US20060138093A1 - Method and apparatus for repairing superalloy components - Google Patents
Method and apparatus for repairing superalloy components Download PDFInfo
- Publication number
- US20060138093A1 US20060138093A1 US11/060,937 US6093705A US2006138093A1 US 20060138093 A1 US20060138093 A1 US 20060138093A1 US 6093705 A US6093705 A US 6093705A US 2006138093 A1 US2006138093 A1 US 2006138093A1
- Authority
- US
- United States
- Prior art keywords
- metallic component
- weld
- welding
- alloy
- component
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- 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
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/20—Bonding
- B23K26/206—Laser sealing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- 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
- B23K10/00—Welding or cutting by means of a plasma
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- 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
- B23K15/00—Electron-beam welding or cutting
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- 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
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/002—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating specially adapted for particular articles or work
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- 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
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/02—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating by means of a press ; Diffusion bonding
- B23K20/021—Isostatic pressure welding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- 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
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/20—Bonding
- B23K26/32—Bonding taking account of the properties of the material involved
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- 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
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/34—Laser welding for purposes other than joining
- B23K26/342—Build-up welding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- 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
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/60—Preliminary treatment
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- 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
- B23K9/00—Arc welding or cutting
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- 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
- B23K9/00—Arc welding or cutting
- B23K9/04—Welding for other purposes than joining, e.g. built-up welding
- B23K9/044—Built-up welding on three-dimensional surfaces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
- B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
- B23P6/007—Repairing turbine components, e.g. moving or stationary blades, rotors using only additive methods, e.g. build-up welding
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/005—Repairing methods or devices
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- 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
- B23K2101/00—Articles made by soldering, welding or cutting
- B23K2101/001—Turbines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- 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
- B23K2103/00—Materials to be soldered, welded or cut
- B23K2103/18—Dissimilar materials
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- 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
- B23K2103/00—Materials to be soldered, welded or cut
- B23K2103/18—Dissimilar materials
- B23K2103/26—Alloys of Nickel and Cobalt and Chromium
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
Definitions
- the present invention relates to a method of repairing metallic components, and in particular to a method of repairing superalloy turbine blades and nozzles.
- GTAW gas tungsten arc welding
- PTAW plasma transferred arc welding
- hot cracking occurs in the filler metal and heat affected zone (HAZ) during welding and is typically in the form of tiny fissures, or micro-cracks, beneath the surface of the weldment.
- Strain age cracking occurs during post weld heat treatment, usually initiating in the HAZ and often propagating well into the adjacent base alloy. Strain age cracks are generally much longer than hot cracks, sometimes extending several inches into the base material.
- weld filler materials that have been most effective in the repair of precipitation strengthened superalloys are those that do not cause hot cracking or strain age cracking. These filler materials are simpler, solid-solution strengthened alloys, but they have significantly lower strength than the superalloys. Therefore, the use of low strength filler materials significantly limits the locations on certain components where weld repairs can be made.
- turbine blades For example, current industry practice for turbine blades permits welding only in areas of very low stress, and some 80 to 90 percent of blade surfaces are non-repairable. Blades with non-repairable damage are generally returned to suppliers as scrap for credit against replacement blades.
- the financial impact on utilities is considerable since a single air-cooled, rotating blade may cost up to thirty-five thousand dollars, and, depending upon the turbine manufacturer and model, each turbine has multiple blade rows consisting of approximately 90 to 120 blades per row.
- Turbine blades are not the only components employing high temperature superalloys and requiring repair. Advanced turbines will employ more components made with the more sophisticated superalloys, thereby increasing the number of different superalloy components that may need weld repair. In fact, it is anticipated that future turbine nozzles will be made of nickel-based superalloys such as GTD-111.
- EBW is currently being used for the repair of gas turbine stationary nozzles, combustion components, and shaft seals where the joint geometry is relatively straight or in one plane.
- EBW has inherent limitations in weld path flexibility and must be performed in a vacuum chamber.
- Application of EBW in the repair of complex blade airfoil shapes would require significant development and is not considered practical at this time.
- a method of repairing a metallic component such as a superalloy turbine blade or nozzle.
- the component is prepared by stripping the protective coatings from it.
- the method of repairing the metallic component comprises subjecting the metallic component to a first hot isostatic processing operation, welding the metallic component, and exposing the metallic component to a second hot isostatic processing operation.
- weld fillers may be added to the weld area.
- the component is finally prepared for re-entry into service.
- One of the advantages of the technique of the invention is that the use of precipitation strengthened filler superalloys more closely matches the mechanical properties of the base alloy.
- Another advantage of the invention is that the use of high energy-low heat methods, such as EBW, as the welding heat source, as opposed to conventional arc welding processes, produces smaller heat affected zones and reduces the stress field due to the lower quantity of heat introduced in the weld zone.
- a further advantage of the invention is that the introduction of a dual hot isostatic process, which brackets the welding application, preconditions the substrate for welding and reduces any micro-cracking inherent with the superalloy blades after welding.
- the invention also includes components repaired according to the methods of the invention, or a metallic component repaired according to a method comprising subjecting a metallic component to a first hot isostatic processing operation, welding the metallic component, and exposing the metallic component to a second hot isostatic processing operation.
- FIG. 1 is a flow chart of an embodiment of the method of the invention
- FIG. 2 is a perspective view of a turbine blade processed in accordance with an embodiment of the invention
- FIG. 3 is a perspective view of a laser welding head and weld filler feeder utilized in accordance with an embodiment of the invention
- FIG. 4 is a cross sectional view taken along the line A-A of FIG. 3 ;
- FIG. 5 is a perspective view of a turbine nozzle processed in accordance with an embodiment of the invention.
- FIG. 6 is a perspective view of a gas tungsten arc welding (GTAW) apparatus utilized in accordance with an embodiment of the invention.
- GTAW gas tungsten arc welding
- FIG. 7 is perspective view of a plasma transferred arc welding (PTAW) apparatus utilized in accordance with an embodiment of the invention.
- PTAW plasma transferred arc welding
- FIG. 1 is a flow chart of an embodiment of the method of the invention.
- a workpiece such as a turbine blade, a turbine nozzle, or other metallic component that has been removed from service, is initially prepared for its repair.
- This prepare workpiece step 22 may include the stripping of any protective coatings from the workpiece, which is commonly accomplished with chemical stripping solutions.
- the prepare workpiece step 22 further includes preparing the specific areas of the workpiece that are to be repaired by conventional methods such as machining and grinding.
- the workpiece is pre-conditioned for welding by subjecting it to a first hot isostatic process (HIP).
- Hot isostatic processing can be described as an idealized hot pressing or forging operation, or as high-pressure heat treatment.
- the basic HIP process subjects a workpiece to a combination of elevated temperatures and isostatic gas pressures (usually inert). Processing is usually carried out in pressure vessels containing internal furnaces at temperatures in the range required for solution annealing. In solution annealing a metal is treated to render it less brittle and more workable. The metal is heated to a common phase and then cooled very slowly and uniformly with time and temperature set to create the desired properties. Annealing increases ductility and relieves internal strains that lead to failures in service.
- weld step 26 the workpiece is welded.
- the weld step 26 can be accomplished using a number of welding apparatuses, for example, weld step 26 may use an LBW apparatus; an EBW welding apparatus; a GTAW welding apparatus; or a PTAW welding apparatus, depending in part upon the workpiece 20 .
- some workpieces have a geometry that makes them difficult to weld using certain welding apparatuses.
- EBW may be difficult to use on a complex-geometry part, such as a turbine blade, but it may be used in an embodiment of the present invention to repair simpler parts, such as a nozzle.
- traditional methods using GTAW or PTAW to repair superalloy parts are limited to a component's low stress areas, an embodiment of the invention allows using GTAW or PTAW to repair high stress areas.
- a weld filler is dispensed.
- dispense weld filler step 28 may dispense a weld filler with strength and temperature properties that are similar to, or the same as, the metal being welded.
- the weld fillers generally employed include IN-939, or IN-738, or derivatives of either, and for nozzles made of GTD-111 the weld fillers generally employed are Rene 80, or derivatives thereof.
- the weld apparatus traverses the workpiece.
- weld step 26 dispense weld filler step 28 , and traverse workpiece step 30 are repeated to weld a workpiece. This repetition is shown in multiple passes/layers step 32 .
- Multiple passes/layers step 32 also accounts for movement of the weld apparatus that is necessary to re-visit a previously welded area on the workpiece and re-weld, or add an additional weld layer to, that previously welded area.
- the weld apparatus movement for traverse workpiece step 30 and multiple passes/layers step 32 may be accomplished by an apparatus such as a positioner 52 , as shown in FIG. 3 .
- the workpiece is exposed to a second HIP process.
- the second HIP step 34 is performed to close voids that may have developed during weld step 26 and may be performed at conditions similar to the first conditioning HIP step 24 .
- the second HIP step 34 may include an initial operation to seal any micro-cracking that had intersected the surface of workpiece 20 .
- micro-cracking does not intersect the surface on small weld buildups; however, it may in large weld repairs or buildups.
- the micro-crack sealing operation may be performed using a lower strength solid-solution strengthened alloy, such as IN-625 over the IN-939 alloy weld filler used to repair a turbine blade of IN-738.
- Such a lower strength solid-solution strengthened alloy even though not suitable for dispense weld filler step 28 , may still seal the surface of workpiece 20 such that it can undergo the second HP process and fuse any micro-cracks that are present. Micro-cracks are discussed in greater detail with reference to FIG. 4 .
- the workpiece is finished, which typically includes grinding, machining, and re-coating operations.
- the shaping process may be performed with commercial computer numerically controlled (CNC) equipment that can accommodate components of complex geometry, such as the blade 40 of FIG. 2 .
- CNC computer numerically controlled
- the finishing step 36 also includes age heat treating.
- the workpiece 20 may then be re-introduced into service.
- FIG. 2 is a perspective view of a turbine blade processed in accordance with an embodiment of the invention. This figures illustrates the complex geometry of the turbine blade that makes it difficult to repair using certain welding apparatuses.
- FIG. 3 is a perspective view of a laser welding head and weld filler feeder utilized in accordance with an embodiment of the invention.
- the laser welding apparatus 42 includes a laser beam 58 that issues from a lower remote end 55 of a weld head 54 .
- the weld head 54 is capable of moving along a plurality of axes by integrating a positioner 52 onto the upper portion 53 of a weld head 54 . This motion is controlled by a position controller 56 , which may be a computer numerically controlled positioning mechanism (CNC).
- a feed pipe 50 introduces precipitation strengthened superalloy weld fillers 44 to a weld application area 60 via a powder feed system 48 .
- the weld filler 44 is typically in a powder form and is employed to replace the component alloy in damaged areas.
- the laser beam 58 together with the weld filler 44 , is directed at the weld application area 60 on the area of the workpiece 20 being repaired.
- the laser welding process can be used to repair equiaxed IN-738 turbine blades and in such a case the weld fillers generally employed are of the IN-939 type or deriviatives thereof.
- the laser welding apparatus 42 may utilize a Nd:YAG (Yttrium Aluminum Garnet—Doped with Nd) laser or a carbon dioxide laser, but is not limited to either.
- FIG. 4 is a cross sectional view taken along the line A-A of FIG. 3 . Due to the high strength of the blade material, very small cracks 71 (commonly referred to as micro-cracking or fissures) tend to form directly under the applied weld bead 67 . These cracks do not intersect the surface 69 of the blade 40 and thus are capable of being sealed by a second HIP process. This second HIP step is depicted by step 34 in FIG. 1 . The second HIP step 34 is performed at conditions similar to the first conditioning HIP step 24 .
- the second HIP step 34 may include an initial micro-cracking sealing operation to seal the very small cracks 71 , should any have intersected the surface 69 , although they typically do not with small weld buildups.
- This micro-cracking sealing operation may be performed using a solid-solution strengthened alloy, such as IN-625 over a IN-939 alloy.
- the weld buildup of IN-625 is used to seal the surface so that it can undergo the second HIP process and fuse any micro-cracks that are present.
- An EBW apparatus could also be used in weld step 26 instead of an LBW apparatus in many instances.
- LBW and EBW are both low heat-high energy processes capable of providing small volume welds with narrow heat affected zones.
- EBW must be performed in a vacuum chamber and has inherent limitations in weld path flexibility. These limit its use to certain applications. But since EBW is currently being used for the repair of gas turbine stationary nozzles, combustion components and shaft seals where the joint geometry is relatively straight or in one plane, EBW can be used in weld step 26 when those or similar components are repaired according to the method of the invention.
- FIG. 5 is a perspective view of a turbine nozzle processed in accordance with an embodiment of the invention. This figure illustrates the geometry of a turbine nozzle 62 that allows using a GTAW to repair it.
- FIG. 6 is a perspective view of a GTAW apparatus utilized in accordance with an embodiment of the invention. This is also sometimes known as tungsten inert gas welding (TIG). GTAW is currently used to weld turbine blades and nozzles. GTAW is often a manual operation and, therefore, is also useful where the workpiece has unusual geometry, or is repaired so rarely that developing a computer controlled process is inefficient, although GTAW is often computer controlled.
- TOG tungsten inert gas welding
- GTAW typically requires a solid welding rod to supply a weld filler, which, when they are solid weld filler rods of the superalloy type, are difficult to fabricate in wire or spool form due in part to their high strength.
- a GTAW process is controlled by computer it employs a wire or spool feed system (not shown) that is similar to powder feed system 48 in that it can also be controlled by a computer (not shown) to supply weld filler.
- wire or spool feed systems are common, and superalloy wires or spools themselves, though expensive and difficult to manufacture, are known as well.
- an electrode 66 projects from a torch body 64 toward a workpiece 20 .
- An arc 70 is created between the electrode 66 and the workpiece 20 by causing a potential difference between them.
- a shielding gas 68 passes through the torch body 64 and surrounds the electrode 66 , arc 70 , and the weld application area 60 .
- the arc 70 is shielded from the atmosphere by the shielding gas 68 , which is an inert gas and usually argon gas.
- Weld filler 44 typically a solid rod in the case of GTAW, is supplied to the arc 70 .
- GTAW is used in weld step 26 of FIG. 1 .
- GTAW is an appropriate welding method in weld step 26 where the workpiece has a complex geometry that does not lend itself to computer-controlled welding.
- turbine nozzles that are made of high temperature superalloys could be repaired using GTAW in weld step 26 of the present invention with weld filler supplied in the form of a rod and manually guided to the appropriate area of the arc.
- FIG. 7 is perspective view of a PTAW apparatus utilized in accordance with an embodiment of the invention.
- PTAW like GTAW, is currently used to repair turbine blades and nozzles. Unlike GTAW, however, PTAW typically uses weld filler 44 supplied in the form of a powder. Thus PTAW may use powder feed system 48 of FIG. 3 . If the welded component requires a superalloy weld filler, then PTAW may lend itself more readily to computer control than GTAW, since superalloy weld fillers 44 are found more easily in powder form.
- an electrode 66 projects toward an orifice 73 within an orifice body 74 .
- Orifice gas 72 flows around electrode 66 and through orifice 73 towards workpiece 20 .
- a plasma arc 75 is created between the electrode 66 and the workpiece 20 by causing a potential difference between them through orifice gas 72 (in a non-transferred plasma arc welding apparatus the potential is created between the electrode 66 and the orifice body 74 ).
- An outer shield cup 76 surrounds the orifice body 74 .
- a shielding gas 68 passes between the outer shield cup 76 and orifice body 74 and surrounds the plasma arc 75 and weld application area 60 .
- the plasma arc 75 and weld application area 60 are shielded from the atmosphere by the shielding gas 68 , which is an inert gas and usually argon gas.
- Weld filler 44 which is typically powder, is supplied to the plasma arc 75 using a powder feed system 48 of FIG. 3 .
- PTAW systems have the advantages of laser welding systems that they can be automated and thus used where fine control of the process is necessary, although PTAW, like GTAW, is a higher energy process than laser welding and may cause more strain age cracking or hot cracking before the second HIP. Where that does not significantly concern the user, however, PTAW may be desired over laser welding systems because PTAW is a manual process and has relatively lower costs associated with the equipment.
Abstract
A method of repairing a metallic component, such as a superalloy turbine blade or turbine nozzle, includes the step of preparing the component by stripping the protective coatings from the component. The component is then pre-conditioned for welding by a first hot isostatic process. Once the conditioning sequence is complete, the component is welded using any of a number of welding techniques and by adding weld fillers to the weld area. After the welding step, the component is sealed by a second hot isostatic process treatment performed at conditions similar to the first hot isostatic process. The component is finally prepared for re-entry into service.
Description
- This application is a continuation-in-part of U.S. application Ser. No. 09/487,931 filed Jan. 20, 2000, now U.S. Pat. No. 6,364,971, which is incorporated by reference.
- The present invention relates to a method of repairing metallic components, and in particular to a method of repairing superalloy turbine blades and nozzles.
- Over the years, superalloy materials have been developed to provide mechanical strength to turbine blades (or “buckets”) and nozzles (or “vanes”) operating at high temperatures. Most modern high temperature superalloy articles such as nickel-based, precipitation strengthened superalloys are complex alloys at the cutting edge of high temperature metallurgy, and no other class of alloys can match their high temperature strength. This strength makes these alloys very useful in high-temperature high-strength requiring applications, such as turbine components.
- These components are difficult and expensive to manufacture, and it is far more desirable to repair a damaged component than to replace one. As a result, a variety of repair methods have been developed, such as conventional fusion welding, plasma thermal metal spraying, brazing, etc. These processes are most suitable for providing relatively thin coatings of weld material. Narrow-gap brazing techniques have been plagued by joint contamination that results in incomplete bonding, even when elaborate thermochemical cleaning processes precede the brazing operation. Narrow gap brazing also lacks the ability to restore damaged or missing areas on a superalloy component or turbine blade. Joints formed using wide gap brazing methods can be difficult to set-up and porosity in the deposited filler material continues to be a concern.
- Traditional weld repair methods that are capable of providing thicker coatings, such as gas tungsten arc welding (GTAW) and plasma transferred arc welding (PTAW), have met with only limited success. These traditional methods have been unsatisfactory because the quantities of certain precipitate-forming elements (mainly aluminum and titanium) that are added specifically to superalloys for high temperature strength cause traditional methods to produce poor welds using superalloy weld fillers. Although GTAW and PTAW are the methods most commonly used in turbine blade repair today they use lower strength weld fillers. Thus, their current use is limited to certain blade surfaces that experience very low stress and to other components that are made with other materials. Turbine nozzles, for example, are currently made with cobalt-based superalloys that lend themselves to repair using current welding or brazing methods.
- More specifically, weld quality is poor because the elements added for high temperature strength result in welds that have a tendency to form or contain cracks. Two distinct types of cracking have been identified: (1) hot cracking and (2) strain age cracking. Hot cracking occurs in the filler metal and heat affected zone (HAZ) during welding and is typically in the form of tiny fissures, or micro-cracks, beneath the surface of the weldment. Strain age cracking occurs during post weld heat treatment, usually initiating in the HAZ and often propagating well into the adjacent base alloy. Strain age cracks are generally much longer than hot cracks, sometimes extending several inches into the base material.
- Weld filler materials that have been most effective in the repair of precipitation strengthened superalloys are those that do not cause hot cracking or strain age cracking. These filler materials are simpler, solid-solution strengthened alloys, but they have significantly lower strength than the superalloys. Therefore, the use of low strength filler materials significantly limits the locations on certain components where weld repairs can be made.
- For example, current industry practice for turbine blades permits welding only in areas of very low stress, and some 80 to 90 percent of blade surfaces are non-repairable. Blades with non-repairable damage are generally returned to suppliers as scrap for credit against replacement blades. The financial impact on utilities is considerable since a single air-cooled, rotating blade may cost up to thirty-five thousand dollars, and, depending upon the turbine manufacturer and model, each turbine has multiple blade rows consisting of approximately 90 to 120 blades per row. Turbine blades, however, are not the only components employing high temperature superalloys and requiring repair. Advanced turbines will employ more components made with the more sophisticated superalloys, thereby increasing the number of different superalloy components that may need weld repair. In fact, it is anticipated that future turbine nozzles will be made of nickel-based superalloys such as GTD-111.
- Various studies have been conducted to evaluate methods for the repair of precipitation strengthened superalloys. These studies have included evaluations of both narrow and wide-gap brazing, gas tungsten arc welding (GTAW), plasma transferred arc welding (PTAW), and electron beam welding (EBW).
- Many experts believe that low heat-high energy welding processes have the highest potential for advancing the state of the art for blade repair. The use of such processes has been shown to reduce cracking while using superalloy weld filler. Laser beam welding (LBW) and EBW are both low heat-high energy processes capable of providing small volume welds with narrow heat affected zones. The laser welding process has seen limited use in the repair of IN-738 superalloy turbine blades. When employed, laser welding has been restricted to regions of very low stress using solid solution strengthened weld filler alloys, mainly IN-625, which provide mechanical properties significantly inferior to those of the base IN-738 material. Structural weld repairs that extend into the more highly stressed regions of the blade cannot be performed currently. EBW is currently being used for the repair of gas turbine stationary nozzles, combustion components, and shaft seals where the joint geometry is relatively straight or in one plane. EBW has inherent limitations in weld path flexibility and must be performed in a vacuum chamber. Application of EBW in the repair of complex blade airfoil shapes would require significant development and is not considered practical at this time. In view of the foregoing, it would be highly desirable to provide an improved technique for repairing metallic parts, such as superalloy turbine blades or other superalloy components.
- According to the invention there is provided a method of repairing a metallic component, such as a superalloy turbine blade or nozzle. The component is prepared by stripping the protective coatings from it. The method of repairing the metallic component comprises subjecting the metallic component to a first hot isostatic processing operation, welding the metallic component, and exposing the metallic component to a second hot isostatic processing operation. In addition, when welding the metallic component, weld fillers may be added to the weld area. The component is finally prepared for re-entry into service.
- One of the advantages of the technique of the invention is that the use of precipitation strengthened filler superalloys more closely matches the mechanical properties of the base alloy. Another advantage of the invention is that the use of high energy-low heat methods, such as EBW, as the welding heat source, as opposed to conventional arc welding processes, produces smaller heat affected zones and reduces the stress field due to the lower quantity of heat introduced in the weld zone. A further advantage of the invention is that the introduction of a dual hot isostatic process, which brackets the welding application, preconditions the substrate for welding and reduces any micro-cracking inherent with the superalloy blades after welding.
- This repair methodology provides a means to extend the current limits of repair to the more highly stressed areas of the component, or to repair components made of superalloys in general. Thus, the invention also includes components repaired according to the methods of the invention, or a metallic component repaired according to a method comprising subjecting a metallic component to a first hot isostatic processing operation, welding the metallic component, and exposing the metallic component to a second hot isostatic processing operation.
- For a better understanding of the nature and objects of the invention, reference should be made to the following detailed description taken in conjunction with the accompanying drawings, in which:
-
FIG. 1 is a flow chart of an embodiment of the method of the invention; -
FIG. 2 is a perspective view of a turbine blade processed in accordance with an embodiment of the invention; -
FIG. 3 is a perspective view of a laser welding head and weld filler feeder utilized in accordance with an embodiment of the invention; -
FIG. 4 is a cross sectional view taken along the line A-A ofFIG. 3 ; -
FIG. 5 is a perspective view of a turbine nozzle processed in accordance with an embodiment of the invention; -
FIG. 6 is a perspective view of a gas tungsten arc welding (GTAW) apparatus utilized in accordance with an embodiment of the invention; and -
FIG. 7 is perspective view of a plasma transferred arc welding (PTAW) apparatus utilized in accordance with an embodiment of the invention. - Like reference numerals refer to corresponding elements throughout the several drawings.
-
FIG. 1 is a flow chart of an embodiment of the method of the invention. In thestep 22, a workpiece, such as a turbine blade, a turbine nozzle, or other metallic component that has been removed from service, is initially prepared for its repair. Thisprepare workpiece step 22 may include the stripping of any protective coatings from the workpiece, which is commonly accomplished with chemical stripping solutions. Theprepare workpiece step 22 further includes preparing the specific areas of the workpiece that are to be repaired by conventional methods such as machining and grinding. - In the
step 24, the workpiece is pre-conditioned for welding by subjecting it to a first hot isostatic process (HIP). Hot isostatic processing can be described as an idealized hot pressing or forging operation, or as high-pressure heat treatment. The basic HIP process subjects a workpiece to a combination of elevated temperatures and isostatic gas pressures (usually inert). Processing is usually carried out in pressure vessels containing internal furnaces at temperatures in the range required for solution annealing. In solution annealing a metal is treated to render it less brittle and more workable. The metal is heated to a common phase and then cooled very slowly and uniformly with time and temperature set to create the desired properties. Annealing increases ductility and relieves internal strains that lead to failures in service. These annealing temperatures coupled with the high pressures generated from thefirst HIP process 24, tend to close voids that might have existed in the original casting as well as those that are induced by creep deformation during service exposure. Closing these voids aids in crack prevention during subsequent welding since it lowers the number of potential crack initiation sites. Heating to temperatures in the solution annealing range during the HIP process also increases the ductility of the alloy, thereby increasing its ability to accommodate welding strains. - In the
step 26, the workpiece is welded. Theweld step 26 can be accomplished using a number of welding apparatuses, for example,weld step 26 may use an LBW apparatus; an EBW welding apparatus; a GTAW welding apparatus; or a PTAW welding apparatus, depending in part upon theworkpiece 20. Regarding the workpiece's effect on the applicable welding apparatus, some workpieces have a geometry that makes them difficult to weld using certain welding apparatuses. For example, and as discussed previously, EBW may be difficult to use on a complex-geometry part, such as a turbine blade, but it may be used in an embodiment of the present invention to repair simpler parts, such as a nozzle. Similarly, while traditional methods using GTAW or PTAW to repair superalloy parts are limited to a component's low stress areas, an embodiment of the invention allows using GTAW or PTAW to repair high stress areas. - In the
step 28, a weld filler is dispensed. For welding workpieces made of superalloys, dispenseweld filler step 28 may dispense a weld filler with strength and temperature properties that are similar to, or the same as, the metal being welded. For example, with turbine blades made of IN-738 the weld fillers generally employed include IN-939, or IN-738, or derivatives of either, and for nozzles made of GTD-111 the weld fillers generally employed are Rene 80, or derivatives thereof. - In the
step 30, the weld apparatus traverses the workpiece. Thus,weld step 26, dispenseweld filler step 28, and traverseworkpiece step 30 are repeated to weld a workpiece. This repetition is shown in multiple passes/layers step 32. Multiple passes/layers step 32 also accounts for movement of the weld apparatus that is necessary to re-visit a previously welded area on the workpiece and re-weld, or add an additional weld layer to, that previously welded area. The weld apparatus movement fortraverse workpiece step 30 and multiple passes/layers step 32 may be accomplished by an apparatus such as apositioner 52, as shown inFIG. 3 . - In the
step 34, the workpiece is exposed to a second HIP process. Thesecond HIP step 34 is performed to close voids that may have developed duringweld step 26 and may be performed at conditions similar to the firstconditioning HIP step 24. Thesecond HIP step 34 may include an initial operation to seal any micro-cracking that had intersected the surface ofworkpiece 20. Typically, micro-cracking does not intersect the surface on small weld buildups; however, it may in large weld repairs or buildups. The micro-crack sealing operation may be performed using a lower strength solid-solution strengthened alloy, such as IN-625 over the IN-939 alloy weld filler used to repair a turbine blade of IN-738. Such a lower strength solid-solution strengthened alloy, even though not suitable for dispenseweld filler step 28, may still seal the surface ofworkpiece 20 such that it can undergo the second HP process and fuse any micro-cracks that are present. Micro-cracks are discussed in greater detail with reference toFIG. 4 . - In the
step 36, the workpiece is finished, which typically includes grinding, machining, and re-coating operations. The shaping process may be performed with commercial computer numerically controlled (CNC) equipment that can accommodate components of complex geometry, such as theblade 40 ofFIG. 2 . The finishingstep 36 also includes age heat treating. Theworkpiece 20 may then be re-introduced into service. -
FIG. 2 is a perspective view of a turbine blade processed in accordance with an embodiment of the invention. This figures illustrates the complex geometry of the turbine blade that makes it difficult to repair using certain welding apparatuses. -
FIG. 3 is a perspective view of a laser welding head and weld filler feeder utilized in accordance with an embodiment of the invention. Thelaser welding apparatus 42 includes alaser beam 58 that issues from a lowerremote end 55 of aweld head 54. Theweld head 54 is capable of moving along a plurality of axes by integrating apositioner 52 onto theupper portion 53 of aweld head 54. This motion is controlled by aposition controller 56, which may be a computer numerically controlled positioning mechanism (CNC). Afeed pipe 50 introduces precipitation strengthenedsuperalloy weld fillers 44 to aweld application area 60 via apowder feed system 48. Theweld filler 44 is typically in a powder form and is employed to replace the component alloy in damaged areas. Thelaser beam 58, together with theweld filler 44, is directed at theweld application area 60 on the area of theworkpiece 20 being repaired. - As mentioned with respect to
FIG. 1 , the laser welding process can be used to repair equiaxed IN-738 turbine blades and in such a case the weld fillers generally employed are of the IN-939 type or deriviatives thereof. Thelaser welding apparatus 42 may utilize a Nd:YAG (Yttrium Aluminum Garnet—Doped with Nd) laser or a carbon dioxide laser, but is not limited to either. -
FIG. 4 is a cross sectional view taken along the line A-A ofFIG. 3 . Due to the high strength of the blade material, very small cracks 71 (commonly referred to as micro-cracking or fissures) tend to form directly under the appliedweld bead 67. These cracks do not intersect the surface 69 of theblade 40 and thus are capable of being sealed by a second HIP process. This second HIP step is depicted bystep 34 inFIG. 1 . Thesecond HIP step 34 is performed at conditions similar to the firstconditioning HIP step 24. Thesecond HIP step 34 may include an initial micro-cracking sealing operation to seal the verysmall cracks 71, should any have intersected the surface 69, although they typically do not with small weld buildups. This micro-cracking sealing operation may be performed using a solid-solution strengthened alloy, such as IN-625 over a IN-939 alloy. The weld buildup of IN-625 is used to seal the surface so that it can undergo the second HIP process and fuse any micro-cracks that are present. - The use of LBW combined with precipitation-strengthened filler superalloys and hot isostatic processing provides the ability to perform welds that have higher strength. The present invention therefore allows repairs to be made in the higher stressed regions of the blade. These repairs, in many cases, will permit repair of blades that would have previously been scrapped.
- An EBW apparatus could also be used in
weld step 26 instead of an LBW apparatus in many instances. As discussed earlier, LBW and EBW are both low heat-high energy processes capable of providing small volume welds with narrow heat affected zones. EBW must be performed in a vacuum chamber and has inherent limitations in weld path flexibility. These limit its use to certain applications. But since EBW is currently being used for the repair of gas turbine stationary nozzles, combustion components and shaft seals where the joint geometry is relatively straight or in one plane, EBW can be used inweld step 26 when those or similar components are repaired according to the method of the invention. -
FIG. 5 is a perspective view of a turbine nozzle processed in accordance with an embodiment of the invention. This figure illustrates the geometry of aturbine nozzle 62 that allows using a GTAW to repair it. -
FIG. 6 is a perspective view of a GTAW apparatus utilized in accordance with an embodiment of the invention. This is also sometimes known as tungsten inert gas welding (TIG). GTAW is currently used to weld turbine blades and nozzles. GTAW is often a manual operation and, therefore, is also useful where the workpiece has unusual geometry, or is repaired so rarely that developing a computer controlled process is inefficient, although GTAW is often computer controlled. - GTAW typically requires a solid welding rod to supply a weld filler, which, when they are solid weld filler rods of the superalloy type, are difficult to fabricate in wire or spool form due in part to their high strength. When a GTAW process is controlled by computer it employs a wire or spool feed system (not shown) that is similar to
powder feed system 48 in that it can also be controlled by a computer (not shown) to supply weld filler. One of ordinary skill in the art is aware that wire or spool feed systems are common, and superalloy wires or spools themselves, though expensive and difficult to manufacture, are known as well. - In the representative GTAW apparatus depicted in
FIG. 6 , anelectrode 66 projects from atorch body 64 toward aworkpiece 20. Anarc 70 is created between theelectrode 66 and theworkpiece 20 by causing a potential difference between them. A shieldinggas 68 passes through thetorch body 64 and surrounds theelectrode 66,arc 70, and theweld application area 60. Thus, thearc 70 is shielded from the atmosphere by the shieldinggas 68, which is an inert gas and usually argon gas.Weld filler 44, typically a solid rod in the case of GTAW, is supplied to thearc 70. - In an embodiment of the invention GTAW is used in
weld step 26 ofFIG. 1 . GTAW is an appropriate welding method inweld step 26 where the workpiece has a complex geometry that does not lend itself to computer-controlled welding. For example, turbine nozzles that are made of high temperature superalloys could be repaired using GTAW inweld step 26 of the present invention with weld filler supplied in the form of a rod and manually guided to the appropriate area of the arc. -
FIG. 7 is perspective view of a PTAW apparatus utilized in accordance with an embodiment of the invention. PTAW, like GTAW, is currently used to repair turbine blades and nozzles. Unlike GTAW, however, PTAW typically usesweld filler 44 supplied in the form of a powder. Thus PTAW may usepowder feed system 48 ofFIG. 3 . If the welded component requires a superalloy weld filler, then PTAW may lend itself more readily to computer control than GTAW, since superalloyweld fillers 44 are found more easily in powder form. - In the representative PTAW apparatus depicted in
FIG. 7 , anelectrode 66 projects toward anorifice 73 within anorifice body 74. Orifice gas 72 flows aroundelectrode 66 and throughorifice 73 towardsworkpiece 20. Aplasma arc 75 is created between theelectrode 66 and theworkpiece 20 by causing a potential difference between them through orifice gas 72 (in a non-transferred plasma arc welding apparatus the potential is created between theelectrode 66 and the orifice body 74). Anouter shield cup 76 surrounds theorifice body 74. A shieldinggas 68 passes between theouter shield cup 76 andorifice body 74 and surrounds theplasma arc 75 andweld application area 60. Thus, theplasma arc 75 andweld application area 60 are shielded from the atmosphere by the shieldinggas 68, which is an inert gas and usually argon gas.Weld filler 44, which is typically powder, is supplied to theplasma arc 75 using apowder feed system 48 ofFIG. 3 . - PTAW systems have the advantages of laser welding systems that they can be automated and thus used where fine control of the process is necessary, although PTAW, like GTAW, is a higher energy process than laser welding and may cause more strain age cracking or hot cracking before the second HIP. Where that does not significantly concern the user, however, PTAW may be desired over laser welding systems because PTAW is a manual process and has relatively lower costs associated with the equipment.
- Those skilled in the art will appreciate that the techniques of the invention can be used to effectuate a variety of repairs. For example, another form of repair is that type performed following damage to the blade by excessive erosion, hot-corrosion, or over-stripping. With this form of damage, turbine blades can become too thin to be repaired by conventional welding methodologies. With LBW, in particular, repairs can be performed on much thinner members; thus, the surface of the blade that has suffered from one of these forms of damage can be restored using a weld overlay technique.
- While the foregoing description and drawings represent the preferred embodiments of the present invention, it will be understood that various additions, modifications and substitutions may be made therein without departing from the spirit and scope of the present invention as defined in the accompanying claims. In particular, it will be clear to those skilled in the art that the present invention may be embodied in other specific forms, structures, arrangements, proportions, and with other elements, materials, and components, without departing from the spirit or essential characteristics thereof. The presently disclosed embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims, and not limited to the foregoing description.
Claims (19)
1-21. (canceled)
22. A method of repairing a metallic component, comprising:
subjecting a metallic component to a first hot isostatic processing operation;
welding the metallic component with a first weld filler using gas tungsten arc welding;
sealing a micro-crack on the surface of the metallic component with a second weld filler; and
exposing the metallic component to a second hot isostatic processing operation.
23. The method of claim 22 , wherein the metallic component comprises a super-alloy metallic component.
24. The method of claim 22 , wherein the metallic component comprises a turbine blade.
25. The method of claim 22 , wherein the metallic component comprises a turbine-nozzle.
26. The method of claim 22 , wherein said subjecting and said exposing are performed at temperatures required for solution annealing.
27. The method of claim 22 , wherein said welding comprises traversing the metallic component at least once.
28. The method of claim 27 , further comprising repeating said traversing.
29. The method of claim 22 , wherein said first weld filler comprises a precipitation strengthened super-alloy.
30. The method of claim 29 , wherein said precipitation strengthened super-alloy comprises IN-939 or a derivative thereof.
31. The method of claim 29 , wherein said precipitation strengthened super-alloy comprises IN-738 or a derivative thereof.
32. The method of claim 29 , wherein said precipitation strengthened super-alloy comprises Rene 80 or a derivative thereof.
33. The method of claim 22 , wherein said sealing comprises welding with said second weld filler that comprises a solid-solution strengthened alloy filler.
34. The method of claim 33 , wherein said solid-solution strengthened alloy filler comprises a lower strength than said first weld filler.
35. The method of claim 33 , wherein said solid-solution strengthened alloy filler comprises IN-625.
36. The method of claim 22 , further comprising preparing the metallic component for repair prior to said subjecting.
37. The method of claim 36 , wherein said preparing comprises:
chemically stripping the metallic component;
machining the metallic component; and
grinding the metallic component.
38. The method of claim 22 , further comprising finishing the metallic component after said exposing.
39. The method of claim 38 , wherein said finishing comprises a process selected from the group consisting of grinding the metallic component, machining the metallic component, re-coating the metallic component, age heat treating the metallic component and combinations thereof.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/060,937 US20060138093A1 (en) | 2000-01-20 | 2005-02-18 | Method and apparatus for repairing superalloy components |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US09/487,931 US6364971B1 (en) | 2000-01-20 | 2000-01-20 | Apparatus and method of repairing turbine blades |
US10/115,204 US6673169B1 (en) | 2000-01-20 | 2002-04-01 | Method and apparatus for repairing superalloy components |
US10/704,240 US20050126664A1 (en) | 2000-01-20 | 2003-11-07 | Method and apparatus for repairing superalloy components |
US11/060,937 US20060138093A1 (en) | 2000-01-20 | 2005-02-18 | Method and apparatus for repairing superalloy components |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/704,240 Continuation US20050126664A1 (en) | 2000-01-20 | 2003-11-07 | Method and apparatus for repairing superalloy components |
Publications (1)
Publication Number | Publication Date |
---|---|
US20060138093A1 true US20060138093A1 (en) | 2006-06-29 |
Family
ID=23937701
Family Applications (4)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US09/487,931 Expired - Fee Related US6364971B1 (en) | 2000-01-20 | 2000-01-20 | Apparatus and method of repairing turbine blades |
US10/115,204 Expired - Fee Related US6673169B1 (en) | 2000-01-20 | 2002-04-01 | Method and apparatus for repairing superalloy components |
US10/704,240 Abandoned US20050126664A1 (en) | 2000-01-20 | 2003-11-07 | Method and apparatus for repairing superalloy components |
US11/060,937 Abandoned US20060138093A1 (en) | 2000-01-20 | 2005-02-18 | Method and apparatus for repairing superalloy components |
Family Applications Before (3)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US09/487,931 Expired - Fee Related US6364971B1 (en) | 2000-01-20 | 2000-01-20 | Apparatus and method of repairing turbine blades |
US10/115,204 Expired - Fee Related US6673169B1 (en) | 2000-01-20 | 2002-04-01 | Method and apparatus for repairing superalloy components |
US10/704,240 Abandoned US20050126664A1 (en) | 2000-01-20 | 2003-11-07 | Method and apparatus for repairing superalloy components |
Country Status (1)
Country | Link |
---|---|
US (4) | US6364971B1 (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2011042007A1 (en) * | 2009-10-08 | 2011-04-14 | Mtu Aero Engines Gmbh | Joining method |
US20120181255A1 (en) * | 2011-01-13 | 2012-07-19 | Bruck Gerald J | Flux enhanced high energy density welding |
US20130326876A1 (en) * | 2011-01-11 | 2013-12-12 | Rolls-Royce Deutschland Ltd & Co Kg | Method for repairing compressor or turbine drums |
US20150306713A1 (en) * | 2012-12-03 | 2015-10-29 | United Technologies Corporation | A method of fabricating a rotor of a turbofan engine |
CN110328448A (en) * | 2019-07-12 | 2019-10-15 | 武汉钢铁有限公司 | A kind of method for laser welding that can eliminate hot rolling δ-TRIP steel bead crack |
EP3932603A4 (en) * | 2019-02-25 | 2022-05-04 | The Chugoku Electric Power Co., Inc. | Welding repair method for precipitation-strengthened cast product |
EP3932602A4 (en) * | 2019-02-25 | 2022-05-11 | The Chugoku Electric Power Co., Inc. | Welding repair method for precipitation-strengthened cast product |
Families Citing this family (60)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6364971B1 (en) | 2000-01-20 | 2002-04-02 | Electric Power Research Institute | Apparatus and method of repairing turbine blades |
US6495793B2 (en) * | 2001-04-12 | 2002-12-17 | General Electric Company | Laser repair method for nickel base superalloys with high gamma prime content |
US6605794B1 (en) * | 2002-09-03 | 2003-08-12 | General Electric Company | Methods for resistance cladding and welding on hot crack susceptible materials |
US20040086635A1 (en) * | 2002-10-30 | 2004-05-06 | Grossklaus Warren Davis | Method of repairing a stationary shroud of a gas turbine engine using laser cladding |
US7137544B2 (en) * | 2002-12-13 | 2006-11-21 | General Electric Company | Apparatus and method for performing welding at elevated temperature |
US7009137B2 (en) * | 2003-03-27 | 2006-03-07 | Honeywell International, Inc. | Laser powder fusion repair of Z-notches with nickel based superalloy powder |
US6639173B1 (en) * | 2003-04-30 | 2003-10-28 | General Electric Company | Electron beam welding method providing post-weld heat treatment |
US20050023256A1 (en) * | 2003-07-31 | 2005-02-03 | Srikanth Sankaranarayanan | 3-D adaptive laser powder fusion welding |
DE10337866B4 (en) * | 2003-08-18 | 2014-07-24 | MTU Aero Engines AG | Process for the production of components for gas turbines |
CN1883151B (en) * | 2003-09-15 | 2010-06-16 | 英特尔公司 | Multicarrier transmitter, multicarrier receiver, and methods for communicating multiple spatial signal streams |
US20050139581A1 (en) * | 2003-12-24 | 2005-06-30 | Yiping Hu | High-strength superalloy joining method for repairing turbine blades |
US20050178750A1 (en) * | 2004-02-13 | 2005-08-18 | Kenny Cheng | Repair of article by laser cladding |
US6972390B2 (en) * | 2004-03-04 | 2005-12-06 | Honeywell International, Inc. | Multi-laser beam welding high strength superalloys |
US7562807B2 (en) * | 2004-05-05 | 2009-07-21 | Electric Power Research Institute | Weld filler for welding dissimilar alloy steels and method of using same |
US6872912B1 (en) | 2004-07-12 | 2005-03-29 | Chromalloy Gas Turbine Corporation | Welding single crystal articles |
DE102004036066A1 (en) * | 2004-07-24 | 2006-02-16 | Mtu Aero Engines Gmbh | Method for repairing or manufacturing a component |
US20060045785A1 (en) * | 2004-08-30 | 2006-03-02 | Yiping Hu | Method for repairing titanium alloy components |
US7371988B2 (en) | 2004-10-22 | 2008-05-13 | Electric Power Research Institute, Inc. | Methods for extending the life of alloy steel welded joints by elimination and reduction of the HAZ |
US7484651B2 (en) | 2004-10-22 | 2009-02-03 | Electric Power Research Institute, Inc. | Method to join or repair superalloy hot section turbine components using hot isostatic processing |
EP1893383A2 (en) * | 2005-02-28 | 2008-03-05 | Electric Power Research Institute, Inc | Method for repairing heat recovery stream generator tube-to-header damage |
US7617603B2 (en) * | 2005-02-28 | 2009-11-17 | Electric Power Research Institute, Inc. | Method for inspection and repair |
US7687151B2 (en) * | 2005-04-12 | 2010-03-30 | General Electric Company | Overlay for repairing spline and seal teeth of a mated component |
US7591057B2 (en) * | 2005-04-12 | 2009-09-22 | General Electric Company | Method of repairing spline and seal teeth of a mated component |
US20060231535A1 (en) * | 2005-04-19 | 2006-10-19 | Fuesting Timothy P | Method of welding a gamma-prime precipitate strengthened material |
CN100402223C (en) * | 2005-06-22 | 2008-07-16 | 中国科学院金属研究所 | Crack repair process for high-pressure turbine blade tip in gas turbine |
US20070068648A1 (en) * | 2005-09-28 | 2007-03-29 | Honeywell International, Inc. | Method for repairing die cast dies |
US7536783B2 (en) * | 2005-10-13 | 2009-05-26 | Siemens Energy, Inc. | Turbine vane airfoil reconfiguration method |
US7322396B2 (en) * | 2005-10-14 | 2008-01-29 | General Electric Company | Weld closure of through-holes in a nickel-base superalloy hollow airfoil |
US20070111119A1 (en) * | 2005-11-15 | 2007-05-17 | Honeywell International, Inc. | Method for repairing gas turbine engine compressor components |
SG134183A1 (en) * | 2006-01-16 | 2007-08-29 | United Technologies Corp | Turbine component trailing edge and platform restoration by laser cladding |
US20080023531A1 (en) * | 2006-07-26 | 2008-01-31 | Schaeffer Jon C | Weldment and a process using dual weld wires for welding nickel -based superalloys |
US8618440B2 (en) | 2007-01-04 | 2013-12-31 | Siemens Energy, Inc. | Sprayed weld strip for improved weldability |
US8561298B2 (en) | 2007-03-01 | 2013-10-22 | Siemens Energy, Inc. | Superalloy component welding at ambient temperature |
US20080267775A1 (en) * | 2007-04-30 | 2008-10-30 | General Electric Company | Nozzle segments and method of repairing the same |
US8186056B2 (en) * | 2007-06-28 | 2012-05-29 | Siemens Energy, Inc. | Turbine vane restoration system |
US7977611B2 (en) * | 2007-07-19 | 2011-07-12 | United Technologies Corporation | Systems and methods for providing localized heat treatment of metal components |
US20090026182A1 (en) * | 2007-07-27 | 2009-01-29 | Honeywell International, Inc. | In-situ brazing methods for repairing gas turbine engine components |
US20090039062A1 (en) * | 2007-08-06 | 2009-02-12 | General Electric Company | Torch brazing process and apparatus therefor |
GB0719873D0 (en) * | 2007-10-12 | 2007-11-21 | Rolls Royce Plc | Shape correcting components |
US8206121B2 (en) * | 2008-03-26 | 2012-06-26 | United Technologies Corporation | Method of restoring an airfoil blade |
KR101035154B1 (en) | 2008-08-08 | 2011-05-17 | 한전케이피에스 주식회사 | The welding method of blade for gas turbine |
DE102008052030B4 (en) * | 2008-10-16 | 2011-06-16 | Mtu Aero Engines Gmbh | Method for connecting at least one turbine blade with a turbine disk or a turbine ring |
SG165202A1 (en) * | 2009-03-25 | 2010-10-28 | United Technologies Corp | Method and apparatus for cleaning a component using microwave radiation |
US9061375B2 (en) * | 2009-12-23 | 2015-06-23 | General Electric Company | Methods for treating superalloy articles, and related repair processes |
US8618434B2 (en) * | 2010-03-22 | 2013-12-31 | Siemens Energy, Inc. | Superalloy repair welding using multiple alloy powders |
US8727203B2 (en) | 2010-09-16 | 2014-05-20 | Howmedica Osteonics Corp. | Methods for manufacturing porous orthopaedic implants |
US9205509B2 (en) * | 2011-08-31 | 2015-12-08 | General Electric Company | Localized cleaning process and apparatus therefor |
US8816259B2 (en) * | 2012-04-06 | 2014-08-26 | Siemens Aktiengesellschaft | Pack heat treatment for material enhancement |
DE102012206125A1 (en) * | 2012-04-13 | 2013-10-17 | MTU Aero Engines AG | Process for the production of low-pressure turbine blades made of TiAl |
US20150190891A1 (en) * | 2012-09-28 | 2015-07-09 | United Technologies Corporation | Repair of Casting Defects |
GB2510562B (en) * | 2013-02-06 | 2015-02-25 | Rolls Royce Plc | Method of forming a bonded assembly |
US9587740B2 (en) * | 2013-04-08 | 2017-03-07 | Caterpillar Inc. | Repaired pistons and collection thereof |
DE102013214781B3 (en) * | 2013-07-29 | 2015-02-26 | MTU Aero Engines AG | Method for repairing a pick-up hook for guide vanes |
US11072044B2 (en) | 2014-04-14 | 2021-07-27 | Siemens Energy, Inc. | Superalloy component braze repair with isostatic solution treatment |
CN106563929B (en) * | 2015-10-08 | 2019-09-17 | 利宝地工程有限公司 | Repair and manufacture the method and turbine engine components of turbine engine components |
JP6445960B2 (en) * | 2015-12-22 | 2018-12-26 | 長野計器株式会社 | Manufacturing method of pressure sensor |
US10556294B2 (en) | 2017-06-06 | 2020-02-11 | General Electric Company | Method of treating superalloy articles |
US10625361B2 (en) * | 2017-06-14 | 2020-04-21 | General Electric Company | Method of welding superalloys |
US11346371B2 (en) | 2018-05-04 | 2022-05-31 | Raytheon Technologies Corporation | Method to strip coatings off of an aluminum alloy fan blade |
CN113828924A (en) * | 2021-11-09 | 2021-12-24 | 湖北三江航天红阳机电有限公司 | K438 high-temperature alloy welding method |
Citations (93)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1554546A (en) * | 1925-04-04 | 1925-09-22 | Rail Welding & Bonding Company | Seam-welding process |
US2681970A (en) * | 1951-02-19 | 1954-06-22 | Union Carbide & Carbon Corp | Gas shielded metal arc welding method |
US2870323A (en) * | 1954-06-15 | 1959-01-20 | Air Reduction | Arc welding |
US2932723A (en) * | 1958-12-24 | 1960-04-12 | Air Reduction | Electric arc welding |
US2938107A (en) * | 1958-01-13 | 1960-05-24 | Smith Corp A O | Series arc welding circuit |
US3185814A (en) * | 1961-12-30 | 1965-05-25 | Siemens Ag | Method and apparatus for overlay welding |
US3215809A (en) * | 1963-06-25 | 1965-11-02 | Morimoto Izumi | Metal-arc welding |
US3223818A (en) * | 1961-04-27 | 1965-12-14 | Smith Corp A O | Method of welding |
US3274371A (en) * | 1965-06-01 | 1966-09-20 | Union Carbide Corp | Method of depositing metal |
US3293400A (en) * | 1966-07-06 | 1966-12-20 | Newport News S & D Co | Submerged arc welding process |
US3420979A (en) * | 1965-06-07 | 1969-01-07 | St Louis Shipbuilding Federal | Submerged arc welding apparatus |
US3546415A (en) * | 1968-11-07 | 1970-12-08 | Flame Spray Ind Inc | Electric arc metallizing device |
US3549856A (en) * | 1967-08-24 | 1970-12-22 | Union Carbide Corp | Gas metal arc welding from one side |
US3624345A (en) * | 1968-10-31 | 1971-11-30 | Babcock & Wilcox Co | Arc welding electrode arrangements |
US3745322A (en) * | 1969-12-24 | 1973-07-10 | Sumitomo Metal Ind | Welding process preventing the bond brittleness of low-alloy steels |
US3746833A (en) * | 1972-02-14 | 1973-07-17 | Mitsubishi Heavy Ind Ltd | Process and apparatus for triple-electrode mig welding using short-circuit and spray-arc deposition |
US3936655A (en) * | 1974-09-26 | 1976-02-03 | Arnoldy Roman F | Magnetic feeding of powder in submerged arc welding |
US3936654A (en) * | 1974-02-21 | 1976-02-03 | La Soudure Electrique Autogene, Procedes Arcos | Process and apparatus for the performance of arc welding and overlaying, preferably submerged arc |
US3957194A (en) * | 1973-08-16 | 1976-05-18 | Rohr Industries, Inc. | Liquid interface diffusion method of bonding titanium and/or titanium alloy structure |
US3978907A (en) * | 1975-03-24 | 1976-09-07 | Volf Iudovich Rabinovich | Method of electroslag remelting by melting main and additional electrodes and machine for effecting said method |
US3984652A (en) * | 1974-10-30 | 1976-10-05 | Dominion Bridge Company, Limited | Method of butt welding |
US4008844A (en) * | 1975-01-06 | 1977-02-22 | United Technologies Corporation | Method of repairing surface defects using metallic filler material |
US4020314A (en) * | 1975-07-17 | 1977-04-26 | Combustion Engineering, Inc. | Delivery of welding flux in a method of submerged arc strip cladding of metallic work pieces |
US4027135A (en) * | 1975-07-17 | 1977-05-31 | Combustion Engineering, Inc. | Apparatus and method for submerged arc strip cladding of metallic work pieces |
US4091253A (en) * | 1973-09-17 | 1978-05-23 | British Steel Corporation | Applying a hard facing to an iron or steel former |
US4143257A (en) * | 1976-04-02 | 1979-03-06 | Nova-Tech Engineering, Inc. | Welding wire feed mechanism |
US4149060A (en) * | 1977-07-25 | 1979-04-10 | Combustion Engineering, Inc. | Angled strip cladding system |
US4214141A (en) * | 1977-12-29 | 1980-07-22 | Kobe Steel, Ltd. | Multiple electrode submerged arc welding method |
US4224360A (en) * | 1978-02-09 | 1980-09-23 | The Japan Steel Works, Inc. | Method of welding for exfoliation prevention of stainless steel weld-overlay |
US4266110A (en) * | 1978-12-13 | 1981-05-05 | Combustion Engineering, Inc. | Clad welding on an inclined surface |
US4307281A (en) * | 1979-09-07 | 1981-12-22 | Ivannikov Alfred V | Method of arc welding |
US4400608A (en) * | 1979-04-27 | 1983-08-23 | Tokyo Shibaura Denki Kabushiki Kaisha | Welding electrode pair and method of welding |
US4442340A (en) * | 1981-10-20 | 1984-04-10 | Kawasaki Steel Corporation | Four-electrode submerged arc welding process |
US4484959A (en) * | 1981-07-17 | 1984-11-27 | Creusot-Loire | Process for the production of a composite metal part and products thus obtained |
US4518625A (en) * | 1983-12-09 | 1985-05-21 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Arc spray fabrication of metal matrix composite monotape |
US4521664A (en) * | 1982-10-26 | 1985-06-04 | Teledyne, Inc. | Process and apparatus for surfacing with high deposition and low dilution |
US4572936A (en) * | 1983-02-19 | 1986-02-25 | Schweissindustrie Oerlikon Buhrle Ag | Submerged arc welding process |
US4584457A (en) * | 1983-06-21 | 1986-04-22 | Thyssen Ag, Vorm August Thyssen-Hutte | Device for arc welding, in particular submerged-arc welding, with one or several fusible electrodes |
US4611744A (en) * | 1982-06-23 | 1986-09-16 | Refurbished Turbine Components Ltd. | Turbine blade repair |
US4702406A (en) * | 1986-10-16 | 1987-10-27 | Carolina Power & Light Company | Forming stable welded joints between dissimilar metals |
US4703885A (en) * | 1985-11-15 | 1987-11-03 | Ga Technologies Inc. | Method of welding austenitic steel to ferritic steel with filler alloys |
US4750944A (en) * | 1985-12-30 | 1988-06-14 | United Technologies Corporation | Laves free cast+hip nickel base superalloy |
US4780594A (en) * | 1987-10-08 | 1988-10-25 | Dimetrics Inc. | Method and apparatus for improved control of supply of filler material to a welding location |
US4782206A (en) * | 1987-01-27 | 1988-11-01 | The Babcock & Wilcox Company | Method and apparatus for controlling weld bead shape to eliminate microfissure defects when shape melting austenitic materials |
US4788412A (en) * | 1986-05-30 | 1988-11-29 | Babcock-Hitachi Kabushiki Kaisha | Method of control and apparatus for hot-wire welding |
US4804815A (en) * | 1987-06-01 | 1989-02-14 | Quantum Laser Corporation | Process for welding nickel-based superalloys |
US4811892A (en) * | 1986-03-08 | 1989-03-14 | Messerschmitt-Boelkow-Blohm Gmbh | Method for diffusion welding under isostatic pressure |
US4817858A (en) * | 1987-05-13 | 1989-04-04 | Bbc Brown Boveri Ag | Method of manufacturing a workpiece of any given cross-sectional dimensions from an oxide-dispersion-hardened nickel-based superalloy with directional coarse columnar crystals |
US4835357A (en) * | 1988-06-20 | 1989-05-30 | Williams International Corporation | Sheet metal laser welding |
US4878953A (en) * | 1988-01-13 | 1989-11-07 | Metallurgical Industries, Inc. | Method of refurbishing cast gas turbine engine components and refurbished component |
US4902873A (en) * | 1978-12-25 | 1990-02-20 | Ivannikov Alfred V | Method of electric arc welding |
US5067649A (en) * | 1987-09-18 | 1991-11-26 | Imperial Chemical Industries Plc | Bonding metal components |
US5071054A (en) * | 1990-12-18 | 1991-12-10 | General Electric Company | Fabrication of cast articles from high melting temperature superalloy compositions |
US5106010A (en) * | 1990-09-28 | 1992-04-21 | Chromalloy Gas Turbine Corporation | Welding high-strength nickel base superalloys |
US5124527A (en) * | 1990-02-21 | 1992-06-23 | Kyodo Oxygen Co., Ltd. | Arc welding method and apparatus |
US5140140A (en) * | 1990-11-15 | 1992-08-18 | Pollack Alex J | Method and apparatus of submerged arc welding with electrodes in tandem |
US5146064A (en) * | 1989-12-29 | 1992-09-08 | Serimer, Societe A Responsabilite Limitee | Mechanical system for automatically guiding one or more electrodes in an arc-welding unit |
US5149939A (en) * | 1991-07-03 | 1992-09-22 | Aichi Sangyo, Co., Ltd. | Automatic welding apparatus |
US5156321A (en) * | 1990-08-28 | 1992-10-20 | Liburdi Engineering Limited | Powder metallurgy repair technique |
US5214265A (en) * | 1990-11-15 | 1993-05-25 | Pollack Alex J | High speed low deposition submerged arc welding apparatus and method |
US5217158A (en) * | 1992-07-14 | 1993-06-08 | Brush Wellman, Inc. | Process for thermodynamically treating a region joining two members |
US5233149A (en) * | 1991-08-02 | 1993-08-03 | Eaton Corporation | Reprocessing weld and method |
US5280849A (en) * | 1992-10-06 | 1994-01-25 | Commonwealth Edison | Welding method for rotating shafts |
US5348212A (en) * | 1992-10-06 | 1994-09-20 | Commonwelth Edison | Welding method for rotatable shafts |
US5383985A (en) * | 1992-06-05 | 1995-01-24 | Gec Alsthom Electromecanique Sa | Method of installing an insert serving as a protective cladding on a part made of martensitic steel or of titanium-based alloy |
US5470524A (en) * | 1993-06-15 | 1995-11-28 | Mtu Motoren- Und Turbinen-Union Muenchen Gmbh | Method for manufacturing a blade ring for drum-shaped rotors of turbomachinery |
US5479704A (en) * | 1993-08-13 | 1996-01-02 | Mtu Motoren-Und Turbinen Union Munchen Gmbh | Process for repairing damaged blades of turboengines |
US5556561A (en) * | 1994-02-17 | 1996-09-17 | Mitsubishi Jukogyo Kabushiki Kaisha | Method of forming a weld joint of austenitic stainless steel/ferritic steel |
US5714735A (en) * | 1996-06-20 | 1998-02-03 | General Electric Company | Method and apparatus for joining components with multiple filler materials |
US5723078A (en) * | 1996-05-24 | 1998-03-03 | General Electric Company | Method for repairing a thermal barrier coating |
US5732467A (en) * | 1996-11-14 | 1998-03-31 | General Electric Company | Method of repairing directionally solidified and single crystal alloy parts |
US5735044A (en) * | 1995-12-12 | 1998-04-07 | General Electric Company | Laser shock peening for gas turbine engine weld repair |
US5755374A (en) * | 1993-06-15 | 1998-05-26 | Lexor Technologies Limited | Method of brazing |
US5762727A (en) * | 1997-04-14 | 1998-06-09 | General Electric Company | Weld repair process and article repaired thereby |
US5783318A (en) * | 1994-06-22 | 1998-07-21 | United Technologies Corporation | Repaired nickel based superalloy |
US5806751A (en) * | 1996-10-17 | 1998-09-15 | United Technologies Corporation | Method of repairing metallic alloy articles, such as gas turbine engine components |
US5822852A (en) * | 1997-07-14 | 1998-10-20 | General Electric Company | Method for replacing blade tips of directionally solidified and single crystal turbine blades |
US5873703A (en) * | 1997-01-22 | 1999-02-23 | General Electric Company | Repair of gamma titanium aluminide articles |
US5897801A (en) * | 1997-01-22 | 1999-04-27 | General Electric Company | Welding of nickel-base superalloys having a nil-ductility range |
US5951792A (en) * | 1997-09-22 | 1999-09-14 | Asea Brown Boveri Ag | Method for welding age-hardenable nickel-base alloys |
US5956845A (en) * | 1996-12-23 | 1999-09-28 | Recast Airfoil Group | Method of repairing a turbine engine airfoil part |
US6023043A (en) * | 1996-05-10 | 2000-02-08 | Mitsubishi Heavy Industries, Ltd. | Method of welding in the horizontal position and welding apparatus therefor |
US6040545A (en) * | 1997-06-10 | 2000-03-21 | Kabushiki Kaisha Toshiba | TIG welding method and welding apparatus |
US6049978A (en) * | 1996-12-23 | 2000-04-18 | Recast Airfoil Group | Methods for repairing and reclassifying gas turbine engine airfoil parts |
US6069334A (en) * | 1998-07-06 | 2000-05-30 | Capitanescu; Dan | Electroslag strip overlay method |
US6109505A (en) * | 1998-06-23 | 2000-08-29 | Snecma Services | Method of diffusion brazing superalloy parts |
US6153854A (en) * | 1996-12-20 | 2000-11-28 | Corus Aluminium Walzprodukte Gmbh | Aluminum sheet product and method of welding structural components |
US6193145B1 (en) * | 1995-12-18 | 2001-02-27 | Framatome | Method for joining two parts of different kinds by heterogeneous butt welding, and uses thereof |
US6247638B1 (en) * | 1999-04-28 | 2001-06-19 | Allison Advanced Development Company | Selectively reinforced member and method of manufacture |
US6284392B1 (en) * | 1999-08-11 | 2001-09-04 | Siemens Westinghouse Power Corporation | Superalloys with improved weldability for high temperature applications |
US6364971B1 (en) * | 2000-01-20 | 2002-04-02 | Electric Power Research Institute | Apparatus and method of repairing turbine blades |
US6428633B1 (en) * | 1997-10-20 | 2002-08-06 | Nippin Steel Corporation | Steel for welded structures and welding wire |
US6884959B2 (en) * | 2001-09-07 | 2005-04-26 | Electric Power Research Institute, Inc. | Controlled composition welding method |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US516010A (en) * | 1894-03-06 | graves | ||
US397194A (en) * | 1889-02-05 | Multiple-signal transmitter | ||
US3546856A (en) * | 1968-03-08 | 1970-12-15 | Kazuo Hiyama | Method of harvesting vine borne crops |
-
2000
- 2000-01-20 US US09/487,931 patent/US6364971B1/en not_active Expired - Fee Related
-
2002
- 2002-04-01 US US10/115,204 patent/US6673169B1/en not_active Expired - Fee Related
-
2003
- 2003-11-07 US US10/704,240 patent/US20050126664A1/en not_active Abandoned
-
2005
- 2005-02-18 US US11/060,937 patent/US20060138093A1/en not_active Abandoned
Patent Citations (99)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1554546A (en) * | 1925-04-04 | 1925-09-22 | Rail Welding & Bonding Company | Seam-welding process |
US2681970A (en) * | 1951-02-19 | 1954-06-22 | Union Carbide & Carbon Corp | Gas shielded metal arc welding method |
US2870323A (en) * | 1954-06-15 | 1959-01-20 | Air Reduction | Arc welding |
US2938107A (en) * | 1958-01-13 | 1960-05-24 | Smith Corp A O | Series arc welding circuit |
US2932723A (en) * | 1958-12-24 | 1960-04-12 | Air Reduction | Electric arc welding |
US3223818A (en) * | 1961-04-27 | 1965-12-14 | Smith Corp A O | Method of welding |
US3185814A (en) * | 1961-12-30 | 1965-05-25 | Siemens Ag | Method and apparatus for overlay welding |
US3215809A (en) * | 1963-06-25 | 1965-11-02 | Morimoto Izumi | Metal-arc welding |
US3274371A (en) * | 1965-06-01 | 1966-09-20 | Union Carbide Corp | Method of depositing metal |
US3420979A (en) * | 1965-06-07 | 1969-01-07 | St Louis Shipbuilding Federal | Submerged arc welding apparatus |
US3293400A (en) * | 1966-07-06 | 1966-12-20 | Newport News S & D Co | Submerged arc welding process |
US3549856A (en) * | 1967-08-24 | 1970-12-22 | Union Carbide Corp | Gas metal arc welding from one side |
US3624345A (en) * | 1968-10-31 | 1971-11-30 | Babcock & Wilcox Co | Arc welding electrode arrangements |
US3546415A (en) * | 1968-11-07 | 1970-12-08 | Flame Spray Ind Inc | Electric arc metallizing device |
US3745322A (en) * | 1969-12-24 | 1973-07-10 | Sumitomo Metal Ind | Welding process preventing the bond brittleness of low-alloy steels |
US3746833A (en) * | 1972-02-14 | 1973-07-17 | Mitsubishi Heavy Ind Ltd | Process and apparatus for triple-electrode mig welding using short-circuit and spray-arc deposition |
US3957194A (en) * | 1973-08-16 | 1976-05-18 | Rohr Industries, Inc. | Liquid interface diffusion method of bonding titanium and/or titanium alloy structure |
US4091253A (en) * | 1973-09-17 | 1978-05-23 | British Steel Corporation | Applying a hard facing to an iron or steel former |
US3936654A (en) * | 1974-02-21 | 1976-02-03 | La Soudure Electrique Autogene, Procedes Arcos | Process and apparatus for the performance of arc welding and overlaying, preferably submerged arc |
US3936655A (en) * | 1974-09-26 | 1976-02-03 | Arnoldy Roman F | Magnetic feeding of powder in submerged arc welding |
US3984652A (en) * | 1974-10-30 | 1976-10-05 | Dominion Bridge Company, Limited | Method of butt welding |
US4008844A (en) * | 1975-01-06 | 1977-02-22 | United Technologies Corporation | Method of repairing surface defects using metallic filler material |
US3978907A (en) * | 1975-03-24 | 1976-09-07 | Volf Iudovich Rabinovich | Method of electroslag remelting by melting main and additional electrodes and machine for effecting said method |
US4027135A (en) * | 1975-07-17 | 1977-05-31 | Combustion Engineering, Inc. | Apparatus and method for submerged arc strip cladding of metallic work pieces |
US4020314A (en) * | 1975-07-17 | 1977-04-26 | Combustion Engineering, Inc. | Delivery of welding flux in a method of submerged arc strip cladding of metallic work pieces |
US4143257A (en) * | 1976-04-02 | 1979-03-06 | Nova-Tech Engineering, Inc. | Welding wire feed mechanism |
US4149060A (en) * | 1977-07-25 | 1979-04-10 | Combustion Engineering, Inc. | Angled strip cladding system |
US4214141A (en) * | 1977-12-29 | 1980-07-22 | Kobe Steel, Ltd. | Multiple electrode submerged arc welding method |
US4224360A (en) * | 1978-02-09 | 1980-09-23 | The Japan Steel Works, Inc. | Method of welding for exfoliation prevention of stainless steel weld-overlay |
US4266110A (en) * | 1978-12-13 | 1981-05-05 | Combustion Engineering, Inc. | Clad welding on an inclined surface |
US4902873A (en) * | 1978-12-25 | 1990-02-20 | Ivannikov Alfred V | Method of electric arc welding |
US4400608A (en) * | 1979-04-27 | 1983-08-23 | Tokyo Shibaura Denki Kabushiki Kaisha | Welding electrode pair and method of welding |
US4307281A (en) * | 1979-09-07 | 1981-12-22 | Ivannikov Alfred V | Method of arc welding |
US4484959A (en) * | 1981-07-17 | 1984-11-27 | Creusot-Loire | Process for the production of a composite metal part and products thus obtained |
US4442340A (en) * | 1981-10-20 | 1984-04-10 | Kawasaki Steel Corporation | Four-electrode submerged arc welding process |
US4611744A (en) * | 1982-06-23 | 1986-09-16 | Refurbished Turbine Components Ltd. | Turbine blade repair |
US4521664A (en) * | 1982-10-26 | 1985-06-04 | Teledyne, Inc. | Process and apparatus for surfacing with high deposition and low dilution |
US4572936A (en) * | 1983-02-19 | 1986-02-25 | Schweissindustrie Oerlikon Buhrle Ag | Submerged arc welding process |
US4584457A (en) * | 1983-06-21 | 1986-04-22 | Thyssen Ag, Vorm August Thyssen-Hutte | Device for arc welding, in particular submerged-arc welding, with one or several fusible electrodes |
US4518625A (en) * | 1983-12-09 | 1985-05-21 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Arc spray fabrication of metal matrix composite monotape |
US4703885A (en) * | 1985-11-15 | 1987-11-03 | Ga Technologies Inc. | Method of welding austenitic steel to ferritic steel with filler alloys |
US4750944A (en) * | 1985-12-30 | 1988-06-14 | United Technologies Corporation | Laves free cast+hip nickel base superalloy |
US4811892A (en) * | 1986-03-08 | 1989-03-14 | Messerschmitt-Boelkow-Blohm Gmbh | Method for diffusion welding under isostatic pressure |
US4788412A (en) * | 1986-05-30 | 1988-11-29 | Babcock-Hitachi Kabushiki Kaisha | Method of control and apparatus for hot-wire welding |
US4702406A (en) * | 1986-10-16 | 1987-10-27 | Carolina Power & Light Company | Forming stable welded joints between dissimilar metals |
US4782206A (en) * | 1987-01-27 | 1988-11-01 | The Babcock & Wilcox Company | Method and apparatus for controlling weld bead shape to eliminate microfissure defects when shape melting austenitic materials |
US4817858A (en) * | 1987-05-13 | 1989-04-04 | Bbc Brown Boveri Ag | Method of manufacturing a workpiece of any given cross-sectional dimensions from an oxide-dispersion-hardened nickel-based superalloy with directional coarse columnar crystals |
US4804815A (en) * | 1987-06-01 | 1989-02-14 | Quantum Laser Corporation | Process for welding nickel-based superalloys |
US5067649A (en) * | 1987-09-18 | 1991-11-26 | Imperial Chemical Industries Plc | Bonding metal components |
US4780594A (en) * | 1987-10-08 | 1988-10-25 | Dimetrics Inc. | Method and apparatus for improved control of supply of filler material to a welding location |
US4878953A (en) * | 1988-01-13 | 1989-11-07 | Metallurgical Industries, Inc. | Method of refurbishing cast gas turbine engine components and refurbished component |
US4835357A (en) * | 1988-06-20 | 1989-05-30 | Williams International Corporation | Sheet metal laser welding |
US5146064A (en) * | 1989-12-29 | 1992-09-08 | Serimer, Societe A Responsabilite Limitee | Mechanical system for automatically guiding one or more electrodes in an arc-welding unit |
US5124527A (en) * | 1990-02-21 | 1992-06-23 | Kyodo Oxygen Co., Ltd. | Arc welding method and apparatus |
US5156321A (en) * | 1990-08-28 | 1992-10-20 | Liburdi Engineering Limited | Powder metallurgy repair technique |
US5106010A (en) * | 1990-09-28 | 1992-04-21 | Chromalloy Gas Turbine Corporation | Welding high-strength nickel base superalloys |
US5374319A (en) * | 1990-09-28 | 1994-12-20 | Chromalloy Gas Turbine Corporation | Welding high-strength nickel base superalloys |
US5214265A (en) * | 1990-11-15 | 1993-05-25 | Pollack Alex J | High speed low deposition submerged arc welding apparatus and method |
US5140140A (en) * | 1990-11-15 | 1992-08-18 | Pollack Alex J | Method and apparatus of submerged arc welding with electrodes in tandem |
US5071054A (en) * | 1990-12-18 | 1991-12-10 | General Electric Company | Fabrication of cast articles from high melting temperature superalloy compositions |
US5149939A (en) * | 1991-07-03 | 1992-09-22 | Aichi Sangyo, Co., Ltd. | Automatic welding apparatus |
US5233149A (en) * | 1991-08-02 | 1993-08-03 | Eaton Corporation | Reprocessing weld and method |
US5383985A (en) * | 1992-06-05 | 1995-01-24 | Gec Alsthom Electromecanique Sa | Method of installing an insert serving as a protective cladding on a part made of martensitic steel or of titanium-based alloy |
US5217158A (en) * | 1992-07-14 | 1993-06-08 | Brush Wellman, Inc. | Process for thermodynamically treating a region joining two members |
US5280849A (en) * | 1992-10-06 | 1994-01-25 | Commonwealth Edison | Welding method for rotating shafts |
US5348212A (en) * | 1992-10-06 | 1994-09-20 | Commonwelth Edison | Welding method for rotatable shafts |
US5755374A (en) * | 1993-06-15 | 1998-05-26 | Lexor Technologies Limited | Method of brazing |
US5470524A (en) * | 1993-06-15 | 1995-11-28 | Mtu Motoren- Und Turbinen-Union Muenchen Gmbh | Method for manufacturing a blade ring for drum-shaped rotors of turbomachinery |
US5479704A (en) * | 1993-08-13 | 1996-01-02 | Mtu Motoren-Und Turbinen Union Munchen Gmbh | Process for repairing damaged blades of turboengines |
US5556561A (en) * | 1994-02-17 | 1996-09-17 | Mitsubishi Jukogyo Kabushiki Kaisha | Method of forming a weld joint of austenitic stainless steel/ferritic steel |
US5783318A (en) * | 1994-06-22 | 1998-07-21 | United Technologies Corporation | Repaired nickel based superalloy |
US5735044A (en) * | 1995-12-12 | 1998-04-07 | General Electric Company | Laser shock peening for gas turbine engine weld repair |
US5846057A (en) * | 1995-12-12 | 1998-12-08 | General Electric Company | Laser shock peening for gas turbine engine weld repair |
US6193145B1 (en) * | 1995-12-18 | 2001-02-27 | Framatome | Method for joining two parts of different kinds by heterogeneous butt welding, and uses thereof |
US6023043A (en) * | 1996-05-10 | 2000-02-08 | Mitsubishi Heavy Industries, Ltd. | Method of welding in the horizontal position and welding apparatus therefor |
US5723078A (en) * | 1996-05-24 | 1998-03-03 | General Electric Company | Method for repairing a thermal barrier coating |
US5994659A (en) * | 1996-06-20 | 1999-11-30 | General Electric Company | Method and apparatus for welding with preheated filler material |
US5714735A (en) * | 1996-06-20 | 1998-02-03 | General Electric Company | Method and apparatus for joining components with multiple filler materials |
US5806751A (en) * | 1996-10-17 | 1998-09-15 | United Technologies Corporation | Method of repairing metallic alloy articles, such as gas turbine engine components |
US5732467A (en) * | 1996-11-14 | 1998-03-31 | General Electric Company | Method of repairing directionally solidified and single crystal alloy parts |
US6153854A (en) * | 1996-12-20 | 2000-11-28 | Corus Aluminium Walzprodukte Gmbh | Aluminum sheet product and method of welding structural components |
US5956845A (en) * | 1996-12-23 | 1999-09-28 | Recast Airfoil Group | Method of repairing a turbine engine airfoil part |
US6049978A (en) * | 1996-12-23 | 2000-04-18 | Recast Airfoil Group | Methods for repairing and reclassifying gas turbine engine airfoil parts |
US5873703A (en) * | 1997-01-22 | 1999-02-23 | General Electric Company | Repair of gamma titanium aluminide articles |
US5897801A (en) * | 1997-01-22 | 1999-04-27 | General Electric Company | Welding of nickel-base superalloys having a nil-ductility range |
US6117564A (en) * | 1997-04-14 | 2000-09-12 | General Electric Co. | Weld repair process and article repaired thereby |
US5762727A (en) * | 1997-04-14 | 1998-06-09 | General Electric Company | Weld repair process and article repaired thereby |
US6040545A (en) * | 1997-06-10 | 2000-03-21 | Kabushiki Kaisha Toshiba | TIG welding method and welding apparatus |
US5822852A (en) * | 1997-07-14 | 1998-10-20 | General Electric Company | Method for replacing blade tips of directionally solidified and single crystal turbine blades |
US5951792A (en) * | 1997-09-22 | 1999-09-14 | Asea Brown Boveri Ag | Method for welding age-hardenable nickel-base alloys |
US6428633B1 (en) * | 1997-10-20 | 2002-08-06 | Nippin Steel Corporation | Steel for welded structures and welding wire |
US6109505A (en) * | 1998-06-23 | 2000-08-29 | Snecma Services | Method of diffusion brazing superalloy parts |
US6069334A (en) * | 1998-07-06 | 2000-05-30 | Capitanescu; Dan | Electroslag strip overlay method |
US6247638B1 (en) * | 1999-04-28 | 2001-06-19 | Allison Advanced Development Company | Selectively reinforced member and method of manufacture |
US6284392B1 (en) * | 1999-08-11 | 2001-09-04 | Siemens Westinghouse Power Corporation | Superalloys with improved weldability for high temperature applications |
US6364971B1 (en) * | 2000-01-20 | 2002-04-02 | Electric Power Research Institute | Apparatus and method of repairing turbine blades |
US6673169B1 (en) * | 2000-01-20 | 2004-01-06 | Electric Power Research Institute, Inc. | Method and apparatus for repairing superalloy components |
US20050126664A1 (en) * | 2000-01-20 | 2005-06-16 | Electric Power Research Institute, Inc. | Method and apparatus for repairing superalloy components |
US6884959B2 (en) * | 2001-09-07 | 2005-04-26 | Electric Power Research Institute, Inc. | Controlled composition welding method |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2011042007A1 (en) * | 2009-10-08 | 2011-04-14 | Mtu Aero Engines Gmbh | Joining method |
US20130326876A1 (en) * | 2011-01-11 | 2013-12-12 | Rolls-Royce Deutschland Ltd & Co Kg | Method for repairing compressor or turbine drums |
US9656354B2 (en) * | 2011-01-11 | 2017-05-23 | Rolls-Royce Deutschland Ltd & Co Kg | Method for repairing compressor or turbine drums |
US20120181255A1 (en) * | 2011-01-13 | 2012-07-19 | Bruck Gerald J | Flux enhanced high energy density welding |
US20150306713A1 (en) * | 2012-12-03 | 2015-10-29 | United Technologies Corporation | A method of fabricating a rotor of a turbofan engine |
EP3932603A4 (en) * | 2019-02-25 | 2022-05-04 | The Chugoku Electric Power Co., Inc. | Welding repair method for precipitation-strengthened cast product |
EP3932602A4 (en) * | 2019-02-25 | 2022-05-11 | The Chugoku Electric Power Co., Inc. | Welding repair method for precipitation-strengthened cast product |
CN110328448A (en) * | 2019-07-12 | 2019-10-15 | 武汉钢铁有限公司 | A kind of method for laser welding that can eliminate hot rolling δ-TRIP steel bead crack |
Also Published As
Publication number | Publication date |
---|---|
US6673169B1 (en) | 2004-01-06 |
US6364971B1 (en) | 2002-04-02 |
US20050126664A1 (en) | 2005-06-16 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US6673169B1 (en) | Method and apparatus for repairing superalloy components | |
US6495793B2 (en) | Laser repair method for nickel base superalloys with high gamma prime content | |
EP3153271B1 (en) | Method of repairing and manufacturing of turbine engine components | |
JP4675482B2 (en) | Turbine rotor modification and repair method | |
US4903888A (en) | Turbine system having more failure resistant rotors and repair welding of low alloy ferrous turbine components by controlled weld build-up | |
EP1296796B1 (en) | Welding superalloy articles | |
US7009137B2 (en) | Laser powder fusion repair of Z-notches with nickel based superalloy powder | |
US4940390A (en) | Turbine system having more failure resistant rotors and repair welding of low alloy ferrous turbine components by controlled weld build-up | |
JP3218567B2 (en) | Welding of high-strength nickel-base superalloys. | |
US20060231535A1 (en) | Method of welding a gamma-prime precipitate strengthened material | |
US5951792A (en) | Method for welding age-hardenable nickel-base alloys | |
EP0332875A2 (en) | More creep resistant turbine rotor, and procedures for repair welding of low alloy ferrous turbine components | |
KR20150113149A (en) | Selective laser melting/sintering using powdered flux | |
CN105705292A (en) | Additive manufacturing using a fluidized bed of powdered metal and powdered flux | |
EP3219434B1 (en) | Repair of superalloys by weld forced crack and braze repair | |
KR20150114535A (en) | Localized repair of superalloy component | |
JPS6233067A (en) | Repair of member with projection | |
KR20150106007A (en) | Localized repair of superalloy component | |
EP1605068A2 (en) | Homogeneous welding via pre-heating for high strength superalloy joining and material deposition | |
KR20150111366A (en) | Deposition of superalloys using powdered flux and metal | |
US6639173B1 (en) | Electron beam welding method providing post-weld heat treatment | |
Lowden et al. | Integrated weld automation for gas turbine blades | |
Steckowicz et al. | Development and implementation of robotized wire arc additive repair of a gas turbine diaphragm | |
Frederick et al. | Laser Weld Repair of Service Exposed IN738 and GTD111 Buckets | |
Lugan et al. | Qualification of Nd: YAG laser direct metal deposition techniques for repair of nickel superalloy components |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- AFTER EXAMINER'S ANSWER OR BOARD OF APPEALS DECISION |