An aircraft engine (12) configured to controllably shed ice during icing conditions is presented. The engine has a fan member (14) operating at a first angular velocity having a surface (18) divided into a first ice accumulating surface (20) configured to collect ice, and a first shadow surface (22) configured to resist the collection of ice. A first flange (16) is disposed between the first ice accumulating surface and the first shadow surface.
AIRCRAFT ENGINE WITH ICE SHEDDING SYSTEM
FLUGZEUGTRIEBWERK MIT EISABLÖSUNG
MOTEUR D'AÉRONEF À DÉLESTAGE DE GLACE
2021-02-17
Patent
Electronic Resource
English
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