A gas turbine engine comprising: at least a first shaft and a second shaft rotating at a higher speed than the first shaft, wherein the first and second shafts (40, 50) rotate about an engine axis of rotation; a geared architecture coupling the first shaft to a fan; at least a first driving turbine configured to drive the first shaft and a second driving turbine to drive the second shaft, wherein the first driving turbine is positioned downstream of the second driving turbine; and a combustor positioned immediately upstream of the second driving turbine, wherein the first driving turbine comprises a plurality of stages including at least a first turbine stage and a second turbine stage spaced immediately aft of the first turbine stage along the axis, the first turbine stage is the most upstream stage of the first driving turbine, the first turbine stage has a first temperature capability that is higher than a second temperature capability of the second turbine stage, and each of the first and second turbine stages (62, 64) are comprised of: a turbine disk (70, 74) comprised of a disk material; a plurality of turbine blades (72, 76) comprised of a blade material, wherein, for the first turbine stage, the disk material comprises a forged powdered metal material and the blade material comprises a ceramic matrix composite material; and the disk material and the blade material for the first and second stages are selected independently of each other based on operational temperatures at each stage's respective location along the first shaft of the first and second turbine stages (62, 64). at least a first shaft and a second shaft rotating at a higher speed than the first shaft, wherein the first and second shafts (40, 50) rotate about an engine axis of rotation; a geared architecture coupling the first shaft to a fan; at least a first driving turbine configured to drive the first shaft and a second driving turbine to drive the second shaft, wherein the first driving turbine is positioned downstream of the second driving turbine; and a combustor positioned immediately upstream of the second driving turbine, wherein the first driving turbine comprises a plurality of stages including at least a first turbine stage and a second turbine stage spaced immediately aft of the first turbine stage along the axis, the first turbine stage is the most upstream stage of the first driving turbine, the first turbine stage has a first temperature capability that is higher than a second temperature capability of the second turbine stage, and each of the first and second turbine stages (62, 64) are comprised of: a turbine disk (70, 74) comprised of a disk material; a plurality of turbine blades (72, 76) comprised of a blade material, wherein, for the first turbine stage, the disk material comprises a forged powdered metal material and the blade material comprises a ceramic matrix composite material; and the disk material and the blade material for the first and second stages are selected independently of each other based on operational temperatures at each stage's respective location along the first shaft of the first and second turbine stages (62, 64). a turbine disk (70, 74) comprised of a disk material; a plurality of turbine blades (72, 76) comprised of a blade material, wherein, for the first turbine stage, the disk material comprises a forged powdered metal material and the blade material comprises a ceramic matrix composite material; and the disk material and the blade material for the first and second stages are selected independently of each other based on operational temperatures at each stage's respective location along the first shaft of the first and second turbine stages (62, 64).