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Centre of basic and applied research specialized in modelling and numerical simulation, Cerfacs, through its facilities and expertise in high-performance computing, deals with major scientific and technical research problems of public and industrial interest.

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A CERFACS researcher elected at the Board of the Combustion Institute

superadmin |  8 August 2016

T. Poinsot has been elected at the Board of the Combustion Institute and will start his term on August 8, 2016. The board decides of all important decisions within the Combustion Institute. For example, this is where the sites for the presigious Symposium (Int.) on Comb. are chosen. The next...Read more

The Zeldovich medal for T. Poinsot at the 36th Symp. (Int.) on Comb.

superadmin |  8 August 2016

At the last Symposium on Combustion in Seoul, Korea, T. Poinsot has been awarded the Zeldovich medal, one of the four Gold medals awarded by the Combustion Institute. The Ya B. Zeldovich is awarded for " contribution to the theory of the fundamentals of reacting flows". It is the third time it...Read more

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From 3 October 2016 to 7 October 2016

Numerical methods for Large Eddy Simulation

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From 10 October 2016 to 12 October 2016

Code coupling using OpenPALM

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Urbano, A., Selle, L., Staffelbach, G., Cuenot, B., Schmitt, T., Ducruix, S. and Candel, S. (2016) Exploration of combustion instability triggering using Large Eddy Simulation of a multiple injector liquid rocket engine, Combustion and Flame, 169 (July), pp. 129–140, ISSN 0010-2180, doi:http://dx.doi.org/10.1016/j.combustflame.2016.03.020

[url] [doi]

@ARTICLE{AR-CFD-16-175, author = {Urbano, A. and Selle, L. and Staffelbach, G. and Cuenot, B. and Schmitt, T. and Ducruix, S. and Candel, S. }, title = {Exploration of combustion instability triggering using Large Eddy Simulation of a multiple injector liquid rocket engine}, year = {2016}, number = {July}, volume = {169}, pages = {129–140}, issn = {0010-2180}, doi = {http://dx.doi.org/10.1016/j.combustflame.2016.03.020}, journal = {Combustion and Flame}, abstract = {This article explores the possibility of analyzing combustion instabilities in liquid rocket engines by making use of Large Eddy Simulations (LES). Calculations are carried out for a complete small-scale rocket engine, including the injection manifold thrust chamber and nozzle outlet. The engine comprises 42 coaxial injectors feeding the combustion chamber with gaseous hydrogen and liquid oxygen and it operates at supercritical pressures with a maximum thermal power of 80 MW. The objective of the study is to predict the occurrence of transverse high-frequency combustion instabilities by comparing two operating points featuring different levels of acoustic activity. The LES compares favorably with the experiment for the stable load point and exhibits a nonlinearly unstable transverse mode for the experimentally unstable operating condition. A detailed analysis of the instability retrieves the experimental data in terms of spectral features. It is also found that modifications of the flame structures and of the global combustion region configuration have similarities with those observed in recent model scale experiments. It is shown that the overall acoustic activity mainly results from the combination of one transverse and one radial mode of the chamber, which are also strongly coupled with the oxidizer injectors. }, keywords = {LES}, url = {http://www.sciencedirect.com/science/article/pii/S0010218016300372}}

Mari, R., Cuenot, B., Rocchi, J., Selle, L. and Duchaine, F. (2016) Effect of pressure on hydrogen / oxygen coupled flame–wall interaction, Combustion and Flame, 168, pp. 409-419, doi:10.1016/j.combustflame.2016.01.004

[url] [doi]

@ARTICLE{AR-CFD-16-176, author = {Mari, R. and Cuenot, B. and Rocchi, J.-Ph. and Selle, L. and Duchaine, F. }, title = { Effect of pressure on hydrogen / oxygen coupled flame–wall interaction}, year = {2016}, volume = {168}, pages = {409-419}, doi = {10.1016/j.combustflame.2016.01.004}, journal = {Combustion and Flame}, abstract = { The design and optimization of liquid-fuel rocket engines is a major scientific and technological challenge. One particularly critical issue is the heating of solid parts that are subjected to extremely high heat fluxes when exposed to the flame. This in turn changes the injector lip temperature, leading to possibly different flame behaviors and a fully coupled system. As the cham- ber pressure is usually much larger than the critical pressure of the mixture, supercritical flow behaviors add even more complexity to the thermal prob- lem. When simulating such phenomena, these thermodynamic conditions raise both modeling and numerical specific issues. In this paper, both sub- critical and supercritical Hydrogen/Oxygen one-dimensional, laminar flames interacting with solid walls are studied by use of conjugate heat transfer simulations, allowing to evaluate the wall heat flux and temperature, their impact on the flame as well as their sensitivity to high pressure and real gas thermodynamics up to 100 bar where real gas effects are important. At low pressure, results are found in good agreement with previous studies in terms of wall heat flux and quenching distance, and the wall stays close to isothermal. On the contrary, due to important changes of the fluid trans- port properties and the flame characteristics, the wall experiences significant heating at high pressure condition and the flame behavior is modified. }, keywords = {Real-gas, thermodynamics, Flame–wall interaction, Conjugate heat transfer}, url = {http://www.sciencedirect.com/science/article/pii/S0010218016000134}}

Gratton, S., Mercier, S., Tardieu, N. and Vasseur, X. (2016) Limited memory preconditioners for symmetric indefinite problems with application to structural mechanics, Numerical Linear Algebra with Applications, doi:10.1002/nla.2058


@ARTICLE{AR-PA-16-27853, author = {Gratton, S. and Mercier, S. and Tardieu, N. and Vasseur, X. }, title = {Limited memory preconditioners for symmetric indefinite problems with application to structural mechanics}, year = {2016}, doi = {10.1002/nla.2058}, journal = {Numerical Linear Algebra with Applications}}

Tseng, Y. -H., Lin, H., Chen, H. -C., Thompson, K., Bentsen, M., Böning, C., Bozec, A., Cassou, C., Chassignet, E. P., Chow, C. H., Danabasoglu, G., Danilov, S., Fameti, R., Fogli, P. G., Fujii, Y., Griffies, S. M., Ilicak, M., Jung, T., Masina, S., Navarra, A., Patara, L., Samuels, B. L., Scheinert, M., Sidorenko, D., Sui, C. -H., Tsujino, H., Valcke, S., Voldoire, A., Wang, Q. and Yeager, S. G. (2016) North and equatorial Pacific Ocean circulation in the CORE-II hindcast simulations, Ocean Modelling, 104, pp. 143-170, doi:10.1016/j.ocemod.2016.06.003

[url] [doi]

@ARTICLE{AR-CMGC-16-159, author = {Tseng, Y.-H. and Lin, H. and Chen, H.-C. and Thompson, K. and Bentsen, M. and Böning, C. and Bozec, A. and Cassou, C. and Chassignet, E.P. and Chow, C.H. and Danabasoglu, G. and Danilov, S. and Fameti, R. and Fogli, P.G. and Fujii, Y. and Griffies, S.M. and Ilicak, M. and Jung, T. and Masina, S. and Navarra, A. and Patara, L. and Samuels, B.L. and Scheinert, M. and Sidorenko, D. and Sui, C.-H. and Tsujino, H. and Valcke, S. and Voldoire, A. and Wang, Q. and Yeager, S.G. }, title = {North and equatorial Pacific Ocean circulation in the CORE-II hindcast simulations}, year = {2016}, volume = {104}, pages = {143-170}, doi = {10.1016/j.ocemod.2016.06.003}, journal = {Ocean Modelling}, url = {http://www.sciencedirect.com/science/article/pii/S146350031630052X}}

Berger, S., Richard, S., Duchaine, F., Staffelbach, G. and Gicquel, L. Y. M. (2016) On the sensitivity of a helicopter combustor wall temperature to convective and radiative thermal loads, Applied Thermal Engineering, 103 (25), pp. 1450-1459, ISSN 1359-4311, doi:10.1016/j.applthermaleng.2016.04.054

[url] [doi]

@ARTICLE{AR-CFD-16-187, author = {Berger, S. and Richard, S. and Duchaine, F. and Staffelbach, G. and Gicquel, L.Y.M. }, title = {On the sensitivity of a helicopter combustor wall temperature to convective and radiative thermal loads}, year = {2016}, number = {25}, volume = {103}, pages = {1450-1459}, issn = {1359-4311}, doi = {10.1016/j.applthermaleng.2016.04.054}, journal = {Applied Thermal Engineering}, abstract = {The design of aeronautical engines is subject to many constraints that cover performance gain as well as increasingly sensitive environmental issues. These often contradicting objectives are currently being answered through an increase in the local and global temperature in the hot stages of the engine. As a result, hot spots could appear causing a premature aging of the combustion chamber. Today, the characterization of wall temperatures is performed experimentally by complex thermocolor tests in advanced phases of the design process. To limit such expensive experiments and integrate the knowledge of the thermal environment earlier in the design process, efforts are currently performed to provide high fidelity numerical tools able to predict the combustion chamber wall temperature including the main physical phenomena: combustion, convection and mixing of hot products and cold flows, radiative transfers as well as conduction in the solid parts. In this paper, partitioned coupling approaches based on a Large Eddy Simulation (LES) solver, a Discrete Ordinate Method radiation solver and an unsteady conduction code are used to investigate the sensitivity of an industrial combustor thermal environment to convection and radiation. Four computations including a reference adiabatic fluid only simulation, Conjugate Heat Transfer, Radiation-Fluid Thermal Interaction and fully coupled simulations are performed and compared with thermocolor experimental data. From the authors knowledge, such comparative study with LES has never been published. It is shown that coupling LES with conduction in walls is feasible in an industrial context with acceptable CPU costs and gives good trends of temperature repartition. Then, for the combustor geometry and operating point studied, computations illustrate that radiation plays an important role in the wall temperature distribution. Comparisons with thermocolor tests are globally in a better agreement when the three solvers are coupled.}, keywords = { Large Eddy Simulation, Conjugate Heat Transfer, Radiation, Combustion chamber}, url = {http://www.sciencedirect.com/science/article/pii/S1359431116305403}}

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Codes acoustiques pour prévoir les instabilités de combustion dans les turbines à gaz EN

17 July 2016 |  

Post-doc position on assimilation of satellite data for the analysis of atmospheric O3 and CO

24 March 2016 |  


The Aviation and Environment (AE) team develops since 2003 a variational data assimilation (DA) suite for the Météo-France...

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