EP1990445A1 - Procédé d'enlèvement d'un revêtement de protection à base de carbure - Google Patents

Procédé d'enlèvement d'un revêtement de protection à base de carbure Download PDF

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Publication number
EP1990445A1
EP1990445A1 EP08251543A EP08251543A EP1990445A1 EP 1990445 A1 EP1990445 A1 EP 1990445A1 EP 08251543 A EP08251543 A EP 08251543A EP 08251543 A EP08251543 A EP 08251543A EP 1990445 A1 EP1990445 A1 EP 1990445A1
Authority
EP
European Patent Office
Prior art keywords
carbide
coating
metal component
based coating
residual
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.)
Withdrawn
Application number
EP08251543A
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German (de)
English (en)
Inventor
Michael J. Minor
Paul M. Pellet
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP1990445A1 publication Critical patent/EP1990445A1/fr
Withdrawn legal-status Critical Current

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    • 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
    • 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

Definitions

  • the present invention relates the repair of metal components, such as gas turbine engine components.
  • the present invention relates to the removal of protective coatings during the repair of metal components.
  • Turbine engine components are exposed to extreme temperatures and pressures during the course of operation. As such, these engine components typically employ high-strength alloys (e.g., superalloys) to preserve the integrity of the components. However, over time, exposed portions of the components are subject to wear, cracking, and other degradations, which can lead to decreases in operational efficiencies and damage to the components.
  • high-strength alloys e.g., superalloys
  • carbide-based coatings such as chromium carbide-based coatings, are typically coated onto engine components to increase wear resistance and sliding mechanics between moving parts.
  • the present invention relates to a method for processing a metal component having a carbide-based coating.
  • the method includes exposing the carbide-based coating to fluoride ions, thereby extracting a carbide material from the carbide-based coating. This provides a residual coating on the metal component, which is then removed from the metal component.
  • FIG. 1 is a sectional view of metal component 10, which includes substrate 12 and coating 14.
  • Metal component 10 may be any type of component capable of containing coating 14, such as turbine engine components.
  • Substrate 12 is a metal substrate (e.g., nickel-based alloys and superalloys, cobalt-based alloys and superalloys, and combinations thereof) of metal component 10, and includes surface 16.
  • Coating 14 is a carbide-based coating formed on surface 16 of substrate 12 (e.g., via plasma spray deposition) to provide wear resistance and sliding properties during use.
  • the term "carbide-based coating” refers to a coating that includes at least one carbide material.
  • suitable carbide materials for use in the carbide-based coating include chromium carbide materials (e.g., Cr 3 C 2 , Cr 7 C 3 , and Cr 23 C 6 ), tungsten carbide materials (e.g., WC), and combinations thereof.
  • Coating 14 may also include other materials, such as nickel chromium (NiCr) alloys, cobalt (Co) alloys, and combinations thereof.
  • NiCr nickel chromium
  • Co cobalt
  • An example of a suitable chromium carbide-based coating for coating 14 includes about 75% by weight of a chromium carbide material and about 25% by weight of a nickel chromium alloy. Suitable coating thicknesses for coating 14 range from about 25 micrometers (about 1 mil) to about 500 micrometers (about 20 mils).
  • coating 14 may be removed by initially exposing metal component 10 to fluoride ions, which react with coating 14 to extract at least a portion of the carbide material (e.g., the chromium-carbide material) from coating 14.
  • Metal component 10 may be exposed to fluoride ions by placing metal component 10 in a chamber containing hydrogen fluoride (HF) gas.
  • HF hydrogen fluoride
  • the chamber may also include additional gases (e.g., H 2 ) to accommodate desired pressures and reaction rates. While within the chamber, the hydrogen fluoride gas and metal component 10 are then heated to a temperature sufficient to generate the fluoride ions from the hydrogen fluoride gas.
  • suitable temperatures for generating the fluoride ions include temperatures of at least about 820°C (about 1500°F), with particularly suitable temperatures ranging from about 870°C (about 1600°F) to about 1100°C (about 2000°F). This causes the fluoride ions of the hydrogen fluoride gas to react with coating 14, thereby extracting at least a portion of the carbide material from coating 14.
  • the amount of carbide material removed from coating 14 is generally dependent on the concentration of the fluoride ions, the temperature used, the surface area of coating 14, and the duration of the extraction. In one embodiment, the extraction is continued until at least about 50% by weight of the carbide material is removed from coating 14. In a more preferred embodiment, the extraction is continued until at least about 75% by weight of the carbide material is removed from coating 14. In an even more preferred embodiment, the extraction is continued until at least about 90% by weight of the carbide material is removed from coating 14. The weight percents of the removed carbide material are based on the pre-extraction weight of coating 14. Examples of suitable durations for the extraction process range from about 10 minutes to about 3 hours, with particularly suitable durations ranging from about 30 minutes to about 1 hour. When the extraction process is complete, metal component 10 may be removed from the chamber and cooled.
  • FIG. 2 is a sectional view of metal component 10 after the extraction process, which includes residual coating 18 disposed on surface 16 of substrate 12. Residual coating 18 is the remaining coating of coating 14 (shown in FIG. 1 ) after the extraction process. Because of the carbide material removal, residual coating 18 primarily includes the non-carbide portion of coating 14 (e.g., the nickel chromium alloy) and any residual amount of the carbide material that was not extracted. However, because a substantial portion of the carbide material was removed, residual coating 18 is structurally weaker than coating 14. Thus, residual coating 18 can be removed from surface 16 of substrate 12 without requiring the high-intensity machining, grinding, or grit blasting that are typically used to remove carbide-based coatings.
  • non-carbide portion of coating 14 e.g., the nickel chromium alloy
  • Residual coating 18 may be removed from surface 16 with low-pressure abrasive techniques (e.g., low-pressure grit blasting). The duration of the removal process may vary depending on the pressure used. However, the pressure required to remove residual coating 18 is substantially less than what is otherwise required to remove a carbide-based coating not subjected to the fluoride-ion extraction process (i.e., coating 14).
  • low-pressure abrasive techniques e.g., low-pressure grit blasting
  • Suitable pressures for removing residual coating 18 from surface 16 include removal pressures that are less than 25% of removal pressures required to remove coating 14 from surface 16 in the same duration, with particularly suitable removal pressures including less than 10% of the removal pressures required to remove coating 14 from surface 16 in the same duration, and with even more particularly suitable removal pressures including less than 5% of the removal pressures required to remove coating 14 from surface 16 in the same duration.
  • the term "removal pressure” refer to a pressure that is actually applied to the coating (e.g., coating 14 or residual coating 18). For removal techniques that are distance dependant (e.g., grit blasting), the discharge pressure is typically greater than the pressure actually applied to the coating.
  • FIG. 3 is a sectional view of metal component 10 after the residual coating 18 is removed.
  • the resulting metal component 10 may undergo the necessary repair processes to restore metal component 10 to operable condition. Because residual coating 18 (shown in FIG. 2 ) can be removed with a low-pressure technique, the risk of damaging surface 16 during the removal process is reduced. Accordingly, pursuant to the present invention, coating 14 (shown in FIG. 1 ) may be removed from substrate 12 while substantially preserving the dimensions of surface 16.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • ing And Chemical Polishing (AREA)
EP08251543A 2007-04-30 2008-04-28 Procédé d'enlèvement d'un revêtement de protection à base de carbure Withdrawn EP1990445A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/796,989 US20080264444A1 (en) 2007-04-30 2007-04-30 Method for removing carbide-based coatings

Publications (1)

Publication Number Publication Date
EP1990445A1 true EP1990445A1 (fr) 2008-11-12

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP08251543A Withdrawn EP1990445A1 (fr) 2007-04-30 2008-04-28 Procédé d'enlèvement d'un revêtement de protection à base de carbure

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US (1) US20080264444A1 (fr)
EP (1) EP1990445A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8967078B2 (en) * 2009-08-27 2015-03-03 United Technologies Corporation Abrasive finish mask and method of polishing a component
EP2354661B1 (fr) * 2010-02-04 2018-04-11 General Electric Technology GmbH Dispositif de combustion pour turbine à gaz
US20150217414A1 (en) * 2014-02-04 2015-08-06 Caterpillar Inc. Method of remanufacturing a component

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4098450A (en) * 1977-03-17 1978-07-04 General Electric Company Superalloy article cleaning and repair method
US5071486A (en) 1986-02-06 1991-12-10 University Of Dayton Process for removing protective coatings and bonding layers from metal parts
US5419927A (en) * 1988-09-26 1995-05-30 Chromalloy Gas Turbine Corporation Process for coating fiber reinforced ceramic composites
US5437737A (en) * 1994-02-07 1995-08-01 United Technologies Corporation Repair coating for superalloy articles, such as gas turbine engine components
US5741378A (en) * 1992-05-06 1998-04-21 United Technologies Corporation Method of rejuvenating cobalt-base superalloy articles
EP0961017A2 (fr) * 1998-05-28 1999-12-01 Mitsubishi Heavy Industries, Ltd. Revêtement de protection résistant aux températures élevées
EP1076114A1 (fr) * 1999-08-11 2001-02-14 General Electric Company Prpcédé pour enlever un revêtement céramique dense de barrière thermique d'une surface
EP1217090A1 (fr) * 2000-12-19 2002-06-26 United Technologies Corporation Procédé de dépôt en phase vapeur pour la réparation des articles en superalliage
EP1286020A2 (fr) * 2001-08-23 2003-02-26 United Technologies Corporation Méthode de réparation d'un composant perforé d'une turbine à gaz
US20050115926A1 (en) 2003-06-16 2005-06-02 General Electric Company Process for removing chromide coatings from metal substrates, and related compositions
EP1721697A1 (fr) * 2005-05-06 2006-11-15 United Technologies Corporation Procédé pour réparer superalliage et inserts
US20070087208A1 (en) * 2005-10-18 2007-04-19 United Technologies Corporation Sacrificial coating for fluoride ion cleaning

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4889589A (en) * 1986-06-26 1989-12-26 United Technologies Corporation Gaseous removal of ceramic coatings
GB0024031D0 (en) * 2000-09-29 2000-11-15 Rolls Royce Plc A nickel base superalloy
US6863738B2 (en) * 2001-01-29 2005-03-08 General Electric Company Method for removing oxides and coatings from a substrate
US7011721B2 (en) * 2001-03-01 2006-03-14 Cannon-Muskegon Corporation Superalloy for single crystal turbine vanes
US6503349B2 (en) * 2001-05-15 2003-01-07 United Technologies Corporation Repair of single crystal nickel based superalloy article
US6599416B2 (en) * 2001-09-28 2003-07-29 General Electric Company Method and apparatus for selectively removing coatings from substrates
US6645926B2 (en) * 2001-11-28 2003-11-11 United Technologies Corporation Fluoride cleaning masking system
US7060366B2 (en) * 2003-02-19 2006-06-13 General Electric Company Article including a substrate with a metallic coating and a chromium-aluminide protective coating thereon, and its preparation and use in component restoration
US7118636B2 (en) * 2003-04-14 2006-10-10 General Electric Company Precipitation-strengthened nickel-iron-chromium alloy
US6905396B1 (en) * 2003-11-20 2005-06-14 Huffman Corporation Method of removing a coating from a substrate
US7125457B2 (en) * 2003-12-31 2006-10-24 General Electric Company Method for removing oxide from cracks in turbine components

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4098450A (en) * 1977-03-17 1978-07-04 General Electric Company Superalloy article cleaning and repair method
US5071486A (en) 1986-02-06 1991-12-10 University Of Dayton Process for removing protective coatings and bonding layers from metal parts
US5419927A (en) * 1988-09-26 1995-05-30 Chromalloy Gas Turbine Corporation Process for coating fiber reinforced ceramic composites
US5741378A (en) * 1992-05-06 1998-04-21 United Technologies Corporation Method of rejuvenating cobalt-base superalloy articles
US5437737A (en) * 1994-02-07 1995-08-01 United Technologies Corporation Repair coating for superalloy articles, such as gas turbine engine components
EP0961017A2 (fr) * 1998-05-28 1999-12-01 Mitsubishi Heavy Industries, Ltd. Revêtement de protection résistant aux températures élevées
EP1076114A1 (fr) * 1999-08-11 2001-02-14 General Electric Company Prpcédé pour enlever un revêtement céramique dense de barrière thermique d'une surface
EP1217090A1 (fr) * 2000-12-19 2002-06-26 United Technologies Corporation Procédé de dépôt en phase vapeur pour la réparation des articles en superalliage
EP1286020A2 (fr) * 2001-08-23 2003-02-26 United Technologies Corporation Méthode de réparation d'un composant perforé d'une turbine à gaz
US20050115926A1 (en) 2003-06-16 2005-06-02 General Electric Company Process for removing chromide coatings from metal substrates, and related compositions
EP1721697A1 (fr) * 2005-05-06 2006-11-15 United Technologies Corporation Procédé pour réparer superalliage et inserts
US20070087208A1 (en) * 2005-10-18 2007-04-19 United Technologies Corporation Sacrificial coating for fluoride ion cleaning

Also Published As

Publication number Publication date
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