Ignition or re-ignition of a gas turbine engine in a cold and rarified atmosphere is a critical issue for aircraft manufacturers. The objective of this thesis is to develop a large eddy simulation (LES) method to study combustion and ignition in realistic aeronautical combustors. The unsteady theoretical approach includes the main features of these phenomena by coupling models for turbulence, fuel spray dispersion and combustion. The LES tool is validated in academic cases and applied to a realistic helicopter combustor configuration featuring 18 identical sectors. The steady regime and the ignition sequence of a single sector are first analysed. Thanks to massively parallel computing, the study is then extended to the full ignition of the 18 sectors, bringing new insight into the physics of this phenomena.
from HAL : Dernières publications http://ift.tt/1tLeRk4
from HAL : Dernières publications http://ift.tt/1tLeRk4
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