• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A gas turbine component (100) includes a substrate (102) formed of a high temperature resistant material and a corrosion resistant layer (106). The corrosion resistant layer (106) is inert to molten salt contaminants and contains a refractory metal vanadate of the formula M x V y O z wherein M is selected from the group consisting of alkaline earth metals, Group IV and V transition metals, rare earth metals and their combinations, and wherein z = x + 2.5y or z = 1.5x + 2.5y or z = 2x + 2.5y.
    公开号:CH708791B1
    申请号:CH01606/14
    申请日:2014-10-20
    公开日:2018-07-13
    发明作者:Wang Limin；Zhong Dalong；Zhou Hong；Edward Thompson Christopher；Bernard Kool Lawrence；Zhang Liming
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    description
    Background of the Invention Higher operating temperatures are continuously sought for gas turbines to increase their efficiency. High temperature resistant materials are widely used to manufacture gas turbine components in various industries, including the aircraft and power generation industries. With increasing operating temperatures, the durability of turbine components at high temperatures must increase accordingly. For this reason, thermal barrier coatings (TBC) are commonly used on gas turbine components such as burners, blades and vanes of high pressure turbines (HPT). The thermal insulation of the TBC enables the turbine components to withstand higher operating temperatures, increases the durability of the components and improves the reliability of the turbine.
    High combustion temperatures within the gas turbine environment can cause molten contaminants in a fuel to corrode not only components made from materials susceptible to molten contaminants, such as silicon-based superalloys and non-oxide ceramics, but also the TBC used to protect the components, attack corrosively and destabilize. This phenomenon, known as hot corrosion, is an accelerated corrosion that results from the presence of contaminants such as Na 2 SO 4 , NaVO 3 and V 2 O 5 that form molten salt deposits on the surface of the component or its protective coating. Hot corrosion can cause the structural material or coating to degrade rapidly, and therefore the component can be severely damaged in tens of thousands of hours.
    Despite the above problems and uncertainties, there is a desire in the industry to use cheaper, lower quality fuels for gas turbines which consequently contain higher concentrations of salt contaminants and therefore exacerbate the problem of hot corrosion. It is therefore becoming increasingly challenging to mitigate the hot corrosion of turbine components.
    Brief Description of the Invention The invention is defined by a turbine component and a method of manufacturing a turbine component according to the independent claims.
    The aforementioned turbine component may further include a thermal barrier coating system disposed between the substrate and at least a portion of the corrosion resistant layer, the corrosion resistant layer being applied directly to the thermal barrier coating system.
    The thermal barrier coating system may further comprise a layer of yttria-stabilized zirconia with a thickness in the range of about 100 pm to about 1150 pm and a first tie layer between the layer of yttria-stabilized zirconia and the substrate.
    In the turbine component of the aforementioned type, the first tie layer can be RCrAIE, wherein R is iron, cobalt and / or nickel and E is yttrium, a rare earth metal and / or another reactive metal.
    Alternatively or additionally, the thermal barrier coating system may further comprise a thermally grown oxide layer between the first binding layer and the layer of zirconium dioxide stabilized with yttrium oxide.
    In the turbine component of the aforementioned type, the thermally grown oxide layer can be Al 2 O 3 .
    The turbine component of any of the types mentioned above may further comprise a second tie layer disposed between the substrate and at least a portion of the corrosion resistant layer, the corrosion resistant layer being applied to the second tie layer, the second tie layer for bonding between the substrate and the corrosion-resistant layer.
    In the turbine component of the aforementioned type, the second binding layer can be aluminide.
    In the turbine component of any type mentioned above, at least a part of the corrosion-resistant layer can be applied directly to the substrate.
    In the turbine component of any type mentioned above, M can be selected from the group consisting of Sc, Y, La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu , Ca, Mg, Ti, Zr, Hf, Nb, Ta and their combinations. Preferably M is selected from the group consisting of Ce, La, Y, Gd and combinations thereof.
    In the turbine component of any type mentioned above, the corrosion-resistant layer may have a thickness in the range of about 50 pm to about 200 pm.
    In the turbine component of any type mentioned above, the substrate may be made of a super alloy.
    CH 708 791 B1 In the aforementioned method, the step of applying a corrosion-resistant layer over the substrate may include providing a thermal barrier coating system on at least a portion of the substrate and applying at least a portion of the corrosion-resistant layer directly on the thermal barrier coating system.
    Additionally, the step of providing a thermal barrier coating system on at least a portion of the substrate may include providing a first tie layer on at least a portion of the substrate and forming a layer of yttria-stabilized zirconia on the first tie layer, the layer of the yttria-stabilized layer Zirconia has a thickness in the range of about 100 pm to about 1150 pm.
    In the method of the aforementioned type, the first tie layer may be RCrAIE, where R is iron, cobalt and / or nickel and E is yttrium, a rare earth metal and / or other reactive metal.
    Alternatively or additionally, the step of providing a thermal barrier coating system on at least part of the substrate may further comprise providing a thermally grown oxide layer between the first bonding layer and the layer of yttrium-stabilized zirconium dioxide.
    In the method of the type mentioned above, the thermally grown oxide layer can be Al 2 O 3 .
    In the method of any of the types mentioned above, the step of applying a corrosion resistant layer over the substrate may include providing a second tie layer on at least a portion of the substrate and applying at least a portion of the corrosion resistant layer directly on the second tie layer. In the method of the aforementioned type, the second binding layer can be aluminide.
    In the method of any of the types mentioned above, the step of applying a corrosion resistant layer over the substrate may include applying at least a portion of the corrosion resistant layer directly to at least a portion of the substrate.
    In the method of any type mentioned above, the M can be selected from the group consisting of Sc, Y, La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb , Lu, Ca, Mg, Ti, Zr, Hf, Nb, Ta and their combinations. The M is preferably selected from the group consisting of Ce, La, Y, Gd and their combinations.
    In the method of any type mentioned above, the corrosion-resistant layer can be applied by a method selected from the group consisting of thermal spraying, cold spraying, sol-gel, PVD, CVD, slurrying, atomizing and combinations thereof consists.
    Brief Description of the Drawing The above and other aspects, features and advantages of the present invention will become more apparent in light of the following detailed description with reference to the accompanying drawing, in which:
    1 shows a schematic view of a turbine component in which a corrosion-resistant layer is applied directly to a thermal barrier coating (TBC) system which lies over the substrate of the turbine component.
    2 shows a schematic view of a turbine component in which a corrosion-resistant layer is applied directly to the substrate of the turbine component.
    3 shows a schematic view of a turbine component in which a corrosion-resistant layer is applied to the substrate of the turbine component via a bonding layer in order to achieve better adhesion between the corrosion-resistant layer and the substrate.
    Detailed Description of the Invention Approximate terms, as used herein in the description and claims, may be used to modify any quantitative representation that could reasonably vary without resulting in a change in the basic function to which they relate is. Accordingly, a value that is modified by a term or terms such as "about" is not to be limited to the specified exact value. In certain embodiments, the term "about" means plus or minus ten percent (10%) of a value. For example, "about 100" would refer to any number between 90 and 110. When expressing «approximately a first value minus a second value», this should modify approximately both values. In some cases, the approximate terms may correspond to the accuracy of an instrument for measuring the value or values.
    Unless otherwise stated, the technical and scientific terms used herein have the same meaning that those of ordinary skill in the art to which this invention belongs will understand. The terms "first," "second," and the like, as used herein, do not mean order, quantity, or meaning, but rather are used to distinguish one element from another. The terms also mean
    CH 708 791 B1 “on” and “an” do not limit the quantity, but denote the presence of at least one of the elements referred to.
    [0031] Embodiments of the present invention provide a turbine component coated with a corrosion resistant layer that is inert to molten salt contaminants contained in the fuel processed by the turbine component. The corrosion-resistant layer comprises a high-melting metal vanadate of the formula M x V y O z , where M is selected from the group consisting of alkaline earth metals, transition metals of groups IV and V, rare earth metals and their combinations, and wherein z = x + 2.5y or z = 1.5x + 2.5y or z = 2x + 2.5y. The corrosion resistant layer is applied to the turbine component as a protective surface before the turbine component is used to process the fuel that contains the molten salt contaminants. It is able to protect the turbine component, as well as its thermal and / or environmental barrier coating systems, which can have a composition that is sensitive to hot corrosion promoted by the molten salt contaminants, from hot corrosion.
    [0032] In some embodiments, the corrosion-resistant layer, which comprises a high-melting metal vanadate of the formula M x V y O z , is also inert to sulfur trioxide (SO 3 ) and thus capable of protecting the turbine component and its thermal and / or environmental barrier coating systems Protect both from hot corrosion promoted by molten salt contaminants and from corrosion caused by gas phase corrosion media, including SO 3 .
    In some embodiments, M in the high-melting metal vanadate of the formula M x V y O z is selected from the group consisting of scandium (Sc), yttrium (Y), lanthanum (La), cerium (Ce), praseodymium (Pr) , Neodymium (Nd), Promethium (Pm), Samarium (Sm), Europium (Eu), Gadolinium (Gd), Terbium (Tb), Dysprosium (Dy), Holmium (Ho), Erbium (Er), Thulium (Tm) , Ytterbium (Yb), lutetium (Lu), calcium (Ca), magnesium (Mg), titanium (Ti), zirconium (Zr), hafnium (Hf), niobium (Nb) and tantalum (Ta). In some specific embodiments, M is selected from the group consisting of Ce, La, Y, Gd and their combinations.
    In some embodiments, the high-melting metal vanadate of the formula M x V y O z is selected from the group consisting of CeVO 4 , LaVO 4 , YVO 4 , GdVO 4 and their combinations.
    The substrate of the turbine components is usually made of high temperature resistant materials, such as superalloy materials and silicon-containing materials. Examples of superalloy materials include nickel-based, cobalt-based, and iron-based alloys, and examples of silicon-containing materials include those with a dispersion of silicon carbide, silicon nitride, metal silicides, and / or silicon reinforcing material in a metallic or non-metallic matrix, as well as which have a matrix containing silicon carbide, silicon nitride and / or silicon and in particular composite materials which contain silicon carbide, silicon nitride, metal silicides (such as niobium and molybdenum silicides) and / or silicon as both the reinforcing material and the matrix material (eg ceramic matrix composites (CMCs) ) use. While the advantages of this invention are described with reference to gas turbine components, the teachings of the invention are generally applicable to any component whose substrate and / or coating system is exposed to molten salt attack.
    In some embodiments, such as a turbine component operating in a high temperature environment, e.g. above 1000 ° C, there are usually thermal barrier coatings (TBCs) on the substrate of the turbine component to increase the high temperature durability of the turbine component, and the corrosion resistant layer can be applied directly to the TBCs. The TBCs typically include a thermally insulating material that is applied to an environmental protective layer to form what is called a TBC system, the binding layer being used to provide better adhesion between the thermal insulating material and the Achieve substrate of the turbine component. The corrosion-resistant layer can be applied directly on the TBC system, i.e. on the layer of thermally insulating material. A widely used thermal insulating material is yttrium oxide stabilized zirconium dioxide (YSZ). A widely used binder layer material is RCrAIE, where R is iron, cobalt and / or nickel and E is yttrium, a rare earth metal and / or other reactive metal.
    In a special embodiment, as shown in FIG. 1, a gas turbine engine component 100 comprises a substrate 102, a TBC system 104 and a corrosion-resistant layer 106, which contains a high-melting metal vanadate of the formula M x V y O z as described above. The TBC system 104 includes a bonding layer 108 that is applied to the substrate 102, a thermally grown oxide (TGO) layer 110 on the bonding layer 108, and a YSZ layer 112 that serves as a TBC that is on the TGO Layer 110 is applied. In a special embodiment, the thermally grown oxide layer is Al 2 O 3 . With the binding layer 108, the YSZ layer 112 and the TGO layer 110 can adhere to the substrate 102 of the turbine component. The YSZ layer 112 can have a thickness in the range from about 100 pm to about 1150 pm. The corrosion-resistant layer 106 is applied directly on the TBC system 104, ie on the YSZ layer 112, and is able to protect the underlying TBC system and the substrate from hot corrosion, which is caused by the molten salt impurities.
    In some embodiments, such as a turbine component operating in a relatively low temperature environment, e.g. from about 800 ° C to about 1000 ° C, there may be no need for a thermal barrier coating system on the substrate of the turbine component, and so the corrosion-resistant layer can be directly on the
    CH 708 791 B1
    Be applied substrate. In some embodiments, a tie layer may be interposed between the corrosion-resistant layer and the turbine component substrate to increase the adhesion of the layers, and so the corrosion-resistant layer is applied to the substrate using the tie layer. In a special embodiment, the binding layer between the corrosion-resistant layer and the substrate is aluminide.
    As shown in FIG. 2, a turbine component 200 includes a substrate 202 and a corrosion-resistant layer 206, as described above, which is applied directly to the substrate 202. In a particular embodiment, as shown in FIG. 3, a turbine component 300 comprises a substrate 302 and a corrosion-resistant layer 306, as described above, which is applied over a bonding layer 304 on the substrate 302, for better adhesion between the corrosion-resistant To reach layer 306 and substrate 302.
    [0040] In some embodiments, a turbine component may include different parts that encounter different processing environments in use. In such a situation, the different parts of the turbine component are coated with a TBC system or not, depending on the environment they encounter, and a corrosion resistant layer that is applied as a protective surface of the turbine component can be with the TBC system or the substrate (or another intermediate layer) on different parts of the component. In a special embodiment, a turbine component comprises e.g. a substrate having a first part protected with a TBC system and a second part without a TBC system. A corrosion-resistant layer of the component has a first part that is applied directly to the TBC system, which lies above the first part of the component substrate, and a second part, which is applied to the second part of the component substrate by means of a bonding layer, which the Adherence of the corrosion-resistant layer to the second part of the component substrate is better supported. In addition, the corrosion resistant layer may further include a third portion which is applied directly to the component substrate without any TBC system or other intermediate layer in between.
    In the above-described embodiments, the corrosion-resistant layer can be applied by a method selected from the group including thermal spraying, cold spraying, sol-gel, physical vapor deposition (PVD), chemical vapor deposition (CVD), slurrying , Atomization, and combinations thereof, and may have a thickness in the range from about 1 pm to about 300 pm, or preferably from about 50 pm to about 200 pm.
    Example In the example, coating materials adapted to form the corrosion-resistant layer as described above were prepared and used for anti-corrosion tests in which the prepared coating materials were mixed with various salts or oxides such as NaVO 3 , Na 2 SO 4 and V 2 O 5 were mixed to investigate anti-corrosion properties.
    Synthesis:
    [0043] The coating materials were synthesized by mixing metal oxides and NH 4 VO 3 (or vanadium oxides) in a desired ratio. The mixed materials were ground and then heated to between 1000-1300 ° C for about 5-24 hours to form a crystalline powder. The powder was then analyzed by an X-ray diffraction (XRD) method to identify the phases.
    Anti corrosion test:
    The above-mentioned powder was mixed with salts or oxides such as NaVO 3 , Na 2 SO 4 , V 2 O 5 in a weight ratio of 6: 1 to 2: 1 and at about 800-920 ° C. for about 1-3 hours heated. The powders were then washed with deionized water and dried for XRD examination. The results showed that the powders were anti-corrosive to the salts and oxides used in the mixture since no new phases appeared in the resulting X-ray diffraction pattern.
    The invention may be embodied in other special forms without departing from the spirit or essential characteristics thereof. The foregoing embodiments are, therefore, to be considered in all respects as illustrative and not restrictive of the invention described herein. The scope of the embodiments of the invention is thus indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein.
    [0046] A gas turbine component includes a substrate formed of a high temperature resistant material and a corrosion resistant layer. The corrosion-resistant layer is inert to the molten salt impurities and contains a high-melting metal vanadate of the formula M x V y O z , where M is selected from the group consisting of alkaline earth metals, transition metals of groups IV and V, rare earth metals and their combinations and where z = x + 2.5y or z = 1.5x + 2.5y or z = 2x + 2.5y.
    CH 708 791 B1
    权利要求:
    Claims (10)
    [1]
    claims
    1. turbine component comprising:
    a substrate formed from a high temperature resistant material and a corrosion resistant layer having a refractory metal vanadate of the formula M x V y O z , where M is selected from the group consisting of alkaline earth metals, transition metals of groups IV and V, rare earth metals and their Combinations are selected and where z = x + 2.5y or z = 1.5x + 2.5y or z = 2x + 2.5y.
    [2]
    2. The turbine component of claim 1, further comprising a thermal barrier coating system disposed between the substrate and at least a portion of the corrosion resistant layer, the corrosion resistant layer being applied directly to the thermal barrier coating system.
    [3]
    3. The turbine component according to claim 2, wherein the thermal barrier coating system has a layer of yttria-stabilized zirconia with a thickness in the range of 100 pm to 1150 pm and a first bonding layer between the layer of yttria-stabilized zirconia and the substrate;
    wherein the first tie layer is preferably RCrAIE, wherein R is iron, cobalt and / or nickel and E is yttrium, a rare earth metal and / or other reactive metal.
    [4]
    4. The turbine component of claim 3, wherein the thermal barrier coating system further comprises a thermally grown oxide layer between the first bonding layer and the layer of zirconia stabilized with yttrium oxide;
    wherein the thermally grown oxide layer is preferably Al 2 O 3 .
    [5]
    The turbine component of claim 3 or 4, further comprising a second tie layer disposed between the substrate and at least a portion of the corrosion resistant layer, the corrosion resistant layer being applied to the second tie layer, the second tie layer for bonding between the substrate and the corrosion-resistant layer, the second bonding layer preferably being an aluminide.
    [6]
    6. Turbine component according to one of claims 1-4, wherein at least part of the corrosion-resistant layer is applied directly to the substrate.
    [7]
    7. Turbine component according to one of claims 1-6, wherein M from the group consisting of Sc, Y, La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, Ca, Mg, Ti, Zr, Hf, Nb, Ta and their combinations are selected; where M is preferably selected from the group consisting of Ce, La, Y, Gd and their combinations.
    [8]
    8. Turbine component according to one of claims 1-7, wherein the corrosion-resistant layer has a thickness in a range from 50 pm to 200 pm; and / or wherein the substrate is made of a super alloy.
    [9]
    9. A method of manufacturing a turbine component comprising:
    Forming a substrate from a high temperature resistant material; and
    Applying a corrosion-resistant layer over the substrate, the corrosion-resistant layer comprising a high-melting metal vanadate of the formula M x V y O z , where M is selected from the group consisting of alkaline earth metals, transition metals of groups IV and V, rare earth metals and their combinations, and wherein z = x + 2.5y or z = 1.5x + 2.5y or z = 2x + 2.5y.
    [10]
    10. The method of claim 9, wherein the corrosion-resistant layer is applied by a method selected from the group consisting of thermal spraying, cold spraying, sol-gel, PVD, CVD, slurries, atomization and combinations thereof.
    CH 708 791 B1
    100
    O2 or SÛ3 gas
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    同族专利:
    公开号 | 公开日
    CN104562006B|2018-08-14|
    JP2015129507A|2015-07-16|
    DE102014115032A1|2015-04-30|
    CH708791A8|2015-06-30|
    CH708791A2|2015-04-30|
    CN104562006A|2015-04-29|
    JP6635651B2|2020-01-29|
    US20150118485A1|2015-04-30|
    引用文献:
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    CA2447978C|2001-05-24|2011-04-26|Fry's Metals, Inc.|Thermal interface material and heat sink configuration|
    US7361386B2|2002-07-22|2008-04-22|The Regents Of The University Of California|Functional coatings for the reduction of oxygen permeation and stress and method of forming the same|
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    EP1752561A1|2005-08-10|2007-02-14|Wärtsilä Schweiz AG|Article protected against high temperature corrosion and reciprocating pistion internal combustion engine or turbine or combustion unit containing the article|
    JP5547415B2|2008-03-19|2014-07-16|関西ペイント株式会社|Rust preventive paint composition|
    US9945036B2|2011-03-22|2018-04-17|General Electric Company|Hot corrosion-resistant coatings and components protected therewith|US9970305B2|2015-09-18|2018-05-15|General Electric Company|Treatment process, oxide-forming treatment composition, and treated component|
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    法律状态:
    2015-05-29| PK| Correction|Free format text: BERICHTIGUNG ERFINDER |
    2015-06-30| PK| Correction|Free format text: ERFINDER BERICHTIGT. |
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    优先权:
    申请号 | 申请日 | 专利标题
    CN201310513463.3A|CN104562006B|2013-10-25|2013-10-25|With the element of anti-corrosion layer protection and the method for manufacturing the element|
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