A turbine vane for a gas turbine engine, comprising: an outer vane platform; an inner vane platform; a first sidewall; a first multiple of axial standoff ribs that extend from the first sidewall; a second sidewall; a second multiple of axial standoff ribs that extend from the second sidewall; and a structural rib that extends between the first multiple of axial standoff ribs and the second multiple of axial standoff ribs, wherein the first sidewall is a pressure side and the second sidewall is a suction side of an airfoil, wherein the first sidewall and the second sidewall extend between the outer vane platform and the inner vane platform, wherein the structural rib extends between the outer vane platform and the inner vane platform, characterised in that the vane further comprises a baffle including a forward baffle section adjacent to the structural rib and an aft baffle section adjacent to the structural rib, wherein each of the first multiple of axial standoff ribs meet with one of the second multiple of axial standoff ribs at a leading edge, wherein each of the first multiple of axial standoff ribs and each of the second multiple of axial standoff ribs extends forward of a multiple of trailing edge apertures, wherein the structural rib does not extend fully between the first sidewall and the second sidewall and is connected to the first and second multiple of axial standoff ribs but not to the first sidewall and the second sidewall, wherein the structural rib and the first and second multiple of axial standoff ribs form a multiple of axial passages, wherein the multiple of axial passages extend between each of the multiple of axial standoff ribs(1 10), wherein each of the multiple of axial passages are defined between a baffle, the structural rib, the multiple of axial standoff ribs, and the respective first and second sidewalls (106, 108), wherein the vane further comprises apertures in a leading edge of the baffle configured to eject cooling air from the baffle. an outer vane platform; an inner vane platform; a first sidewall; a first multiple of axial standoff ribs that extend from the first sidewall; a second sidewall; a second multiple of axial standoff ribs that extend from the second sidewall; and a structural rib that extends between the first multiple of axial standoff ribs and the second multiple of axial standoff ribs, wherein the first sidewall is a pressure side and the second sidewall is a suction side of an airfoil, wherein the first sidewall and the second sidewall extend between the outer vane platform and the inner vane platform, wherein the structural rib extends between the outer vane platform and the inner vane platform, characterised in that the vane further comprises a baffle including a forward baffle section adjacent to the structural rib and an aft baffle section adjacent to the structural rib, wherein each of the first multiple of axial standoff ribs meet with one of the second multiple of axial standoff ribs at a leading edge, wherein each of the first multiple of axial standoff ribs and each of the second multiple of axial standoff ribs extends forward of a multiple of trailing edge apertures, wherein the structural rib does not extend fully between the first sidewall and the second sidewall and is connected to the first and second multiple of axial standoff ribs but not to the first sidewall and the second sidewall, wherein the structural rib and the first and second multiple of axial standoff ribs form a multiple of axial passages, wherein the multiple of axial passages extend between each of the multiple of axial standoff ribs(1 10), wherein each of the multiple of axial passages are defined between a baffle, the structural rib, the multiple of axial standoff ribs, and the respective first and second sidewalls (106, 108), wherein the vane further comprises apertures in a leading edge of the baffle configured to eject cooling air from the baffle.