# US 11,078,800 B2 · Turbomachine rotor and method for producing same > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,078,800 B2 - Document ID: US11078800B2 - Status: Granted - Kind: B2 - Application number: 16/349,551 - Filed: 2017-11-13 - Published: 2019-08-29 - Granted: 2021-08-03 - Earliest claimed: 2016-11-14 - Assignees: MAN Energy Solutions SE - Applicants: MAN Energy Solutions SE - Inventors: Yves Bidaut; Sascha Schob; Christian Gold - Web page: https://patentgrep.com/patent/US11078800B2 ## CPC - F01D 5/3061: {by welding, brazing} - B23P 15/006: {turbine wheels} - F01D 5/141: {Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147)} - F05D 2230/10: by removing material - F05D 2230/237: Brazing - F05D 2230/238: Soldering - F05D 2270/114: by limiting mechanical stresses - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - B23P: METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS (arrangements for copying or controlling B23Q) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A turbomachine rotor having a radially inner hub element, a radially outer cover element, and rotor blades which extend between the hub element and the cover element and have rotor blade airfoils. The rotor blades are an integral component of the hub element and are bonded to the cover element according to a first alternative or are an integral component of the cover element and are bonded to the hub element according to a second alternative. The rotor blades have an integral socket adjacently to the cover element according to the first alternative or adjacently to the hub element according to the second alternative, and the rotor blades are bonded to the cover element according to the first alternative or to the hub element according to the second alternative via the socket. ## Claims ### Claim 1 A turbomachine rotor, comprising: a radially inner hub element; a radially outer shroud element; a plurality of moving blades comprising moving blade leafs extending between the hub element and the shroud element having a first axial width, wherein the moving blades are one of: an integral part of the hub element and are connected to the shroud element in a bonded manner, the moving blades comprise a first integral base having a second axial width that is greater than the first axial width, adjacent to the shroud element, via which the moving blades are connected in a bonded manner to the shroud element or an integral part of the shroud element and are connected to the hub element in a bonded manner, the moving blades comprise a second integral base having a third axial width that is greater than the first axial width, adjacent to the hub element via which the moving blades are connected in a bonded manner to the hub element. ### Claim 2 (depends on 1) The turbomachine rotor according to claim 1, wherein one of the first integral base and the second integral base include a transition radius between 0.5% and 2.5% of an outer diameter of the turbomachine rotor. ### Claim 3 (depends on 2) The turbomachine rotor according to claim 2, wherein the transition radius is between 0.5% and 2.0% of the outer diameter of the turbomachine rotor. ### Claim 4 (depends on 2) The turbomachine rotor according to claim 2, wherein the transition radius is between 1.0% and 2.5% of the outer diameter of the turbomachine rotor. ### Claim 5 (depends on 4) The turbomachine rotor according to claim 4, wherein the transition radius is between 1.0% and 2.0% of the outer diameter of the turbomachine rotor. ### Claim 6 (depends on 2) The turbomachine rotor according to claim 2, wherein the transition radius in the respective transition region is greater than a radius in a region of a respective bonded connection. ### Claim 7 (depends on 1) The turbomachine rotor according to claim 1, wherein the one of: the hub element, the moving blades, and the bases are produced as integral assemblies by milling or the shroud element, the moving blades, and the bases are produced as integral assemblies by milling. ### Claim 8 (depends on 1) The turbomachine rotor according to claim 1, wherein the one of: the moving blades and the shroud element are connected to one another in a bonded manner by soldering or the moving blades and the hub element are connected to one another in a bonded manner by soldering. ### Claim 9 A method for producing a turbomachine rotor, comprising: providing a plurality of moving blades comprising moving blade leafs each having a first axial width; providing one of: a hub element that is integrally bonded with the moving blades and a separate shroud element or a shroud element that is integrally bonded with the moving blades and a separate hub element, connecting the separate hub element or the separate shroud element to the moving blades via respective bases base having a second axial width that is greater than the first axial width. ### Claim 10 (depends on 9) The method for producing the turbomachine rotor according to claim 9, wherein one of: the hub element, the moving blades, and the bases are each provided as integral assemblies by milling or the shroud element, the moving blades, and the bases are each provided as integral assemblies by milling. ### Claim 11 (depends on 9) The method for producing the turbomachine rotor according to claim 9, wherein one of: the moving blades and the shroud element are each provided as integral assemblies by milling or the moving blades and the hub element are connected to one another by soldering in a region of the respective bases of the moving blades.