A turbine vane for a gas turbine engine comprising: inner and outer platforms (74, 76) joined by a radially extending airfoil, the airfoil including leading and trailing edges (82, 84) joined by spaced apart pressure and suction sides to provide an exterior airfoil surface, the airfoil including an airfoil cooling passage; and a platform cooling passage (112, 114) arranged within at least one of the inner and outer platforms (74, 76), the platform cooling passage (112, 114) including multiple cooling regions (122, 124, 126) with one of the cooling regions (122, 124, 126) arranged beneath the airfoil cooling passage, wherein the platform cooling passage (112, 114) includes a radially extending inlet, the multiple cooling regions (122, 124, 126) corresponds to first, second and third cooling regions (122, 124, 126) providing a tortuous cooling passage, the first cooling region adjoining the inlet, and an elongated rib is arranged near the inlet and separates the first and second cooling regions (122, 124); wherein the at least one of the inner and outer platforms (74, 76) includes a platform perimeter provided by forward and aft edges (142, 144) joined to one another by pressure and suction side edges (146, 148); the first cooling region and the rib are generally parallel to the pressure side edge; the third cooling region is generally parallel to the aft edge; and the platform cooling passage (112, 114) includes an axially extending portion joined to the third cooling region that is generally perpendicular to the aft edge and characterised in that the axial extending portion terminates in a welded plug. inner and outer platforms (74, 76) joined by a radially extending airfoil, the airfoil including leading and trailing edges (82, 84) joined by spaced apart pressure and suction sides to provide an exterior airfoil surface, the airfoil including an airfoil cooling passage; and a platform cooling passage (112, 114) arranged within at least one of the inner and outer platforms (74, 76), the platform cooling passage (112, 114) including multiple cooling regions (122, 124, 126) with one of the cooling regions (122, 124, 126) arranged beneath the airfoil cooling passage, wherein the platform cooling passage (112, 114) includes a radially extending inlet, the multiple cooling regions (122, 124, 126) corresponds to first, second and third cooling regions (122, 124, 126) providing a tortuous cooling passage, the first cooling region adjoining the inlet, and an elongated rib is arranged near the inlet and separates the first and second cooling regions (122, 124); wherein the at least one of the inner and outer platforms (74, 76) includes a platform perimeter provided by forward and aft edges (142, 144) joined to one another by pressure and suction side edges (146, 148); the first cooling region and the rib are generally parallel to the pressure side edge; the third cooling region is generally parallel to the aft edge; and the platform cooling passage (112, 114) includes an axially extending portion joined to the third cooling region that is generally perpendicular to the aft edge and characterised in that the axial extending portion terminates in a welded plug.