# US 9,040,870 B2 · Device for re-contouring a gas turbine blade > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,040,870 B2 - Document ID: US9040870B2 - Status: Granted - Kind: B2 - Application number: 13/723,222 - Filed: 2012-12-21 - Published: 2013-06-27 - Granted: 2015-05-26 - Earliest claimed: 2011-12-22 - Assignees: Lufthansa Technik AG - Applicants: Lufthansa Technik AG - Inventors: Stefan Czerner - Web page: https://patentgrep.com/patent/US9040870B2 ## CPC - B23K 26/352: for surface treatment - B23K 26/34: Laser welding for purposes other than joining - B23K 26/354: by melting - B23P 6/002: {Repairing turbine components, e.g. moving or stationary blades, rotors, (B23P6/045 takes precedence)} - B23Q 1/25: Movable or adjustable work or tool supports - B23Q 9/0014: {Portable machines provided with or cooperating with guide means supported directly by the workpiece during action} - B24B 19/14: for grinding turbine blades, propeller blades or the like (using grinding belts B24B21/16) - F01D 5/00: Blades; Blade-carrying members (nozzle boxes F01D9/02); Heating, heat-insulating, cooling or antivibration means on the blades or the members {(special arrangements in rotors dealing with breaking off of part thereof F01D21/045)} - F01D 5/005: {Repairing methods or devices} - B23C 3/00: Milling particular work; Special milling operations; Machines therefor (milling gear-teeth B23F, {heat assisted machining B23P25/00}) - B23K 37/04: for holding or positioning work - B23K 2101/001: {Turbines} - B23P 6/00: Restoring or reconditioning objects (straightening or restoring form of sheet metal, metal rods, metal tubes, metal profiles, or specific articles made therefrom B21D1/00, B21D3/00; repairing defective or damaged objects by casting techniques B22D19/10) - B23P 6/007: {using only additive methods, e.g. build-up welding} - F05D 2230/80: Repairing, retrofitting or upgrading methods - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - B23K: SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM - B23P: METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS (arrangements for copying or controlling B23Q) - B23Q: DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING (tools of the kind used in lathes or boring machines B23B27/00); MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT - B24B: MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING (grinding of gear teeth B23F, of screw-threads B23G1/36; by electro-erosion B23H; abrasive or related blasting B24C; tools for grinding, buffing or sharpening B24D; polishing compositions C09G1/00; abrasives C09K3/14; electrolytic etching or polishing C25F3/00; grinding arrangements for use on assembled railway tracks E01B31/17); DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - B23C: MILLING (broaching B23D; broach-milling in making gears B23F; arrangement for copying or controlling B23Q) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A device for recontouring a gas turbine blade includes at least one support configured to rest on an edge of the gas turbine blade during the recontouring, at least one side bearing configured to rest on an intake side or an outlet side of the gas turbine blade during the recontouring and a machining unit for machining the gas turbine blade. The machining unit is configured to fuse at least one partial area of the edge of the gas turbine blade using a beam of energy that is targeted such that material of the blade solidifies into a new contour, substantially without the addition of supplementary material. ## Claims ### Claim 1 A device for recontouring a gas turbine blade, the device comprising: at least one support configured to rest on an edge of the gas turbine blade during the recontouring; at least one side bearing configured to rest on at least one of an intake side or outlet side of the gas turbine blade during the recontouring; a machining unit for machining the gas turbine blade, the machining unit being configured to fuse at least one partial area of the edge of the gas turbine blade using a beam of energy that is targeted such that material of the blade solidifies into a new contour, substantially without the addition of supplementary material. ### Claim 2 (depends on 1) The device according to claim 1, wherein the at least one support includes at least two supports and the at least one side bearing includes at least two side bearings. ### Claim 3 (depends on 2) The device according to claim 2, wherein the machining unit is disposed between the two of the supports. ### Claim 4 (depends on 1) The device according to claim 1, wherein each of the side bearings include at least two locating points or faces. ### Claim 5 (depends on 4) The device according to claim 4, wherein each support includes a locating point or face, and wherein the locating points or faces of a first of the side bearings is disposed on a contact level with the locating point or face of a first of the supports. ### Claim 6 (depends on 5) The device according to claim 5, wherein the locating points or faces of a second of the side bearings are disposed on a contact level with a locating point or face of a second support. ### Claim 7 (depends on 1) The device according to claim 1, wherein at least one of the supports or side bearings include a hinge-mounted roller. ### Claim 8 (depends on 1) The device according to claim 1, where a press-on assembly is disposed on at least one of the intake side or outlet side of the gas turbine blade facing the side bearings. ### Claim 9 (depends on 8) The device according to claim 8, wherein the press-on assembly includes at least one of pneumatic, hydraulic or spring elements. ### Claim 10 (depends on 8) The device according to claim 8, wherein the press-on assembly includes hinge-mounted rollers. ### Claim 11 (depends on 7) The device according to claim 7, wherein the hinge-mounted roller is drivable by a driving device. ### Claim 12 (depends on 11) The device according to claim 11, wherein the driving device and the machining unit are controlled as coupled. ### Claim 13 (depends on 1) The device according to claim 1, wherein the machining unit includes a laser unit. ### Claim 14 (depends on 1) The device according to claim 1, wherein each support includes two rollers, which are connected to one another by a hinge-mounted shaft, and wherein the device is configured such that machining takes place between the two rollers.