Patent ID: 11840930

Abstract:
A vane for a gas turbine engine, the vane including: an inner diameter platform and an outer diameter platform and an airfoil that extends between the inner diameter platform and the outer diameter platform, the airfoil having a leading edge, a trailing edge, a pressure side and a suction side, the inner diameter platform has a suction side mate face and a pressure side mate face, wherein the suction side mate face and the pressure side mate face of the inner diameter platform have an axial feather seal slot and a radial seal slot, the axial feather seal slot includes a leading edge portion that extends from the radial seal slot towards a leading edge of the inner diameter platform and a trailing edge portion that extends from the radial seal slot towards a trailing edge of the inner diameter platform, and a chamfer extends between the radial seal slot and the trailing edge portion of the axial feather seal slot.