Numerical simulation of a Rotating Detonation with a realistic injector designed for separate supply of gaseous hydrogen and oxygen

Gaillard, Thomas; Davidenko, Dmitry; Dupoirieux, F.

doi:10.1016/j.actaastro.2017.09.011

Cited by 72 publications

(21 citation statements)

References 31 publications

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“…3e indicates 33% of the injected fuel is consumed at the surface of contact, so only 67% of the reactive mixture is burned by detonation combustion. A similar phenomenon is also observed by Gaillard et al (2017) that 30% of the injected mass is consumed by the contact-surface chemical reaction. Such chemical reactions burn fuel at approximately constant pressure conditions, so they generate more entropy than detonation combustion (Kailasanath, 2000;Heiser and Pratt, 2002), which is unfavorable to improve the thermal cycle efficiency.…”

Section: Flow Field Of Stratified Injectionsupporting

confidence: 79%

“…Due to the unique advantages of detonation combustion, more scholars have begun to pay attention to the use of detonation to achieve aerospace propulsion. In recent years, the use of detonation for energy release in engines As injection remains the key issue affecting RDE's performance, a large number of studies on the effect of injection have been carried out Tsuboi et al, 2015;Gaillard et al, 2017;Smirnov et al, 2018Smirnov et al, , 2019Zhang et al, 2018;Wang et al, 2019;Zheng YS et al, 2019). Smirnov et al (2018Smirnov et al ( , 2019 tested the initiation and propagation process of rotating detonation wave using three types of gas mixture and different injection patterns.…”

Section: Introductionmentioning

confidence: 99%

“…Their results showed that it was the interaction of the products and fresh gas occurring on the fuel-detonation products' contact surface that affected the detonation stability. In (Gaillard et al, 2017), a developed flame surface was observed around the fuel-detonation products' contact surface. Injection through discrete holes caused nearly 30% consumption of the injected mass by deflagration, which was unfavorable to the improvement of the thermal cycle efficiency.…”

Section: Introductionmentioning

confidence: 99%

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Performance of rotating detonation engine with stratified injection

Lei

Yang

Ding

et al. 2020

J. Zhejiang Univ. Sci. A

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In this study, a numerical study based on Euler equations and coupled with detail chemistry model is used to improve the propulsion performance and stability of the rotating detonation engine. The proposed fuel injection called stratified injection functions by suppressing the isobaric combustion process occurring on the contact surface between fuel and detonation products, and thus the proportion of fuel consumed by detonation wave increases from 67% to 95%, leading to more self-pressure gain and lower entropy generation. A pre-mixed hydrogen-oxygen-nitrogen mixture is used as a reactive mixture. The computational results show that the propulsion performance and the operation stability of the engine with stratified injection are both improved, the temperature of the flow field is notably decreased, the specific impulse of the engine is improved by 16.3%, and the average temperature of the engine with stratified injection is reduced by 19.1%.

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Section: Flow Field Of Stratified Injectionsupporting

confidence: 79%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Performance of rotating detonation engine with stratified injection

Lei

Yang

Ding

et al. 2020

J. Zhejiang Univ. Sci. A

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“…Some preliminary 3D simulations were also studied. [18][19][20][21][22][23] Eude et al 24 used the adaptive mesh refinement to calculate the 3D simulations of RDE. They found that the pressures at inner and outer wall were different because of the effect of the curvature, and the effected curvature become larger when the chamber diameter reduced and the chamber width increased.…”

Section: Introductionmentioning

confidence: 99%

Propagation characteristics of rotating detonation wave in plane–radial structure with different pressure conditions

Xia

Zhuo

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper simulates the propagation characteristics of rotating detonation wave in the plane–radial structure for mixtures of 2H2 + O2 + 3.76N2. Two-dimensional numerical simulation was modeled, and two kinds of typical flow field and corresponding operating range were obtained under various pressure conditions. Due to the influence of curvature, the detonation wave is strengthened near the outer concave boundary and weakened near the inner convex one. The pressure ratio was varied from 1.6 to 10 by varying both stagnation and back pressure for detonation parameters and flow parameters. It is found that these parameters are dependent only on stagnation pressure for higher pressure ratio. While the pressure ratio is low, the back pressure also has an effect on them. The detonation wave height initially increases and then decreases as stagnation pressure increases, and the pressure ratio has a significant effect on it for lower pressure ratio. The inlet block ratio varies slightly from 14% to 21%. The exit average Mach number has small fluctuations between 0.89 and 1.05. The exit supersonic flow ratio varies from 14% to 74%, and the peak value is gained when pressure ratio is 6. The exit pressure amplifying ratio varies from 1.45 to 1.95, and the maximum value is obtained when pressure ratio is 2.5.

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“…This reactant fill-zone is where fuel and oxidizer are available for combustion just upstream of each detonation wave. In this way, each successive detonation wave passes through sufficient fuel and oxidizer to sustain it [6]. Above each detonation wave, an oblique shock and shear layer form.…”

Section: Introduction 1rdre Overviewmentioning

confidence: 99%

Descending Modal Transition Dynamics in a Large Eddy Simulation of a Rotating Detonation Rocket Engine

et al. 2021

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Rotating detonation rocket engines (RDREs) exhibit various unsteady phenomena, including modal transitions, that significantly affect their operation, performance and stability. The dynamics of the detonation waves are studied during a descending modal transition (DMT) where four co-rotating detonations waves decrease to three in a gaseous methane-oxygen RDRE. Detonation wave tracking is applied to capture, visualize and analyze unsteady, 3D detonation wave dynamics data within the combustion chamber of the RDRE. The mechanism of a descending modal transition is the failure of a detonation wave in the RDRE, and in this study, the failing wave is identified along with its failure time. The regions upstream of each relative detonation show the mixture and flow-field parameters that drive detonation failure. Additionally, it is shown that descending modal transitions encompass multiple phases of detonation decay and recovery with respect to RDREs. The results show high upstream pressure, heat release and temperature, coupled with insufficient propellants, lead to detonation wave failure and non-recovery of the trailing detonation wave during a descending modal transition. Finally, the Wolanski wave stability criterion regarding detonation critical reactant mixing height provides insight into detonation failure or sustainment.

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Numerical simulation of a Rotating Detonation with a realistic injector designed for separate supply of gaseous hydrogen and oxygen

Cited by 72 publications

References 31 publications

Performance of rotating detonation engine with stratified injection

Performance of rotating detonation engine with stratified injection

Propagation characteristics of rotating detonation wave in plane–radial structure with different pressure conditions

Descending Modal Transition Dynamics in a Large Eddy Simulation of a Rotating Detonation Rocket Engine

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