Study of the Effects of Various Injection Geometries on the Operation of a Rotating Detonation Engine

Duvall, James; Chacon, Fabian; Harvey, Chadwick; Gamba, Mirko

doi:10.2514/6.2018-0631

Cited by 35 publications

(6 citation statements)

References 20 publications

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“…Explanations for this deficit can be attributed to the curvature effect, compared to a theoretical 1D detonation, and also to mixture heterogeneities. According to the authors, a lower mixing efficiency could also be responsible for the unstable regime with two counter-rotating waves (Duvall et al, 2018). also observed a speed deficit of about 20% compared to the CJ speed for a similar injection configuration.…”

Section: Toward Partially Premixed Injectionmentioning

confidence: 92%

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: Toward Partially Premixed Injectionmentioning

confidence: 92%

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

Naour¹,

Davidenko

Gaillard

et al. 2023

Front. Aerosp. Eng.

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show abstract

“…For successful engine operation, propellant injection and mixing must occur within the period of the detonation wave (or wavetrain, should multiple wave fronts be present) [14][15][16]. Similarly, the hot exhaust products need to be expelled before appreciable reintroduction of propellant can occur -otherwise, propellant injection may co-exist with hot products and promote parasitic deflagration (combustion not associated with a traveling wave -a loss mechanism [17,18]) within the combustion chamber.…”

Section: A Experiments Geometry and Dynamicsmentioning

confidence: 99%

Modeling Thermodynamic Trends of Rotating Detonation Engines

Koch,

Kutz

2020

Preprint

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The formation of a number of co-and counter-rotating coherent combustion wave fronts is the hallmark feature of the Rotating Detonation Engine (RDE). The engineering implications of wave topology are not well understood nor quantified, especially with respect to parametric changes in combustor geometry, propellant chemistry, and injection and mixing schemes. In this article, a modeling framework that relates the time and spacial scales of the RDE to engineering performance metrics is developed and presented. The model is built under assumptions of backpressure-insensitivity and nominally choked gaseous propellant injection. The Euler equations of inviscid, compressible fluid flow in one dimension are adapted to model the combustion wave dynamics along the circumference of an annular-type rotating detonation engine. These adaptations provide the necessary mass and energy input and output channels to shape the traveling wave fronts and decaying tails. The associated unit processes of injection, mixing, combustion, and exhaust are all assigned representative time scales necessary for successful wave propagation. We find that the separation, or lack of, these time scales are responsible for the behavior of the system, including wave co-and counterpropagation and bifurcations between these regimes and wave counts. Furthermore, as there is no imposition of wave topology, the model output is used to estimate the net available mechanical work output and thermodynamic efficiency from the closed trajectories through pressure-volume and temperature-entropy spaces. These metrics are investigated with respect to variation in the characteristic scales for the RDE unit physical processes.

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“…While this is for a typical configuration, other variations where the entire cylindrical region is used (Yao et al, 2017) or the detonation passes radially (Huff et al, 2019;Sato et al, 2017) have also been studied (Zhou et al, 2016). The design of the injectors is a critical challenge in RDEs (Duvall et al, 2018;Rankin et al, 2017). If the pressure in the annulus is less than the critical pressure, the throat is choked, leading to constant mass flow rate.…”

Section: Introductionmentioning

confidence: 99%

Numerical and boundary condition effects on the prediction of detonation engine behavior using detailed numerical simulations

Sato

Beck

Raman

2023

Front. Aerosp. Eng.

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High-fidelity numerical simulations of an experimental rotating detonation engine with discrete fuel/air injection were conducted. A series of configurations with different feed-plenum pressures but with constant equivalence ratio were studied. Detailed chemical kinetics for the hydrogen/air system is used. A resolution study for the full rotating detonation engine (RDE) system simulation is also conducted. Two kinds of boundary conditions, a total pressure boundary and a constant mass flow rate boundary, are used to assess the effects of the inlet boundary. As mass flow rate is increased, the total pressure boundary causes more error in the axial pressure distribution while the constant mass flow rate gives a better solution for all cases ran. The simulations confirm experimental findings, and reproduce qualitative as well as some of the quantitative trends. These results demonstrate that a) fuel-air mixing is highly non-uniform within the detonation chamber, leading to variations in local equivalence ratio, b) the fuel and oxidizer injectors experience significant backflow as the detonation wave passes over, but recover at different rates which further augments the inefficiencies in mixing, and c) parasitic combustion in the mixing region makes the detonation wave weak by extending the reaction zone across the wave.

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Study of the Effects of Various Injection Geometries on the Operation of a Rotating Detonation Engine

Cited by 35 publications

References 20 publications

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

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

Modeling Thermodynamic Trends of Rotating Detonation Engines

Numerical and boundary condition effects on the prediction of detonation engine behavior using detailed numerical simulations

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