• 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:
    The invention relates to an article (10) comprising a substrate (20), a bonding layer (30) disposed on the substrate (20), a reinforcing layer (40) disposed on the bonding layer (30) Reinforcing layer has hydrogen to reduce formation of thermally grown oxide, which is produced on the bonding layer (30), and a protective layer (50), which is arranged on the reinforcing layer (40). The invention further relates to a method for producing such an article (10).
    公开号:CH708649B1
    申请号:CH00127/15
    申请日:2013-07-15
    公开日:2017-11-15
    发明作者:Das Rupak；Conrad Schaeffer Jon
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    description
    Background of the Invention The subject matter disclosed herein relates to reinforced articles, such as gas turbine components, and more particularly to reinforced articles that are creep resistant and methods for making the same.
    Gas turbines accelerate gases, forcing the gases into a combustion chamber in which heat is added to increase the volume of the gases. The expanded gases are then directed to a turbine to extract the energy generated by the expanded gases. To withstand the high temperatures and extreme operating conditions in gas turbines, gas turbine components, such as turbine blades, are fabricated from metal, ceramic, or ceramic matrix composites.
    Environmental barrier coatings are applied to the surface of gas turbine components to provide additional protection and to thermally isolate the gas turbine components during operation of the gas turbine at high temperatures. An environmental barrier coating is at least one protective layer applied to a component or substrate using a bonding layer. The protective layer is a ceramic material, and it may also contain multiple layers. The hot gas environment in gas turbines results in oxidation of the bond layer and the formation of a thermally grown oxide layer at the interface between the bond layer and the protective layer.
    The thermally grown oxide layer due to shearing stress e.g. due to centrifugal loading or thermal expansion differences in the outer protective layers of the environmental barrier coatings creeps into one or more layers of the environmental barrier coating. Creep of the thermally grown oxide layer causes cracking in the outer protective layers of the environmental barrier coating and / or the substrate and / or reduces the overall life of the component.
    It is therefore desirable to provide reinforced articles with improved creep resistance, oxidation resistance and / or temperature resistance, and methods of making same which solve one or more of the aforementioned problems.
    Brief Description of the Invention According to the invention, an article comprises: a substrate; a bonding layer disposed on the substrate; a reinforcing layer disposed on the bonding layer, the reinforcing layer comprising hydrogen to reduce formation of thermally grown oxide generated at the bonding layer; and a protective layer disposed on the reinforcing layer.
    According to the invention, a method comprises: arranging a bonding layer on a substrate; Arranging a reinforcing layer on the bonding layer, wherein the reinforcing layer comprises hydrogen; and disposing a protective layer on the reinforcing layer, wherein the reinforcing layer reduces formation of thermally grown oxide generated at the bonding layer.
    These and other advantages and features will become more apparent from the following description taken in conjunction with the accompanying drawings.
    Brief Description of the Drawings The foregoing and other features and advantages of the invention will become more apparent from the following detailed description taken in conjunction with the accompanying drawings, in which:
    Fig. 1 is a cross-sectional partial view of an object;
    FIG. 2 is a cross-sectional partial view of another object; FIG. and
    Fig. 3 is a cross-sectional partial view of another article.
    The detailed description explains embodiments of the invention together with advantages and features by way of example with reference to the drawings.
    Detailed Description of the Invention Embodiments described herein generally relate to reinforced articles and methods of making same. There is provided an article having a reinforcing layer in association with a substrate, a bonding layer and a protective layer.
    Referring to FIG. 1, an article 10 comprises a substrate 20. On the substrate 20, a bonding layer 30 is disposed. A reinforcing layer 40 is disposed on the bonding layer 30. A protective layer 50 is disposed on the reinforcing layer 40.
    The substrate 20 is a metal, a ceramic or a ceramic matrix composite (CMC) material. In one embodiment, the substrate 20 is a gas turbine component. In another embodiment, the substrate is a turbine blade, a vane, a shroud, a liner, a combustor, a transition piece, a rotor component, an exhaust flap, a gasket, or a fuel nozzle. In yet another embodiment, the substrate 20 is a turbine blade that is created using a CMC material.
    The bonding layer 30 assists in bonding the protective layer 50 to the substrate 20. In one embodiment, the bonding layer 30 comprises silicon.
    The protective layer 50 protects the substrate against the effects of environmental conditions to which the article 10 is exposed during operation, such as hot gas, water vapor, and / or oxygen. The protective layer 50 is any material suitable for protecting the substrate 20 from contacting hot gas, water vapor, and / or oxygen when the article 10 is in operation. In one embodiment, the protective layer 50 comprises a ceramic material. In a further embodiment, the protective layer 50 comprises silicon.
    In one embodiment, the protective layer 50 comprises a single layer. In another embodiment, the protective layer 50 has multiple layers of different materials. In yet another embodiment, the protective layer 50 is an environmental barrier coating (EBC) comprising multiple layers of different materials.
    The protective layer 50 is coated on the reinforcing layer 40 using any suitable method, including, but not limited to, air plasma spraying (APS), chemical vapor deposition (CVD), plasma enhanced CVD (PECVD), dip coating, spin coating, and electrophoretic deposition (EPD ), applied.
    During operation of the article 10 at high temperatures, exposure to hot gases, water vapor and / or oxygen results in oxidation of the bonding layer 30. Upon melting and oxidation, the bonding layer 30 forms a viscous fluid layer (not shown), such as a viscous glass layer. The viscous fluid layer has thermally grown oxide (TGO). The viscous fluid layer moves or slides under a shear stress caused by a centrifugal load applied to the article 10 during operation and a difference in thermal expansion coefficients to the protective layer 50. This phenomenon is called "creeping". The creep of the protective layer 50 results in cracking and / or reduces the overall life of the component.
    The reinforcing layer 40 is applied in an interface between the bonding layer 30 and the protective layer 50 using any of the same methods used to apply the protective layer 50. In one embodiment, the reinforcing layer 40 is applied using spin coating. In another embodiment, the reinforcing layer 40 is a continuous layer that is continuous with a surface of the bonding layer 30.
    The reinforcing layer 40 reduces, inhibits or prevents thermally grown oxide generated at the bonding layer 30. The reinforcing layer 40 has hydrogen.
    In one embodiment, the hydrogen molecules in the reinforcing layer 40 reduce or prevent thermally grown oxide formed on the bonding layer 30 by passivation of the surface of the bonding layer 30, whereby the hydrogen molecules form hydrogen bonds with the bonding layer 30. The formation of these hydrogen bonds leaves few possible reaction sites available for oxidation of the bonding layer 30 when in contact with oxygen or oxide ions.
    In another embodiment, the interaction of the hydrogen molecules in the reinforcing layer 40 with the bonding layer 30 and the formation of the hydrogen bonds results in the formation of a meshed network in the reinforcing layer 40. This network serves as a mechanical / chemical barrier against oxidation of the bonding layer 30. The resulting network is superhydrophobic, trapping air and hot gas in the network formed pores. The nanoporous transport of hot gas results in a mean free path which is less than the diameter of a passage, whereby the surface free energy of the reinforcing layer 40 is reduced. Contact between a hot gas and the bonding layer 30 is reduced or prevented, thereby reducing or preventing the amount of the thermally grown oxide formed on the bonding layer 30. The reinforcing layer 40 further promotes bonding or adhesion of the bonding layer 30 to the protective layer 50.
    In yet another embodiment, a fraction or all of the hydrogen molecules in the reinforcing layer 40 react with oxygen molecules present in a thermally grown oxide layer formed on the bonding layer 30. The hydrogen molecules in the reinforcing layer 40 provide a competing reaction to the reaction of the bonding layer 30. The competitive reaction reduces the amount of material lost due to the oxidation of the bonding layer 30. The competitive reaction also reduces or prevents the formation of thermally grown oxide formed on the bonding layer 30.
    权利要求:
    Claims (20)
    [1]
    Referring to Figure 2, in yet another embodiment, the reinforcing layer 40 reverses oxidation of the bonding layer 30, thereby reversing the effects of creep. The hydrogen molecules in the reinforcing layer 40 react with silicon dioxide (SiO 2) in a thermally grown oxide layer 60, which is generated by oxidation of the bonding layer 30. The hydrogen molecules remove oxygen atoms of the silicon dioxide and combine with them. The removal of oxygen from the thermally grown oxide layer 60 reverses the formation of the thermally grown oxide layer 60, thereby reducing or preventing creep. Referring to FIG. 3, in one embodiment, the article 10 further includes an additional reinforcing layer 70. The additional reinforcing layer 70 is disposed on the substrate 20 between the substrate 20 and the bonding layer 30. The additional reinforcement layer 70 comprises the same materials, is applied using the same methods, and has the same characteristics as described above with respect to the reinforcement layer 40. In one embodiment, the additional reinforcement layer 70 comprises the same materials, is applied by the same method, and has the same properties as the reinforcement layer 40. In another embodiment, the additional reinforcement layer 70 comprises other materials, and / or is applied to the substrate 20 by a different method, and / or has different properties than the reinforcement layer 40. The additional reinforcing layer 70, in conjunction with the bonding layer 30, promotes bonding of the protective layer 50 to the substrate 20. The thickness of the reinforcing layer 40 and / or the additional reinforcing layer 70 ranges from about 1 nm to about 100 μm. In a further embodiment, the thickness of the reinforcement layer 40 and / or the additional reinforcement layer 70 is in a range of about 1 nm to about 50 μm. In yet another embodiment, the thickness of the reinforcing layer 40 and / or the additional reinforcing layer 70 is from about 1 nm to about 10 μm. In yet another embodiment, the thickness of the reinforcing layer 40 and / or the additional reinforcing layer 70 is uniform or substantially uniform. The reinforcing layer 40 and / or the additional reinforcing layer 70 provide improved oxidation resistance, creep resistance, and / or temperature resistance equal to or greater than 2400 ° F (1315.556 ° C), thereby improving the performance and life of the article be improved. The method comprises arranging the bonding layer 30 on a substrate 20, arranging a reinforcing layer 40 on the bonding layer 30, and disposing a protective layer 50 on the reinforcing layer 40. In a further embodiment, the method further comprises placing an additional reinforcement layer 70 between the substrate 20 and the bonding layer 30. While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. In addition, it should be understood that while various embodiments of the invention have been described, aspects of the invention may only include some of the described embodiments. Accordingly, the invention should not be construed as being limited by the foregoing description, but is limited only by the scope of the appended claims. claims
    An article (10) comprising: a substrate (20); a bonding layer (30) disposed on the substrate (20); a reinforcing layer (40) disposed on the bonding layer (30), the reinforcing layer (40) comprising hydrogen to reduce formation of thermally grown oxide formed on the bonding layer (30); and a protective layer (50) disposed on the reinforcing layer (40).
    [2]
    The article (10) of claim 1, wherein the substrate (20) comprises a ceramic or ceramic matrix composite.
    [3]
    The article (10) of claim 1, wherein the bonding layer (30) comprises silicon.
    [4]
    The article (10) of claim 1 wherein the reinforcing layer (40) reacts with the thermally grown oxide formed on the bonding layer (30).
    [5]
    The article (10) of claim 1 wherein the reinforcing layer (40) passivates a surface of the bonding layer (30) by forming hydrogen bonds by providing hydrogen.
    [6]
    The article (10) of claim 1, wherein an additional reinforcing layer (70) is disposed between the substrate (20) and the bonding layer (30), wherein the additional reinforcing layer (70) comprises hydrogen to promote formation of thermally grown oxide, which is produced at the bonding layer (30).
    [7]
    The article (10) of claim 1, wherein the protective layer (50) comprises at least two layers.
    [8]
    The article (10) of claim 1, wherein the substrate (10) is a gas turbine component.
    [9]
    The article (10) of claim 1, wherein the substrate (20) is a turbine blade, vane, shroud or shroud, liner, combustor, transition piece, rotor component, exhaust valve, gasket or fuel nozzle.
    [10]
    The article (10) of claim 1, wherein the protective layer (50) is an environmental barrier coating.
    [11]
    11. A method of manufacturing an article (10) according to any one of the preceding claims, comprising: arranging a bonding layer (30) on a substrate (20); Arranging a reinforcing layer (40) on the bonding layer (30), wherein the reinforcing layer (40) comprises hydrogen; and disposing a protective layer (50) on the reinforcing layer (40), wherein the reinforcing layer (40) reduces formation of thermally grown oxide generated at the bonding layer (30).
    [12]
    The method of claim 11, wherein the substrate (20) comprises a ceramic or ceramic matrix composite.
    [13]
    13. The method of claim 11, wherein the bonding layer (30) comprises silicon.
    [14]
    14. The method of claim 11, wherein the reinforcing layer (40) reacts by providing hydrogen with the thermally grown oxide formed on the bonding layer (30).
    [15]
    15. The method of claim 11, wherein the reinforcing layer (40) passivates a surface of the bonding layer (30) by forming hydrogen bonds by providing hydrogen.
    [16]
    The method of claim 11, further comprising disposing an additional reinforcing layer (70) between the substrate (20) and the bonding layer (30), wherein the additional reinforcing layer (70) comprises hydrogen, the additional reinforcing layer (70) forming of thermally grown oxide produced at the tie layer (30).
    [17]
    The method of claim 11, wherein the protective layer (50) comprises at least two layers.
    [18]
    The method of claim 11, wherein the substrate (20) is a gas turbine component.
    [19]
    19. The method of claim 11, wherein the substrate (20) is a turbine blade, a vane, a shroud or shroud, a liner, a combustion chamber, a transition piece, a rotor component, an exhaust valve, a gasket or a fuel nozzle.
    [20]
    The method of claim 11, wherein the protective layer (50) is an environmental barrier coating.
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    同族专利:
    公开号 | 公开日
    DE112013003856T5|2015-05-07|
    WO2014022081A1|2014-02-06|
    US20140037970A1|2014-02-06|
    JP2015530963A|2015-10-29|
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4257735A|1978-12-15|1981-03-24|General Electric Company|Gas turbine engine seal and method for making same|
    DE4229600C1|1992-07-07|1993-11-25|Mtu Muenchen Gmbh|Protective layer for titanium components and process for their manufacture|
    US6906339B2|2001-09-05|2005-06-14|Rensselaer Polytechnic Institute|Passivated nanoparticles, method of fabrication thereof, and devices incorporating nanoparticles|
    JP4969094B2|2004-12-14|2012-07-04|三菱重工業株式会社|Thermal barrier coating member and production thereof, and gas turbine|
    US20060280955A1|2005-06-13|2006-12-14|Irene Spitsberg|Corrosion resistant sealant for EBC of silicon-containing substrate and processes for preparing same|
    US20060280954A1|2005-06-13|2006-12-14|Irene Spitsberg|Corrosion resistant sealant for outer EBL of silicon-containing substrate and processes for preparing same|
    DE102006016995A1|2006-04-11|2007-10-18|Mtu Aero Engines Gmbh|Component with an armor|
    US7416790B2|2006-12-08|2008-08-26|General Electric Company|Coating systems containing rhodium aluminide-based layers|
    FR2918672B1|2007-07-09|2009-10-09|Onera |METHOD FOR PROTECTING THE SURFACE OF AN INTERMETALLIC ALLOY SUBSTRATE BASED ON TITANIUM ALUMINIDE AGAINST CORROSION|
    JP5074123B2|2007-08-08|2012-11-14|株式会社日立製作所|High temperature wear resistant member and method for producing high temperature wear resistant member|
    US20090186237A1|2008-01-18|2009-07-23|Rolls-Royce Corp.|CMAS-Resistant Thermal Barrier Coatings|
    DE102008056741A1|2008-11-11|2010-05-12|Mtu Aero Engines Gmbh|Wear protection layer for Tial|
    US20100129673A1|2008-11-25|2010-05-27|Rolls-Royce Corporation|Reinforced oxide coatings|
    US9056802B2|2009-07-31|2015-06-16|General Electric Company|Methods for making environmental barrier coatings using sintering aids|
    US9061375B2|2009-12-23|2015-06-23|General Electric Company|Methods for treating superalloy articles, and related repair processes|
    US9945036B2|2011-03-22|2018-04-17|General Electric Company|Hot corrosion-resistant coatings and components protected therewith|
    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2021-02-26| PL| Patent ceased|
    优先权:
    申请号 | 申请日 | 专利标题
    US13/566,680|US20140037970A1|2012-08-03|2012-08-03|Reinforced articles and methods of making the same|
    PCT/US2013/050455|WO2014022081A1|2012-08-03|2013-07-15|Reinforced articles and methods of making the same|
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