Soot and radiation modeling in laminar ethylene flames with tabulated detailed chemistry

Dorey, Luc-Henry; Bertier, Nicolas; Tessé, Lionel; Dupoirieux, F.

doi:10.1016/j.crme.2011.09.004

Cited by 14 publications

(9 citation statements)

References 68 publications

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“…The times for the MDA are further split into computations including (w wall term) and excluding (w/o wall term) the wall term calculation in Eqs. (14)e (16). For the latter, predetermined fields for G w of a previous time step were used.…”

Section: Appendix D Optimum Number Of Gray Gases In the Slwmentioning

confidence: 99%

Detailed radiation modeling of a partial-oxidation flame

Garten

Hunger

Messig

et al. 2015

International Journal of Thermal Sciences

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Section: Appendix D Optimum Number Of Gray Gases In the Slwmentioning

confidence: 99%

Detailed radiation modeling of a partial-oxidation flame

Garten

Hunger

Messig

et al. 2015

International Journal of Thermal Sciences

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“…The radiative power emitted by a gaseous cell is computed by Eq. 15 which considers that soot particles are the main radiator in the gas phase [30], [45]. The cold reference temperature [46] ( ) is taken at the initial system temperature of 280 K. The equivalent surface of soot is given by the product where the term represents the soot specific area and taken at 8 cm -1 as the average value found in reference [47] and the term is a cell volume.…”

Section: Eq 12mentioning

confidence: 99%

Micro and Full-Scale Experiments on Hybrid Rocket Fuel and Prelude to Hybrid Rocket Combustor Simulations

Mangeot

Gascoin

Gillard³

2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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The high density polyethylene, as hybrid rocket fuel, has been chosen to be studied. Thermogravimetric analysis allowed to determine an Arrhenius type equation for its regression rate. A flash pyrolysis coupled to GC/MS/FID has been used to observe influence of oxidative environment on pyrolysis byproducts quantity. With a test bench, the regression rate of the solid fuel under various conditions (pressure, oxidizer mass flow rate, oxygen mass fraction) has been evaluated at an average value of 0.2 mm.s -1 . The Marxman law is completed with other studies conducted at higher oxidizer mass flow rates, between 0.6 and 20 g.s -1 .cm -2 . Finally, the first hybrid rocket combustor simulation is presented along its governing equations. Preliminary comparison gives a numerical regression rate 10% above the value found during experimental firing despite assumptions on the gas phase model. Nomenclature= nozzle throat area = pre-exponential factor = specific heat = energy of activation = soot particle diameter = form factor = soot volume fraction = body forces = oxidizer mass flow rate = enthalpy of reaction

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“…[22][23][24]. As far as computational validation is concerned, the implemented models for two-phase flows, combustion, and turbulence have also been extensively validated and assessed through many previous investigations, such as those recently conducted by Chedevergne [25], Dorey et al [26], Sainte-Rose et al [27], Chedevergne et al [28], or Doisneau et al [29]. Three different numerical simulations will be reported later to address the grid sensitivity issue.…”

Section: Numerical Aspectsmentioning

confidence: 99%

Computational Fluid Dynamics Investigation of a Mach 12 Scramjet Engine

Moule

Sabelnikov

Mura

et al. 2014

Journal of Propulsion and Power

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The description of combustion in high-speed turbulent flows, where turbulent mixing, compressibility effects, and chemical kinetics processes are competing, still remains a challenging issue for numerical simulations. The key features of such turbulent supersonic reactive flows are integrated into a turbulence-chemistry interaction closure, which relies on the partially stirred reactor framework. The corresponding closure, hereafter denoted as the unsteady partially stirred reactor model, is incorporated into the ONERA computational fluid dynamics code CEDRE. The computational model is used to investigate a Mach 12 rectangular-to-elliptical-shape-transition scramjet engine developed and operated at the University of Queensland. Results of Reynolds-averaged Navier-Stokes numerical simulations based on either the unsteady partially stirred reactor concept or the classical quasi-laminar closure are presented and compared. Similar results in terms of pressure distributions are obtained, thus confirming that the essential point to cope with such scramjet engine conditions is to represent satisfactorily the compressible flowfield. The Reynolds-averaged Navier-Stokes numerical simulations are subsequently used to investigate the engine performance, through the calculation of energetic efficiencies. The obtained results bring useful insights into the classical quasi-one-dimensional performance analyses. In particular, the inlet injection scheme is found to display the best performance with a combustion efficiency of 78%.

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Soot and radiation modeling in laminar ethylene flames with tabulated detailed chemistry

Cited by 14 publications

References 68 publications

Detailed radiation modeling of a partial-oxidation flame

Detailed radiation modeling of a partial-oxidation flame

Micro and Full-Scale Experiments on Hybrid Rocket Fuel and Prelude to Hybrid Rocket Combustor Simulations

Computational Fluid Dynamics Investigation of a Mach 12 Scramjet Engine

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