A method of fabricating a turbine wheel comprising a rotor disk and a plurality of turbine blades each operatively connected to the rotor disk through a blade mount, wherein the method comprises: locating a cooling passage within a blade mount preliminary configuration and a cooling inlet on a surface of the blade mount preliminary configuration; optionally, locating a stress relief hole passing through a rotor disk preliminary configuration; the method, characterized in that: designing a rotor disk bonding surface geometry of the rotor disk preliminary configuration and a blade mount bonding surface geometry of the blade mount preliminary configuration is based upon location of the cooling passage, the cooling inlet, and, optionally, the stress relief hole, and further based upon a stress analysis of the turbine wheel; generating a rotor disk production configuration and a blade mount production configuration based upon the respective rotor disk preliminary configuration having the rotor disk bonding surface geometry and the blade mount preliminary configuration having the blade mount bonding surface geometry; forming the blade mount based upon the blade mount production configuration and the rotor disk based upon the rotor disk production configuration, wherein the blade mount and the rotor disk are formed from dissimilar materials having different mechanical and/or thermal properties; forming a blade ring comprising a plurality of blade mounts; and bonding the blade ring to the rotor disk to form a bond line, wherein the bond line is located between the cooling passage and the optional stress relief hole, when present, and wherein the bond line is spaced from the cooling inlet and the cooling passage. locating a cooling passage within a blade mount preliminary configuration and a cooling inlet on a surface of the blade mount preliminary configuration; optionally, locating a stress relief hole passing through a rotor disk preliminary configuration; the method, characterized in that: designing a rotor disk bonding surface geometry of the rotor disk preliminary configuration and a blade mount bonding surface geometry of the blade mount preliminary configuration is based upon location of the cooling passage, the cooling inlet, and, optionally, the stress relief hole, and further based upon a stress analysis of the turbine wheel; generating a rotor disk production configuration and a blade mount production configuration based upon the respective rotor disk preliminary configuration having the rotor disk bonding surface geometry and the blade mount preliminary configuration having the blade mount bonding surface geometry; forming the blade mount based upon the blade mount production configuration and the rotor disk based upon the rotor disk production configuration, wherein the blade mount and the rotor disk are formed from dissimilar materials having different mechanical and/or thermal properties; forming a blade ring comprising a plurality of blade mounts; and bonding the blade ring to the rotor disk to form a bond line, wherein the bond line is located between the cooling passage and the optional stress relief hole, when present, and wherein the bond line is spaced from the cooling inlet and the cooling passage. designing a rotor disk bonding surface geometry of the rotor disk preliminary configuration and a blade mount bonding surface geometry of the blade mount preliminary configuration is based upon location of the cooling passage, the cooling inlet, and, optionally, the stress relief hole, and further based upon a stress analysis of the turbine wheel; generating a rotor disk production configuration and a blade mount production configuration based upon the respective rotor disk preliminary configuration having the rotor disk bonding surface geometry and the blade mount preliminary configuration having the blade mount bonding surface geometry; forming the blade mount based upon the blade mount production configuration and the rotor disk based upon the rotor disk production configuration, wherein the blade mount and the rotor disk are formed from dissimilar materials having different mechanical and/or thermal properties; forming a blade ring comprising a plurality of blade mounts; and bonding the blade ring to the rotor disk to form a bond line, wherein the bond line is located between the cooling passage and the optional stress relief hole, when present, and wherein the bond line is spaced from the cooling inlet and the cooling passage.