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== An optimization-based approach to detailed chemistry tabulation ==
Finding a progress variable so that all relevant species can be retrieved from its knowledge, is not always straightforward; specifically for fuel mixtures composed of more than a single hydrocarbon, or for simpler fuels but under conditions where the global reaction progress is not continuous, for instance in the case of cool-flame ignition. To overcome these difficulties, automated methods are discussed to define progress variables in which all species of a chemical scheme, even minor ones, are involved. This is done formulating constraints applied to progress variables definition: they should evolve in a monotonic manner from fresh to burnt gases and species derivative in progress variable-space should stay moderate for tabulation accuracy. This set of constraints is discretized along chemical trajectories observed in laminar canonical flames, to be formulated in terms of an ensemble of inequalities, which are solved using optimization tools. The outcome is a set of weighting coefficients to be applied to every species of the detailed chemical scheme, in order to construct the progress variable-space. The methods have been successfully applied to methane and kerosene premixed flamelets and to n-heptane self-ignition, under conditions with cool-flame effects.

{| class="wikitable"
|+ Automated progress variable definition
|-
| [[File:CF_160_4_YS_TAB.png|center|400px]]
| [[File:YC_alpha_optim.png|center|200px]]
| [[File:OH_Optim.png|center|300px]]
|-
| Coefficients of the optimized progress variable for CH4/Air combustion
| Progress variable is expressed from all species mass fraction
| OH tabulation valid at all equivalence ratios
|}

* N. Yi-Shuai, L. Vervisch, P.-D. Tao (2013) An optimization-based approach to detailed chemistry tabulation: Automated progress variable definition, Combust. Flame, 160(4): 776-785.

== LES of a Trapped Vortex Combustor ==
Flow and flame dynamics inside a trapped vortex combustor are analyzed from Large Eddy Simulation (LES) results compared against measurements. The Navier-Stokes equations are solved in their fully compressible form over a cartesian grid resorting to immersed boundaries to account for the complex geometry, composed of an annular flow impacting a set of axisymmetric rods (flame holders) before interacting with a cavity. Various cases are considered, varying the main flow rate, the length of the cavity, injecting secondary-air and also adding a swirling motion. From these cases, three main cavity flow regimes emerge. The modeling of molecular diffusion in LES with presumed probability density function (pdf), as filter of premixed flamelets, is also discussed. It is shown that a dynamic correction to molecular diffusion may be computed from the pdf control parameters to ensure the correct laminar flame speed, whatever the mesh used. Finally, the study of the turbulent flame evolution within the cavity in the various cases, suggests that swirling motion is mandatory to favor the global burner stability.

{| class="wikitable"
|+ Immersed boundaries are used to optimize the geometry of a trapped vortex combustor
|-
| [[File:TVC1.png|center|400px]]
| [[File:TVC2.png|center|400px]]
| [[File:TVC3.png|center|400px]]
|-
| Geometry of the Trapped Vortex Combustion chamber
| Q-critrion - Visualisation of the turbulent flow topology
| Comparison against experiments
|}

* C. Merlin, P. Domingo, L. Vervisch (2012) Large Eddy Simulation of turbulent flames in a Trapped Vortex Combustor (TVC) - A flamelet presumed-pdf closure preserving laminar flame speed, Comptes Rendus Mecanique, 340 (11/12), pp. 917-932.

== Immersed boundaries in LES of compressible flows==
Methods to immerse walls in a structured mesh are examined in the context of fully compressible solutions of the Navier Stokes equations. The ghost cell approach is tested along with compressible conservative immersed boundaries in canonical flow configurations; the reflexion of pressure waves on walls arbitrarily inclined on a cartesian mesh is studied, and mass conservation issues examined in both a channel flow inclined at various angles and flow past a cylinder. Then, results from Large Eddy Simulation of a flow past a rectangular cylinder and a transonic cavity flow are compared against experiments, using either a multi-block mesh conforming to the wall or immersed boundaries. Different strategies to account for unresolved transport by velocity fluctuations in LES are also compared. It is found that immersed boundaries allow for reproducing most of the coupling between flow instabilities and pressure-signal properties observed in the transonic cavity flow. To conclude, the complex geometry of a trapped vortex combustor, including a cavity, is simulated and results compared against experiments.

{| class="wikitable"
|+ Immersed boundaries are developed for fully compressible simulations
|-
| [[File:IBM1.png|center|400px]]
| [[File:IBM2.png|center|400px]]
|-
| [[File:IBM3.png|center|500px]]
|-
| Pressure wave reflection on inclined walls
| Transonic cavity flow simulation
| Comparison of pressure spectra against measurements
|}

* C. Merlin, P. Domingo, L. Vervisch (2013) Immersed Boundaries in Large Eddy Simulation of Compressible Flows, Flow Turbulence and Combustion, 90(1), pp. 29-68.

== DNS of a Rapid Compression Machine ==
Turbulence and combustion inside a compression machine, experimentally studied by Guibert et al. [Flow Turbulence and Combust. 84(1):~79-85, 2010], are simulated to get some insight on flow-physics  and ignition scenarios of a reactive-gas mixture pushed by a piston through a turbulence-grid, to be compressed in a fifty-five cubic-centimeter volume. Large Eddy Simulation (LES) with a structured-mesh solver and immersed boundaries are first performed for an inert mixture undergoing the compression, to validate the simulation procedure against experimental results. Then, keeping the flow admission-sequence the same, but downsizing its geometry, a Direct Numerical Simulation (DNS) analysis of the compression/ignition sequence is reported. Simulation parameters are varied for ignition to occur in mixtures featuring various temperature stratification patterns, due to wall cooling and turbulence characteristics. As previously discussed in the literature, conditions favoring spotty- or homogeneous-ignition are evidenced. Depending on characteristic times (coherent structure residence time, flow engulfment and mixing times) ignition may occur within localized compression zones, between vortical structures leading to spotty-ignition, or more homogeneously within large scale flow structures. Very small differences in local temperature and flow topology appear to lead to different routes toward successful auto-ignition. The underlying mechanisms are analyzed from an internal energy budget expressed as a  temperature balance equation, to delineate between the contribution of the global adiabatic compression and localized flow divergence induced by turbulence velocity fluctuations. After primary ignition, the propagation phase of ignition is strongly influenced by the acoustic field and the specific temperature scalar dissipation-rate patterns. It is also shown that three-dimensional vortex stretching plays a crucial role, hence two and three-dimensional DNS lead to different ignition scenarios under similar chemical and turbulence intensity conditions.

{| class="wikitable"
|+ Analysis of ignition regimes after rapid compression - Homogeneous mixture stratified in temperature
|-
| [[File:RCM1.png|center|400px]]
| [[File:RCM2.png|center|400px]]
| [[File:RCM3.png|center|400px]]
|-
| Flow injection sequence - Resolution of <math>20 \mu m </math>
| Ignition patterns
| Regime Diagram
|}

* G. Lodier, C. Merlin, P. Domingo, L. Vervisch, F. Ravet (2012) Self-ignition scenarios after rapid compression of a turbulent mixture weakly-stratified in temperature, Combust. Flame 159(11): 3358-3371.

== Mixing time-history effects: Flow-Controlled Chemistry Tabulation ==
The time history of mixing is known to play a crucial and non-trivial role in non-premixed turbulent combustion. In a first part, Eulerian balance equations are derived for both a flow residence time and a characteristic time of the mixing which the particles gathered in a fluid element have been subjected to in their flow histories. These equations are analyzed and solved in a Large Eddy Simulation (LES) context for a fuel jet mixing with an oxidizer coflow. Typical responses of filtered mixture fraction versus flow residence time are highlighted. In a second part, a Flow-Controlled Chemistry Tabulation (FCCT) is devised in which the effects of unresolved fluctuations of thermochemical variables in LES are simulated, combining partially-stirred reactors with tabulated chemistry. The reactor evolutions are organized to mimick flow engulfment and micro-mixing, so as to reproduce the observed filtered mixture fraction versus residence time response. This allows for dynamically building sub-grid scale joint probability density functions, and thereby the sub-filter response of the non-premixed flames, according to four control parameters: the filtered mixture fraction, the progress of reaction, the flow residence time and a mixing time. Finally, LES of the Cabra et al.  [Combust. Flame 143 (2005) 491--506] fuel-jet lifted-flame developing in a vitiated oxidizer environment is performed and results are compared against measurements.

{| class="wikitable"
|+ Analysis of time-history of turbulent mixing and fully new approach to turbulent combustion modeling
|-
| [[File:FCCT1.png|center|400px]]
| [[File:FCCT2.png|center|400px]]
| [[File:FCCT3.png|center|400px]]
|-
| FCCT procedure
| Dynamic construction of advanced chemistry tabulation 
| Turbulent flame response to micro-mixing history
|}

* N. Enjalbert, P. Domingo, L. Vervisch (2012) Mixing time-history effects in Large Eddy Simulation of non-premixed turbulent flames: Flow-Controlled Chemistry Tabulation, Combust. Flame 159(1): 336-352.

== DNS of a non-reacting HIT ==

This is a very simple DNS computation of a HIT with a constant-properties gas.<br/>
The main parameters of the simulation are:
* temporal integration: RK3,
* spatial scheme: 4th order skew symmetric
* no AV.

In this series of computations, the number of cell is increased from 64^3 to 256^3.

{| class="wikitable"
|+ HIT on increasing number of cells. The displayed field is <math>\nabla \wedge U</math>
|-
| [[File:HIT_0064cube.png|center|400px]]
| [[File:HIT_0128cube.png|center|400px]]
| [[File:HIT_0256cube.png|center|400px]]
|-
|<math>N_c=64^3 \quad Re_t = 40</math>
|<math>N_c=128^3 \quad Re_t = 100</math>
|<math>N_c=256^3 \quad Re_t = 250</math>
|}


== DNS of a non-reacting supercritical mixing layer ==

This simulation is a DNS of a HIT non-reacting supercritical mixing layer with real-gas properties (equation of state, thermodynamic laws and transport laws).<br/>
The main parameters of the simulation are:
* temporal integration: RK3,
* spatial scheme: 4th order skew symmetric
* 2D / Periodic in all directions
* 3.2 Million cells
* EOS: Soave-Redlich-Kwong.
* Transport laws: Chung et al.

[[Image:supercritical_mixing_layer_rho_mixness.png|800px|Supercritical Mixing Layer]]

The fields that are displayed are:
* '''up :''' the density which varies from 80 kg/m3 in the cold stream to 800 kg/m3 in the hot stream.
* '''down :''' the mixness ratio which varies from 0 in pure constitutents to 1 for perfect mixness.

<br/>

----

<br/>

[[Media:supercritical_mixing_layer_mix.avi]]

<br/>

This video shows the temporal evolution of mixness ratio during the simulation.<br/>
'''Warning''':
* no Artificial Viscosity was used and the mesh was slightly too coarse: a few "wiggles" are visible from time to time near the steepest gradients...
* this video is best visualized with [http://www.videolan.org/ VLC].


== Flame base stabilization in vitiated partially-premixed mixture ==
[[File:nice_QW.png]]

* P. Domingo, L. Vervisch, D. Veynante (2008) Large-Eddy Simulation of a lifted methane jet flame in a vitiated coflow Combust. Flame 152(3): 415-432.


== Electric field and edge-flame ==
[[File:electric_edges_1.png|500px]] 

* M. Belhi, P. Domingo, P. Vervisch (2010) Direct numerical simulation of the effect of an electric field on flame stability  Combust. Flame 157 2286–2297.


== NSCBC vs 3D-NSCBC in jets ==
[[File:jet_NSCBC_1D.png|500px]] [[File:jet_3DNSCBC_bis.png|300px]]

* G. Lodato, P. Domingo, L. Vervisch (2008) Three-dimensional boundary conditions for Direct and Large-Eddy Simulation of compressible flows J. of Comp. Phys. 227(10): 5105-5143.


== Impinging round jets ==
Wall/jet interaction
[[File:jet_wall_1.png|400px]]]] 

[[File:jet_wall_2.png|400px]]
[[File:jet_wall_3.png|300px]]

* G. Lodato, L. Vervisch, P. Domingo (2009) A compressible wall-adapting similarity mixed model for large-eddy simulation of the impinging round jet Phys. Fluids 21:035102.


== Ignition of a bluff-body burner ==

[[File:igni_bluff_1.png]]

* V. Subramanian, P. Domingo, L. Vervisch (2010) Large-Eddy Simulation of forced ignition of an annular bluff-body burner Combust. Flame 157(3): 579-601.


== Bunsen flame ==

[[File:bunsen.png|400px]]

* G. Lodato, P. Domingo, L. Vervisch, D. Veynante (2009) Scalar variances: LES against measurements and mesh optimization criterion; scalar gradient: a three-dimensional estimation from planar measurements using DNS In Studying turbulence by using numerical simulation databases XII, (Eds Center for Turbulence Research) Stanford, pp. 387-398


== Jet flame-surface ==

[[File:jet_flame_DNS.png|400px]]

* L. Vervisch, P. Domingo, G. Lodato, D. Veynante (2010) Scalar energy fluctuations in Large-Eddy Simulation of turbulent flames: Statistical budgets and mesh quality criterion Combust. Flame 157(4): 778-789.
* D. Veynante, G. Lodato, P. Domingo, L. Vervisch, E. R. Hawkes (2010) Estimation of three-dimensional flame surface densities from planar images in turbulent premixed combustion Exp. in Fluids 49:267-278.


== Nonpremixed jet flame ==

[[File:sandia_flame.png|400px]]

* G. Godel, P. Domingo, L. Vervisch (2009) Tabulation of NOx chemistry for Large-Eddy Simulation of non-premixed turbulent flames Proc. Combust. Inst. 32: 1555-1551.