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.

Abstract: A vane for a gas turbine engine includes at least one airfoil. A first platform has a first rail located at a first end of the airfoil. A second platform has a second rail located at a second end of the airfoil. A first chordal seal is located on an axially aft surface of the first rail. A second chordal seal is located on an aft surface of the second rail and has a second radius of curvature at least partially truncated by an outer edge of the second rail.

Abstract: A gas turbine engine includes first and second arc segments that each have leading and trailing sides and first and second circumferential sides. The first circumferential side includes a first slot portion and the second circumferential side includes a second slot portion. The first and second slot portions are in registration and together define a seal slot. At least the first slot portion has a first concave arced back wall. A feather seal is entrapped in the seal slot and includes first and second feather seal circumferential sides. At least the first feather seal circumferential side has a first convex arced edge that is adjacent the first concave arced back wall of the first slot portion.

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.

Abstract: A vane for a gas turbine engine includes at least one airfoil. A first platform has a first rail located at a first end of the airfoil. A second platform has a second rail located at a second end of the airfoil. A first chordal seal is located on an axially aft surface of the first rail. A second chordal seal is located on an aft surface of the second rail and has a second radius of curvature at least partially truncated by an outer edge of the second rail.

Abstract: A gas turbine engine includes first and second arc segments that each have leading and trailing sides and first and second circumferential sides. The first circumferential side includes a first slot portion and the second circumferential side includes a second slot portion. The first and second slot portions are in registration and together define a seal slot. At least the first slot portion has a first concave arced back wall. A feather seal is entrapped in the seal slot and includes first and second feather seal circumferential sides. At least the first feather seal circumferential side has a first convex arced edge that is adjacent the first concave arced back wall of the first slot portion.