Patent ID: 11428105

Abstract:
An airfoil assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil that has an airfoil section extending 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, and the airfoil section defining a pressure side and a suction side separated in a circumferential direction. A platform includes a first and second platform portions attached to the root section. Each of the first and second platform portions includes a shoe section and a platform section extending in the circumferential direction from the shoe section to establish a gas path surface, and the shoe sections of the first and second platforms are circumferentially arranged on opposed sides of the root section to capture the root section in a root cavity established between the shoe sections. A method of assembly is also disclosed.