On the effects of reactant stratification and wall curvature in non-premixed rotating detonation combustors

Athmanathan, Venkat; Braun, James; Ayers, Zachary M.; Fugger, Christopher A.; Webb, Austin M.; Slipchenko, Mikhail N.; Paniagua, Guillermo; Roy, Sukesh; Meyer, Terrence R.

doi:10.1016/j.combustflame.2022.112013

Cited by 49 publications

(2 citation statements)

References 59 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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“…Researchers have examined the impact of the wall curvature and deflagrative losses. Their findings indicate that the detonation wave propagation velocity is lower than the C-J value in the non-premixed or premixed rotating detonation combustors [41,42]. The study investigates the effects of equivalence ratio and inlet mass flux on the propagation characteristics of the rotating detonation wave.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study on the Propagation Characteristics of Rotating Detonation Wave with Liquid Hydrocarbon/High-Enthalpy Air Mixture

Jia,

Zhang,

Meng

et al. 2023

Aerospace

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Rotating detonation engines (RDEs) are a promising propulsion technology featuring high thermal efficiency and a simple structure. To adapt the practical engineering applications of ramjet RDEs, rotating detonation combustion using a liquid hydrocarbon and pure air mixture will be required. This paper presents an experimental study on the propagation characteristics of rotating detonation waves with a liquid hydrocarbon and high-enthalpy air mixture in a hollow cylindrical chamber. The parameters, such as the equivalence ratio and inlet mass flux, are considered in this experiment. The frequency and the propagation velocity of rotating detonation combustion are analyzed under typical operations. The experimental results show that the peak pressure and propagation velocity of the rotating detonation wave are close to the C-J theoretical values under the inlet mass flux of 400 kg/(m2s). Both the propagation velocity and peak pressure of the rotating detonation wave decrease as the mass flux and equivalence ratio are reduced while the number of detonation wavefronts increases. Detonation wave instability tends to occur when the inlet mass flux decreases. There is a transition progress from thermo-acoustic combustion to rotating detonation combustion in the experiment under the condition of mass flux 350 kg/(m2s) and the equivalent ratio 0.8. The static pressure in the chamber is higher during detonation combustion than during thermo-acoustic combustion. These experimental results provide evidence that rotating detonation waves have the potential to significantly improve propulsion performance. The findings can serve as a valuable reference for the practical engineering application of rotating detonation engines.

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Effect of channel expansion angle near injector outlet on a rotating detonation engine performance

Nakajima,

Matsuoka,

Itouyama

et al. 2024

Shock Waves

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A rotating detonation engine (RDE) is expected to achieve a pressure gain (PG) in which the total pressure of the product at the engine exit exceeds the total pressure of the supplied oxidizer. However, many non-ideal phenomena exist in the RDE, which hinder the achievement of a PG. This study focused on the channel expansion angle near injector outlet which is considered to impact the structure of detonation wave and the PG performance. Combustion tests were conducted by varying the channel expansion angle near the axially injected oxidizer injector outlet to 90$$^{\circ }$$ ∘ and 30$$^{\circ }$$ ∘ . As a result, the thrust was not affected by the expansion angle, but the propagation velocity of detonation wave at an expansion angle of 90$$^{\circ }$$ ∘ was approximately 5% higher than that at an expansion angle of 30$$^{\circ }$$ ∘ . A comparison utilizing the pressure increase ratio obtained from the fluctuating pressure in the combustion chamber suggested that the Mach number of the detonation wave was higher for an expansion angle of 90$$^{\circ }$$ ∘ . As a result of evaluating the PG performance utilizing the equivalent available pressure obtained from thrust measurements, it was not confirmed to differ with changes in the expansion angle.

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On the effects of reactant stratification and wall curvature in non-premixed rotating detonation combustors

Cited by 49 publications

References 59 publications

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

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

Experimental Study on the Propagation Characteristics of Rotating Detonation Wave with Liquid Hydrocarbon/High-Enthalpy Air Mixture

Effect of channel expansion angle near injector outlet on a rotating detonation engine performance

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