Fan blade platform feature for improved blade-off performance

Details Fan blade platform feature for improved blade-off performance Fan blade platform feature for improved blade-off performance

F - Mech Eng,Light,Heat,Weapons

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F01D 5/14 (2006.01) F01D 21/04 (2006.01) F01D 25/14 (2006.01) F04D 29/32 (2006.01) F04D 29/38 (2006.01)

Patent

CA 2466797

A fan blade for a gas turbine engine having an airfoil with a leading edge; a trailing edge; a concave side; and a convex side. The blade has an integral platform with: a convex fillet merging with the airfoil; a forward edge; an aft edge; and a thickness defined between a top surface and an underside surface. The platform includes a stiffener on the underside surface adjacent the convex side of the blade, such that the stiffener defines a blade-off event platform fracture path on a second side of the platform adjacent the following blade and adjacent the convex side of the airfoil.

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