An anti-icing device is designed for resisting the ice accretion occurring in the air intake system of hovercraft gas turbine, which may affect its normal operation. The anti-icing purpose was achieved by mixing hot bleed air from the engine compressor and cold intake ambient air. Some research on the bleed air heating system was done by using 3D numerical simulation method. Under the set parameter of bleed air, the ambient temperature range for different bleed air flow was obtained and the corresponding anti-icing effect was also simulated. When the ambient temperature changed, the influence of anti-icing device’s working on total pressure loss of air intake system and the distributing condition of the compressor inlet surface velocity nonuniformity were investigated, and their changing law under different icing condition was obtained. The researching results provide theoretical and practical guidance and support for ships equipped with gas turbine when sailing in low temperature region.

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