Detonation diffraction from circular tubes to cones

Khasainov, Boris; Presles, Henri‐Nöel; Desbordes, D.; Demontis, Pietro; Vidal, Pierre

doi:10.1007/s00193-005-0262-9

Cited by 43 publications

(22 citation statements)

References 3 publications

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“…Some computed solutions are compared with other works in Table 4. The minimum induction zone length was found to be 15 mm in the present computations, which is pretty close to the result (0.147 cm) by Joseph et al [33] while a little small than the result (0.16 cm) by Qu [34]; nevertheless, much larger than the reported value (2.0×10 3 cm)by Oran et al [35].…”

Section: One-dimensional Detonationsupporting

confidence: 88%

Additive Runge-Kutta methods for H2/O2/Ar detonation with a detailed elementary chemical reaction model

Ren

Ning

2013

Chin. Sci. Bull.

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We report here the additive Runge-Kutta methods for computing reactive Euler equations with a stiff source term, and in particular, their applications in gaseous detonation simulations. The source term in gaseous detonation is stiff due to the presence of wide range of time scales during thermal-chemical non-equilibrium reactive processes and some of these time scales are much smaller than that of hydrodynamic flow. The high order, L-stable, additive Runge-Kutta methods proposed in this paper resolved the stiff source term into the stiff part and non-stiff part, in which the stiff part was solved implicitly while the non-stiff part was handled explicitly. The proposed method was successfully applied to simulating the gaseous detonation in a stoichiometric H 2 /O 2 /Ar mixture based on a detailed elementary chemical reaction model comprised of 9 species and 19 elementary reactions. The results showed that the stiffly accurate additive Runge-Kutta methods can capture the discontinuity well, and describe the detonation complex wave configurations accurately such as the triple wave structure and cellular pattern. Reacting flows, specifically in gaseous combustion, have been a significant topic of active research for more than one hundred years. The strong coupling between hydrodynamic flow and chemical kinetics is complex and even today many phenomena are not very well understood yet. Gaseous detonation is a process of supersonic combustion in which a shock wave is propagated and supported by the energy release in a reaction zone behind it. It is the more powerful and destructive of the two general classes of combustion, the other one being deflagration. The primary difficulty in computing reacting flows is the source term stiffness inherent in the reactive Euler equations in temporal integrations. Besides, the viscous stress and heat flux terms in the boundary layers can cause the stiffness too. The source terms are stiff because the thermal-chemical non-equilibrium reactive processes possess a wide range of time scales and some of them are much smaller than that of hydrodynamic flow [1]. The simulation will be inefficient when the explicit methods rather than the implicit methods are used, because the time-step sizes dictated by the stability restraint in explicit methods are much smaller than those required by the CFL condition. Due to these limitations in explicit methods, the implicit methods are normally required to simulate gaseous detonation. The practical implicit methods for gaseous detonation simulation can be categorized into two classes, i.e. the time-splitting method and the additive semi-implicit method [2,3].The time-splitting methods [4][5][6][7][8], resolve the source term of reactive Euler equations into ( ) ( ),   t

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Section: One-dimensional Detonationsupporting

confidence: 88%

Additive Runge-Kutta methods for H2/O2/Ar detonation with a detailed elementary chemical reaction model

Ren

Ning

2013

Chin. Sci. Bull.

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“…[14][15][16] or a cone-shaped exit with a gradual area change that reduces lateral expansion. [17][18][19][20] To enhance the transmission efficiency of the pre-detonator, a combination method using a "reflector" and "overfilling" of the driver gas was proposed in references 21) and 22), as shown in Fig. 1(b).…”

Section: Introductionmentioning

confidence: 99%

Influence of Channel Width on Cylindrical Detonation Wave Propagation

Kameyama

Nawata

Himono

et al. 2016

AEROSPACE TECHNOLOGY JAPAN

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To achieve stable detonation wave propagation to large-bore pulse detonation engine (PDE) combustors, we investigated an initiator for PDEs that uses a pre-detonator, reflector, and driver gas. In this initiator, a planar detonation wave from the pre-detonator becomes a cylindrical detonation wave after collision with the reflector. Wakita et al. previously posited two hypotheses regarding the dominant factors that determine the threshold of propagation to the target gas, which is a stoichiometric hydrogen-oxygen mixture diluted with nitrogen. This study reveals whether the threshold is determined by w/λ or λ/r. To analyze the effect of channel width w on the transition of the cylindrical detonation wave, experiments were conducted for w = 10 mm and w = 15 mm. However, the results could not elucidate whether the threshold is determined by λ/r or w/λ. To clearly distinguish between the effects of w/λ and λ/r, a narrow channel width w' = 3 mm was chosen and implemented using a torus-shaped obstacle. The results showed that a cylindrical detonation wave propagates without quenching when the nitrogen concentration is above 40%, corresponding to the cell size λ greater than w. Accordingly, the cylindrical detonation propagation threshold was determined to be independent of w/λ.

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“…However, subsequent experimental studies showed that d c = 13 is not realized, as reviewed in [13]. Many methods for enhancing the detonation transition at the abrupt change of area have been proposed, and typical methods include the use of 1) shock reflection and shock-focusing devices [14][15][16] and 2) a cone-shaped exit with a gradual area change that reduces the lateral expansion [12,[17][18][19].…”

Section: Introductionmentioning

confidence: 99%

Detonation Transition Around Cylindrical Reflector of Pulse Detonation Engine Initiator

Wakita

Tamura

Terasaka

et al. 2013

Journal of Propulsion and Power

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To achieve reliable transmission of detonation waves to a pulse detonation engine (PDE) combustor (detonation chamber), the authors propose a PDE initiator that uses a cylindrical reflector downstream of a predetonator exit. The detonation wave propagates around the reflector to change the wave shape in three transition stages: from a planar detonation wave in the predetonator to an expanding cylindrical detonation wave, from the cylindrical wave to a planar toroidal detonation wave, and from the toroidal wave to a planar

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Detonation diffraction from circular tubes to cones

Cited by 43 publications

References 3 publications

Additive Runge-Kutta methods for H2/O2/Ar detonation with a detailed elementary chemical reaction model

Additive Runge-Kutta methods for H2/O2/Ar detonation with a detailed elementary chemical reaction model

Influence of Channel Width on Cylindrical Detonation Wave Propagation

Detonation Transition Around Cylindrical Reflector of Pulse Detonation Engine Initiator

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