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公开(公告)号：US20100040476A1
公开(公告)日：2010-02-18
申请号：US11968368
申请日：2008-01-02
IPC分类号： F01D5/28
CPC分类号： C23C10/04 , C23C10/18 , C23C10/26 , C23C10/28 , C23C10/52 , C23C10/60 , F01D5/288 , Y10T428/12931
摘要： A gas turbine engine turbine blade comprising an airfoil section, a platform section, an under platform section, and a dovetail section, an exterior surface of the dovetail section comprising a shank exterior surface and a serrated exterior surface. The blade further comprises a silicon-modified diffusion aluminide layer a surface of a turbine blade section selected from the group consisting of an exterior surface of the under platform section, the exterior surface of the dovetail section, and combinations thereof, the silicon modified diffusion aluminide layer having a concentration of silicon at a surface of the silicon-modified diffusion aluminide layer in the range of about 1 weight percent to about 10 weight percent and a concentration of aluminum at the surface of the silicon modified diffusion aluminide layer in the range of about 5 weight percent to about 25 weight percent.
摘要翻译： 一种燃气涡轮发动机涡轮叶片，包括翼型部分，平台部分，下平台部分和燕尾部分，燕尾部分的外表面包括柄外表面和锯齿形外表面。 叶片还包括硅改性的扩散铝化物层，涡轮叶片部分的表面，其选自下部平台部分的外表面，燕尾部分的外表面及其组合，硅改性扩散铝化物 在硅改性扩散铝化物层的表面具有约1重量％至约10重量％的范围内的具有硅浓度的层，并且在硅改性扩散铝化物层的表面处的铝的浓度在约 5重量％至约25重量％。
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公开(公告)号：US07597934B2
公开(公告)日：2009-10-06
申请号：US11358339
申请日：2006-02-21
CPC分类号： C23C10/04 , C23C10/18 , C23C10/26 , C23C10/28 , C23C10/52 , C23C10/60 , F01D5/288 , Y10T428/12931
摘要： A method for making a gas turbine engine turbine blade comprising an airfoil section a platform section, an under platform section, and a dovetail section, the exterior surface of the dovetail section comprising a shank exterior surface and a serrated exterior surface. The blade further includes a silicon-modified diffusion aluminide layer a surface of a turbine blade section selected from the group consisting of the exterior surface of the under platform section, the exterior surface of the dovetail section, and combinations thereof, the aluminide layer having a concentration of silicon at a surface of the aluminide layer in the range of about 1 weight percent to about 10 weight percent and a concentration of aluminum at the surface of the aluminide layer in the range of about 5 weight percent to about 25 weight percent.
摘要翻译： 一种用于制造燃气涡轮发动机涡轮叶片的方法，其包括翼型部分，平台部分，下平台部分和燕尾部分，燕尾部分的外表面包括柄外表面和锯齿形外表面。 叶片还包括硅改性的扩散铝化物层，涡轮叶片部分的表面，其选自下部平台部分的外表面，燕尾部分的外表面及其组合，铝化物层具有 在铝化物层的表面上硅的浓度在约1重量％至约10重量％的范围内，铝化物层的表面的铝浓度在约5重量％至约25重量％的范围内。
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3.发明申请Layered thermal barrier coatings containing lanthanide series oxides for improved resistance to CMAS degradation 审中-公开包含镧系元素氧化物的分层热障涂层，以改善对CMAS降解的抵抗力公开(公告)号：US20070160859A1
公开(公告)日：2007-07-12
申请号：US11327091
申请日：2006-01-06
IPC分类号： B32B15/04
CPC分类号： C23C28/042 , C23C28/048 , C23C28/321 , C23C28/3215 , C23C28/325 , C23C28/345 , C23C28/3455 , C23C28/36 , F01D5/288 , F05D2300/2118 , Y02T50/67 , Y02T50/671 , Y02T50/6765
摘要： A coating applied as a two layer system. The outer layer is an oxide of a group IV metal selected from the group consisting of zirconium oxide, hafnium oxide and combinations thereof, which are doped with an effective amount of a lanthanum series oxide. These metal oxides doped with a lanthanum series addition comprises a high weight percentage of the outer coating. As used herein, lanthanum series means an element selected from the group consisting of 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) and combinations thereof, and lanthanum series oxides are oxides of these elements. When the zirconium oxide is doped with an effective amount of a lanthanum series oxide, a dense reaction layer is formed at the interface of the outer layer of TBC and the CMAS. This dense reaction layer prevents CMAS infiltration below it. The second layer, or inner layer underlying the outer layer, comprises a layer of partially stabilized zirconium oxide.
摘要翻译： 涂层作为两层体系。 外层是掺杂有有效量的镧系氧化物的选自氧化锆，氧化铪及其组合的IV族金属的氧化物。 掺杂有镧系列添加剂的这些金属氧化物包括外涂层的高重量百分比。 如本文所用，镧系指选自镧（La），铈（Ce），镨（Pr），钕（Nd），ium（Pm），钐（Sm），铕（Eu）， 钆（Gd），铽（Tb），镝（Dy），钬（Ho），铒（Er），ium（Tm），镱（Yb），镥（Lu）及其组合，以及镧系氧化物是 这些元素。 当氧化锆掺杂有效量的镧系氧化物时，在TBC的外层和CMAS的界面处形成致密的反应层。 这种致密的反应层可防止CMAS渗透在其下方。 外层的第二层或内层包含部分稳定的氧化锆层。
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公开(公告)号：US07993759B2
公开(公告)日：2011-08-09
申请号：US11968368
申请日：2008-01-02
CPC分类号： C23C10/04 , C23C10/18 , C23C10/26 , C23C10/28 , C23C10/52 , C23C10/60 , F01D5/288 , Y10T428/12931
摘要： A gas turbine engine turbine blade comprising an airfoil section, a platform section, an under platform section, and a dovetail section, an exterior surface of the dovetail section comprising a shank exterior surface and a serrated exterior surface. The blade further comprises a silicon-modified diffusion aluminide layer a surface of a turbine blade section selected from the group consisting of an exterior surface of the under platform section, the exterior surface of the dovetail section, and combinations thereof, the silicon modified diffusion aluminide layer having a concentration of silicon at a surface of the silicon-modified diffusion aluminide layer in the range of about 1 weight percent to about 10 weight percent and a concentration of aluminum at the surface of the silicon modified diffusion aluminide layer in the range of about 5 weight percent to about 25 weight percent.
摘要翻译： 一种燃气涡轮发动机涡轮叶片，包括翼型部分，平台部分，下平台部分和燕尾部分，燕尾部分的外表面包括柄外表面和锯齿形外表面。 叶片还包括硅改性的扩散铝化物层，涡轮叶片部分的表面，其选自下部平台部分的外表面，燕尾部分的外表面及其组合，硅改性扩散铝化物 在硅改性扩散铝化物层的表面具有约1重量％至约10重量％的范围内的具有硅浓度的层，并且在硅改性扩散铝化物层的表面处的铝的浓度在约 5重量％至约25重量％。
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公开(公告)号：US20070196686A1
公开(公告)日：2007-08-23
申请号：US11358339
申请日：2006-02-21
CPC分类号： C23C10/04 , C23C10/18 , C23C10/26 , C23C10/28 , C23C10/52 , C23C10/60 , F01D5/288 , Y10T428/12931
摘要： The present invention is a gas turbine engine turbine blade comprising an airfoil section having at least an exterior surface, a platform section having an exterior surface, an under platform section having an exterior surface, and a dovetail section having an exterior surface, the exterior surface of the dovetail section comprising a shank exterior surface and a serrated exterior surface. The blade further comprises a silicon-modified diffusion aluminide layer a surface of a turbine blade section selected from the group consisting of the exterior surface of the under platform section, the exterior surface of the dovetail section, and combinations thereof, the silicon modified diffusion aluminide layer having a concentration of silicon at a surface of the silicon-modified diffusion aluminide layer in the range of about 1 weight percent to about 10 weight percent and a concentration of aluminum at the surface of the silicon modified diffusion aluminide layer in the range of about 5 weight percent to about 25 weight percent. The present invention is also a method for making such a gas turbine engine blade.
摘要翻译： 本发明是一种燃气涡轮发动机涡轮叶片，其包括具有至少外表面的翼型部分，具有外表面的平台部分，具有外表面的下平台部分和具有外表面的燕尾部分， 的燕尾部分包括柄外表面和锯齿形外表面。 叶片还包括硅改性的扩散铝化物层，涡轮叶片部分的表面，其选自下平台部分的外表面，燕尾部分的外表面及其组合，硅改性扩散铝化物 在硅改性扩散铝化物层的表面具有约1重量％至约10重量％的范围内的具有硅浓度的层，并且在硅改性扩散铝化物层的表面处的铝的浓度在约 5重量％至约25重量％。 本发明也是制造这种燃气涡轮发动机叶片的方法。
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公开(公告)号：US07666528B2
公开(公告)日：2010-02-23
申请号：US12317032
申请日：2008-12-17
CPC分类号： C23C26/00 , C23C28/3215 , C23C28/3455 , C23C30/00 , F01D5/284 , F01D5/288 , F05D2230/31 , F05D2260/95 , Y02T50/67
摘要： According to an embodiment of the invention, an article of manufacture for use in a gas turbine engine is disclosed. The article comprises a part having a surface covered with a ceramic thermal barrier coating. The thermal barrier coating has an outer surface covered with a sacrificial phosphate coating, wherein the sacrificial phosphate coating reacts with contaminant compositions to prevent contaminant infiltration into the thermal barrier coating.
摘要翻译： 根据本发明的实施例，公开了一种用于燃气涡轮发动机的制品。 该制品包括具有覆盖有陶瓷热障涂层的表面的部分。 热障涂层具有覆盖有牺牲磷酸盐涂层的外表面，其中牺牲磷酸盐涂层与污染物组合物反应以防止污染物渗透到热障涂层中。
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7.发明申请Low conductivity, thermal barrier coating system for ceramic matrix composite (CMC) articles 审中-公开陶瓷基复合材料（CMC）制品的低导电性，热障涂层体系公开(公告)号：US20080292803A1
公开(公告)日：2008-11-27
申请号：US11903096
申请日：2007-09-20
IPC分类号： B05D1/36
CPC分类号： C04B41/89 , C04B41/009 , C04B41/52 , C23C28/042 , C23C28/322 , C23C28/345 , C23C28/3455 , C04B41/5096 , C04B41/5035 , C04B41/522 , C04B41/4527 , C04B41/5024 , C04B41/5037 , C04B41/5042 , C04B2111/00405 , C04B41/5044 , C04B35/565 , C04B35/806
摘要： In accordance with an embodiment of the invention, a thermal barrier coating for inclusion in a thermal barrier coating/environmental barrier coating system (TBC/EBC system) for use on a silicon based substrate is disclosed. The thermal barrier coating comprising up to about 9 mol percent of a stabilizer and up to 91 mol percent of primary oxide selected from the group consisting of zirconia, hafnia and mixtures thereof. The stabilizer comprises: a first metal oxide selected from the group consisting of yttria, calcia, ceria, scandia, magnesia, india and mixtures thereof, a second metal oxide of a trivalent metal atom selected from the group consisting of lanthana, gadolinia, neodymia, samaria, dysprosia, ytterbia, erbia, and mixtures thereof. The first metal oxide is in an amount of from about 3 to about 5 mol %, the second metal oxide is in an amount of from about 0.25 to about 6 mol %.
摘要翻译： 根据本发明的一个实施例，公开了一种用于包含在用于硅基衬底的隔热涂层/环境阻挡涂层系统（TBC / EBC系统）中的热障涂层。 所述热障涂层包括高达约9mol％的稳定剂和至多91mol％的选自氧化锆，铪的主要氧化物及其混合物。 稳定剂包括：选自氧化钇，氧化钙，二氧化铈，钪，氧化镁，印度及其混合物的第一金属氧化物，选自氧化镧，氧化钆，氧化钕， samaria，dysprosia，ytterbia，erbia及其混合物。 第一金属氧化物的量为约3至约5mol％，第二金属氧化物的量为约0.25至约6mol％。
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8.发明授权High temperature turbine nozzle for temperature reduction by optical reflection and process for manufacturing 失效用于通过光学反射降温的高温涡轮喷嘴和用于制造的工艺公开(公告)号：US06926496B2
公开(公告)日：2005-08-09
申请号：US10335486
申请日：2002-12-31
CPC分类号： F23M5/00 , F23M2900/05004 , F23R3/002 , Y02T50/67
摘要： A high temperature gas turbine component for use in the gas flow path that also is a specular optical reflector. A thin layer of a high temperature reflector is applied to the gas flow path of the component, that is, the surface of the component that forms a boundary for hot combustion gases. The component typically includes a thermal barrier coating overlying the high temperature metallic component that permits the component to operate at elevated temperatures. The thermal barrier coating must be polished in order to provide a surface that can suitably reflect the radiation into the gas flow path. A thin layer of the high temperature reflector the is applied over the polished thermal barrier coating by a process that can adequately adhere the reflector to the polished surface without increasing the roughness of the surface. The high temperature reflector can be applied to any surface aft of the compressor, such as on a turbine nozzle. The surface reflects radiation back into the hot gas flow path. The reflected radiation is not focused onto any other hardware component. The design of the component is such that the radiation is returned to the gas flow path rather than absorbed into a component wall that only serves to increase the temperature of the wall.
摘要翻译： 用于气体流路的高温燃气轮机部件，其也是镜面光学反射器。 将高温反射器的薄层施加到部件的气体流动路径，即构成热燃烧气体边界的部件的表面。 该部件通常包括覆盖高温金属部件的热障涂层，其允许部件在升高的温度下操作。 必须抛光热障涂层，以便提供可以适当地将辐射反射到气体流动路径中的表面。 通过能够将反射器充分地粘附到抛光表面而不增加表面粗糙度的工艺，将高温反射体的薄层施加在抛光的热障涂层上。 高温反射器可以应用于压缩机后面的任何表面，例如在涡轮喷嘴上。 该表面将辐射反射回热气流路径。 反射的辐射没有集中在任何其他硬件组件上。 部件的设计使得辐射返回到气体流动路径而不是被吸收到仅用于增加壁的温度的部件壁中。
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9.发明授权Method for improving the performance of oxidizable ceramic materials in oxidizing environments 失效在氧化环境中提高可氧化陶瓷材料性能的方法公开(公告)号：US06485791B1
公开(公告)日：2002-11-26
申请号：US09544041
申请日：2000-04-06
申请人： Bangalore A. Nagaraj
发明人： Bangalore A. Nagaraj
IPC分类号： C23C1430
CPC分类号： C04B41/009 , C04B41/52 , C04B41/89 , C23C28/04 , C04B41/4529 , C04B41/5035 , C04B41/53 , C04B41/5031 , C04B41/522 , C04B41/0072 , C04B41/5037 , C04B41/5042 , C04B35/565 , C04B35/584 , C04B35/806
摘要： Improved adhesion of thermal barrier coatings to nonmetallic substrates using a dense layer of ceramic on an underlying nonmetallic substrate that includes at least one oxidizable component. The improved adhesion occurs because the application of the dense ceramic layer forms a diffusion barrier for oxygen. This diffusion barrier prevents the oxidizable component of the substrate from decomposing. The present invention applies ceramic by a process that deposits a relatively thick and dense ceramic layer on the underlying substrate. The formation of the dense layer of ceramic avoids the problem of void formation associated with ceramic formation by most prior art thermal decomposition processes. The formation of voids has been associated with premature spalling of thermal barrier layers and other protective layers applied to substrates.
摘要翻译： 使用包含至少一种可氧化组分的下层非金属基底上的致密陶瓷层来改善热障涂层对非金属基底的粘合性。 由于应用致密的陶瓷层形成氧的扩散阻挡层，所以发生改善的粘附。 该扩散阻挡层防止基底的可氧化成分分解。 本发明通过在下面的衬底上沉积相对厚且致密的陶瓷层的方法来应用陶瓷。 通过大多数现有技术的热分解过程，陶瓷致密层的形成避免了与陶瓷形成相关的空隙形成的问题。 空隙的形成已经与施加到基底上的热障层和其它保护层的过早剥落有关。
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公开(公告)号：US06283715B1
公开(公告)日：2001-09-04
申请号：US09405479
申请日：1999-09-24
IPC分类号： F01D514
CPC分类号： C23C28/3215 , C23C4/00 , C23C28/321 , C23C28/325 , C23C28/34 , C23C28/3455 , F01D5/288 , Y02T50/67 , Y02T50/673
摘要： A gas turbine component has a platform, a shank extending downwardly from the platform, and an airfoil extending upwardly from the platform. The gas turbine component is coated by first applying a first chromide layer overlying the base metal of at least a portion of the shank and interdiffused therewith, and second applying a second coating on at least a portion of the airfoil. The second coating optionally includes a second chromide layer contacting the base metal of the airfoil and interdiffused therewith, and includes an aluminide protective layer overlying the second chromide layer. The first chromide layer on the shank and the second chromide layer on the airfoil may be within the same chromium composition range (for example, from about 20 to about 30 weight percent chromium) and thickness range (for example, from about 0.001 to about 0.002 inch), and deposited at the same time.
摘要翻译： 燃气轮机部件具有平台，从平台向下延伸的柄部以及从平台向上延伸的翼型件。 通过首先施加覆盖柄的至少一部分的基底金属并与其相互扩散的第一铬化物层，并且在翼型的至少一部分上施加第二涂层来涂覆燃气轮机部件。 第二涂层任选地包括与翼型件的母材接触并与其相互扩散的第二铬化物层，并且包括覆盖在第二铬化物层上的铝化物保护层。 刀柄上的第一铬化物层和翼型上的第二铬化物层可以在相同的铬组成范围内（例如，约20至约30重量％的铬）和厚度范围（例如，约0.001至约0.002 英寸），并同时沉积。
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