Dark zones of solid propellant flames: Critically assessed datasets, quantitative model comparison, and detailed chemical analysis

Anderson, William R.; Meagher, Nancy E.; Vanderhoff, John A.

doi:10.1016/j.combustflame.2011.01.010

Cited by 17 publications

(8 citation statements)

References 28 publications

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“…This region is characterized by a large temperature increase, resulting from HCN and NO reacting to final products. The temperature in this zone can approach the adiabatic limit [3].…”

Section: Deflagration In Solid Explosivesmentioning

confidence: 99%

“…The second is the dark zone as illustrated in Figure 1. Within this zone, the intermediate products are comparatively unreactive, causing a time delay for the radicals to build up in concentration before ignition in the luminous flame [3]. The height of the dark zone above the condensed phase is very important in determining the flame structure at low pressures and the burn rate at high pressure.…”

Section: Deflagration In Solid Explosivesmentioning

confidence: 99%

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Modeling Deflagration in Energetic Materials using the Uintah Computational Framework

Beckvermit

Harman

Bezdjian

et al. 2015

Procedia Computer Science

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Predictive computer simulations of highly resolved large-scale 3D deflagrations and detonations are dependent on a robust reaction model embedded in a computational framework capable of running on massively parallel computer architectures. We have been developing such a model in the Uintah Computational Framework, which has exhibited good strong and weak scaling characteristics up to 512K cores [16]. Our focus is on predicting a Deflagration to Detonation Transition (DDT) when a large number of energetic devices are present. An example of this is a semi-tractor-trailer loaded with thousands of mining boosters that rolled over, ignited and went through a DDT. Our current reaction model adapts components from a) Ward, Son and Brewster[22] which incorporates the effects of pressure and initial temperature on deflagration, b) Berghout et al.[9] to model burning in cracks of damaged explosives, and c) Souers[20] for describing fully developed detonation. The reaction model has been subjected to extensive validation against experimental tests. Current efforts are focused on the effects of varying the grid resolution on multiple aspects of deflagration and the transition to detonation.

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“…This region is characterized by a large temperature increase, resulting from HCN and NO reacting to final products. The temperature in this zone can approach the adiabatic limit [3].…”

Section: Deflagration In Solid Explosivesmentioning

confidence: 99%

Section: Deflagration In Solid Explosivesmentioning

confidence: 99%

Modeling Deflagration in Energetic Materials using the Uintah Computational Framework

Beckvermit

Harman

Bezdjian

et al. 2015

Procedia Computer Science

View full text Add to dashboard Cite

show abstract

“…It is widely accepted that the major combustion gaseous products from nitro-based propellants are H 2 O, CO, CO 2 , H 2 , and N 2 , whereas the HCN, NH 3 , CH 4 , nitrogen oxides, benzene, acrylonitrile, toluene, furan, aromatic amines, benzopyrene, and various polycyclic aromatic hydrocarbons are detected in minor concentrations. However, the dark zone of the propellants has much different chemicals as the intermediates with higher molecular weight than those of the luminous flame zone [13]. The gas phase reactions could become more complicated if new energetic ingredients are included.…”

Section: Introductionmentioning

confidence: 99%

Transformation of Combustion Nanocatalysts inside Solid Rocket Motor under Various Pressures

Li¹,

Liu

Fu³

et al. 2019

Nanomaterials

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In this paper, the dependences of the morphology, particle sizes, and compositions of the condensed combustion products (CCP) of modified double-base propellants (1,3,5-trimethylenetrinitramine (RDX) as oxidizer) on the chamber pressure (<35 MPa) and nickel inclusion have been evaluated under a practical rocket motor operation. It has been shown that higher pressure results in smaller average particle sizes of the CCPs. The CCPs of Ni-containing propellants have more diverse morphologies, including spherical particles, large layered structures, and small flakes coated on large particles depending on the pressure. The specific surface area (SSA) of CCPs is in the range of 2.49 to 3.24 m2 g−1 for propellants without nickel are less dependent on the pressure, whereas it is 1.22 to 3.81 Ni-based propellants. The C, N, O, Al, Cu, Pb, and Si are the major elements presented on the surfaces of the CCP particles of both propellants. The compositions of CCPs from Ni-propellant are much more diverse than another one, but only three or four major phases have been found for both propellants under any pressure. The metallic copper is presented in CCPs for both propellants when the chamber pressure is low. The lead salt as the catalyst has been transformed in to Pb(OH)Cl as the most common products of lead-based catalysts with pressure lower than 15 MPa. When pressure is higher than 5 MPa, the nickel-based CCPs has been found to contain one of the following crystalline phases: Pb2Ni(NO2)6, (NH4)2Ni(SO4)2·6H2O, C2H2NiO4·2H2O, and NiO, depending on the pressure.

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“…The foam layer is a two-phase region that is composed of liquid and gas bubbles which are formed by decomposition and evaporation. The dark zone is a gas-phase region where relatively slow reactions occur, usually involving NO, N 2 O and HCN [73,74]. The temperature increases from the liquid's boiling point (or decomposition temperature) to its adiabatic flame temperature in this transition zone (foam layer and dark zone).…”

Section: Combustion Of Tmeda·8hnomentioning

confidence: 99%

Spray and Combustion of Gelled Hypergolic Propellants for Future Rocket and Missile Engines

Thynell¹,

Adair²,

Goddard³

et al. 2014

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Dark zones of solid propellant flames: Critically assessed datasets, quantitative model comparison, and detailed chemical analysis

Cited by 17 publications

References 28 publications

Modeling Deflagration in Energetic Materials using the Uintah Computational Framework

Modeling Deflagration in Energetic Materials using the Uintah Computational Framework

Transformation of Combustion Nanocatalysts inside Solid Rocket Motor under Various Pressures

Spray and Combustion of Gelled Hypergolic Propellants for Future Rocket and Missile Engines

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