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Abstract : Due to efforts to reduce NOx emissions of aeronautical combustors, there is a recent trend towards lean combustion technologies. This results in novel injector designs, which are characterized by increased geometrical complexity and new injection strategies for the liquid fuel, such as multipoint systems. Both elements create addiionnal challenges for numerical simulation tools. Large-Eddy simulation (LES) is regarded as the most promising method to capture complex flow phenomena in such an application. In the present work, two main areas of interest are considered: The first is wall modeling, which remains a challenging field in LES, in particular for complex geometries. A new implementation method for wall functions that uses a no-slip condition at the wall is proposed. It is shown that in a realistic burner geometry the new formulation yields improved results compared to a classical implementation. Furthermore, the capability of a typical LES with wall models to predict the pressure drop in a representative geometry is assessed and sources of error are identified. The second topic is the simulation of liquid fuel in a combustor. With Eulerian and Lagrangian methods, two different approaches are available for this task. The Eulerian approach considers a droplet spray as a continuum for which transport equations can be formulated. In the Lagrangian formulation, individual droplets are tracked, which leads to a simple formulation, but can be challenging in terms of numerics due to the large number of particles to be treated. The comparison of these methods under identical conditions (gaseous flow solver, physical models) is a central aspect of the present work. The most important phenomena that are studied in view of the final application are evaporation and the problem of transverse liquid jets in a gaseous crossflow as a simplified representation of a multipoint system. The final application case is the configuration af a single aeronautical injector mounted in an experimental test bench. It allows to simultaneously apply all prelimary developments. The flow considerd is non-reactive but otherwise corresponds to a partial load regime in an aero-engine. Due to the pre-heated condition, the spray issued by the multi-point injection undergoes evaporation. This flow is simulated using Eulerian and Lagrangian methods and the results are compared to experimental data.
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Contributor : Séverine Toulouse <>
Submitted on : Tuesday, February 2, 2010 - 3:25:12 PM
Last modification on : Wednesday, November 29, 2017 - 4:53:26 PM
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  • HAL Id : tel-00452501, version 1



Félix Jaegle. LARGE EDDY SIMULATION OF EVAPORATING SPRAYS IN COMPLEX GEOMETRIES USING EULERIAN AND LAGRANGIAN METHODS. Engineering Sciences [physics]. Institut National Polytechnique de Toulouse - INPT, 2009. English. ⟨tel-00452501⟩



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