GB2401117A - A method of preventing aluminising and a mask to prevent aluminising - Google Patents

A method of preventing aluminising and a mask to prevent aluminising Download PDF

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Publication number
GB2401117A
GB2401117A GB0310015A GB0310015A GB2401117A GB 2401117 A GB2401117 A GB 2401117A GB 0310015 A GB0310015 A GB 0310015A GB 0310015 A GB0310015 A GB 0310015A GB 2401117 A GB2401117 A GB 2401117A
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United Kingdom
Prior art keywords
mask
chromising
powder
aluminising
metal substrate
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GB0310015A
Inventor
David Frederick Bettridge
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Rolls Royce PLC
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Rolls Royce PLC
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Priority to GB0310015A priority Critical patent/GB2401117A/en
Publication of GB2401117A publication Critical patent/GB2401117A/en
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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
    • 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
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/04—Diffusion into selected surface areas, e.g. using masks

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

Abstract

A mask for masking a metal turbine blade (10) to prevent aluminising of a selected area, the root (12) and the shank (14), of the metal turbine blade (10) comprises a chromising composition (20) arranged on the selected area, the root (12) and the shank (14), of the metal turbine blade (10) and an aluminising mask (22) arranged on the chromising composition (20). The chromising composition consists of a fine chromium containing powder, an inert refractory diluent powder and a halide activator and a binder made into a slurry. The chromising composition contains constituents that will produce a local chromising reaction adjacent the selected area, the root 12 and the shank 14, of the turbine blade (10) where the chromising composition (20) has been applied simultaneously as the remainder, the platform (16) and the aerofoil (18), of the turbine blade (10) are aluminised during the aluminising heat treatment process. The aluminising mask may be a slurry or a powder filled box.

Description

24011 17
A METHOD OF PREVENTING ALUMINISING AND A MASK TO PREVENT
ALUMINISING
The present invention relates to a method and a mask for partial masking of a metal substrate to prevent diffusion of aluminium into, aluminising of, selected areas of the metal substrate.
Superalloy substrates, for example those used in gas turbine engine turbine blades and/or turbine vanes, are aluminized to provide protection against deterioration by oxidation and sulphate promoted corrosion processes that occur at the high operating temperature experienced during use. However, formation of the aluminised coating, nickel aluminide coating, produced by aluminising of the superalloy substrate, produces a dimensional growth on the superalloy substrate. The dimensional growth may exceed the dimensional tolerance of fitting/mating surfaces leading to assembly problems and possible mechanical failure in highly stressed regions, e.g. firtree roots, or dovetail roots, of turbine blades, due to the extreme brittleness of the nickel aluminide coating at temperatures below the ductile-brittle transition temperature of about 700 C.
To avoid these problems, it is normal practice to protect these regions, for example the firtree, or dovetail, roots of the turbine blades, against aluminising by covering these regions with masking slurries and/or powder filled metallic/protective boxes. These masking slurries and/or powder filled metallic/protective boxes are very effective when the aluminized coatings are produced by low temperature pack aluminizing processes. But these masking slurries and or powder filled metallic/protective boxes allow some seepage of the aluminised coating into the regions covered by the masking slurry or powder filled metallic/protective boxes when the aluminised coatings are produced by the more invasive, high temperature, vapour phase aluminizing processes. The masking slurry may also produce undesirable alloy depletion and carburisation affects in the superalloy substrate through reaction with the masking slurry constituents and halide atmosphere S during the aluminide coating heat treatment process.
Our UK patents GB1241013 and GB2008621B are examples of masking slurries and our UK patent GB2210387B is an example of a powder filled metallic box.
Accordingly the present invention seeks to provide a novel mask to prevent aluminizing, which reduces, preferably overcomes, the above- mentioned problems.
Accordingly the present invention provides a mask for partial masking of a metal substrate to prevent aluminislng of a selected area of the metal substrate wherein the mask IS comprises a chromising composition arranged on the selected area of the metal substrate and an aluminizing mask arranged on the chromising composition.
Preferably the chromising composition comprising chromium powder, ferrochrome powder or other chromium containing powder, an inert refractory diluent powder and a halide activator.
Preferably the inert refractory diluent powder comprises alumina or zirconia.
Preferably the halide activator comprises ammonium chloride.
Preferably the chromising composition comprises 40wt% to 60wt% chromium powder, 0.05 to lwt% ammonium chloride and the balance alumina powder.
Preferably the chromising composition is mixed with a binder to form a slurry.
Preferably the binder is an organic binder.
Preferably the organic binder comprises nitro- cellulose, methyl methacrylate or polyvinyl alcohol.
The aluminising mask may comprise a slurry and alternatively the aluminizing mask may comprise a powder filled box.
The present invention also seeks to provide a novel method of preventing aluminising, which reduces, preferably overcomes, the above-mentioned problems. The present invention also provides a method of preventing aluminising of a selected area of a metal substrate during a high temperature vapour phase aluminising process comprising applying a chromising composition to the selected area of the metal substrate, applying an aluminising mask on the chromising composition, aluminising areas of the metal substrate other than the selected area of the metal substrate and simultaneously producing a chromising reaction adjacent to the selected area of the metal substrate and between the selected area of the metal substrate and the mask to produce a chromium enriched zone at the selected area of the metal substrate.
Preferably the chromising composition comprises chromium powder, ferrochrome powder or other chromium containing powder, an inert refractory diluent powder and a halide activator.
So Preferably the inert refractory diluent powder comprises alumina or zirconia.
Preferably the halide activator comprises ammonium chloride.
Preferably the chromising composition comprises 40wt% to 60wt% chromium powder, 0.05 to lwt% ammonium chloride and the balance alumina powder.
Preferably the chromising composition is mixed with a binder to form a slurry.
Preferably the binder is an organic binder.
Preferably the organic binder comprises nitro cellulose, methyl methacrylate or polyvinyl alcohol.
The aluminising mask may comprise a slurry and alternatively the aluminising mask may comprise a powder filled box.
Preferably the metal substrate comprises a nickel- based superalloy, a cobalt-based superalloy or an iron- based superalloy.
Preferably the metal substrate is a turbine blade or a gas turbine engine component.
The present invention will be more fully described by way of example with reference to the accompanying drawings in which: Figure 1 is a view of a turbine blade.
Figure 2 is an enlarged cross-sectional view of a turbine blade coated with a chromising slurry and an aluminizing mask according to the present invention.
Figure 2A is an enlarged cross-sectional view of the chromising slurry and aluminising mask shown in figure 2.
Figure 3 shows a turbine blade coated with a chromising slurry and positioned within a powder filled box according to the present invention.
A gas turbine engine turbine blade 10, as shown in figure 1, comprises a root 12, a shank 14, a platform 16 and an aerofoil 18. The turbine blade 10 comprises a superalloy, for example a nickel-based superalloy, a cobalt-based superalloy or an iron-based superalloy. The aerofoil 18 and that surface of the platform 16 adjacent to the aerofoil 18 of the turbine blade 10 are to be alum_nised and the root 12 and shank 14 of the turbine blade 10 are not to be aluminized.
As shown in figure 2 a chromising slurry 20 is applied onto a selected area, the root 12 and the shank 14, of the turbine blade 10 by brushing, dipping or other suitable process and then the chromising slurry 20 is dried. A conventional aluminizing mask, or stop off, 22 for example Comprising nickel oxide powder, or nickel powder, a refrs.ctory powder, zirconia, and an organic resin binder as desc ibed in GB2008621B, is applied onto the chromising slurry 20 by brushing, dipping or other suitable process and:hen the aluminising mask 22 is dried. The chromising slurry 20 and aluminising mask 22 prevent aluminising of the selected areas, root 12 and shank 14, of the turbine blade 10.
An example of a chromising slurry 20 consists of a s fine chromium containing powder, an equally fine inert refractory diluent powder and a small amount of a halide activator. The chromium containing powder is for example simply chromium powder or ferrochrome powder. The inert refractory diluent powder is for example alumina powder or zirconia powder, the halide activator is for example ammonium chloride or sodium fluoride. The exact formulation is optimised for a given set of aluminising parameters and superalloy substrate. A typical example consists of 40wt% to 60wt% chromium powder 20-40 IS micrometers particle size, 0.05wt% to 1.00wt% ammonium chloride powder 2 to 10 micrometers particle size and the balance alumina 20 to 50 micrometers particle size.
Those skilled in the art of chromising will appreciate that many different formulations of halide activated JO chromising powder may be used successfully as alternatives to the above example.
After blending the powder constituents, an organic binder, for example methyl methacrylate, nitro-cellulose or poly vinyl alcohol is added to produce a chromising slurry as that may be applied to the metal substrate by brushing, dipping etc to give good coverage without cracking or lifting after drying. The number of applications of the chromising slurry required to produce the desired amount of chromium enrichment and to prevent aluminising penetration may be determined by trial for specific aluminising conditions and each application of the chromising slurry is allowed to dry before a further application of the chromising slurry.
In use the turbine blade 10 with the chromising slurry 20 and the aluminising mask 22 is located in an aluminising chamber and the turbine blade 10 is subjected to a high temperature vapour phase aluminising process to aluminise the aerofoil 18 and the adjacent platform surfaces 16. The turbine blade 10 is heated under a protective atmosphere, of for example argon or hydrogen, to an aluminising temperature of at least 1030 C. As the temperature increases, the binders used in the chromising slurry 20 and the aluminising mask 22 thermally decompose leaving the powder layers in place on the outer surface of the selected area, the root 12 and shank 14, of the turbine blade 10.
IO As the temperature increases further, increasing amounts of aluminium halide vapour are generated from an aluminium halide source to facilitate the aluminising reaction. The aluminising mask 22 restricts the inward penetration of the aluminising vapour in the selected area, the root 12 and the shank 14, of the turbine blade 10, such that the partial pressure of aluminium halide vapour decreases substantially through the thickness of the aluminising mask 22 towards the chromising slurry 20. Under the low aluminium activity and high chromium activity conditions that prevail in the vicinity of the chromising slurry 20, a chromising reaction is thermodynamically favoured so that chromising of the selected area, the root 12 and the shank 14, of the turbine blade 10 takes place instead of aluminising.
After completion of the high temperature vapour aluminising process the turbine blade 10 is fibre brushed to remove residual masking materials to leave a clean chromised, chromium enriched, surface on the selected area, root 12 and shank 14, of the turbine blade 10 and an aluminized, aluminium enriched, surface on the remainder, the aerofoil 18 and platform 16, of the turbine blade 10.
A chromium enriched surface is much more ductile than an aluminium enriched surface and therefore the chromium enriched surface has minimal effect on the important creep ano fatigue properties of the metal substrate. The presence of the chromising environment during processing also reduces, or prevents, the carburisation and alloy depletion problems mentioned previously, that may arise in the metal substrate from reaction between the alloy constituents and the aluminising mask decomposition products and the aluminising halide atmosphere.
Unlike aluminising, very little surface growth is produced by the chromising so that there is very little impact on the close tolerance dimensions of the firtree roots, or dovetail roots, of the turbine blades.
Chromised coatings, chromium enriched coatings, applied to superalloy substrates provide good protection against low temperature, Type 2, forms of sulphate promoted corrosion and therefore provide an additional benefit to the masked area. It will be recognised from this that if it is desired the method of the present invention may be used to achieve simultaneous aluminising and chromising of different areas of the same component to enhance its service life.
As shown in figure 3 a chromising slurry 20 is applied onto a selected area, the root 12 and the shank 14, of the turbine blade 10 by brushing, dipping or other suitable process and then the chromising slurry 20 is dried. The selected area, the root 12 and the shank 14, of the turbine blade 10 is positioned into a tight fitting metal box 24 o: and the remaining space within the metal box 24 is filled with a conventional aluminising mask 26 comprising nickel oxide powder, or nickel powder, a refractory powder, zirconia, and an organic resin binder as described in GB2008621B or a physical mixture comprising nickel powder, a nickel alloy powder or an alloy powder of the same metal as the metal substrate and a refractory powder, alumina, as described in GB2210387B. The chromising slurry 20, metal box 24 and aluminising mask 26 prevent aluminising of the selected area, the root 12 and the shank 14, of the turbine 3s blade 10.
An example of a chromising slurry 20 consists of a fine chromium containing powder, an equally fine inert refractory diluent powder and a small amount of a halide activator. The chromium containing powder is for example simply chromium powder or ferrochrome powder. The inert refractory diluent powder is for example alumina powder or zirconia powder, the halide activator is for example ammonium chloride or sodium fluoride. The exact formulation is optimised for a given set of aluminising parameters and superalloy substrate. A typical example consists of 40wt% to 60wt% chromium powder 20-40 micrometers particle size, 0.05wt% to 1.00wt% ammonium chloride powder 2 to 10 micrometers particle size and the balance alumina 20 to 50 micrometers particle size.
IS After blending the powder constituents, an organic binder, for example methyl methacrylate, nitro-cellulose or poly vinyl alcohol is added to produce a chromising slurry that may be applied to the metal substrate by brushing, dipping eta to give good coverage without cracking of lifting after drying. The number of applications of the chromising slurry required to produce the desired amount of chromium enrichment to prevent aluminising penetration may be determined by trial for specific aluminising conditions and each application of the chromising slurry is allowed to dry before a further application of the chromising slurry.
In use the turbine blade 10 with the chromising slurry 20, the metal box 24 and the aluminising mask 26 is located in an aluminising chamber and the turbine blade 10 is subjected to a high temperature vapour phase aluminising process to aluminise the aerofoil 18 and the adjacent platform surfaces 16. The turbine blade 10 is heated under a protective atmosphere, of for example argon or hydrogen, to an aluminising temperature of at least 1030 C. As the temperature increases, the binders used in the chromising slurry 20 and the aluminising mask 26 thermally decompose leaving the powder layers in place on the outer surface of the selected area, the root 12 and the shank 14, of the turbine blade 10. As the temperature increases further, increasing amounts of aluminium halide vapour are generated from an aluminium halide source to facilitate the aluminising reaction. The metal box 24 and the aluminizing mask 26 restricts the inward penetration of the aluminising vapour in the selected area, the root 12 and the shank 14 of the turbine blade 10, such that the partial pressure of aluminium halide vapour decreases substantially through the thickness of the aluminizing mask 22 towards the chromising slurry 20. Under the low aluminium activity and high chromium activity conditions that prevail in the vicinity of the chromising slurry 20, a chromising reaction is thermodynamically favoured so that chromising of the selected area, the root 12 and the shank 14, of the turbine blade 10 takes place instead of aluminising.
After completion of the high temperature vapour aluminizing process the turbine blade 10 is fibre brushed to remove residual masking materials to leave a clean chromised, chromium enriched, surface on the selected area, the root 12 and the shank, 14 of the turbine blade 10 and an aluminized, aluminium enriched, surface on the remainder, the aerofoil 18 and platform 16, of the turbine blade 10.
is Although the present invention has been described with reference to masking superalloy substrates it may be possible to use the invention with other metal substrates.

Claims (26)

  1. Claims: 1. A mask for partial masking of a metal substrate to prevent
    aluminising of a selected area of the metal substrate wherein the mask comprises a chromising composition arranged on the selected area of the metal substrate and an aluminising mask arranged on the chromising composition.
  2. 2. A mask as claimed in claim 1 wherein the chromising composition comprising chromium powder, ferrochrome powder or other chromium containing powder, an inert refractory diluent powder and a halide activator.
  3. 3. A mask as claimed in claim 2 wherein the inert refractory diluent powder comprises alumina or zirconia.
  4. 4. A mask as claimed in claim 2 or claim 3 wherein the halide activator comprises ammonium chloride.
  5. 5. A mask as claimed in any of claims 1 to 4 wherein the chromising composition comprises 40wt% to 60wt% chromium powder, 0.05 to lwt% ammonium chloride and the balance alumina powder.
  6. 6. A mask as claimed in any of claims 2 to 5 wherein the chromising composition is mixed with a binder to form a slurry.
  7. 7. A mask as claimed in claim 6 wherein the binder is an organic binder.
  8. 8. A mask as claimed in claim 7 wherein the organic binder comprises nitro-cellulose, methyl methacrylate or polyvinyl alcohol.
  9. 9. A mask as claimed in any of claims 1 to 8 wherein the aluminizing mask comprises a slurry.
  10. 10. A mask as claimed in any of claims 1 to 8 wherein the aluminising mask comprises a powder filled box.
  11. 11. A mask for partial masking of a metal substrate to prevent aluminizing of a selected area of the metal substrate substantially as hereinbefore described with reference to figure 2 of the accompanying drawings.
  12. 12. A mask for partial masking of a metal substrate to prevent aluminising of a selected area of the metal substrate substantially as hereinbefore described with reference to figure 3 of the accompanying drawings.
  13. 13. A method of preventing aluminizing of a selected area of a metal substrate during a high temperature vapour phase aluminizing process comprising applying a chromising composition to the selected area of the metal substrate, applying an aluminising mask on the chromising composition, JO aluminizing areas of the metal substrate other than the selected area of the metal substrate and simultaneously producing a chromising reaction adjacent to the selected area of the metal substrate and between the selected area of the metal substrate and the mask to produce a chromium IS enriched zone at the selected area of the metal substrate.
  14. 14. A method as claimed in claim 13 wherein the chromising composition comprises chromium powder, ferrochrome powder or other chromium containing powder, an inert refractory diluent powder and a halide activator.
  15. 15. A method as claimed in claim 14 wherein the inert refractory diluent powder comprises alumina or zirconia.
  16. 16. A method as claimed in claim 14 or claim 15 wherein the halide activator comprises ammonium chloride.
  17. 17. A method as claimed in any of claims 14 to 16 wherein the chromising composition comprises 40wt% to 60wt% chromium powder, 0.05 to lwt% ammonium chloride and the balance alumina powder.
  18. 18. A method as claimed in any of claims 14 to 17 wherein the chromising composition is mixed with a binder to form a slurry.
  19. 19. A method as claimed in claim 18 wherein the binder is an organic binder.
  20. 20. A method as claimed in claim 19 wherein the organic binder comprises nitro-cellulose, methyl methacrylate or polyvinyl alcohol.
  21. 21. A method as claimed in any of claims 13 to 20 wherein the aluminising mask comprises a slurry.
  22. 22. A method as claimed in any of claims 13 to 20 wherein the aluminising mask comprises a powder filled box.
  23. 23. A method as claimed in any of claims 13 to 22 wherein the metal substrate comprises a nickel-based superalloy, a cobalt-based superalloy or an iron-based superalloy.
  24. 24. A method as claimed in any of claims 13 to 23 wherein the metal substrate is a turbine blade or a gas turbine l0 engine component.
  25. 25. A method of preventing aluminizing of a selected area of a metal substrate substantially as hereinbefore described with reference to figure 2 of the accompanying drawings.
  26. 26. A method of preventing aluminising of a selected area of a metal substrate substantially as hereinbefore described with reference to figure 3 of the accompanying drawings.
GB0310015A 2003-05-01 2003-05-01 A method of preventing aluminising and a mask to prevent aluminising Withdrawn GB2401117A (en)

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Cited By (16)

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Publication number Priority date Publication date Assignee Title
GB2421032A (en) * 2004-12-11 2006-06-14 Siemens Ind Turbomachinery Ltd A method of protecting a component against hot corrosion
EP1772529A1 (en) * 2005-10-07 2007-04-11 Siemens Aktiengesellschaft Dry chemical composition, use thereof to form a layer system and method for coating
DE102005060243A1 (en) * 2005-12-14 2007-06-21 Man Turbo Ag Process for coating hollow internally cooled gas turbine blades with adhesive-, zirconium oxide ceramic- and Cr diffusion layers useful in gas turbine engine technology has adhesive layer applied by plasma or high rate spraying method
WO2007147387A2 (en) * 2006-06-20 2007-12-27 Mtu Aero Engines Gmbh Method of repairing intake coatings
WO2007147708A2 (en) * 2006-06-24 2007-12-27 Siemens Aktiengesellschaft Method of protecting a component against hot corrosion and a component protected by said method
US20090263237A1 (en) * 2006-06-08 2009-10-22 Paul Box Coated turbine component and method of coating a turbine component
CN102161029A (en) * 2010-02-12 2011-08-24 西门子公司 Overspray shielding device and method
EP2778251A1 (en) * 2013-03-13 2014-09-17 Howmet Corporation A maskant for use in aluminizing a turbine component
WO2015108766A1 (en) * 2014-01-14 2015-07-23 Praxair S.T. Technology, Inc. Methods of applying chromium diffusion coatings onto selective regions of a component
US20160010472A1 (en) * 2012-02-21 2016-01-14 Howment Corporation Coating and coating method for gas turbine engine component
WO2017040111A1 (en) * 2015-08-28 2017-03-09 Praxair S.T. Technology, Inc. Novel mask formulation to prevent aluminizing onto the pre-existing chromide coating
EP3293281A1 (en) * 2016-09-13 2018-03-14 General Electric Company Process for forming diffusion coating on substrate
US9970094B2 (en) 2014-01-14 2018-05-15 Praxair S.T. Technology, Inc. Modified slurry compositions for forming improved chromium diffusion coatings
DE102017213553A1 (en) * 2017-08-04 2019-02-07 MTU Aero Engines AG VESSEL FOR FLOW MACHINE WITH VARIOUS DIFFUSION PROTECTION LAYERS AND METHOD OF MANUFACTURING THEREOF
CN110923621A (en) * 2019-10-31 2020-03-27 中国航发南方工业有限公司 Protective coating for aluminum-chromium co-infiltration and preparation method and application thereof
EP3475459B1 (en) * 2016-06-22 2024-01-24 General Electric Technology GmbH Coating process for applying a bifurcated coating

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Cited By (38)

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Publication number Priority date Publication date Assignee Title
GB2421032A (en) * 2004-12-11 2006-06-14 Siemens Ind Turbomachinery Ltd A method of protecting a component against hot corrosion
US7998600B2 (en) 2005-10-07 2011-08-16 Siemens Aktiengesellschaft Dry composition, its use, layer system and coating process
EP1772529A1 (en) * 2005-10-07 2007-04-11 Siemens Aktiengesellschaft Dry chemical composition, use thereof to form a layer system and method for coating
WO2007042392A1 (en) * 2005-10-07 2007-04-19 Siemens Aktiengesellschaft Dry composition, use of its layer system and coating process
DE102005060243A1 (en) * 2005-12-14 2007-06-21 Man Turbo Ag Process for coating hollow internally cooled gas turbine blades with adhesive-, zirconium oxide ceramic- and Cr diffusion layers useful in gas turbine engine technology has adhesive layer applied by plasma or high rate spraying method
US8277195B2 (en) * 2006-06-08 2012-10-02 Siemens Aktiengesellschaft Coated turbine component and method of coating a turbine component
US20090263237A1 (en) * 2006-06-08 2009-10-22 Paul Box Coated turbine component and method of coating a turbine component
WO2007147387A2 (en) * 2006-06-20 2007-12-27 Mtu Aero Engines Gmbh Method of repairing intake coatings
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WO2007147708A2 (en) * 2006-06-24 2007-12-27 Siemens Aktiengesellschaft Method of protecting a component against hot corrosion and a component protected by said method
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WO2007147708A3 (en) * 2006-06-24 2008-03-27 Siemens Ag Method of protecting a component against hot corrosion and a component protected by said method
US8596985B2 (en) 2006-06-24 2013-12-03 Siemens Aktiengesellschaft Method of protecting a component against hot corrosion and a component protected by said method
GB2439313A (en) * 2006-06-24 2007-12-27 Siemens Ag Protecting components against hot corrosion using sequential chromium diffusion coatings and ceramic coatings
CN102161029A (en) * 2010-02-12 2011-08-24 西门子公司 Overspray shielding device and method
US20160010472A1 (en) * 2012-02-21 2016-01-14 Howment Corporation Coating and coating method for gas turbine engine component
EP2631325A3 (en) * 2012-02-21 2017-08-09 Howmet Corporation Coating and coating method for gas turbine component
EP2778251A1 (en) * 2013-03-13 2014-09-17 Howmet Corporation A maskant for use in aluminizing a turbine component
JP2014224305A (en) * 2013-03-13 2014-12-04 ハウメット コーポレイションＨｏｗｍｅｔ Ｃｏｒｐｏｒａｔｉｏｎ Maskant used for aluminizing turbine component
US10113225B2 (en) 2013-03-13 2018-10-30 Howmet Corporation Maskant for use in aluminizing a turbine component
WO2015108766A1 (en) * 2014-01-14 2015-07-23 Praxair S.T. Technology, Inc. Methods of applying chromium diffusion coatings onto selective regions of a component
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EP3094759A1 (en) * 2014-01-14 2016-11-23 Praxair S.T. Technology, Inc. Methods of applying chromium diffusion coatings onto selective regions of a component
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