Response of a burning heterogeneous propellant to small pressure disturbances

Buckmaster, J.; Jackson, T. L.; Massa, Luca; Ulrich, M.

doi:10.1016/j.proci.2004.07.024

Cited by 8 publications

(7 citation statements)

References 5 publications

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“…Instantaneous total heat output generated from the three-dimensional combustion code. The surface regression and consumption of heterogeneous units in the propellant are evident.The numerical framework described above is currently being used to investigate a variety of important issues: the burning of non-spherical AP particles; proper LES boundary conditions; the acoustic response of heterogeneous propellant combustion[125]; extracting 1-D descriptions for coupling with large scale solid rocket motor simulations[126]; and ejection of aluminum from the burning surface into the chamber flow[127][128][129].This massively parallel, 3D model of propellant burning describes a process which is itself only one of many submodels within a larger, massively parallel model of an entire solid fuel rocket motor. In addition to the propellant combustion, the material dynamics of the rocket case and the joints between case sections are simulated, flow through the exit nozzle is fully resolved, surface regression of the propellant is followed as the propellant burns, acoustic stability of the interior gas flow is examined, and accumulation of aluminum slag in the region near the exhaust nozzle and its effects of restricting exit flows are all included in the fully 3D model.…”

mentioning

confidence: 99%

Computational combustion

Westbrook

Mizobuchi

Poinsot

et al. 2005

Proceedings of the Combustion Institute

226

119

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Progress in the field of computational combustion over the past 50 years is reviewed. Particular attention is given to those classes of models that are common to most system modeling efforts, including fluid dynamics, chemical kinetics, liquid sprays, and turbulent flame models. The developments in combustion modeling are placed into the time-dependent context of the accompanying exponential growth in computer capabilities and Moore's Law. Superimposed on this steady growth, the occasional sudden advances in modeling capabilities are identified and their impacts are discussed. Integration of submodels into system models for spark ignition, diesel and homogeneous charge, compression ignition engines, surface and catalytic combustion, pulse combustion, and detonations are described. Finally, the current state of combustion modeling is illustrated by descriptions of a very large jet lifted 3D turbulent hydrogen flame with direct numerical simulation and 3D large eddy simulations of practical gas burner combustion devices.

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mentioning

confidence: 99%

Computational combustion

Westbrook

Mizobuchi

Poinsot

et al. 2005

Proceedings of the Combustion Institute

226

119

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“…When there are multiple peaks (greater than 1), multiple modes will be ampli¦ed. For other packs examined in [16], the real part of R is also greater than 1 for some frequencies, with the possibility of L * -instability.…”

Section: Pressure Fluctuationsmentioning

confidence: 90%

“…Both questions identi¦ed here have been examined in [16], albeit for a two-dimensional (2D) propellant. Figure 7 shows the results for one set of calculations reported in [16].…”

Section: Pressure Fluctuationsmentioning

confidence: 99%

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Issues related to heterogeneous solid-propellant combustion

Jackson

2011

Progress in Propulsion Physics

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Over the past decade, a considerable amount of e¨orts has been dedicated to computational simulations of heterogeneous solid-propellant combustion. A variety of tools have emerged from those studies. The most important are the modeling of propellant morphology, homogenization, and an unsteady three-dimensional (3D) combustion code with complete coupling of the gas-phase combustion processes and the solidphase heat conduction across the unsteadily regressing nonplanar propellant surface. The combustion code is both parallel and scalable. These tools have been applied to the study of both nonaluminized and aluminized (conventional size Al and nano-Al) heterogeneous propellants. A number of important problems will be reviewed using these tools.

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“…For example, we recently examined the response to small-pressure disturbances created by an impinging acoustic wave. 5 The results of Ref. 1 are for random packs of AP disks and those of Refs.…”

Section: Introductionmentioning

confidence: 95%

Burning of Ammonium-Perchlorate Ellipses and Spheroids in Fuel Binder

Wang

Buckmaster

Jackson

2006

Journal of Propulsion and Power

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Our simulations of heterogeneous propellant combustion have always assumed that the oxidizer particles (ammonium perchlorate) are disks (two dimensional) or spheres (three dimensional). Here the effects on the burning rate are examined when the disks/spheres are replaced by ellipses/ellipsoids. In two dimensions, it is shown that an area-preserving deformation of a pack of disks, generating a pack of ellipses, can lead to significant variations in the burning rate. However, if the ellipses are randomly packed, so that the alignment of their axes is random, the shape effect is small. In three dimensions, volume-preserving deformation, which generates ellipsoids, leads to burning rate changes no greater than those in two dimensions. Absent a random packing algorithm for ellipsoids, it is speculated that here also a random alignment of the axes would eliminate the effect.

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Response of a burning heterogeneous propellant to small pressure disturbances

Cited by 8 publications

References 5 publications

Computational combustion

Computational combustion

Issues related to heterogeneous solid-propellant combustion

Burning of Ammonium-Perchlorate Ellipses and Spheroids in Fuel Binder

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