A vane for a gas turbine engine comprising: a first airfoil; a first chordal seal located adjacent a first end of the first airfoil, wherein the first chordal seal is located on a rail located on an opposite side of a first platform from the first airfoil and a first pair of transition regions extend along a pair of edges of the first chordal seal; a second chordal seal located adjacent a second end of the first airfoil, wherein the first chordal seal includes a first edge parallel to a first edge on the second chordal seal; and a cusp of material spaced radially inward from the first chordal seal; characterised by further comprising: a recess in the rail on an opposite side of the cusp of material from the first chordal seal, wherein the cusp of material is defined by one of the first pair of transition regions along an axially downstream edge of the cusp of material and by the recess along an axially forward edge of the cusp of material; and wherein the second chordal seal extends in a chordal direction along an axially facing surface of an outer rail, the second chordal seal includes an axially facing surface that is configured to face axially downstream relative to an axis of the gas turbine engine, and the axially facing surface is axially spaced from the axially facing surface by a second pair of transition regions, wherein the first and second pair of transition regions (116, 108) each include a pair of fillets having a radius of curvature. a first airfoil; a first chordal seal located adjacent a first end of the first airfoil, wherein the first chordal seal is located on a rail located on an opposite side of a first platform from the first airfoil and a first pair of transition regions extend along a pair of edges of the first chordal seal; a second chordal seal located adjacent a second end of the first airfoil, wherein the first chordal seal includes a first edge parallel to a first edge on the second chordal seal; and a cusp of material spaced radially inward from the first chordal seal; characterised by further comprising: a recess in the rail on an opposite side of the cusp of material from the first chordal seal, wherein the cusp of material is defined by one of the first pair of transition regions along an axially downstream edge of the cusp of material and by the recess along an axially forward edge of the cusp of material; and wherein the second chordal seal extends in a chordal direction along an axially facing surface of an outer rail, the second chordal seal includes an axially facing surface that is configured to face axially downstream relative to an axis of the gas turbine engine, and the axially facing surface is axially spaced from the axially facing surface by a second pair of transition regions, wherein the first and second pair of transition regions (116, 108) each include a pair of fillets having a radius of curvature. a recess in the rail on an opposite side of the cusp of material from the first chordal seal, wherein the cusp of material is defined by one of the first pair of transition regions along an axially downstream edge of the cusp of material and by the recess along an axially forward edge of the cusp of material; and wherein the second chordal seal extends in a chordal direction along an axially facing surface of an outer rail, the second chordal seal includes an axially facing surface that is configured to face axially downstream relative to an axis of the gas turbine engine, and the axially facing surface is axially spaced from the axially facing surface by a second pair of transition regions, wherein the first and second pair of transition regions (116, 108) each include a pair of fillets having a radius of curvature.