Rotor integral alabeado con álabes soldados en el disco de Ti-6242 y Ti-6246; método para la fabricación de semejante rotor, compresor y turbina de gas con semejante rotor

Rotor (1) integral alabeado con un disco (2) y una multitud de álabes (3) dispuestos en el disco mediante soldadura, comprendiendo el rotor integral alabeado un disco (2) de Ti-6246 y los álabes de Ti-6242 ó Ti-6246, se caracteriza por que los materiales del disco (2) y del álabe (3) se diferencian en la microestructura de su estructura y el disco (2) presenta una estructura laminar con una microestructura con una multitud de láminas que se encuentran unas junto a otras de α-titanio y β-titanio. Compressor, preferably a high-pressure compressor of a gas turbine, comprises at least one integrally bladed rotor made of a disk (2) and many blades (3), which are disposed on the disk, where the integrally bladed rotor comprises at least one titanium material comprising titanium-6246 and titanium-6242. The materials of the disk and the blades differ in their chemical composition and/or their micro-structure. Independent claims are also included for: (1) an integrally bladed rotor with the disk and many blades disposed on the disk, where the integrally bladed rotor has at least one titanium material comprising titanium-6246 and titanium-6242, and the materials of the disk and the blade differ in their chemical composition and/or their micro-structure; (2) producing an integrally bladed rotor, preferably for a compressor, comprising welding the blades to the disk by a pressure welding method supported by high-frequency current, where the current is conducted through the joint surfaces and leads to local melting of surfaces, and providing a disk, which is formed from titanium-6246 or lamellar titanium-6246 for the welded joint (4), and forming the blades from titanium-6242 or bimodal titanium-6246; and (3) a gas turbine with integrally bladed rotor.