Experimental determination of critical conditions for hydrogen-air detonation propagation in partially confined geometry

Rudy, W.; Dziubanii, K.; Żbikowski, Mateusz; Teodorczyk, A.

doi:10.1016/j.ijhydene.2016.04.056

Cited by 19 publications

(7 citation statements)

References 7 publications

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“…Quenching occurs if the detonation is not able to overcome the expansion losses coming from the presence of the interface. Experiments conducted by Rudy et al [15,20,21] and Grune et al [22] to determine the propagation limits of detonations in H 2 -O 2 and H 2 -Air using the same experimental configuration as Dabora et al [18] confirmed their findings, namely a h crit ∼ 3λ for stoichiometric H 2 -Air, and…”

Section: Introductionmentioning

confidence: 60%

Influence of the chemical modeling on the quenching limits of gaseous detonation waves confined by an inert layer

Taileb

Melguizo-Gavilanes

Chinnayya

2020

Combustion and Flame

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The effect of chemistry modeling on the flow structure and quenching limits of detonations propagating into reactive layers bounded by an inert gas is investigated numerically. Three different kinetic schemes of increasing complexity are used to model a stoichiometric H 2-O 2 mixture: single-step, three-step chainbranching and detailed chemistry. Results show that while the macroscopic characteristics of this type of detonations e.g. velocities, cell-size irregularity and leading shock dynamics, are similar among the models tested, their instantaneous structures are significantly different before and upon interaction with the inert layer when compared using a fixed height. When compared at their respective critical heights, h crit , i.e. the reactive layer height at which successful detonation propagation is no longer possible, similarities in their structures become apparent. The numerically predicted critical heights increase as h crit, Detailed � h crit, 3-Step < h crit, 1-Step. Notably, h crit, Detailed was found to be in agreement with experimentally reported values. The physical mechanisms present in detailed chemistry and ne

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Section: Introductionmentioning

confidence: 60%

Influence of the chemical modeling on the quenching limits of gaseous detonation waves confined by an inert layer

Taileb

Melguizo-Gavilanes

Chinnayya

2020

Combustion and Flame

View full text Add to dashboard Cite

show abstract

“…There are some limitations in this work that can be improved in future works. In order to limit the issues to a relatively simple view, one-dimensional simulation carried out here ignores the influence of turbulence, boundary layer, obstacles, heat transfer with walls, triple-point of shockwave and so on [41][42][43][44], which are believed to have non-ignorable effect on temperature distribution and occurrence of auto-ignition.…”

Section: Discussionmentioning

confidence: 99%

Numerical study on transition of hydrogen/air flame triggered by auto-ignition under effect of pressure wave in an enclosed space

Wei

Shang

Cai

et al. 2017

International Journal of Hydrogen Energy

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End gas auto-ignition and transition of flame front are considered as the main causes of severe pressure oscillation in spark-ignition engines, which is one of the major features of knock and superknock. The knowledge of characteristics of auto-ignition, flame front development, propagation of pressure wave and relations between them, still needs to be maintained. In this study, flame front transition induced by pressure wave and auto-ignition are investigated using one-dimensional simulation with detailed chemistry in an enclosed space Calculation cases with different initial thermodynamic conditions are investigated. Mass fraction of OH is employed as indicator of autoignition progress under variable conditions caused by pressure wave. Different propagation modes of flame front, including subsonic deflagration, detonation and supersonic deflagration, are developed under the effects of both pressure wave and auto-ignition. Results show that mass fraction of OH could successfully reflect auto-ignition progress, thus indicating occurrence and sequence of auto-ignition at different locations. Transitions from deflagration to detonation and detonation to supersonic deflagration are found to be triggered by sequential auto-ignition with different gradient of auto-ignition progress ahead of flame front induced by pressure wave.

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“…The fuel is injected at the front end of an air inlet of the aircraft, the detonation of the oblique detonation wave is induced by a shock wave generated by a wedge surface at the lower end of a combustion chamber, and the energy is rapidly released and accelerated through the expansion of a tail nozzle to generate strong thrust (Fig. 1 shows) [8,9] . The ODE has attracted extensive research; its post-wave chemical reaction is more intense and full, with a better diffusion combustion rate and high propulsion potential of nearly isovolumetric combustion [10,11] .…”

Section: Introductionmentioning

confidence: 99%

Study on fuel/air mixing based on oblique detonation engine

Xiang

Xie

et al. 2022

Preprint

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Currently, the inflow conditions used in the study of oblique detonation engines are ideal premixed inflow, and there are few studies on non-premixed inflow. The fuel mixing process in the flow field structure and mixing degree for forming oblique blast waves has essential significance. This paper uses a combination of theoretical analysis and numerical simulation to study the inlet section of the oblique detonation engine. The governing equations are the inviscid Euler equations coupled with chemical reaction source terms, and the second-order TVD scheme is used to solve the equations. First, this paper compared the influence of the single hydrogen nozzle parameters on the flow field structure and the hydrogen mole fraction distribution at the outlet, optimized the hydrogen jet structure, and analyzed the coupling effect between the incoming flow and the jet. The closer the nozzle location is to the supersonic inlet, the lower the Mach number, and the higher the equivalence ratio of hydrogen to oxygen, the better the fuel and air mixing effect. And too large or too small hydrogen injection angle will make the hydrogen too concentrated on the wall and insufficient penetration depth, which reduces the mixing of hydrogen. Secondly, while maintaining the same fuel mass flow rate as the single hydrogen nozzle, this paper increases the number of hydrogen nozzles, thereby increasing the obstruction to the incoming flow and improving the fuel mixing effect. Finally, because the physical ramp and aerodynamic ramp as a method of increasing mixing will lead to fuel concentration on the wall, which is not conducive to the subsequent combustion, this paper proposes an optimization model of the strut injection method. The results show that strut injection can effectively improve the mixing degree of hydrogen and air at the exit and solve the problem of fuel concentration at the wall by using the staggered jet and baroclinic effect of hydrogen. This paper reveals the law of fuel injection in the inlet and provides essential data support for studying oblique detonation engines in a non-premixed environment.

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Experimental determination of critical conditions for hydrogen-air detonation propagation in partially confined geometry

Cited by 19 publications

References 7 publications

Influence of the chemical modeling on the quenching limits of gaseous detonation waves confined by an inert layer

Influence of the chemical modeling on the quenching limits of gaseous detonation waves confined by an inert layer

Numerical study on transition of hydrogen/air flame triggered by auto-ignition under effect of pressure wave in an enclosed space

Study on fuel/air mixing based on oblique detonation engine

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