutions and configurations developed under laboratory conditions. This requires understanding the fundamentals of detonation dynamics relevant to the RDE and the interrelated optimizations of the device components. This article summarizes some of the authors’ experimental and numerical work on fundamental and applied issues now considered to affect, individually or in combination, the efficiency and reliability of the RDE. These are the structure of the detonation reaction zone, the detonation dynamics for rotating regimes, the injection configurations, the chamber geometry, and the integration constraints.

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Section: Injection Element Of Semi-impingement Typesupporting

confidence: 89%

Rotating detonation combustors for propulsion: Some fundamental, numerical and experimental aspects

Naour¹,

Davidenko

Gaillard

et al. 2023

Front. Aerosp. Eng.

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“…5a is most likely due to impingement of the jet exiting the injector on the center body. The sharp turn at the junction between the air gap and the combustor annulus is also expected to create separation bubbles that would also induce a forward pressure loss [14].…”

Section: Comparison To the Baseline Geometrymentioning

confidence: 99%

Effects of Increased RDC Injector Diodicity

Bischoff

Rehberg

Barnouin

et al. 2023

AIAA AVIATION 2023 Forum

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High-diodicity inlets seem like an ideal candidate for minimizing pressure losses during reactant injection in Rotating Detonation Combustors (RDC) while offering a higher resistance to backflow. In this study, the effect of a diode geometry in an RDC air injector is investigated experimentally and numerically. Different geometries based on the Tesla valve are implemented in the air injector and tested under non-reacting conditions. The effect of the diode geometry on pressure losses in both flow directions and on the diodicity is investigated. It is observed that the diode feature only minimally affects the forward pressure loss while showing an increased pressure loss for the reverse flow of up to approximately 45% at high mass fluxes. Key geometric parameters of the chosen diode geometry for increasing the diodicity are identified throughout this study. A parallel numerical study of a representative diode geometry offers insight on the flow structure for both flow directions. For the forward flow a pair of counter-rotating vortices is formed inside the diode feature while for the reverse flow a single vortex is formed.

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“…The development of a plane wave disturbance leads to the formation of a cellular detonation structure [12]. Rotating detonation have been studied experimentally and numerically in [13,14]. Studies of continuous circular detonation show that the front of detonation combustion is a complex shock-wave structure consisting of at least two triple configurations.…”

Section: Introductionmentioning

confidence: 99%

Multi-point ignition of air/fuel mixture by the initiated subcritical streamer discharge

et al. 2022

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Computational Study of Reactants Mixing in a Rotating Detonation Combustor Using Compressible RANS

Cited by 11 publications

References 32 publications

Rotating detonation combustors for propulsion: Some fundamental, numerical and experimental aspects

Rotating detonation combustors for propulsion: Some fundamental, numerical and experimental aspects

Effects of Increased RDC Injector Diodicity

Multi-point ignition of air/fuel mixture by the initiated subcritical streamer discharge

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