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1. 发明申请

US20050048305A1 Optical reflector for reducing radiation heat transfer to hot engine parts 有权
标题翻译：用于减少辐射热量传递到热机部件的光学反射器
公开(公告)号：US20050048305A1
公开(公告)日：2005-03-03
申请号：US10651420
申请日：2003-08-29
申请人： John Ackerman , Paul Arszman , Bangalore Nagaraj , Nicole Justis
发明人： John Ackerman , Paul Arszman , Bangalore Nagaraj , Nicole Justis
IPC分类号： B63H1/16 , C23C28/00 , C23C30/00 , F01D5/28 , F23M5/00 , F23R3/00
CPC分类号： F23M5/00 , C23C28/322 , C23C28/345 , C23C28/3455 , C23C30/00 , F01D5/288 , F05D2230/314 , F05D2230/90 , F05D2300/504 , F05D2300/611 , F23M2900/05004 , F23R3/007 , Y02T50/67 , Y02T50/672 , Y02T50/673 , Y10T428/12
摘要： A high temperature gas turbine component for use in the gas flow path that comprises a specular optical reflector coating system. A thin specular optical reflector coating system 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. The thin reflector coating system comprises a thin high temperature and corrosion resistant refractory stabilizing layer, which is applied over a thin reflective metal layer, which is applied over a thin high temperature and corrosion resistant refractory sealing layer. The coating system 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 coating system 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 that only serves to increase the temperature of such a component.
摘要翻译：一种用于气体流路的高温燃气轮机部件，包括镜面光反射涂层系统。将薄镜面光反射涂层系统应用于部件的气体流动路径，即构成热燃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。薄反射器涂层系统包括薄的耐高温和耐腐蚀的耐火稳定层，其被涂覆在薄的反射金属层上，其被涂覆在薄的耐高温和耐腐蚀的耐火密封层上。涂层系统通过可以将反射器充分地粘附到抛光表面而不增加表面粗糙度的方法施加在抛光的热障涂层上。涂层系统将辐射反射回热气流路径或大气中。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这种部件的温度的部件中。

2. 发明申请

US20050039459A1 HIGH TEMPERATURE SPLASH PLATE FOR TEMPERATURE REDUCTION BY OPTICAL REFLECTION AND PROCESS FOR MANUFACTURING 失效
标题翻译：光学反射温度降低的高温刮板和制造工艺
公开(公告)号：US20050039459A1
公开(公告)日：2005-02-24
申请号：US10335657
申请日：2002-12-31
申请人： John Ackermann , Paul Arszman , Bangalore Nagaraj , Craig Young , Nicole Justis
发明人： John Ackermann , Paul Arszman , Bangalore Nagaraj , Craig Young , Nicole Justis
IPC分类号： F01D5/28 , C23C30/00 , F01D25/08 , F02C7/00 , F02C7/24 , F23R3/00 , F23R3/10 , F23R3/42
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。

3. 发明申请

US20050008780A1 Aluminide coating of turbine engine component 失效
标题翻译：涡轮发动机部件的铝酸盐涂层
公开(公告)号：US20050008780A1
公开(公告)日：2005-01-13
申请号：US10615094
申请日：2003-07-08
申请人： John Ackerman , Michael Weimer , Joseph Heaney , William Walston , Bangalore Nagaraj
发明人： John Ackerman , Michael Weimer , Joseph Heaney , William Walston , Bangalore Nagaraj
IPC分类号： C23C10/08 , C23C16/04 , C23C16/20 , C23C16/56 , C23C16/00
CPC分类号： C23C16/56 , C23C10/08 , C23C16/045 , C23C16/20 , Y02T50/67
摘要： A method for forming an aluminide coating on a turbine engine component having an external surface and an internal cavity defined by an internal surface that is connected to the external surface by at least one hole. The method is conducted in a vapor coating container having a hollow interior coating chamber, and includes the steps of loading the coating chamber with the component to be coated; flowing a tri-alkyl aluminum coating gas into the loaded coating chamber at a specified temperature, pressure, and time to deposit an aluminum coating on the external and internal surfaces of the component; and heating the component in a nonoxidizing atmosphere at a specified temperature and time to form an aluminide coating on the external and internal surfaces. The coated component is typically then maintained at an elevated temperature in the presence of oxygen to form an oxide coating on the external and internal surfaces of the component. In one embodiment, the turbine engine component is a turbine engine blade having an external surface and an internal cooling cavity having an internal surface that is connected to the external surface by cooling holes.
摘要翻译：一种用于在涡轮发动机部件上形成铝化物涂层的方法，所述方法具有外表面和由内表面限定的内腔，所述内表面通过至少一个孔连接到所述外表面。该方法在具有中空的内部涂覆室的蒸气涂覆容器中进行，并且包括以下步骤：将涂覆室与待涂覆的部件装载; 在特定温度，压力和时间下将三烷基铝涂层气体流入装载的涂覆室中，以将铝涂层沉积在部件的外表面和内表面上; 并在特定温度和时间下在非氧化气氛中加热组分，以在外表面和内表面上形成铝化物涂层。然后将涂覆的组分在氧的存在下保持在升高的温度，以在组件的外表面和内表面上形成氧化物涂层。在一个实施例中，涡轮发动机部件是具有外表面和内部冷却腔的涡轮发动机叶片，其具有通过冷却孔连接到外表面的内表面。

4. 发明申请

US20050053467A1 Aluminide or chromide coating of turbine engine rotor component 失效
公开(公告)号：US20050053467A1
公开(公告)日：2005-03-10
申请号：US10655835
申请日：2003-09-05
申请人： John Ackerman , Michael Weimer , Joseph Heaney , Robert Zimmerman , Bangalore Nagaraj , Brian Hazel , Nripendra Das
发明人： John Ackerman , Michael Weimer , Joseph Heaney , Robert Zimmerman , Bangalore Nagaraj , Brian Hazel , Nripendra Das
IPC分类号： C23C10/02 , C23C16/16 , C23C16/20 , F01D5/28 , F01D5/14
CPC分类号： F01D5/288 , C23C10/02 , C23C16/16 , C23C16/20 , F05D2230/90 , F05D2300/611 , Y02T50/67
摘要： A turbine engine rotor component, such as a compressor or turbine disk or seal element, is protected from corrosion by depositing an aluminum or chromium coating on the component. The deposition can be performed by a vapor deposition process, such as metal organic chemical vapor deposition (MOCVD), to a coating thickness of from about 0.2 to about 50 microns, typically from about 0.5 to about 3 microns. In one embodiment, the method is conducted in a vapor coating container having a hollow interior coating chamber, and includes the steps of loading the coating chamber with the component to be coated; and flowing a tri-alkyl aluminum or chromium carbonyl coating gas into the loaded coating chamber at a specified temperature, pressure, and time to deposit an aluminum or chromium coating on the surface of the component. The coated component is then heated in a nonoxidizing atmosphere to a specified temperature to form an aluminide or chromide coating on the surface. The coated component is typically then heated or maintained at an elevated temperature in the presence of oxygen to form an oxide coating on the surface of the component.

5. 发明申请

US20050100757A1 Thermal barrier coating having a heat radiation absorbing topcoat 审中-公开
标题翻译：具有散热吸收面漆的隔热涂层
公开(公告)号：US20050100757A1
公开(公告)日：2005-05-12
申请号：US10712821
申请日：2003-11-12
申请人： William Stowell , Bangalore Nagaraj , Andrew Skoog , Jane Murphy , John Ackerman , Daniel Ivkovich
发明人： William Stowell , Bangalore Nagaraj , Andrew Skoog , Jane Murphy , John Ackerman , Daniel Ivkovich
IPC分类号： C23C28/00 , F01D5/28 , B21D39/00
CPC分类号： C23C28/345 , C23C8/42 , C23C8/80 , C23C24/08 , C23C28/321 , C23C28/3215 , C23C28/324 , C23C28/3455 , F01D5/288 , F05D2300/2118 , Y02T50/67 , Y02T50/671 , Y02T50/6765 , Y10T428/12535 , Y10T428/12556 , Y10T428/12611
摘要： Coating systems suitable for protecting components exposed to high-temperature environments, such as the hot gas flow path through a gas turbine engine. A multilayer thermal barrier coating (TBC) system characterized by a low coefficient of thermal conductivity and having a heat-absorbing topcoat comprised of the thermal decomposition product of at least one metallic element and at least one ceramic precursor binder component.
摘要翻译：涂覆系统适用于保护暴露于高温环境的组件，例如通过燃气涡轮发动机的热气流路径。一种多层热障涂层（TBC）系统，其特征在于低导热系数，并具有由至少一种金属元素和至少一种陶瓷前体粘合剂组分的热分解产物组成的吸热顶涂层。

6. 发明申请

US20110151219A1 Coating Systems for Protection of Substrates Exposed to Hot and Harsh Environments and Coated Articles 审中-公开
标题翻译：用于保护暴露于热和恶劣环境和涂层制品的基材的涂层系统
公开(公告)号：US20110151219A1
公开(公告)日：2011-06-23
申请号：US12751667
申请日：2010-03-31
申请人： Bangalore Nagaraj , Terry Lee Few , Timothy P. McCaffrey , Brian P. L'Heureux
发明人： Bangalore Nagaraj , Terry Lee Few , Timothy P. McCaffrey , Brian P. L'Heureux
IPC分类号： B32B7/02 , B32B9/04 , B32B5/00
CPC分类号： C23C28/36 , C23C4/11 , C23C28/3215 , C23C28/345 , C23C28/3455 , F23M2900/05003 , F23M2900/05004 , F23R3/007 , F23R2900/00018 , Y02T50/67 , Y02T50/6765 , Y10T428/24967 , Y10T428/263
摘要： Coating system for reducing CMAS infiltration of substrates includes at least an inner ceramic layer and an outer alumina-containing layer. The outer layer includes up to 50 percent by weight titania. Additional ceramic layers and alumina-containing layers may be provided. The coating may be used for gas turbine engine components. Deposition techniques for the coating layers may depend on the end use of the component. Coated articles include a substrate, an optional bond coat on the substrate and a coating over the bond coat or on at least a portion of the substrate in the absence of a bond coat. The inner ceramic layer(s) exhibit a microstructure indicative of a deposition technique selected from thermal spray, physical vapor deposition, and suspension plasma spray, whereas the outer alumina-containing layer exhibits a microstructure indicative of suspension plasma spray, solution plasma spray, and a high velocity oxygen fuel spray.
摘要翻译：用于减少CMAS浸渗衬底的涂覆系统至少包括内部陶瓷层和外部含氧化铝的层。外层包含多达50重量％的二氧化钛。可以提供另外的陶瓷层和含氧化铝的层。涂层可用于燃气轮机发动机部件。涂层的沉积技术可能取决于组件的最终用途。涂层制品包括基材，基材上的任选的粘合涂层和在粘合涂层上的涂层或在不存在粘合涂层的基底的至少一部分上的涂层。内部陶瓷层表现出指示沉积技术的微观结构，其选自热喷涂，物理气相沉积和悬浮等离子体喷涂，而外部含氧化铝的层显示出指示悬浮等离子体喷涂，溶液等离子喷涂和高速氧气喷雾。

7. 发明申请

US20070224411A1 Protection of thermal barrier coating by impermeable barrier coating 审中-公开
标题翻译：通过防渗涂层保护热障涂层
公开(公告)号：US20070224411A1
公开(公告)日：2007-09-27
申请号：US11607380
申请日：2006-12-01
申请人： Brian Hazel , Irene Spitsberg , Christine Govern , Bangalore Nagaraj
发明人： Brian Hazel , Irene Spitsberg , Christine Govern , Bangalore Nagaraj
IPC分类号： B05D1/36
CPC分类号： C23C28/3215 , C23C28/321 , C23C28/325 , C23C28/345 , C23C28/3455 , C23C28/36 , F05B2230/90 , F05C2253/12 , Y02T50/67 , Y02T50/6765 , Y10T428/12611 , Y10T428/249953 , Y10T428/263 , Y10T428/31678
摘要： According to an embodiment of the invention, disclosed is a composite comprising a porous thermal barrier coating on a metallic part and an impermeable barrier coating adjacent to the outer surface of the thermal barrier coating. The impermeable barrier coating is dense and non-porous and comprises a rare earth silicate, the impermeable barrier coating thereby preventing infiltration of the contaminant composition into the thermal barrier coating.
摘要翻译：根据本发明的一个实施例，公开了一种复合材料，其包括在金属部件上的多孔热障涂层和邻近该热障涂层的外表面的不可渗透的阻隔涂层。不透水的阻隔涂层是致密且无孔的并且包含稀土硅酸盐，不透水的阻隔涂层从而防止污染物组合物渗透到热障涂层中。

8. 发明申请

US20060280962A1 THERMAL/ENVIRONMENTAL BARRIER COATING SYSTEM FOR SILICON-CONTAINING MATERIALS 有权
标题翻译：含硅材料的热/环境阻隔涂层系统
公开(公告)号：US20060280962A1
公开(公告)日：2006-12-14
申请号：US11160185
申请日：2005-06-13
申请人： Brian Hazel , Irene Spitsberg , Christine Govern , Bangalore Nagaraj
发明人： Brian Hazel , Irene Spitsberg , Christine Govern , Bangalore Nagaraj
IPC分类号： B32B17/06 , B32B19/00 , B32B9/00
CPC分类号： C23C28/04 , C04B41/009 , C04B41/52 , C04B41/89 , F01D5/284 , F01D5/288 , Y10T428/12576 , C04B41/4527 , C04B41/5096 , C04B41/5037 , C04B41/5024 , C04B41/5031 , C04B41/5044 , C04B41/5042 , C04B41/4529 , C04B41/522 , C04B35/565 , C04B35/584 , C04B35/806
摘要： A coating system for Si-containing materials, particularly Si-based composites used to produce articles exposed to high temperatures. The coating system is a compositionally-graded thermal/environmental barrier coating (T/EBC) system that includes an intermediate layer containing yttria-stabilized hafnia (YSHf) and mullite, alumina and/or an aluminosilicate, which is used in combination with an inner layer between a Si-containing substrate and the intermediate layer and a thermal-insulating top coat overlying the intermediate layer. The intermediate layer provides environmental protection to the silicon-containing substrate, and has a coefficient of thermal expansion between that of the top coat and that of the inner layer so as to serve as a transition layer therebetween. The intermediate layer is particular well suited for use in combination with an inner layer of an alkaline earth metal aluminosilicate (such as BSAS) and a top coat formed of YSZ or YSHf.
摘要翻译：用于含Si材料的涂层系统，特别是用于生产暴露于高温的制品的Si基复合材料。涂层系统是一种组成分级的热/环境屏障涂层（T / EBC）系统，其包括含有氧化钇稳定的铪（YSHf）和莫来石，氧化铝和/或铝硅酸盐的中间层，其与内部在含Si衬底和中间层之间的层和覆盖中间层的绝热顶涂层。中间层为含硅基材提供环境保护，并且具有顶涂层与内层层之间的热膨胀系数，以便在其间作为过渡层。中间层特别适用于与碱土金属硅铝酸盐（如BSAS）的内层和由YSZ或YSHf形成的顶层组合使用。

9. 发明申请

US20070104969A1 Layered paint coating for turbine blade environmental protection 有权
公开(公告)号：US20070104969A1
公开(公告)日：2007-05-10
申请号：US11266857
申请日：2005-11-04
申请人： Bangalore Nagaraj , Brian Hazel
发明人： Bangalore Nagaraj , Brian Hazel
IPC分类号： B05D1/32 , B05D1/12 , B05D3/02
CPC分类号： C23C24/08 , C23C26/00 , C23C30/00 , F01D5/288 , F05D2300/50212 , Y02T50/67 , Y02T50/671
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 blade further comprises a corrosion resistant coating on 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 corrosion resistant coating comprising a particulate corrosion resistant component comprising from about 5 weight percent to about 100 weight percent corrosion resistant non-alumina particulates having a CTE greater than that of alumina particulates and balance alumina particulates, and a binder component. The present invention also includes methods for making such a gas turbine engine blade.

10. 发明申请

US20060166017A1 THERMAL/ENVIRONMENTAL BARRIER COATING WITH TRANSITION LAYER FOR SILICON-COMPRISING MATERIALS 有权
标题翻译：具有过渡层的热/环境阻挡层涂层用于含硅材料
公开(公告)号：US20060166017A1
公开(公告)日：2006-07-27
申请号：US11040158
申请日：2005-01-21
申请人： Irene Spitsberg , Christine Govern , Bangalore Nagaraj , Brian Hazel , David Mitchell
发明人： Irene Spitsberg , Christine Govern , Bangalore Nagaraj , Brian Hazel , David Mitchell
IPC分类号： B32B15/04 , C25D5/42
CPC分类号： C04B35/195 , C04B35/16 , C04B35/185 , C04B41/009 , C04B41/52 , C04B41/89 , C04B2111/00405 , C04B2235/3208 , C04B2235/3213 , C04B2235/3215 , C04B2235/3224 , C04B2235/3427 , C04B2235/3436 , C04B2235/3454 , C04B2235/3463 , C23C28/042 , C23C28/048 , F05B2230/90 , F05C2253/12 , Y10T428/12576 , Y10T428/12667 , Y10T428/12729 , C04B41/4527 , C04B41/5024 , C04B41/5042 , C04B41/5051 , C04B41/5044 , C04B41/5027 , C04B41/522 , C04B35/565 , C04B35/584 , C04B35/806
摘要： An article comprising a substrate formed of a silicon-comprising material, such as an article exposed to the hostile thermal environment of a gas turbine engine. The article further comprises an environmental barrier layer, e.g., an alkaline earth metal aluminosilicate, and a top coat comprising zirconia or hafnia stabilized with an oxide of a metal selected from the group consisting of magnesium, calcium, scandium, yttrium, and lanthanide metals, and mixtures thereof. The article further comprises a transition layer between the environmental barrier layer and the top coat, the transition layer comprising zirconia or hafnia stabilized with an oxide of a metal selected from the group consisting of magnesium, calcium, scandium, yttrium, and lanthanide metals; and a low CTE oxide selected from the group consisting of niobia and tantala; and mixtures thereof. A method for preparing a thermal/environmental barrier coating system on a substrate formed of a silicon-comprising material is also disclosed.
摘要翻译：一种制品，其包括由含硅材料形成的基底，例如暴露于燃气涡轮发动机的恶劣热环境的制品。该制品还包括环境屏障层，例如碱土金属铝硅酸盐，以及包含氧化锆或氢氧化铪的顶涂层，所述氧化锆或铪被选自镁，钙，钪，钇和镧系金属的金属氧化物稳定，及其混合物。该制品还包括在环境阻挡层和顶部涂层之间的过渡层，过渡层包含用选自镁，钙，钪，钇和镧系金属的金属的氧化物稳定的氧化锆或氢化铪; 和选自iobia和tantala的低CTE氧化物; 及其混合物。还公开了一种在由含硅材料形成的基底上制备热/环境屏障涂层系统的方法。

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