Discrete particle simulation for the initial stages of ice accretion in aircraft engines: initial model development

Discrete particle simulation for the initial stages of ice accretion in aircraft engines: initial model development

Elements of a discrete particle model that might find application in aircraft engine icing studies are introduced in this paper. As it currently stands, the model is in an embryonic state but it does provides a framework from which further developments can easily proceed. It provides a convenient basis for assessment of aerodynamic particle drag, surface friction, heat transfer and other effects likely to be relevant in the engine icing problem. The model treats the initial stage of accretion, before the inviscid stagnation point flow field is measurably affected by the presence of the ice build-up. The intention is to provide an indication flow field and surface conditions that are likely to lead to stable accretion of ice prior to detectable changes in the aerodynamics of the stagnation point flow field. Preliminary results from the model are presented to demonstrate the current functionality of the model.

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