Classifications

• • 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
  • 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
  • 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
• • 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
• • 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
  • F05D2230/80—Repairing, retrofitting or upgrading methods

Definitions

• This invention relates generally to the field of materials technologies, and more particularly to material additive processes, and in one embodiment to a process for performing a functionally based repair to a superalloy component.
• superalloy materials are among the most difficult materials to weld due to their susceptibility to weld solidification cracking and strain age cracking.
• the term "superalloy” is used herein as it is commonly used in the art, i.e., a highly corrosion and oxidation resistant alloy that exhibits excellent mechanical strength and resistance to creep at high temperatures.
• Superalloys typically include a high nickel or cobalt content.
• superalloys examples include alloys sold under the trademarks and brand names Hastelloy, Inconel alloys (e.g., IN 738, IN 792, IN 939), Rene alloys (e.g., Rene N5, Rene 80, Rene 142), Haynes alloys, Mar M, CM 247, CM 247 LC, C263, 718, X-750, ECY 768, 282, X45, PWA 1483 and CMSX (e.g., CMSX-4) single crystal alloys. It is known to utilize selective laser melting (SLM) or selective laser sintering (SLS) to melt a thin layer of superalloy powder particles onto a superalloy substrate.
• SLM selective laser melting
• SLS selective laser sintering
• the melt pool is shielded from the atmosphere by applying an inert gas, such as argon, during the laser heating.
• an inert gas such as argon
• These processes tend to trap the oxides (e.g., aluminum and chromium oxides) that are adherent on the surface of the particles within the layer of deposited material, resulting in porosity, inclusions and other defects associated with the trapped oxides.
• Post process hot isostatic pressing (HIP) is often used to collapse these voids, inclusions and cracks in order to improve the properties of the deposited coating.
• the application of these processes is also limited to horizontal surfaces due to the requirement of pre-placing the powder.
• Laser microcladding is a 3D-capable process that deposits a small, thin layer of material onto a surface by using a laser beam to melt a flow of powder directed toward the surface.
• the powder is propelled toward the surface by a jet of gas, and when the powder is a steel or alloy material, the gas is argon or other inert gas which shields the molten alloy from atmospheric oxygen.
• Laser microcladding is limited by its low deposition rate, such as on the order of 1 to 6 cm 3 /hr.
• the protective argon shield tends to dissipate before the clad material is fully cooled, superficial oxidation and nitridation may occur on the surface of the deposit, which is problematic when multiple layers of clad material are necessary to achieve a desired cladding thickness.
• FIG.1 is a conventional chart illustrating the relative weldability of various superalloys as a function of their aluminum and titanium content.
• Alloys such as Inconel ® IN718 which have relatively lower concentrations of these elements, and consequentially relatively lower gamma prime content, are considered relatively weldable, although such welding is generally limited to low stress regions of a component.
• Alloys such as Inconel ® IN939 which have relatively higher concentrations of these elements are much more difficult to weld.
• a dashed line 10 indicates a recognized upper boundary of a zone of weldability. The line 10 intersects 3 wt.% aluminum on the vertical axis and 6 wt.% titanium on the horizontal axis.
• FIG. 1 is a conventional diagram illustrating the relative weldability of various superalloy materials.
• FIG. 2 is a cross-sectional view of a superalloy component undergoing a material addition process.
• FIG. 3 is a perspective view of a gas turbine blade.
• the present inventors now extend the capability described in United States Patent Application Publication No. US 2013/0136868 A1 by disclosing methods wherein an additive superalloy material is deposited onto an original superalloy material such that the additive superalloy material has a property that is different from a counterpart property of the original superalloy material.
• the property that is changed between the original material and the additive material may be material composition, grain structure, principal grain axis, grain boundary strengthened and/or porosity, as non-limiting examples.
• the additive material itself may have a varying property across its volume, with all or only portions of the additive material being different than the original superalloy material.
• a property of the additive material may be selected in response to an expected environment in which the resulting component may be designed to operate.
• FIG. 2 is a partial cross-sectional illustration of a superalloy component 20, which may be a gas turbine engine hot gas path component, for example, such as a blade, vane or combustor nozzle or burner.
• Component 20 is illustrated as undergoing a material addition process wherein a plurality of layers 22, 24, 26, 28 of additive superalloy material has been deposited on an original superalloy material 30.
• the original superalloy material 30 may be an original cast material from which the component 20 had been manufactured, or it may be a layer of material added to the component 20 during a previous repair or fabrication step.
• FIG. 2 illustrates additive superalloy material layer 28 in the process of being deposited onto previously deposited layer 26, such as by a process similar to those described in United States Patent Application Publication No. US 2013/0136868 A1 .
• a layer 32 of mixed powdered superalloy material and powdered flux material has been deposited onto layer 26 and is being melted by an energy beam such as laser beam 34 traversing across the layer 32 in the direction of arrow 36.
• the laser beam 34 melts the powders to form a melt pool 38 wherein a layer of slag material 40 floats to cover the layer of additive superalloy material 28.
• the melt pool 38 cools and solidifies behind the traversing 36 laser beam 34.
• the layer of slag 40 is then removed (not shown) by any convenient method, for example grit blasting, to reveal a new surface 42 of the additive superalloy material 28.
• the present inventors are now able to provide a repair that is responsive to such varying operational conditions, such as by providing more oxidation resistance in the tip region 56 and more corrosion and erosion resistance at the platform 54, for example.
• This improvement can be implemented during the original manufacturing of the blade 50 or during a repair activity where service induced cracks 58 in the original (typically cast) superalloy material are removed and the cracked material is replaced with an additive superalloy material that has a property that is different from a counterpart property of the original superalloy material.
• a region 60 of the blade platform 54 is illustrated as having been repaired in such a manner, with the repaired blade 50 now being able to provide improved performance during operation (such as number of hours before cracking develops, or resistance to erosion or corrosion, etc.) when compared to the originally manufactured blade.
• the composition of the additive material is different from a composition of the original superalloy material 30.
• there may be compositional variation across the volume of the additive material such as when topmost additive material layers 26, 28 have a composition different from bottommost additive material layers 22, 24.
• the compositional variation across the volume of the additive material may alternatively or additionally be accomplished within a single layer, such as by varying the composition of deposited powdered material layer 32 across the surface of layer 26. Such variation may be accomplished by varying the composition of the powdered alloy material, the powdered flux material, or both.
• additional powdered aluminum may be included in regions where higher oxidation resistance is desired.
• the composition of the powdered flux material may be varied, such as by including more scavenger elements to reduce impurities in the resulting additive alloy.
• the grain structure of the additive superalloy material 22, 24, 26, 28 may be different than that of the original superalloy material 30. This is accomplished by controlling the process of solidification of the melt pool 38.
• original superalloy material 30 may be conventionally cast with an equiaxed grain structure.
• FIG. 2 with the direction of movement of the laser beam in direction 36, one may appreciate that the weld pool 38 is cooled primarily by the underlying alloy material, and that the resulting grain growth direction will be generally vertical.
• the grain growth direction will not be completely perpendicular to the underlying surface, but rather, it will be tilted by a few degrees off of vertical. As the tilt tends to accumulate as a plurality of layers 22, 24, 26, 28 are applied, the material will tend to develop an equiaxed grain structure. Recognizing this phenomenon, the present inventors control the solidification conditions and the direction of movement 36 from layer to layer, such as by alternating the direction of movement by 180 degrees between layers, to maintain a directionally solidified grain structure in the resulting overall additive material volume
• any desired additive material grain structure may be achieved over any original material grain structure, including controlling a principal grain axis of a directionally solidified additive superalloy material to be not parallel to a principal grain axis of a directionally solidified original superalloy material.
• Other embodiments may include controlling a material addition process such that a porosity of the additive superalloy material is different from a porosity of the original superalloy material or other portions of the additive material volume. This may be accomplished by including fugitive or hollow particles within the powdered material layer
• a coefficient of thermal conductivity, coefficient of thermal expansion, hardness or wear property of the material may thus be varied, and may be further varied by the selective addition of graphite particles.
• Still another example includes locally strengthening the grain boundaries of a portion of the component such as by the addition of boron in the deposition process.
• a local increase in the coefficient of thermal expansion of the repaired regions 60 of the gas turbine blade 50 of FIG. 3 when compared with the surrounding original superalloy material in a remaining portion of the platform 54 will result in regions 60 expanding more than the surrounding material when the blade 50 is heated.
• the additive superalloy material and an adjacent region 62 of the original superalloy material (which may be important and otherwise crack-prone) will experience compressive forces when the blade 50 is returned to an elevated operating temperature environment in a gas turbine engine.
• the resulting compressive stress will tend to mitigate the reoccurrence of cracks 58 in repaired region 60 and in its surrounding material 62 during subsequent operation.
• a blade formed of alloy IN 939 may have a repair region 60 formed with alloy 825. Alloy 939 has a coefficient of thermal expansion of 14.0 in/in/K while alloy 825 has a coefficient of thermal expansion of 17.1 in/in/K. The resulting difference in thermal growth at operating temperature will tend to develop compressive stress in region 60 and in its surrounding material when the blade 50 is returned to service.
• a repair regiment for a superalloy gas turbine component may now include the step of evaluating the performance of an original superalloy material upon removal of the component from the operating environment of a service-run gas turbine engine. Should the evaluation identify a service-limiting region of the component, it may be possible to identify a superalloy material having a property that is different from the counterpart property of the original superalloy material that would provide the component with improved performance in the engine. Likely, such material may have a composition that is above line 10 in FIG. 1 . Such material can be applied as an additive material during a repair of the component in place of the original superalloy material using a process such as is illustrated in FIG. 2, or a replacement component can be so manufactured. The repaired or replacement component is then available for further service in the operating environment of the gas turbine engine.
• a gas turbine engine burner may be repaired or manufactured to have a burner tip with a superalloy composition responsive to a fuel type to be used in the engine.
• gas turbine burner tips are typically replaced with Hast X alloy because of the ease of fabrication of that alloy. It is now possible to customize the tip repair with an additive superalloy material that provides improved performance when exposed to high sulfur or other less desirable fuels.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• Physics & Mathematics (AREA)
• Optics & Photonics (AREA)
• Plasma & Fusion (AREA)
• General Engineering & Computer Science (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Powder Metallurgy (AREA)
• Laser Beam Processing (AREA)

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• 2014
  • 2014-07-09 WO PCT/US2014/045931 patent/WO2015017093A1/en active Application Filing
  • 2014-07-09 DE DE112014003501.7T patent/DE112014003501T5/de active Pending
  • 2014-07-09 KR KR1020167005571A patent/KR102280670B1/ko not_active Application Discontinuation
  • 2014-07-09 CN CN201480042526.4A patent/CN105431250B/zh active Active

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