Mate face arrangement for gas turbine engine components

Abstract

A component for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending in a radial direction from a platform, the airfoil section extending in an axial direction between an airfoil leading edge and an airfoil trailing edge, and the airfoil section extending in the circumferential direction between pressure and suction sides. The platform extends in the axial direction between a platform leading edge and a platform trailing edge, and extends in the circumferential direction between a first mate face and a second mate face. The platform has a radially facing surface joined with the airfoil section and has a cold side surface opposed to the radially facing surface. A first thickness is defined between the radially facing surface and the cold side surface adjacent the first mate face, and a second thickness is defined between the radially facing surface and the cold side surface adjacent the second mate face. The first thickness is greater than the second thickness from at least the airfoil leading edge to the airfoil trailing edge with respect to the axial direction. A method of assembly is also disclosed.