US20130272917A1 - Metallic bondcoat or alloy with a high gamma/gamma' transition temperature and a component - Google Patents
Metallic bondcoat or alloy with a high gamma/gamma' transition temperature and a component Download PDFInfo
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- US20130272917A1 US20130272917A1 US13/884,375 US201113884375A US2013272917A1 US 20130272917 A1 US20130272917 A1 US 20130272917A1 US 201113884375 A US201113884375 A US 201113884375A US 2013272917 A1 US2013272917 A1 US 2013272917A1
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- alloy
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
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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
- 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
- C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
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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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
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- 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
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- 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
- F05D2260/00—Function
- F05D2260/95—Preventing corrosion
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the invention relates to a metallic bondcoat with phases of ⁇ and ⁇ ′ a component.
- Components for the hot gas path in gas turbines are made from Ni- or Co based materials. These materials are optimized for strength and are not able to withstand oxidation and/or corrosion attack at higher temperatures. Therefore, these kinds of materials must be protected against oxidation by MCrAlY-coatings which can be used as bondcoats for thermal barrier coating (TBC) systems as well.
- TBC thermal barrier coating
- the MCrAlY coating is needed against hot gas attack on one side and on the other side this coating is needed to adhere the TBC to the substrate. Improving such systems against oxidation will lead to increased bondcoats service temperatures with increased life properties.
- MCrAlY overlay coatings are coated mainly by low pressure plasma spraying (LPPS), air plasma spraying (APS), electron beam physical vapor deposition (EBPVD), cold spray (CS) or high velocity oxy-fuel (HVOF) process.
- LPPS low pressure plasma spraying
- APS air plasma spraying
- EBPVD electron beam physical vapor deposition
- CS cold spray
- HVOF high velocity oxy-fuel
- the MCrAlY coating is based on nickel and/or cobalt, chromium, aluminum, silicon, rhenium and rare earth elements like yttrium.
- With increasing bondcoat temperatures these coatings can fail which can lead to spallation of the thermal barrier coating. Therefore, with increasing service temperatures, improved coatings are needed to withstand the oxidation attack. Additionally this kind of coatings should have acceptable thermo-mechanical properties. These requests can only be achieved by an optimized composition of the bond coat.
- FIG. 1 a turbine blade
- FIG. 2 a gas turbine
- FIG. 3 a list of superalloys.
- FIG. 1 shows a perspective view of a rotor blade 120 or guide vane 130 of a turbomachine, which extends along a longitudinal axis 121 .
- the turbomachine may be a gas turbine of an aircraft or of a power plant for generating electricity, a steam turbine or a compressor.
- the blade or vane 120 , 130 has, in succession along the longitudinal axis 121 , a securing region 400 , an adjoining blade or vane platform 403 and a main blade or vane part 406 as well as a blade or vane tip 415 .
- the vane 130 may have a further platform (not shown) at its vane tip 415 .
- a blade or vane root 183 which is used to secure the rotor blades 120 , 130 to a shaft or disk (not shown), is formed in the securing region 400 .
- the blade or vane root 183 is designed, for example, in hammerhead form. Other configurations, such as a fir-tree or dovetail root, are possible.
- the blade or vane 120 , 130 has a leading edge 409 and a trailing edge 412 for a medium which flows past the main blade or vane part 406 .
- the blade or vane 120 , 130 may in this case be produced by a casting process, also by means of directional solidification, by a forging process, by a milling process or combinations thereof.
- Workpieces with a single-crystal structure or structures are used as components for machines which, in operation, are exposed to high mechanical, thermal and/or chemical stresses.
- Single-crystal workpieces of this type are produced, for example, by directional solidification from the melt. This involves casting processes in which the liquid metallic alloy solidifies to form the single-crystal structure, i.e. the single-crystal workpiece, or solidifies directionally.
- dendritic crystals are oriented along the direction of heat flow and form either a columnar crystalline grain structure (i.e. grains which run over the entire length of the workpiece and are referred to here, in accordance with the language customarily used, as directionally solidified) or a single-crystal structure, i.e. the entire workpiece consists of one single crystal.
- a transition to globular (polycrystalline) solidification needs to be avoided, since non-directional growth inevitably forms transverse and longitudinal grain boundaries, which negate the favorable properties of the directionally solidified or single-crystal component.
- directionally solidified microstructures refers in general terms to directionally solidified microstructures, this is to be understood as meaning both single crystals, which do not have any grain boundaries or at most have small-angle grain boundaries, and columnar crystal structures, which do have grain boundaries running in the longitudinal direction but do not have any transverse grain boundaries.
- This second form of crystalline structures is also described as directionally solidified microstructures (directionally solidified structures).
- the blades or vanes 120 , 130 may likewise have coatings protecting against corrosion or oxidation, e.g. MCrAlX (M is at least one element selected from the group consisting of iron (Fe), cobalt (Co), nickel (Ni), X is an active element and represents yttrium (Y) and/or silicon and/or at least one rare earth element, or hafnium (Hf)). Alloys of this type are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
- the density is preferably 95% of the theoretical density.
- thermal barrier coating consisting for example of ZrO 2 , Y 2 O 3 —ZrO 2 , i.e. unstabilized, partially stabilized or fully stabilized by yttrium oxide and/or calcium oxide and/or magnesium oxide and/or one or more of rare earth element (lanthanum, gadolinium, yttrium, etc.), which is preferably the outermost layer, to be present on the MCrAlX.
- ZrO 2 , Y 2 O 3 —ZrO 2 i.e. unstabilized, partially stabilized or fully stabilized by yttrium oxide and/or calcium oxide and/or magnesium oxide and/or one or more of rare earth element (lanthanum, gadolinium, yttrium, etc.), which is preferably the outermost layer, to be present on the MCrAlX.
- the thermal barrier coating covers the entire MCrAlX layer.
- Columnar grains are produced in the thermal barrier coating by means of suitable coating processes, such as for example electron beam physical vapor deposition (EB-PVD).
- EB-PVD electron beam physical vapor deposition
- the thermal barrier coating may include porous grains which have microcracks or macrocracks for improving its resistance to thermal shocks.
- the thermal barrier coating is therefore preferably more porous than the MCrAlX layer.
- the blade or vane 120 , 130 may be hollow or solid in form. If the blade or vane 120 , 130 is to be cooled, it is hollow and may also have film-cooling holes 418 (indicated by dashed lines).
- FIG. 2 shows, by way of example, a partial longitudinal section through a gas turbine 100 .
- the gas turbine 100 has a rotor 103 which is mounted such that it can rotate about an axis of rotation 102 , has a shaft 101 and is also referred to as the turbine rotor.
- the annular combustion chamber 110 is in communication with a, for example, annular hot-gas passage 111 , where, by way of example, four successive turbine stages 112 form the turbine 108 .
- Each turbine stage 112 is formed, for example, from two blade or vane rings. As seen in the direction of flow of a working medium 113 , in the hot-gas passage 111 a row of guide vanes 115 is followed by a row 125 formed from rotor blades 120 .
- the guide vanes 130 are secured to an inner housing 138 of a stator 143 , whereas the rotor blades 120 of a row 125 are fitted to the rotor 103 for example by means of a turbine disk 133 .
- a generator (not shown) is coupled to the rotor 103 .
- the compressor 105 While the gas turbine 100 is operating, the compressor 105 sucks in air 135 through the intake housing 104 and compresses it. The compressed air provided at the turbine-side end of the compressor 105 is passed to the burners 107 , where it is mixed with a fuel. The mix is then burnt in the combustion chamber 110 , forming the working medium 113 . From there, the working medium 113 flows along the hot-gas passage 111 past the guide vanes 130 and the rotor blades 120 . The working medium 113 is expanded at the rotor blades 120 , transferring its momentum, so that the rotor blades 120 drive the rotor 103 and the latter in turn drives the generator coupled to it.
- Substrates of the components may likewise have a directional structure, i.e. they are in single-crystal form (SX structure) or have only longitudinally oriented grains (DS structure).
- SX structure single-crystal form
- DS structure longitudinally oriented grains
- iron-based, nickel-based or cobalt-based superalloys are used as material for the components, in particular for the turbine blade or vane 120 , 130 and components of the combustion chamber 110 .
- the guide vane 130 has a guide vane root (not shown here) facing the inner housing 138 of the turbine 108 and a guide vane head at the opposite end from the guide vane root.
- the guide vane head faces the rotor 103 and is fixed to a securing ring 140 of the stator 143 .
- a new modified coating was developed which fulfils the requirements described above.
- This coating has a good long term life, acceptable mechanical properties and improved oxidation resistance. This is based on the presence of tantalum (Ta) in a nickel based alloy but preferably without rhenium (Re). Tantalum (Ta) stabilizes the formation of a three phase system ( ⁇ ′/ ⁇ / ⁇ ) with a high ⁇ ′/ ⁇ transition temperature. This will reduce the local stresses as well because tantalum (Ta) will stabilize the high transition temperatures of ⁇ ′ which is higher than the bondcoat service temperature.
- hafnium (Hf), silicon (Si) or zirconium (Zr) or any melting depressant (B) in the coating there is preferably no need for hafnium (Hf), silicon (Si) or zirconium (Zr) or any melting depressant (B) in the coating.
- a composition (Ni-25Co-17Cr-10Al-1.5Re-Y) which contains rhenium (Re) instead of tantalum (Ta) has a lower ⁇ ′/ ⁇ transition temperature because no tantalum (Ta) is added.
- the bondcoat is preferably a nickel (Ni) based super alloy with addition of cobalt (Co), chromium (Cr), aluminum (Al) and optionally yttrium (Y) which is preferably consisting of these elements.
- the alloy contains no molybdenum (Mo), and/or no tungsten (W) and/or no columbium (Nb) and/or no platinum (Pt).
- Mo molybdenum
- W tungsten
- Nb columbium
- Pt platinum
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- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
Description
- This application is the US National Stage of International Application No. PCT/EP2011/069515 filed Nov. 7, 2011 and claims benefit thereof, the entire content of which is hereby incorporated herein by reference. The International Application claims priority to the U.S. application Ser. No. 12/953,531 filed Nov. 24, 2010, the entire contents of which is hereby incorporated herein by reference.
- The invention relates to a metallic bondcoat with phases of γ and γ′ a component.
- Components for the hot gas path in gas turbines are made from Ni- or Co based materials. These materials are optimized for strength and are not able to withstand oxidation and/or corrosion attack at higher temperatures. Therefore, these kinds of materials must be protected against oxidation by MCrAlY-coatings which can be used as bondcoats for thermal barrier coating (TBC) systems as well. In TBS systems, the MCrAlY coating is needed against hot gas attack on one side and on the other side this coating is needed to adhere the TBC to the substrate. Improving such systems against oxidation will lead to increased bondcoats service temperatures with increased life properties.
- To protect the materials against hot corrosion/oxidation, MCrAlY overlay coatings are coated mainly by low pressure plasma spraying (LPPS), air plasma spraying (APS), electron beam physical vapor deposition (EBPVD), cold spray (CS) or high velocity oxy-fuel (HVOF) process. The MCrAlY coating is based on nickel and/or cobalt, chromium, aluminum, silicon, rhenium and rare earth elements like yttrium. With increasing bondcoat temperatures, these coatings can fail which can lead to spallation of the thermal barrier coating. Therefore, with increasing service temperatures, improved coatings are needed to withstand the oxidation attack. Additionally this kind of coatings should have acceptable thermo-mechanical properties. These requests can only be achieved by an optimized composition of the bond coat.
- It is therefore the aim of the invention to solve the above mentioned problem.
- The problem is solved by a metallic coating or an alloy and a component according to the independent claims.
- In the dependent claims further amendments are disclosed which can be arbitrarily combined with each other to yield further advantages.
- It shows
-
FIG. 1 a turbine blade, -
FIG. 2 a gas turbine and -
FIG. 3 a list of superalloys. - The figures and the description are only embodiments of the invention.
-
FIG. 1 shows a perspective view of arotor blade 120 or guidevane 130 of a turbomachine, which extends along alongitudinal axis 121. - The turbomachine may be a gas turbine of an aircraft or of a power plant for generating electricity, a steam turbine or a compressor.
- The blade or
vane longitudinal axis 121, a securingregion 400, an adjoining blade orvane platform 403 and a main blade orvane part 406 as well as a blade orvane tip 415. - As a
guide vane 130, thevane 130 may have a further platform (not shown) at itsvane tip 415. - A blade or
vane root 183, which is used to secure therotor blades securing region 400. - The blade or
vane root 183 is designed, for example, in hammerhead form. Other configurations, such as a fir-tree or dovetail root, are possible. - The blade or
vane edge 409 and atrailing edge 412 for a medium which flows past the main blade orvane part 406. - In the case of conventional blades or
vanes regions vane - Superalloys of this type are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949.
- The blade or
vane - Workpieces with a single-crystal structure or structures are used as components for machines which, in operation, are exposed to high mechanical, thermal and/or chemical stresses.
- Single-crystal workpieces of this type are produced, for example, by directional solidification from the melt. This involves casting processes in which the liquid metallic alloy solidifies to form the single-crystal structure, i.e. the single-crystal workpiece, or solidifies directionally.
- In this case, dendritic crystals are oriented along the direction of heat flow and form either a columnar crystalline grain structure (i.e. grains which run over the entire length of the workpiece and are referred to here, in accordance with the language customarily used, as directionally solidified) or a single-crystal structure, i.e. the entire workpiece consists of one single crystal. In these processes, a transition to globular (polycrystalline) solidification needs to be avoided, since non-directional growth inevitably forms transverse and longitudinal grain boundaries, which negate the favorable properties of the directionally solidified or single-crystal component.
- Where the text refers in general terms to directionally solidified microstructures, this is to be understood as meaning both single crystals, which do not have any grain boundaries or at most have small-angle grain boundaries, and columnar crystal structures, which do have grain boundaries running in the longitudinal direction but do not have any transverse grain boundaries. This second form of crystalline structures is also described as directionally solidified microstructures (directionally solidified structures).
- Processes of this type are known from U.S. Pat. No. 6,024,792 and EP 0 892 090 A1.
- The blades or
vanes - The density is preferably 95% of the theoretical density.
- A protective aluminum oxide layer (TGO=thermally grown oxide layer) forms on the MCrAlX layer (as an intermediate layer or an outermost layer).
- It is also possible for a thermal barrier coating, consisting for example of ZrO2, Y2O3—ZrO2, i.e. unstabilized, partially stabilized or fully stabilized by yttrium oxide and/or calcium oxide and/or magnesium oxide and/or one or more of rare earth element (lanthanum, gadolinium, yttrium, etc.), which is preferably the outermost layer, to be present on the MCrAlX.
- The thermal barrier coating covers the entire MCrAlX layer. Columnar grains are produced in the thermal barrier coating by means of suitable coating processes, such as for example electron beam physical vapor deposition (EB-PVD).
- Other coating processes are conceivable, for example atmospheric plasma spraying (APS), LPPS, VPS, solution precursor plasma spray (SPPS) or CVD. The thermal barrier coating may include porous grains which have microcracks or macrocracks for improving its resistance to thermal shocks. The thermal barrier coating is therefore preferably more porous than the MCrAlX layer.
- The blade or
vane vane -
FIG. 2 shows, by way of example, a partial longitudinal section through agas turbine 100. - In the interior, the
gas turbine 100 has arotor 103 which is mounted such that it can rotate about an axis ofrotation 102, has a shaft 101 and is also referred to as the turbine rotor. - An
intake housing 104, acompressor 105, a, for example,toroidal combustion chamber 110, in particular an annular combustion chamber, with a plurality of coaxially arrangedburners 107, aturbine 108 and the exhaust-gas housing 109 follow one another along therotor 103. - The
annular combustion chamber 110 is in communication with a, for example, annular hot-gas passage 111, where, by way of example, foursuccessive turbine stages 112 form theturbine 108. - Each
turbine stage 112 is formed, for example, from two blade or vane rings. As seen in the direction of flow of a workingmedium 113, in the hot-gas passage 111 a row ofguide vanes 115 is followed by arow 125 formed fromrotor blades 120. - The guide vanes 130 are secured to an
inner housing 138 of astator 143, whereas therotor blades 120 of arow 125 are fitted to therotor 103 for example by means of aturbine disk 133. - A generator (not shown) is coupled to the
rotor 103. - While the
gas turbine 100 is operating, thecompressor 105 sucks inair 135 through theintake housing 104 and compresses it. The compressed air provided at the turbine-side end of thecompressor 105 is passed to theburners 107, where it is mixed with a fuel. The mix is then burnt in thecombustion chamber 110, forming the workingmedium 113. From there, the workingmedium 113 flows along the hot-gas passage 111 past theguide vanes 130 and therotor blades 120. The workingmedium 113 is expanded at therotor blades 120, transferring its momentum, so that therotor blades 120 drive therotor 103 and the latter in turn drives the generator coupled to it. - While the
gas turbine 100 is operating, the components which are exposed to the hot workingmedium 113 are subject to thermal stresses. The guide vanes 130 androtor blades 120 of thefirst turbine stage 112, as seen in the direction of flow of the workingmedium 113, together with the heat shield bricks which line theannular combustion chamber 110, are subject to the highest thermal stresses. - To be able to withstand the temperatures which prevail there, they can be cooled by means of a coolant.
- Substrates of the components may likewise have a directional structure, i.e. they are in single-crystal form (SX structure) or have only longitudinally oriented grains (DS structure).
- By way of example, iron-based, nickel-based or cobalt-based superalloys are used as material for the components, in particular for the turbine blade or
vane combustion chamber 110. - Superalloys of this type are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949.
- The
guide vane 130 has a guide vane root (not shown here) facing theinner housing 138 of theturbine 108 and a guide vane head at the opposite end from the guide vane root. The guide vane head faces therotor 103 and is fixed to a securingring 140 of thestator 143. - A new modified coating was developed which fulfils the requirements described above. This coating has a good long term life, acceptable mechanical properties and improved oxidation resistance. This is based on the presence of tantalum (Ta) in a nickel based alloy but preferably without rhenium (Re). Tantalum (Ta) stabilizes the formation of a three phase system (γ′/γ/β) with a high γ′/γ transition temperature. This will reduce the local stresses as well because tantalum (Ta) will stabilize the high transition temperatures of γ′ which is higher than the bondcoat service temperature.
- Therefore there is preferably no need for hafnium (Hf), silicon (Si) or zirconium (Zr) or any melting depressant (B) in the coating.
- Very good results show the following elemental composition for getting the proposed 3-phase-system with increased γ′ transition temperatures: Ni-23Co-20Cr-10Al-4.5Ta.
- A composition (Ni-25Co-17Cr-10Al-1.5Re-Y) which contains rhenium (Re) instead of tantalum (Ta) has a lower γ′/γ transition temperature because no tantalum (Ta) is added.
- The bondcoat is preferably a nickel (Ni) based super alloy with addition of cobalt (Co), chromium (Cr), aluminum (Al) and optionally yttrium (Y) which is preferably consisting of these elements.
- Very preferably it is a MCrAl(X) alloy, with M=Ni, Co.
- Preferably the alloy contains no molybdenum (Mo), and/or no tungsten (W) and/or no columbium (Nb) and/or no platinum (Pt).
Claims (16)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/884,375 US20130272917A1 (en) | 2010-11-24 | 2011-11-07 | Metallic bondcoat or alloy with a high gamma/gamma' transition temperature and a component |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/953,531 US20120128526A1 (en) | 2010-11-24 | 2010-11-24 | Metallic Bondcoat or Alloy with a High y/y' Transition Temperature and a Component |
US12953531 | 2010-11-24 | ||
PCT/EP2011/069515 WO2012069306A1 (en) | 2010-11-24 | 2011-11-07 | METALLIC BONDCOAT OR ALLOY WITH A HIGH γ/γ' TRANSITION TEMPERATURE AND A COMPONENT |
US13/884,375 US20130272917A1 (en) | 2010-11-24 | 2011-11-07 | Metallic bondcoat or alloy with a high gamma/gamma' transition temperature and a component |
Publications (1)
Publication Number | Publication Date |
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US20130272917A1 true US20130272917A1 (en) | 2013-10-17 |
Family
ID=45023808
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
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US12/953,531 Abandoned US20120128526A1 (en) | 2010-11-24 | 2010-11-24 | Metallic Bondcoat or Alloy with a High y/y' Transition Temperature and a Component |
US13/884,375 Abandoned US20130272917A1 (en) | 2010-11-24 | 2011-11-07 | Metallic bondcoat or alloy with a high gamma/gamma' transition temperature and a component |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
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US12/953,531 Abandoned US20120128526A1 (en) | 2010-11-24 | 2010-11-24 | Metallic Bondcoat or Alloy with a High y/y' Transition Temperature and a Component |
Country Status (4)
Country | Link |
---|---|
US (2) | US20120128526A1 (en) |
EP (1) | EP2622110B1 (en) |
CN (1) | CN103354841B (en) |
WO (1) | WO2012069306A1 (en) |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
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US20070051199A1 (en) * | 2005-05-26 | 2007-03-08 | Snecma Services | Superalloy powder |
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US4447503A (en) * | 1980-05-01 | 1984-05-08 | Howmet Turbine Components Corporation | Superalloy coating composition with high temperature oxidation resistance |
US5002834A (en) * | 1988-04-01 | 1991-03-26 | Inco Alloys International, Inc. | Oxidation resistant alloy |
EP0486489B1 (en) | 1989-08-10 | 1994-11-02 | Siemens Aktiengesellschaft | High-temperature-resistant, corrosion-resistant coating, in particular for components of gas turbines |
DE3926479A1 (en) | 1989-08-10 | 1991-02-14 | Siemens Ag | RHENIUM-PROTECTIVE COATING, WITH GREAT CORROSION AND / OR OXIDATION RESISTANCE |
KR100354411B1 (en) | 1994-10-14 | 2002-11-18 | 지멘스 악티엔게젤샤프트 | Protective layer for protecting parts against corrosion, oxidation and excessive thermal stresses, as well as process for producing the same |
EP0861927A1 (en) | 1997-02-24 | 1998-09-02 | Sulzer Innotec Ag | Method for manufacturing single crystal structures |
EP0892090B1 (en) | 1997-02-24 | 2008-04-23 | Sulzer Innotec Ag | Method for manufacturing single crystal structures |
WO1999067435A1 (en) | 1998-06-23 | 1999-12-29 | Siemens Aktiengesellschaft | Directionally solidified casting with improved transverse stress rupture strength |
US6231692B1 (en) | 1999-01-28 | 2001-05-15 | Howmet Research Corporation | Nickel base superalloy with improved machinability and method of making thereof |
EP1204776B1 (en) | 1999-07-29 | 2004-06-02 | Siemens Aktiengesellschaft | High-temperature part and method for producing the same |
DE50104022D1 (en) | 2001-10-24 | 2004-11-11 | Siemens Ag | Protective layer containing rhenium to protect a component against corrosion and oxidation at high temperatures |
DE50112339D1 (en) | 2001-12-13 | 2007-05-24 | Siemens Ag | High-temperature resistant component made of monocrystalline or polycrystalline nickel-based superalloy |
WO2008010965A1 (en) * | 2006-07-18 | 2008-01-24 | Exxonmobil Research And Engineering Company | High performance coated material with improved metal dusting corrosion resistance |
EP2550374A1 (en) * | 2010-03-23 | 2013-01-30 | Siemens Aktiengesellschaft | Metallic bondcoat or alloy with a high / ' transition temperature and a component |
US9074268B2 (en) * | 2010-03-23 | 2015-07-07 | Siemens Aktiengesellschaft | Metallic bondcoat with a high gamma/gamma' transition temperature and a component |
-
2010
- 2010-11-24 US US12/953,531 patent/US20120128526A1/en not_active Abandoned
-
2011
- 2011-11-07 US US13/884,375 patent/US20130272917A1/en not_active Abandoned
- 2011-11-07 EP EP11787639.1A patent/EP2622110B1/en not_active Not-in-force
- 2011-11-07 CN CN201180056126.5A patent/CN103354841B/en not_active Expired - Fee Related
- 2011-11-07 WO PCT/EP2011/069515 patent/WO2012069306A1/en active Application Filing
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20070051199A1 (en) * | 2005-05-26 | 2007-03-08 | Snecma Services | Superalloy powder |
Also Published As
Publication number | Publication date |
---|---|
CN103354841B (en) | 2015-09-09 |
US20120128526A1 (en) | 2012-05-24 |
WO2012069306A1 (en) | 2012-05-31 |
EP2622110B1 (en) | 2015-08-12 |
EP2622110A1 (en) | 2013-08-07 |
CN103354841A (en) | 2013-10-16 |
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