Numerical Modeling of Supersonic Combustion: Validation and Vitiation Studies Using FLUENT

Mattick, Stephen J.; Frankel, Steven

doi:10.2514/6.2005-4287

Cited by 6 publications

(7 citation statements)

References 12 publications

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“…In the domain of supersonic combustion, many scholars have made a comparative analysis of these two turbulence models. Mattick and Frankel [39] conducted numerical simulation with Fluent for the study on the vitiation effects of supersonic combustion flow using these two models and found that they have their own advantages and disadvantages. In general, the Realizable k-ε model was better in predicting jet flow field, but both models were unsatisfactory in terms of reaction flow field, which might be caused by the defects of early Fluent platform and the simple combustion model.…”

Section: Turbulence Models and Subgrid Modelsmentioning

confidence: 99%

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Supersonic Combustion Modeling and Simulation on General Platforms

et al. 2022

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Supersonic combustion is an advanced technology for the next generation of aerospace vehicles. In the last two decades, numerical simulation has been widely used for the investigation on supersonic combustion. In this paper, the modeling and simulation of supersonic combustion on general platforms are thoroughly reviewed, with emphasis placed on turbulence modeling and turbulence–chemistry interactions treatment which are both essential for engineering computation of supersonic combustion. It is found that the Reynolds-averaged Navier–Stokes methods on the general platforms have provided useful experience for the numerical simulation in engineering design of supersonic combustion, while the large eddy simulation methods need to be widely utilized and further developed on these platforms. Meanwhile, the species transport models as a kind of reasonable combustion model accounting for the turbulence–chemistry interactions in supersonic combustion have achieved good results. With the development of new combustion models, especially those designed in recent years for high-speed combustion, the turbulence–chemistry interactions treatment for numerical simulation of supersonic combustion based on general platforms is expected to be further mature in the future.

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Section: Turbulence Models and Subgrid Modelsmentioning

confidence: 99%

“…In the study of two kinds of combustor, Mattick and Frankel [39] adopted the finiterate model, based on the detailed reaction mechanism, and the eddy-dissipation model, based on the global reaction mechanism and EDC model, respectively. For the coaxial jet combustor, the Composition PDF Transport model was adopted.…”

Section: Combustion Modelsmentioning

confidence: 99%

Supersonic Combustion Modeling and Simulation on General Platforms

et al. 2022

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“…For the turbulent combustion model, the non-premixed equilibrium PDF (probability density function) approach [14,15] is applied to simulate the gas phase reaction of C 4 H 6 . The basis of the non-premixed modeling approach is that under a certain set of simplifying assumptions, the instantaneous thermochemical state of the fluid is related to a conserved scalar quantity known as the mixture fraction f defined as follows:…”

Section: Mathematic and Physical Modelsmentioning

confidence: 99%

Numerical investigation on cavity structure of solid-fuel scramjet combustor

Pei

Hou

2014

Acta Astronautica

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“…5 The vitiation effects in dual mode scramjet combustors were experimentally and numerically studied. 6,14 Critical issues regarding dual mode scramjet combustors are discussed in detail in the previous work. 4,7,10,[13][14][15][20][21][22][23][24][25] This study investigates the effects of the inlet conditions on the dual-mode combustor flow field.…”

Section: Introductionmentioning

confidence: 99%

A three-dimensional computational study of the effect of the inlet conditions on supersonic mixing and combustion

Abdel-Salam

Micklow

2012

Proceedings of the Institution of Mechanical Engineers, Part G:

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In recent years, a significant amount of high-speed combustion research has been directed toward optimization of scramjet combustors, and in particular on the efficiency of fuel-air mixing and reaction taking place in the engine. This article numerically investigates the flow characteristics of a dual-mode scramjet-combustor configuration. Results are presented for a three-dimensional combustor model with a single wall-mounted raised (compression) ramp as a fuel injector. Hydrogen is used as the fuel and is injected through the raised ramp (which has an aspect ratio of 0.5) parallel to the air stream. Vitiated air with different concentrations of H 2 O and CO 2 are used at the inlet boundary. Three equivalence ratios were simulated, 0.25, 0.31, and 0.41. Numerical results are obtained using a finite volume computational fluid dynamics code. Initially, three forms of the two-equation k-" turbulent model were tested: the standard, the RNG, and the realizable with unstructured grids. Final results were obtained with the RNG form of the k-" turbulent model. Results show that the combustion efficiency decreases with the increase of the equivalence ratio. Also, the cases with CO 2 show slightly higher combustion efficiencies.

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Numerical Modeling of Supersonic Combustion: Validation and Vitiation Studies Using FLUENT

Cited by 6 publications

References 12 publications

Supersonic Combustion Modeling and Simulation on General Platforms

Supersonic Combustion Modeling and Simulation on General Platforms

Numerical investigation on cavity structure of solid-fuel scramjet combustor

A three-dimensional computational study of the effect of the inlet conditions on supersonic mixing and combustion

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