Large-Eddy Simulation of Unsteady Wall Heat Transfer in a High Pressure Combustion Chamber

Tramecourt, Nathalie; Masquelet, Matthieu; Menon, Suresh

doi:10.2514/6.2005-4124

Cited by 9 publications

(8 citation statements)

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“…It is a significant improvement compared with simpler mechanisms previously used in similar rocket engines configurations [28,29]. However, the stiffness of this mechanism makes it especially hard to integrate numerically.…”

Section: Formulationmentioning

confidence: 99%

Large-Eddy Simulation of Flame-Turbulence Interactions in a Shear Coaxial Injector

Masquelet

Menon

2010

Journal of Propulsion and Power

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The turbulent combustion inside the main chamber of a liquid rocket engine is difficult to numerically model because of the wide range of scales involved, the complex thermodynamics at elevated pressure, and the influence of heat transfer. Here, a single-element gaseous-hydrogen-gaseous-oxygen shear-coaxial injector is studied. This case involves complex physical processes that are simulated using a large-eddy simulation approach. In particular, modeling of the nonpremixed turbulent combustion and its impact on the wall heat flux is addressed. This large-eddy simulation of the compressible multispecies Navier-Stokes equations is solved using a hybrid central-upwind scheme with a thermally perfect formulation. To keep the computational cost reasonable, priority was given to the near-field resolution over the near-wall resolution. The modeled flame anchoring and dynamics provide a satisfactory estimate of the wall heat flux. The unsteady and three-dimensional features of the flow are discussed in length, and the implications of the unique features of this shear-coaxial GH 2 -GO 2 injector for turbulent combustion modeling are analyzed.Nomenclature C , C = model coefficients for the subgrid closure D = mass diffusivity, m 2 s 1 e T = total energy (internal kinetic) per unit mass, J kg 1 H sgs = subgrid enthalpy flux, J m 2 h k = partial massic enthalpy of species k, J kg 1 J k = mass diffusion flux, kg m 2 k sgs = turbulent kinetic energy, m 2 s 2 N S = number of species considered P sgs = production of turbulent kinetic energy, kg m 1 s 3 p = pressure, pa Q IK = heat flux in the Irving-Kirkwood form, J m 2 Q sgs k = subgrid enthalpy flux due to diffusion of species k, J m 2 R = gas constant, J kg 1 K 1 T = temperature, k t = time, s u = velocity, m s 1 V k = diffusion velocity of species k, m s 1 x i = Cartesian coordinate, m Y k = mass fraction of species k = grid filter size, m sgs = subgrid dissipation of turbulent kinetic energy, kg m 1 s 3 sgs k = subgrid species diffusive flux, kg m 2 = thermal conductivity, W m 1 K 1 = dynamic viscosity, Pa s = density, kg m 3 sgs = subgrid heat flux, J m 2 ij = stress tensor Subscripts i, j = Cartesian direction k = species k property m = mixture property Superscripts x = spatially filtered quantitỹ x = Favre-filtered quantity x sgs = subgrid quantity

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Section: Formulationmentioning

confidence: 99%

Large-Eddy Simulation of Flame-Turbulence Interactions in a Shear Coaxial Injector

Masquelet

Menon

2010

Journal of Propulsion and Power

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“…The strength, the life cycle, and the cooling system effectiveness are highly dependent on heat transfer into and out of the system [10], and the number of studies addressing the heat transfer into the chamber walls are still inadequate.…”

Section: Introductionmentioning

confidence: 99%

One- and Three-Dimensional Wall Heat Flux Calculations in a O2/H2 System

Vaidyanathan

Gustavsson

Segal

2010

Journal of Propulsion and Power

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“…This calls for new cooling technologies, for example, in the combustion chamber of the rocket engine where high thermal loads up to 100 MW/m 2 occur [1]. An improved performance of the rocket engines should not be accomplished though at the expense of an increased weight of the rocket itself.…”

Section: Introductionmentioning

confidence: 99%

“…An improved performance of the rocket engines should not be accomplished though at the expense of an increased weight of the rocket itself. This calls for new cooling technologies, for example, in the combustion chamber of the rocket engine where high thermal loads up to 100 MW/m 2 occur [1]. Innovative cooling methods that are able to deal with such loads are currently under investigation.…”

Section: Introductionmentioning

confidence: 99%

Numerical simulation of transpiration cooling through porous material

Dahmen

Gotzen

Müller

et al. 2014

Numerical Methods in Fluids

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SUMMARYTranspiration cooling using ceramic matrix composite materials is an innovative concept for cooling rocket thrust chambers. The coolant (air) is driven through the porous material by a pressure difference between the coolant reservoir and the turbulent hot gas flow. The effectiveness of such cooling strategies relies on a proper choice of the involved process parameters such as injection pressure, blowing ratios, and material structure parameters, to name only a few. In view of the limited experimental access to the subtle processes occurring at the interface between hot gas flow and porous medium, reliable and accurate simulations become an increasingly important design tool. In order to facilitate such numerical simulations for a carbon/carbon material mounted in the side wall of a hot gas channel that are able to capture a spatially varying interplay between the hot gas flow and the coolant at the interface, we formulate a model for the porous medium flow of Darcy–Forchheimer type. A finite‐element solver for the corresponding porous medium flow is presented and coupled with a finite‐volume solver for the compressible Reynolds‐averaged Navier–Stokes equations. The two‐dimensional and three‐dimensional results at Mach number Ma = 0.5 and hot gas temperature THG=540 K for different blowing ratios are compared with experimental data. Copyright © 2014 John Wiley & Sons, Ltd.

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Large-Eddy Simulation of Unsteady Wall Heat Transfer in a High Pressure Combustion Chamber

Cited by 9 publications

References 0 publications

Large-Eddy Simulation of Flame-Turbulence Interactions in a Shear Coaxial Injector

Large-Eddy Simulation of Flame-Turbulence Interactions in a Shear Coaxial Injector

One- and Three-Dimensional Wall Heat Flux Calculations in a O2/H2 System

Numerical simulation of transpiration cooling through porous material

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