Raytheon Technologies Corporation

Rtx Corporation

Matthew R Zsunkan

David R Lyders

Arun K Theertham

Peter Karkos

Jordan J Franklin

Chong H Park

An assembly for a gas turbine engine includes an airfoil that includes an airfoil section that extends from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extends between a tip portion and the root section in a radial direction. The airfoil section defines a pressure side and a suction side separated in a thickness direction. A platform is dimensioned to receive a retention pin to mount the platform to a rotatable hub. The platform includes a plurality of composite layers that define an internal cavity. A filler includes a stacked composite structure in the internal cavity that extends between the plurality of composite layers.

Platform for an airfoil of a gas turbine engine

A fan blade platform seal includes a platform portion including a first side and a second side opposite the first side. The platform portion further includes a flow path surface extending between the first side and the second side and a bonding surface opposite the flow path surface. The fan blade platform seal further includes a first seal portion including a first bonding segment including a first outer surface, mounted to the platform portion on the first side of the platform portion, and a first inner surface opposite the first outer surface. The fan blade platform seal further includes a stiffening portion mounted to the first inner surface. The stiffening portion includes a first bonding layer bonded to the first inner surface and a stiffening layer bonded to the first bonding layer on a first layer side of the stiffening layer.

Fan blade platform seal and method for forming same

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Hartford, CT, United States of America

Matthew R Zsunkan