Abstract
In turbofan engine, ice accretion on spinning cone may lead to a decline in the engine aerodynamic performance and an increase of the vibration amplitude of the engine. An understanding of the mechanisms responsible for ice shedding process is necessary in order to optimize the spinning cone design and de-icing system to avoid hazardous ice shedding. In this paper, the Cohesive Zone Method (CZM) and the eXtended Finite Element Method (XFEM) are introduced to simulate the ice shedding process from a spinning cone. The CZM is applied to simulate the initiation and propagation of ice/spinning cone interface crack. The XFEM is introduced to model crack path inside the ice. This research method could provide a reference for ice shedding analysis of other parts of aero-engine. The research result could also be used to further study on optimization of the electro-thermal and hot-air de-icing system and ice shedding trajectory and impact simulations.
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