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1.发明授权公开(公告)号：US07181915B2
公开(公告)日：2007-02-27
申请号：US10335647
申请日：2002-12-31
申请人： John Frederick Ackermann , Paul V. Arszman , Bangalore A. Nagaraj , Craig D. Young , Nicole Justis
发明人： John Frederick Ackermann , Paul V. Arszman , Bangalore A. Nagaraj , Craig D. Young , Nicole Justis
CPC分类号： F01D5/288 , F05D2230/90 , F05D2300/133 , F05D2300/143 , F05D2300/211 , F05D2300/504 , F05D2300/611 , F23M2900/05004 , F23R3/002 , Y02T50/67 , Y02T50/672 , Y02T50/673
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 centerbody. The surface reflects radiation back into the hot gas flow path or into the atmosphere. 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 or sent to the atmosphere 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部的任何表面，例如在中心体上。 该表面将辐射反射回热气流路或进入大气。 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或送到大气中，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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2.发明授权公开(公告)号：US06925811B2
公开(公告)日：2005-08-09
申请号：US10335442
申请日：2002-12-31
CPC分类号： F23R3/06 , F23M5/00 , F23M2900/05004 , F23R3/002 , F23R2900/03042 , Y02T50/67 , Y02T50/675 , Y10T428/12542
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 flow path surface 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 then 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 combustor wall. 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 which 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流路表面，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。 然后通过可以将反射器充分地粘附到抛光表面而不增加表面的粗糙度的工艺，将高温反射体的薄层施加在抛光的热障涂层上。 高温反射器可以施加到压缩机后面的任何表面，例如在燃烧器壁上。 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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3.发明授权公开(公告)号：US07003959B2
公开(公告)日：2006-02-28
申请号：US10335657
申请日：2002-12-31
IPC分类号： F23M5/00
CPC分类号： F01D25/08 , F23M2900/05004 , F23R3/002 , F23R3/10 , Y02T50/67 , Y02T50/672 , Y02T50/675 , Y10T428/12542
摘要： A high temperature splash plate for use in the combustor of a gas turbine engine that also is a specular optical reflector. A thin layer of a high temperature reflector is applied to the surface of the splash plate 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 then 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 surface reflects radiation in the direction of the turbine back into the hot gas flow path. The reflected radiation is not focused onto any other hardware component. The design of the splash plate is such that the radiation is not directed to an adjacent component, which only serves to increase the temperature of the wall of the component.
摘要翻译： 用于燃气轮机发动机的燃烧室中的高温飞溅板，其也是镜面光学反射器。 将高温反射器的薄层施加到形成热燃烧气体边界的部件的飞溅板的表面上。 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。 然后通过可以将反射器充分地粘附到抛光表面而不增加表面的粗糙度的工艺，将高温反射体的薄层施加在抛光的热障涂层上。 该表面将涡轮方向上的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。 飞溅板的设计使得辐射不被引导到相邻的部件，其仅用于增加部件的壁的温度。
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4.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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公开(公告)号：US06842980B2
公开(公告)日：2005-01-18
申请号：US10274315
申请日：2002-10-17
CPC分类号： F23R3/10 , F23R3/002 , F23R2900/00005 , Y10T29/4932 , Y10T29/49321 , Y10T29/49323 , Y10T29/49346 , Y10T29/49982 , Y10T29/49988
摘要： A combustor for a gas turbine engine includes a deflector assembly that enhances heat transfer from the combustor and minimizes low cycle fatigue stresses induced within the combustor. The deflector assembly includes a plurality of deflectors secured to a spectacle plate. Each deflector has tapered edges and includes a plurality of cylindrical projections extending outward from the deflector to facilitate heat transfer. The projections include rounded edges and are arranged in a high density pattern. The deflector is coated with a thermal barrier coating and a bondcoat to minimize exposure to hot combustion gases or flame radiation.
摘要翻译： 用于燃气涡轮发动机的燃烧器包括偏转器组件，该偏转器组件增强了来自燃烧器的热传递并使在燃烧器内感应的低循环疲劳应力最小化。 偏转器组件包括固定到眼镜板的多个偏转器。 每个偏转器具有锥形边缘并且包括从偏转器向外延伸的多个圆柱形凸起以促进热传递。 突起包括圆形边缘并且以高密度图案布置。 偏转器涂有热障涂层和粘合剂涂层，以最小化暴露于热燃烧气体或火焰辐射。
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公开(公告)号：US06557349B1
公开(公告)日：2003-05-06
申请号：US09550522
申请日：2000-04-17
IPC分类号： F02C100
CPC分类号： F23R3/10 , F23R3/002 , F23R2900/00005 , Y10T29/4932 , Y10T29/49321 , Y10T29/49323 , Y10T29/49346 , Y10T29/49982 , Y10T29/49988
摘要： A combustor for a gas turbine engine includes a deflector assembly that enhances heat transfer from the combustor and minimizes low cycle fatigue stresses induced within the combustor. The deflector assembly includes a plurality of deflectors secured to a spectacle plate. Each deflector has tapered edges and includes a plurality of cylindrical projections extending outward from the deflector to facilitate heat transfer. The projections include rounded edges and are arranged in a high density pattern. The deflector is coated with a thermal barrier coating and a bondcoat to minimize exposure to hot combustion gases or flame radiation.
摘要翻译： 用于燃气涡轮发动机的燃烧器包括偏转器组件，该偏转器组件增强了来自燃烧器的热传递并使在燃烧器内感应的低循环疲劳应力最小化。 偏转器组件包括固定到眼镜板的多个偏转器。 每个偏转器具有锥形边缘并且包括从偏转器向外延伸的多个圆柱形凸起以促进热传递。 突起包括圆形边缘并且以高密度图案布置。 偏转器涂有热障涂层和粘合剂涂层，以最小化暴露于热燃烧气体或火焰辐射。
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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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8.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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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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