A variable geometry turbocharger assembly comprising: a turbine housing having an exhaust gas inlet and an outlet, a volute connected to the inlet, and a nozzle wall adjacent the volute; a turbine wheel carried within the turbine housing and attached to a shaft; a plurality of vanes disposed within the turbine housing between the exhaust gas inlet and turbine wheel, each vane comprising: an inner airfoil surface oriented adjacent the turbine wheel; an outer airfoil surface oriented opposite and parallel to the inner airfoil surface; first and second axial surfaces (70, 72) each positioned perpendicular to and interposed between the inner and outer airfoil surfaces (68, 66); a leading edge positioned along a first inner and outer airfoil surface junction; a trailing edge positioned along a second inner and outer airfoil surface junction; characterized in that each of the first and second axial surfaces (70, 72) comprises a composite construction of a solid section and a cored-out section, wherein the solid section of one of the first and second axial surface (70, 72) occupies at least 25 percent of the axial surface area extending from the leading edge towards the trailing edge, and wherein the cored-out section for the same one of the first and second axial surface (70, 72) extends from the trailing edge towards the leading edge; and in that the solid section of the first axial surface is positioned opposite from the cored-out section of the second axial surface. a turbine housing having an exhaust gas inlet and an outlet, a volute connected to the inlet, and a nozzle wall adjacent the volute; a turbine wheel carried within the turbine housing and attached to a shaft; a plurality of vanes disposed within the turbine housing between the exhaust gas inlet and turbine wheel, each vane comprising: an inner airfoil surface oriented adjacent the turbine wheel; an outer airfoil surface oriented opposite and parallel to the inner airfoil surface; first and second axial surfaces (70, 72) each positioned perpendicular to and interposed between the inner and outer airfoil surfaces (68, 66); a leading edge positioned along a first inner and outer airfoil surface junction; a trailing edge positioned along a second inner and outer airfoil surface junction; an inner airfoil surface oriented adjacent the turbine wheel; an outer airfoil surface oriented opposite and parallel to the inner airfoil surface; first and second axial surfaces (70, 72) each positioned perpendicular to and interposed between the inner and outer airfoil surfaces (68, 66); a leading edge positioned along a first inner and outer airfoil surface junction; a trailing edge positioned along a second inner and outer airfoil surface junction; characterized in that each of the first and second axial surfaces (70, 72) comprises a composite construction of a solid section and a cored-out section, wherein the solid section of one of the first and second axial surface (70, 72) occupies at least 25 percent of the axial surface area extending from the leading edge towards the trailing edge, and wherein the cored-out section for the same one of the first and second axial surface (70, 72) extends from the trailing edge towards the leading edge; and in that the solid section of the first axial surface is positioned opposite from the cored-out section of the second axial surface.