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A method for joining a cast metal material blade ring and a metal material hub structure into a turbine rotor. One of the blade ring and the hub structure is mounted in a holder and the other is mounted in a rotation holder for being rotated. At least one of these mountings is heated, and then they

A method for joining a cast metal material blade ring and a metal material hub structure into a turbine rotor. One of the blade ring and the hub structure is mounted in a holder and the other is mounted in a rotation holder for being rotated. At least one of these mountings is heated, and then they are pressed together with a selected force while rotating to weld the ring interior wall and the disk side to form the assembled structure.

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1. A turbine rotor formed of a cast metal blade ring, including blades arrayed about its outer periphery and a frustoconical inner periphery, and a metal hub including an accommodation passageway centered about an axis of rotation, lubrication ports extending from the accommodation passageway to the

1. A turbine rotor formed of a cast metal blade ring, including blades arrayed about its outer periphery and a frustoconical inner periphery, and a metal hub including an accommodation passageway centered about an axis of rotation, lubrication ports extending from the accommodation passageway to the exterior of the metal hub, and a disk part radially outward from the accommodation passageway with a disk side configured such that at least a portion of the disk side is positioned against a portion of the inner periphery and joined together by an inertial friction weld formed by inertial friction welding after heating at least one of the portion of the disk side and the portion of the inner periphery wall to a temperature of about (1000° F.) 538° C. less than the melting point of the portion. 2. The rotor of claim 1 wherein both a ring interior wall of the blade ring and the hub disk part are heated to an temperature of about (1000° F.) 538° C. less than the melting point of the surface. 3. The rotor of claim 1 wherein at least one of a ring interior wall of the blade ring and the hub disk part is heated to a temperature of about (700° F.) 371° C. less than the melting point of the surface. 4. The rotor of claim 1 wherein the blade ring comprises a directionally solidified or conventional casting. 5. The rotor of claim 1 wherein the blade ring is made of a nickel base superalloy. 6. The rotor of claim 1 wherein the metal hub is formed of forged or cast metal. 7. The rotor of claim 1 wherein the metal hub is made of a nickel base superalloy. 8. The rotor of claim 1 wherein the hub includes a passageway through a shaft coupling part thereof about which the disk part is provided with the passageway extending substantially perpendicular to a plane extended through corresponding points in each of the blades. 9. A turbine rotor comprising: a cast metal blade ring including blades arrayed about an outer periphery and having a frustoconical inner periphery; anda metal hub including a first disk part with a frustoconical outer periphery that is mated with, and joined by an inertial friction weld to, the frustoconical inner periphery of the blade ring, the metal hub including a second disk part that is frustoconical and adjoins a first side of the first disk part, wherein the second disk part includes an annular stair-step portion on an outer surface of the second disk part adjacent to the first disk part. 10. The turbine rotor of claim 9 wherein the inertial friction weld is a weld formed by preheating at least one portion of the frustoconical inner periphery of the blade ring or the frustoconical outer periphery of the first disk part of the metal hub to a temperature of about (1000° F.) 538° C. less than a melting point of the portion, followed by inertial friction welding of the frustoconical inner periphery of the blade ring to the frustoconical outer periphery of the first disk part of the metal hub. 11. The turbine rotor of claim 9 wherein the blade ring is a directionally solidified casting. 12. The turbine rotor of claim 9 wherein the blade ring is formed of a nickel base superalloy. 13. The turbine rotor of claim 12 where in the metal hub is formed of a nickel base superalloy. 14. The turbine rotor of claim 13 wherein the metal hub is a directionally solidified casting.