US20140272166A1 - Coating system for improved leading edge erosion protection - Google Patents
Coating system for improved leading edge erosion protection Download PDFInfo
- Publication number
- US20140272166A1 US20140272166A1 US14/099,658 US201314099658A US2014272166A1 US 20140272166 A1 US20140272166 A1 US 20140272166A1 US 201314099658 A US201314099658 A US 201314099658A US 2014272166 A1 US2014272166 A1 US 2014272166A1
- Authority
- US
- United States
- Prior art keywords
- coating
- leading edge
- airfoil
- chrome
- coating layer
- 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
-
- 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
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
-
- 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
- C23C24/00—Coating starting from inorganic powder
- C23C24/02—Coating starting from inorganic powder by application of pressure only
- C23C24/04—Impact or kinetic deposition of particles
-
- 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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/04—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings of inorganic non-metallic material
- C23C28/042—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings of inorganic non-metallic material including a refractory ceramic layer, e.g. refractory metal oxides, ZrO2, rare earth oxides
-
- 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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/04—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings of inorganic non-metallic material
- C23C28/044—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings of inorganic non-metallic material coatings specially adapted for cutting tools or wear applications
-
- 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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
- C23C28/322—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer only coatings of metal elements only
-
- 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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
- C23C28/324—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal matrix material layer comprising a mixture of at least two metals or metal phases or a metal-matrix material with hard embedded particles, e.g. WC-Me
-
- 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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
- C23C28/343—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one DLC or an amorphous carbon based layer, the layer being doped or not
-
- 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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
- C23C28/347—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with layers adapted for cutting tools or wear applications
-
- 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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/40—Coatings including alternating layers following a pattern, a periodic or defined repetition
- C23C28/44—Coatings including alternating layers following a pattern, a periodic or defined repetition characterized by a measurable physical property of the alternating layer or system, e.g. thickness, density, hardness
-
- 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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
-
- 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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/02—Selection of particular materials
- F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/324—Blades
-
- 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
- F05D2230/31—Layer deposition
-
- 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
- F05D2230/90—Coating; Surface treatment
-
- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/22—Non-oxide ceramics
- F05D2300/226—Carbides
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/22—Non-oxide ceramics
- F05D2300/226—Carbides
- F05D2300/2263—Carbides of tungsten, e.g. WC
Definitions
- the present disclosure relates generally to coatings, and more specifically to coating systems to reduce erosion and corrosion in gas turbine engines.
- Gas turbine engines are used to power aircraft, watercraft, power generators, and the like.
- Gas turbine engines typically include a compressor, a combustor, and a turbine.
- the compressors and turbine of the turbine engine can include turbine disks or turbine shafts, as well as a number of blades mounted to the turbine disks/shafts that extend radially outwardly therefrom into the gas flow path.
- Also included in the turbine engine are rotating, as well as static, seal elements that channel the airflow used for cooling certain components such as turbine blades and vanes. The airflow channeled by these rotating, as well as static, seal elements carry corrodant deposits to the turbine blades. As the maximum operating temperature of the turbine engine increases, the turbine blades are subjected to higher temperatures. Debris entering the engine can present issues for the compressor and other components.
- Alkaline sulfate, sulfites, chlorides, carbonates, oxides, and other corrodant salt deposits can be sources of erosion and corrosion.
- ingested dirt, fly ash, volcanic ash, concrete dust, sand, sea salt, etc. are a major source of erosion. This can lead to failure or premature removal and replacement of the compressor blades unless the damage is reduced or repaired.
- Conventional plasma vapor deposition (PVD) processes such as cathodic arc and E-beam PVD are widely used methods for depositing erosion resistant coatings on the airfoils of compressor blades and vanes.
- PVD processes such as cathodic arc and E-beam PVD typically introduce high residual stress on the leading edge of the compressor airfoils during the coating process.
- high residual stress from the coating process is coupled with out-of-plane stress from the leading edge geometry and thermal expansion mismatch between coating and substrate, it can result in coating spallation in the as-coated condition providing insufficient leading edge erosion protection.
- Coating methods and coating compositions for compressor blades and vanes that provide high angle solid particle erosion protection on the leading edge of compressor airfoils are desired.
- Coating methods and coating compositions that also provide lower angle solid particle erosion protection on the concave and convex sides of the airfoils are desired.
- a coating system in accordance with the present disclosure may include the application of an erosion resistant coating to a portion of a gas turbine engine blade.
- the coating may be applied to a preselected exterior surface of the airfoil blades.
- the coating may be applied to the leading edge surface of the airfoil to increase the erosion resistance of the leading edge.
- the coating may also be applied to the concave side surface, the convex side surface, or combinations thereof.
- the coating may be formed from tungsten-tungsten carbide, tungsten carbide cobalt, cobalt-chrome-tungsten carbide, chrome carbide-nickel, chrome carbide-nickel-chrome, or a diamond like carbon material.
- the process may also include a metallic bond coat layer positioned between the coating and the surface of the airfoil.
- the surface of the airfoil may also be nitrided or carburized before the application of the coating.
- the coating may be applied to the airfoil using high velocity oxygen fuel spray, high velocity air fuel spray, solution plasma spray, cold spray, chemical vapor deposition, electo spark deposition, plasma enhanced chemical vapor deposition, or air plasma spray method.
- FIG. 1 is a perspective view of a turbine with portions broken away to show the vanes within the turbine;
- FIG. 2 is a perspective view of a vane segment showing a series of airfoils
- FIG. 2A is a perspective view of a series of compressor blades with each compressor including an airfoil;
- FIG. 3 is a sectional view taken along lines 3 - 3 of FIG. 2 showing an airfoil having the coating of the present disclosure formed on the leading edge of the airfoil;
- FIG. 4 is a sectional view of an airfoil having the coating of the present disclosure formed on a surface of the leading edge of the airfoil;
- FIG. 5 is a sectional view of an airfoil having the coating of the present disclosure formed on the leading edge and concave side of the airfoil;
- FIG. 6 is a sectional view of an airfoil having the coating of the present disclosure formed on the leading edge and the concave and convex sides of the airfoil;
- FIG. 7 is a sectional view of an airfoil having the coating of the present disclosure formed on the leading edge on an airfoil that has been nitrided or carburized and treated with a metallic bond coat layer.
- FIG. 8 is a photograph of an airfoil sample showing erosion of the leading edge of the airfoil due to sand ingestion
- FIG. 9 is a photograph of another airfoil sample showing erosion to the leading edge of the airfoil.
- FIG. 10 includes photographs of test samples showing erosion of the leading edge of airfoil samples.
- the present disclosure is directed to a coating system that provides an enhanced airfoil 14 including leading edge erosion protection for a turbine 11 , as shown in FIGS. 1-2A . More particularly, the present disclosure is directed to one or more coatings that provide enhanced high angle solid particle erosion protection on compressor airfoils 14 , as shown, for example, in FIGS. 3-7 .
- the coating is primarily applied to the leading edge 12 of the airfoils 14 , as shown in FIGS. 3 , 4 , and 7 .
- the coating(s) may also provide low angle solid particle erosion protection on the concave 16 and convex 18 sides of the airfoils 14 , as shown in FIGS. 5 and 6 .
- the coating 31 for example, formed on the leading edge 12 of the airfoils 14 is selected from group consisting of tungsten-tungsten carbide, tungsten carbide cobalt, cobalt-chrome-tungsten carbide, chrome carbide-nickel, chrome carbide-nickel-chrome, and diamond like carbon.
- the coating 31 on the leading edge 12 is preferably applied by use of a high velocity oxygen fuel (HVOF) spray, a high velocity air fuel (HVAF) spray, a solution plasma spray, a cold spray, chemical vapor deposition (CVD), electro spark deposition, plasma enhanced chemical vapor deposition (PE-CVD), or air plasma spray method.
- HVOF high velocity oxygen fuel
- HVAC high velocity air fuel
- CVD chemical vapor deposition
- PE-CVD electro spark deposition
- PE-CVD plasma enhanced chemical vapor deposition
- airfoil 14 may have first coating 31 applied to leading edge 12 while a second coating 32 is applied to both concave surface 16 and convex surface 18 as shown in FIG. 3 .
- airfoil 14 may have first coating 31 applied to leading edge 12 while second coating 132 is applied over first coating and on both concave and convex surfaces 16 and 18 as shown in FIG. 4 .
- airfoil 14 may have a coating 231 applied to both leading edge 12 and concave surface 16 while omitting any coating on convex surface 18 as shown in FIG. 5 .
- airfoil 14 may have a coating 331 applied to leading edge 12 , concave surface 16 , and convex surface 18 as shown in FIG. 6 .
- airfoil 14 may have a first coating 431 applied to leading edge 12 , concave surface 16 , and convex surface 18 and a second coating 432 applied over first coating 431 at leading edge 12 .
- airfoil 14 may have a first coating applied to leading edge 12 , a second coating applied to concave surface 16 , and a third coating applied to convex surface 18 .
- the first, second, and third coatings may be all the same, all different, or any suitable combination thereof.
- first coating may be applied to leading edge 12 , concave surface 16 , and convex surface 18 .
- One or more coatings may be applied over the first coating on one or more of the leading edge 12 , concave surface 16 , and convex surface 18 .
- the first coating may be the same or different than the one or more coatings.
- the coatings 31 , 32 , 132 , 231 , 331 , 431 , 432 discussed previously are selected from the group consisting of TiAlN, AlTiN, TiAlN/TiN multilayer, TiAlN/Cr multilayer, tungsten-tungsten carbide, tungsten carbide cobalt, cobalt-chrome-tungsten carbide, chrome carbide-nickel, chrome carbide-nickel-chrome, and diamond like carbon.
- the coatings 31 , 32 , 132 , 231 , 331 , 431 , 432 may be applied by applied by PVD, HVOF, HVAF, solution plasma spray, cold spray, CVD, electro spark deposition, or PE-CVD.
- PVD processes such as cathodic arc and E-beam PVD are widely used methods for depositing erosion resistant coatings.
- PVD processes such as cathodic arc and E-beam PVD typically introduce high residual stress on the leading edge of the compressor airfoils during the coating process.
- high residual stress from the coating process is coupled with out-of-plane stress from the leading edge geometry and thermal expansion mismatch between coating and substrate, it can result in coating spallation in the as-coated condition and insufficient leading edge erosion protection during engine operation.
- Coatings applied by HVOF, HVAF, solution plasma spray, cold spray, CVD, electro spark deposition, and PE-CVD can introduce lower residual stresses on the leading edge 12 of the compressor airfoil 14 when the right coating materials are used, which leads to better high angle solid particle erosion protection on the leading edge 12 .
- a powder size less than 50 ⁇ m is used normally to obtain a smooth surface finish.
- the powder size is preferably smaller than 20 ⁇ m to obtain the desired finish on the airfoil 14 .
- Ni, Ti, Cr, or other metallic bond coat layers 24 can be used between the coatings and the airfoil 14 .
- the surface of the airfoil 14 can be nitrided and carburized 431 before the application of the coating 432 to improve corrosion and erosion resistance, as shown, for example, in FIG. 7 .
- the thickness of the coating 31 , 231 , 331 , 432 on the leading edge 12 is from about 10 ⁇ m to about 100 ⁇ m. In another example, the thickness of the coating 31 , 231 , 331 , 432 on the leading edge 12 is from about 35 ⁇ m to about 75 ⁇ m.
- the thickness of the coating 32 , 132 , 231 , 331 on the concave 16 and convex side 18 is from about 5 ⁇ m to about 50 ⁇ m. In another example, the thickness of the coating 32 , 132 , 231 , 331 on the concave 16 and convex 18 sides is from about 15 ⁇ m to about 35 ⁇ m.
- the thickness of the metallic bond coat layer 431 is from about 2.5 ⁇ m to about 10 ⁇ m.
- the nitrided or carburized depth on the airfoil 14 is from about 10 ⁇ m to about 50 ⁇ m.
- FIG. 8 is a photograph of an airfoil sample showing erosion of the leading edge of the airfoil due to sand ingestion.
- the leading edge 12 of the airfoil 14 was coated with TiN applied by cathodic arc physical vapor deposition (PVD).
- PVD cathodic arc physical vapor deposition
- LPER Leading Edge Preferential Erosion
- FIG. 9 Another airfoil sample showing erosion to the leading edge of the airfoil is shown in FIG. 9 .
- the leading edge 12 of the airfoil 14 was treated with TiAlN applied by cathodic arc physical vapor deposition (PVD).
- PVD cathodic arc physical vapor deposition
- FIG. 10 A series of photographs of erosion test result samples are shown in FIG. 10 from testing performed by the University of Cincinnati. In these tests, the leading edges of the airfoil samples were subjected to a particulate applied in a series of stages. In the first stage, 0.995 Kg of 95% Arizona Road Dust (ARD) A4 (silica based sand with 80 ⁇ m nominal diameter) with 5% Mil E-5007C crushed quartz (75 ⁇ 100 ⁇ m) was used. The photographs taken at stage one indicate the amount of erosion that has occurred to the leading edge of the test samples. The samples were subjected to multiple stages of erosion testing including a ninth stage where 1.1 Kg of ARD A4 was used. The photographs taken at stage nine indicate the amount of erosion that occurred to the leading edge of the test samples.
- ARD Arizona Road Dust
- the tungsten carbide tungsten (WC/W) sample applied with the chemical vapor deposition (CVD) method shows a clean edge with no erosion.
- the coating microstructure is tungsten carbide (WC) particles dispersed in tungsten (W).
Abstract
A gas turbine engine includes airfoils. At least a portion of the airfoils are coated with a coating that provides for erosion and corrosion protection for the portion of the airfoils.
Description
- This application claims priority to and the benefit of U.S. Provisional Patent Application No. 61/779,722, filed 13 Mar. 2013, the disclosure of which is now incorporated herein by reference.
- The present disclosure relates generally to coatings, and more specifically to coating systems to reduce erosion and corrosion in gas turbine engines.
- Gas turbine engines are used to power aircraft, watercraft, power generators, and the like. Gas turbine engines typically include a compressor, a combustor, and a turbine. The compressors and turbine of the turbine engine can include turbine disks or turbine shafts, as well as a number of blades mounted to the turbine disks/shafts that extend radially outwardly therefrom into the gas flow path. Also included in the turbine engine are rotating, as well as static, seal elements that channel the airflow used for cooling certain components such as turbine blades and vanes. The airflow channeled by these rotating, as well as static, seal elements carry corrodant deposits to the turbine blades. As the maximum operating temperature of the turbine engine increases, the turbine blades are subjected to higher temperatures. Debris entering the engine can present issues for the compressor and other components.
- Alkaline sulfate, sulfites, chlorides, carbonates, oxides, and other corrodant salt deposits can be sources of erosion and corrosion. In addition, ingested dirt, fly ash, volcanic ash, concrete dust, sand, sea salt, etc. are a major source of erosion. This can lead to failure or premature removal and replacement of the compressor blades unless the damage is reduced or repaired. Conventional plasma vapor deposition (PVD) processes such as cathodic arc and E-beam PVD are widely used methods for depositing erosion resistant coatings on the airfoils of compressor blades and vanes. However, PVD processes such as cathodic arc and E-beam PVD typically introduce high residual stress on the leading edge of the compressor airfoils during the coating process. When high residual stress from the coating process is coupled with out-of-plane stress from the leading edge geometry and thermal expansion mismatch between coating and substrate, it can result in coating spallation in the as-coated condition providing insufficient leading edge erosion protection.
- Coating methods and coating compositions for compressor blades and vanes that provide high angle solid particle erosion protection on the leading edge of compressor airfoils are desired. Coating methods and coating compositions that also provide lower angle solid particle erosion protection on the concave and convex sides of the airfoils are desired.
- The present application discloses one or more of the features recited in the appended claims and/or the following features which, alone or in any combination, may comprise patentable subject matter.
- A coating system in accordance with the present disclosure may include the application of an erosion resistant coating to a portion of a gas turbine engine blade. In some embodiments, the coating may be applied to a preselected exterior surface of the airfoil blades. The coating may be applied to the leading edge surface of the airfoil to increase the erosion resistance of the leading edge. The coating may also be applied to the concave side surface, the convex side surface, or combinations thereof.
- In some embodiments, the coating may be formed from tungsten-tungsten carbide, tungsten carbide cobalt, cobalt-chrome-tungsten carbide, chrome carbide-nickel, chrome carbide-nickel-chrome, or a diamond like carbon material. The process may also include a metallic bond coat layer positioned between the coating and the surface of the airfoil. The surface of the airfoil may also be nitrided or carburized before the application of the coating.
- In some embodiments, the coating may be applied to the airfoil using high velocity oxygen fuel spray, high velocity air fuel spray, solution plasma spray, cold spray, chemical vapor deposition, electo spark deposition, plasma enhanced chemical vapor deposition, or air plasma spray method.
- These and other features of the present disclosure will become more apparent from the following description of the illustrative embodiments.
-
FIG. 1 is a perspective view of a turbine with portions broken away to show the vanes within the turbine; -
FIG. 2 is a perspective view of a vane segment showing a series of airfoils; -
FIG. 2A is a perspective view of a series of compressor blades with each compressor including an airfoil; -
FIG. 3 is a sectional view taken along lines 3-3 ofFIG. 2 showing an airfoil having the coating of the present disclosure formed on the leading edge of the airfoil; -
FIG. 4 is a sectional view of an airfoil having the coating of the present disclosure formed on a surface of the leading edge of the airfoil; -
FIG. 5 is a sectional view of an airfoil having the coating of the present disclosure formed on the leading edge and concave side of the airfoil; -
FIG. 6 is a sectional view of an airfoil having the coating of the present disclosure formed on the leading edge and the concave and convex sides of the airfoil; -
FIG. 7 is a sectional view of an airfoil having the coating of the present disclosure formed on the leading edge on an airfoil that has been nitrided or carburized and treated with a metallic bond coat layer. -
FIG. 8 is a photograph of an airfoil sample showing erosion of the leading edge of the airfoil due to sand ingestion; -
FIG. 9 is a photograph of another airfoil sample showing erosion to the leading edge of the airfoil; and -
FIG. 10 includes photographs of test samples showing erosion of the leading edge of airfoil samples. - For the purposes of promoting an understanding of the principles of the disclosure, reference will now be made to a number of illustrative embodiments illustrated in the drawings and specific language will be used to describe the same.
- The present disclosure is directed to a coating system that provides an enhanced
airfoil 14 including leading edge erosion protection for a turbine 11, as shown inFIGS. 1-2A . More particularly, the present disclosure is directed to one or more coatings that provide enhanced high angle solid particle erosion protection oncompressor airfoils 14, as shown, for example, inFIGS. 3-7 . The coating is primarily applied to the leadingedge 12 of theairfoils 14, as shown inFIGS. 3 , 4, and 7. The coating(s) may also provide low angle solid particle erosion protection on the concave 16 and convex 18 sides of theairfoils 14, as shown inFIGS. 5 and 6 . - The
coating 31, for example, formed on the leadingedge 12 of theairfoils 14 is selected from group consisting of tungsten-tungsten carbide, tungsten carbide cobalt, cobalt-chrome-tungsten carbide, chrome carbide-nickel, chrome carbide-nickel-chrome, and diamond like carbon. Thecoating 31 on the leadingedge 12 is preferably applied by use of a high velocity oxygen fuel (HVOF) spray, a high velocity air fuel (HVAF) spray, a solution plasma spray, a cold spray, chemical vapor deposition (CVD), electro spark deposition, plasma enhanced chemical vapor deposition (PE-CVD), or air plasma spray method. By applying thecoating 31 primarily to the leadingedge 12, weight increase of theairfoils 14 is minimized. Thecoating 31 also provides increased corrosion resistance. - In one illustrative embodiment,
airfoil 14 may havefirst coating 31 applied to leadingedge 12 while asecond coating 32 is applied to bothconcave surface 16 and convexsurface 18 as shown inFIG. 3 . In another illustrative embodiment,airfoil 14 may havefirst coating 31 applied to leadingedge 12 whilesecond coating 132 is applied over first coating and on both concave andconvex surfaces FIG. 4 . In still yet another illustrative example,airfoil 14 may have acoating 231 applied to both leadingedge 12 andconcave surface 16 while omitting any coating onconvex surface 18 as shown inFIG. 5 . In another illustrative embodiment,airfoil 14 may have acoating 331 applied to leadingedge 12,concave surface 16, and convexsurface 18 as shown inFIG. 6 . In still yet another illustrative example,airfoil 14 may have afirst coating 431 applied to leadingedge 12,concave surface 16, and convexsurface 18 and asecond coating 432 applied overfirst coating 431 at leadingedge 12. - In still yet another example,
airfoil 14 may have a first coating applied to leadingedge 12, a second coating applied toconcave surface 16, and a third coating applied to convexsurface 18. The first, second, and third coatings may be all the same, all different, or any suitable combination thereof. - In addition, the first coating may be applied to leading
edge 12,concave surface 16, and convexsurface 18. One or more coatings may be applied over the first coating on one or more of the leadingedge 12,concave surface 16, and convexsurface 18. In some examples, the first coating may be the same or different than the one or more coatings. - The
coatings coatings - Conventional PVD processes such as cathodic arc and E-beam PVD are widely used methods for depositing erosion resistant coatings. However, PVD processes such as cathodic arc and E-beam PVD typically introduce high residual stress on the leading edge of the compressor airfoils during the coating process. When high residual stress from the coating process is coupled with out-of-plane stress from the leading edge geometry and thermal expansion mismatch between coating and substrate, it can result in coating spallation in the as-coated condition and insufficient leading edge erosion protection during engine operation. Coatings applied by HVOF, HVAF, solution plasma spray, cold spray, CVD, electro spark deposition, and PE-CVD can introduce lower residual stresses on the leading
edge 12 of thecompressor airfoil 14 when the right coating materials are used, which leads to better high angle solid particle erosion protection on the leadingedge 12. - If coating spray methods such as HVOF, HVAF, solution plasma spray, and cold spray are used, a powder size less than 50 μm is used normally to obtain a smooth surface finish. The powder size is preferably smaller than 20 μm to obtain the desired finish on the
airfoil 14. For both theleading edge coatings 12 and the convex 18 and the concave 16 side coatings, Ni, Ti, Cr, or other metallic bond coat layers 24 can be used between the coatings and theairfoil 14. The surface of theairfoil 14 can be nitrided and carburized 431 before the application of thecoating 432 to improve corrosion and erosion resistance, as shown, for example, inFIG. 7 . - In one example, the thickness of the
coating edge 12 is from about 10 μm to about 100 μm. In another example, the thickness of thecoating edge 12 is from about 35 μm to about 75 μm. The thickness of thecoating convex side 18, for example, is from about 5 μm to about 50 μm. In another example, the thickness of thecoating bond coat layer 431, for example, is from about 2.5 μm to about 10 μm. The nitrided or carburized depth on theairfoil 14, for example, is from about 10 μm to about 50 μm. -
FIG. 8 is a photograph of an airfoil sample showing erosion of the leading edge of the airfoil due to sand ingestion. In this photograph, the leadingedge 12 of theairfoil 14 was coated with TiN applied by cathodic arc physical vapor deposition (PVD). As can be seen the Leading Edge Preferential Erosion (LEPER) is present and is detrimental to gas turbine performance. Another airfoil sample showing erosion to the leading edge of the airfoil is shown inFIG. 9 . The leadingedge 12 of theairfoil 14 was treated with TiAlN applied by cathodic arc physical vapor deposition (PVD). As can be seen, Leading Edge Preferential Erosion (LEPER) is present in the edge of the airfoil. - A series of photographs of erosion test result samples are shown in
FIG. 10 from testing performed by the University of Cincinnati. In these tests, the leading edges of the airfoil samples were subjected to a particulate applied in a series of stages. In the first stage, 0.995 Kg of 95% Arizona Road Dust (ARD) A4 (silica based sand with 80 μm nominal diameter) with 5% Mil E-5007C crushed quartz (75˜100 μm) was used. The photographs taken at stage one indicate the amount of erosion that has occurred to the leading edge of the test samples. The samples were subjected to multiple stages of erosion testing including a ninth stage where 1.1 Kg of ARD A4 was used. The photographs taken at stage nine indicate the amount of erosion that occurred to the leading edge of the test samples. As can be seen, the tungsten carbide tungsten (WC/W) sample applied with the chemical vapor deposition (CVD) method shows a clean edge with no erosion. The coating microstructure is tungsten carbide (WC) particles dispersed in tungsten (W). - While the disclosure has been illustrated and described in detail in the foregoing drawings and description, the same is to be considered as exemplary and not restrictive in character, it being understood that only illustrative embodiments thereof have been shown and described and that all changes and modifications that come within the spirit of the disclosure are desired to be protected.
Claims (13)
1. A method for coating a portion of a gas turbine engine blade, the method comprising the steps of
providing a gas turbine blade, the blade further comprising an airfoil section having an exterior surface and
applying a coating layer to a preselected exterior surface selected from the group consisting of the leading edge surface, the concave side surface, the convex side, and combinations thereof, the coating layer selected from the group consisting of tungsten-tungsten carbide, tungsten carbide cobalt, cobalt-chrome-tungsten carbide, chrome carbide-nickel, chrome carbide-nickel-chrome, and diamond like carbon,
wherein the coating layer at the leading edge surface has a thickness from about 10 μm to about 100 μm.
2. The method of claim 1 , wherein the coating layer at the leading edge surface has a thickness from about 35 μm to about 75 μm.
3. The method of claim 2 , wherein the coating layer at the concave and convex surfaces is from about 5 μm to about 50 μm.
4. The method of claim 1 , further including the step of applying a metallic bond coat layer to the exterior surface of the airfoil before the coating layer.
5. The method of claim 4 , wherein the metallic bond coat layer has a thickness from about 2.5 μm to about 10 μm.
6. The method of claim 5 , wherein the metallic bond coat layer is selected from the group consisting of Ni, Ti, and Cr.
7. The method of claim 1 , further including the step of nitriding the surface of the airfoil.
8. The method of claim 7 , wherein the nitrided depth is from about 10 μm to about 50 μm.
9. The method of claim 1 , further including the step of carburizing the surface of the airfoil.
10. The method of claim 9 , wherein the carburized depth is from about 10 μm to about 50 μm.
11. The method of claim 1 , wherein the coating is applied using coating spray methods from the group consisting of HVOF, HVAF, solution plasma spray, electo spark deposition, and cold spray.
12. The method of claim 11 , wherein the coating powder size is less than 50 μm.
13. The method of claim 12 , wherein the powder size is less than 20 μm.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/099,658 US20140272166A1 (en) | 2013-03-13 | 2013-12-06 | Coating system for improved leading edge erosion protection |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US201361779722P | 2013-03-13 | 2013-03-13 | |
US14/099,658 US20140272166A1 (en) | 2013-03-13 | 2013-12-06 | Coating system for improved leading edge erosion protection |
Publications (1)
Publication Number | Publication Date |
---|---|
US20140272166A1 true US20140272166A1 (en) | 2014-09-18 |
Family
ID=49883244
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/099,658 Abandoned US20140272166A1 (en) | 2013-03-13 | 2013-12-06 | Coating system for improved leading edge erosion protection |
Country Status (2)
Country | Link |
---|---|
US (1) | US20140272166A1 (en) |
WO (1) | WO2014143244A1 (en) |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2017009295A1 (en) * | 2015-07-13 | 2017-01-19 | Nuovo Pignone Tecnologie Srl | Turbomachine blade with protective structure, turbomachine, and method of forming a protective structure |
EP3470680A1 (en) * | 2017-10-16 | 2019-04-17 | OneSubsea IP UK Limited | Erosion resistant blades for compressors |
US10304665B2 (en) | 2011-09-07 | 2019-05-28 | Nano-Product Engineering, LLC | Reactors for plasma-assisted processes and associated methods |
EP3889393A1 (en) * | 2020-03-31 | 2021-10-06 | General Electric Company | Turbomachine airfoil having a variable thickness thermal barrier coating |
US20210402482A1 (en) * | 2020-06-25 | 2021-12-30 | U.S. Army DEVCOM, Army Research Laboratory | Controlling cold spray deposition adhesion for induced substrate release |
US11286794B2 (en) * | 2019-12-17 | 2022-03-29 | Rolls-Royce North American Technologies, Inc. | Erosion-resistant coating with patterned leading edge |
US11441545B2 (en) | 2020-02-25 | 2022-09-13 | General Electric Company | Tungsten-based erosion-resistant leading edge protection cap for rotor blades |
US11662300B2 (en) | 2019-09-19 | 2023-05-30 | Westinghouse Electric Company Llc | Apparatus for performing in-situ adhesion test of cold spray deposits and method of employing |
US11795830B2 (en) | 2017-11-02 | 2023-10-24 | Hardide Plc | Water droplet erosion resistant coatings for turbine blades and other components |
US11898986B2 (en) | 2012-10-10 | 2024-02-13 | Westinghouse Electric Company Llc | Systems and methods for steam generator tube analysis for detection of tube degradation |
US11935662B2 (en) | 2019-07-02 | 2024-03-19 | Westinghouse Electric Company Llc | Elongate SiC fuel elements |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5439354A (en) * | 1993-06-15 | 1995-08-08 | General Electric Company | Hollow airfoil impact resistance improvement |
US5891267A (en) * | 1997-01-16 | 1999-04-06 | General Electric Company | Thermal barrier coating system and method therefor |
US6242050B1 (en) * | 1998-11-24 | 2001-06-05 | General Electric Company | Method for producing a roughened bond coat using a slurry |
US6447932B1 (en) * | 2000-03-29 | 2002-09-10 | General Electric Company | Substrate stabilization of superalloys protected by an aluminum-rich coating |
US20060165517A1 (en) * | 2005-01-27 | 2006-07-27 | Snecma | Method for repairing a rubbing surface of a turbomachine variable-pitch blade |
US20060257663A1 (en) * | 2003-03-03 | 2006-11-16 | Doll Gary L | Wear resistant coatings to reduce ice adhesion on air foils |
US20100226783A1 (en) * | 2009-03-06 | 2010-09-09 | General Electric Company | Erosion and Corrosion Resistant Turbine Compressor Airfoil and Method of Making the Same |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4741975A (en) * | 1984-11-19 | 1988-05-03 | Avco Corporation | Erosion-resistant coating system |
US8118561B2 (en) * | 2004-07-26 | 2012-02-21 | General Electric Company | Erosion- and impact-resistant coatings |
US20060051502A1 (en) * | 2004-09-08 | 2006-03-09 | Yiping Hu | Methods for applying abrasive and environment-resistant coatings onto turbine components |
US8123872B2 (en) * | 2006-02-22 | 2012-02-28 | General Electric Company | Carburization process for stabilizing nickel-based superalloys |
US20100304107A1 (en) * | 2009-05-27 | 2010-12-02 | United Technologies Corporation | Layered coating for erosion protection |
US20110052406A1 (en) * | 2009-08-25 | 2011-03-03 | General Electric Company | Airfoil and process for depositing an erosion-resistant coating on the airfoil |
-
2013
- 2013-12-06 US US14/099,658 patent/US20140272166A1/en not_active Abandoned
- 2013-12-06 WO PCT/US2013/073575 patent/WO2014143244A1/en active Application Filing
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5439354A (en) * | 1993-06-15 | 1995-08-08 | General Electric Company | Hollow airfoil impact resistance improvement |
US5891267A (en) * | 1997-01-16 | 1999-04-06 | General Electric Company | Thermal barrier coating system and method therefor |
US6242050B1 (en) * | 1998-11-24 | 2001-06-05 | General Electric Company | Method for producing a roughened bond coat using a slurry |
US6447932B1 (en) * | 2000-03-29 | 2002-09-10 | General Electric Company | Substrate stabilization of superalloys protected by an aluminum-rich coating |
US20060257663A1 (en) * | 2003-03-03 | 2006-11-16 | Doll Gary L | Wear resistant coatings to reduce ice adhesion on air foils |
US20060165517A1 (en) * | 2005-01-27 | 2006-07-27 | Snecma | Method for repairing a rubbing surface of a turbomachine variable-pitch blade |
US20100226783A1 (en) * | 2009-03-06 | 2010-09-09 | General Electric Company | Erosion and Corrosion Resistant Turbine Compressor Airfoil and Method of Making the Same |
Cited By (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10304665B2 (en) | 2011-09-07 | 2019-05-28 | Nano-Product Engineering, LLC | Reactors for plasma-assisted processes and associated methods |
US10679829B1 (en) | 2011-09-07 | 2020-06-09 | Nano-Product Engineering, LLC | Reactors and methods for making diamond coatings |
US11898986B2 (en) | 2012-10-10 | 2024-02-13 | Westinghouse Electric Company Llc | Systems and methods for steam generator tube analysis for detection of tube degradation |
JP2018527500A (en) * | 2015-07-13 | 2018-09-20 | ヌオーヴォ・ピニォーネ・テクノロジー・ソチエタ・レスポンサビリタ・リミタータNuovo Pignone Tecnologie S.R.L. | Turbomachine blade with protective structure, turbomachine, and method of forming protective structure |
WO2017009295A1 (en) * | 2015-07-13 | 2017-01-19 | Nuovo Pignone Tecnologie Srl | Turbomachine blade with protective structure, turbomachine, and method of forming a protective structure |
EP3470680A1 (en) * | 2017-10-16 | 2019-04-17 | OneSubsea IP UK Limited | Erosion resistant blades for compressors |
US10914183B2 (en) | 2017-10-16 | 2021-02-09 | Onesubsea Ip Uk Limited | Erosion resistant blades for compressors |
US11795830B2 (en) | 2017-11-02 | 2023-10-24 | Hardide Plc | Water droplet erosion resistant coatings for turbine blades and other components |
US11935662B2 (en) | 2019-07-02 | 2024-03-19 | Westinghouse Electric Company Llc | Elongate SiC fuel elements |
US11662300B2 (en) | 2019-09-19 | 2023-05-30 | Westinghouse Electric Company Llc | Apparatus for performing in-situ adhesion test of cold spray deposits and method of employing |
US11286794B2 (en) * | 2019-12-17 | 2022-03-29 | Rolls-Royce North American Technologies, Inc. | Erosion-resistant coating with patterned leading edge |
US11441545B2 (en) | 2020-02-25 | 2022-09-13 | General Electric Company | Tungsten-based erosion-resistant leading edge protection cap for rotor blades |
US11629603B2 (en) * | 2020-03-31 | 2023-04-18 | General Electric Company | Turbomachine airfoil having a variable thickness thermal barrier coating |
EP3889393A1 (en) * | 2020-03-31 | 2021-10-06 | General Electric Company | Turbomachine airfoil having a variable thickness thermal barrier coating |
US20210402482A1 (en) * | 2020-06-25 | 2021-12-30 | U.S. Army DEVCOM, Army Research Laboratory | Controlling cold spray deposition adhesion for induced substrate release |
Also Published As
Publication number | Publication date |
---|---|
WO2014143244A1 (en) | 2014-09-18 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US20140272166A1 (en) | Coating system for improved leading edge erosion protection | |
US11859499B2 (en) | Turbine clearance control coatings and method | |
US9926794B2 (en) | Turbine blade tip treatment for industrial gas turbines | |
US4936745A (en) | Thin abradable ceramic air seal | |
US9581041B2 (en) | Abradable ceramic coatings and coating systems | |
US7666515B2 (en) | Turbine component other than airfoil having ceramic corrosion resistant coating and methods for making same | |
US9109279B2 (en) | Method for coating a blade and blade of a gas turbine | |
US20140301861A1 (en) | Airfoil having an erosion-resistant coating thereon | |
US7294413B2 (en) | Substrate protected by superalloy bond coat system and microcracked thermal barrier coating | |
US10273822B2 (en) | Aluminum alloy coating with rare earth and transition metal corrosion inhibitors | |
EP3239475B1 (en) | Outer airseal abradable rub strip | |
JP2008133827A (en) | Ceramic corrosion resistant coating for oxidation resistance | |
KR20140103066A (en) | Turbomachine component with an erosion and corrosion resistant coating system and method for manufacturing such a component | |
US8708659B2 (en) | Turbine engine component having protective coating | |
US10435776B2 (en) | Fire containment coating system for titanium | |
US20080080978A1 (en) | Coated turbine engine components and methods for making the same | |
Stolle | Conventional and advanced coatings for turbine airfoils | |
US20200248577A1 (en) | Fusible bond for gas turbine engine coating system | |
JP2018535322A (en) | Turbine clearance control coating and method |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: ROLLS-ROYCE CORPORATION, INDIANA Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:SHIM, SUNGBO;CYBULSKY, MICHAEL;SINATRA, RAYMOND;SIGNING DATES FROM 20131013 TO 20151030;REEL/FRAME:037219/0818 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- AFTER EXAMINER'S ANSWER OR BOARD OF APPEALS DECISION |