Classifications

• • C—CHEMISTRY; METALLURGY
  • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
  • C23G—CLEANING OR DE-GREASING OF METALLIC MATERIAL BY CHEMICAL METHODS OTHER THAN ELECTROLYSIS
  • C23G5/00—Cleaning or de-greasing metallic material by other methods; Apparatus for cleaning or de-greasing metallic material with organic solvents
• • C—CHEMISTRY; METALLURGY
  • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
  • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
  • C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
  • C23C18/16—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by reduction or substitution, e.g. electroless plating
  • C23C18/1601—Process or apparatus
  • C23C18/1603—Process or apparatus coating on selected surface areas
  • C23C18/1614—Process or apparatus coating on selected surface areas plating on one side
  • C23C18/1616—Process or apparatus coating on selected surface areas plating on one side interior or inner surface
• • C—CHEMISTRY; METALLURGY
  • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
  • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
  • C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
  • C23C18/16—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by reduction or substitution, e.g. electroless plating
  • C23C18/1601—Process or apparatus
  • C23C18/1633—Process of electroless plating
  • C23C18/1689—After-treatment
• • C—CHEMISTRY; METALLURGY
  • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
  • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
  • C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
  • C23C18/16—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by reduction or substitution, e.g. electroless plating
  • C23C18/31—Coating with metals
  • C23C18/32—Coating with nickel, cobalt or mixtures thereof with phosphorus or boron
• • 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
  • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
  • B23P6/00—Restoring or reconditioning objects
  • B23P6/04—Repairing fractures or cracked metal parts or products, e.g. castings
  • B23P6/045—Repairing fractures or cracked metal parts or products, e.g. castings of turbine components, e.g. moving or stationary blades, rotors, etc.

Definitions

• This application relates to a maskant material which protects a surface being subjected to fluoride ion cleaning.
• Gas turbine engines are known, and typically include a compressor which delivers compressed air into a combustor section.
• a fan may deliver air into the compressor section in some types of turbine engines.
• the air is mixed with fuel and ignited. Products of this combustion pass downstream over turbine rotors.
• the turbine rotors, the compressor, and the fan all included any number of airfoil structures which are subject to stresses both from mechanical and temperature issues.
• a crack may form in one of the airfoil components.
• Various techniques are known for repairing the cracks in an airfoil.
• One challenge is that the cracks may occur while the airfoil component is still in service in the turbine engine.
• metal oxides may form within the cracks.
• One type of airfoil component is formed of nickel alloys.
• the nickel may include a small percentage of titanium or aluminum, as an example.
• fluoride ion cleaning is utilized.
• a fluoride ion gas is present in a chamber around the part. The fluoride will combine with the oxides, and the oxides are cleaned from the cracks.
• a method of treating a surface includes the steps of providing a plating including at least some nickel over a nickel alloy surface in a thickness less than 0.0005" (0.001 cm), and exposing the surface to a fluoride ion cleaning to remove impurities on the surface, and leaving at least some of the plating.
• the nickel alloy includes at least one of aluminum and titanium.
• the fluoride ion cleaning may be hydrogen fluoride ion cleaning.
• the surface is part of a component having a crack with oxides to be cleaned by the fluoride ion cleaning.
• the component has an airfoil.
• the component is a gas turbine engine component.
• the nickel plating is deposited in a thickness that is generally less than a depth of the crack.
• the crack is repaired after the fluoride ion cleaning.
• the component has internal cavities, and an inner wall spaced inwardly from an outer wall.
• the crack is in the inner wall, and the plating is the inner wall is done with an electroless plating technique.
• the plating is provided by a nickel alloy.
• the crack extending from the inner wall to the outer wall, and the plating is done on both the outer wall and the inner wall.
• the nickel plating is greater than or equal to about 0.0001" (0.000254 cm) and less than or equal to about 0.0002" (0.0005 cm).
• the plating is deposited in a thickness that is generally less than the depth of the crack. [0001] In another embodiment according to any of the previous embodiments, the plating is greater than or equal to about 0.0001" (0.000254 cm) and less than or equal to about 0.0002" (0.0005 cm).
• a method of repair includes the steps of providing a plating including at least some nickel over a nickel alloy component that has a crack to be repaired the plating being less than 0.0005" (0.001 cm) thick, exposing the component to a fluoride ion cleaning to remove impurities in the crack, and leaving at least some of the plating, and repairing the crack in the component.
• the component has internal cavities, and an inner wall spaced inwardly from an outer wall.
• the crack is in the inner wall, and the plating is done on the inner wall with electroless plating technique.
• the plating is provided by a nickel alloy.
• the nickel plating is deposited in a thickness that is generally less than the depth of the crack.
• the nickel plating is greater than or equal to about 0.0001" (0.000254 cm) and less than or equal to about 0.0002" (0.0005 cm).
• a gas turbine engine component has an airfoil formed of a nickel alloy include at least one or aluminum and titanium, and nickel plating over a surface of the airfoil, deposited in a thickness of greater than or equal to about 0.0001" (0.000254 cm) and less than or equal to about 0.0002" (0.0005 cm), and a repaired crack.
• Figure 1 shows an example airfoil component.
• Figure 2 shows a crack
• Figure 3 shows the method steps associated with this application.
• Figure 4 shows an example airfoil component after the method of Figure 3 is complete.
• Figure 5 shows example areas of a component.
• Figure 6 shows another application.
• Component 20 may be a turbine blade or a turbine vane. As known, component 20 has an airfoil shape.
• a crack 22 is shown in a surface.
• the crack must be repaired before the part is returned for service.
• Various techniques are known for repairing the cracks, and any one of the actual methods for repairing may benefit from the teachings of this application.
• the crack 22 will develop metal oxides as shown at 23. This occurs as the component 20 will typically remain in service after the crack occurs, and thus, the exposed surfaces in the crack will form oxides.
• the component 20 is formed of nickel alloy, and may contain materials in addition to nickel, such as aluminum and titanium.
• fluoride ion cleaning technique is hydrogen fluoride gas cleaning.
• fluoride ion techniques may be utilized in this method.
• fluorocarbon cleaning is one known fluoride ion cleaning technique.
• Figure 3 shows a method of repairing the component while avoiding intergranular attack.
• the component 20 may be cleaned as shown at 60.
• a nickel plating 61 is placed on the component 20. While the nickel plating 61 may occur at all areas of the component, it may also only be utilized at areas which are subject to the most stress, if that is more economical.
• the nickel plating may be plated by compound electroplating.
• the nickel plate may be deposited to a thickness of greater than or equal to about .0001" (.000254 cm) to less than or equal to about 0.0005" (0.001 cm). More narrowly, the thickness may be less than or equal to about 0.0002" (0.005 cm).
• a surface 19 of the component 20 is shown with the nickel plating 70.
• the crack 22 is typically much thicker than the thickness of the nickel plating, and thus the nickel plating will not block access to the crack during the fluoride ion cleaning 62. Further, the nickel plating 70 will likely not adhere to the oxide materials 23 in the crack 22. Finally, should it be determined that the nickel plating does complicate the cleaning of the crack 22, the crack 22 may be masked during the plating process.
• the plated component has been subject to fluoride ion cleaning at 62.
• This cleaning technique may be as known, and remove the oxides 23.
• the plating 70 is intended to survive the cleaning process, at least in part, such that it is on the final cleaned component.
• Some repair 63 is then utilized to repair the crack and restore the component 20. Braze repairs are but one example of a method that may be utilized.
• a portion of a material 200 shows the effect of fluoride ion cleaning on an area that has been plated. This can be contrasted to an area 202 wherein plating did not occur. As can be seen in area 202, a number of cracks can be seen at 205. These cracks are the result of intergranular attack. Similar cracks are not found in area 200.
• Figure 6 shows another application to the component 20.
• airfoil components such as component 20 have an outer wall 300, but also tend to have internal cavities such as shown at 299. These cavities pass cooling air within the component.
• a crack 302 is shown on an inner wall 301 of component 20.
• a layer 304 may be applied to the surface 301 prior to cleaning of the crack 302.
• electroless plating techniques may be necessary.
• nickel alloys such as nickel-boron, or nickel-phosphorous, may be utilized.
• the thickness of the layer 304 may be generally the same as the thicknesses as mentioned above for the external layer.
• Another potential situation is illustrated in Figure 6, and wherein the crack has a portion 402 extending to the outer wall or surface 300. In this embodiment, a layer 400 would also be placed on the outer wall 300, such that the combined crack 302 and 402 can be repaired.
• the method may provide benefits to any fluoride ion cleaning of a nickel alloy surface.

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• Chemical & Material Sciences (AREA)
• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Chemical & Material Sciences (AREA)
• Chemical Kinetics & Catalysis (AREA)
• Materials Engineering (AREA)
• Metallurgy (AREA)
• Organic Chemistry (AREA)
• General Engineering & Computer Science (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Chemically Coating (AREA)

Applications Claiming Priority (2)

Publications (2)

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• 2012
  • 2012-05-31 US US13/484,364 patent/US20130323066A1/en not_active Abandoned
• 2013
  • 2013-05-15 EP EP20130796366 patent/EP2855734A4/de not_active Withdrawn
  • 2013-05-15 WO PCT/US2013/041077 patent/WO2013180951A1/en active Application Filing
  • 2013-05-15 SG SG11201407922WA patent/SG11201407922WA/en unknown

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