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1. 发明授权

US06933066B2 Thermal barrier coating protected by tantalum oxide and method for preparing same 失效
标题翻译：由氧化钽保护的热障涂层及其制备方法
公开(公告)号：US06933066B2
公开(公告)日：2005-08-23
申请号：US10317731
申请日：2002-12-12
申请人： Bangalore Aswatha Nagaraj , John Frederick Ackerman , William Randolph Stowell , Ching-Pang Lee
发明人： Bangalore Aswatha Nagaraj , John Frederick Ackerman , William Randolph Stowell , Ching-Pang Lee
IPC分类号： B32B3/00 , B32B15/04 , C23C16/06 , C23C28/00 , C23C30/00 , F03B3/12
CPC分类号： C23C28/00 , C23C30/00 , F01D5/288 , F05D2240/11 , F05D2300/21 , Y10T428/24917 , Y10T428/24926 , Y10T428/265
摘要： A thermal barrier coating for an underlying metal substrate of articles that operate at, or are exposed to, high temperatures, as well as being exposed to environmental contaminant compositions. This coating includes an inner layer nearest to the underlying metal substrate comprising a ceramic thermal barrier coating material, as well as an outer layer having an exposed surface and comprising tantalum oxide in an amount sufficient to protect the thermal barrier coating at least partially against environmental contaminants that become deposited on the exposed surface and optionally an intermediate layer between the inner and outer layers comprising alumina. This coating can be used to provide a thermally protected article having a metal substrate and optionally a bond coat layer adjacent to and overlaying the metal substrate. The thermal barrier coating can be prepared by forming the inner layer comprising the ceramic thermal barrier material, optionally forming the intermediate layer comprising the alumina over the inner layer, and then forming the outer layer comprising the tantalum oxide over the intermediate (inner) layer.
摘要翻译：用于在高温下操作或暴露于高温以及暴露于环境污染物组合物的制品的基础金属基底的热障涂层。该涂层包括最接近底层金属基底的内层，其包含陶瓷热障涂层材料，以及具有暴露表面的外层，并且包含足以保护热障涂层的氧化钽至少部分地防止环境污染物其沉积在暴露的表面上，并且任选地沉积在包含氧化铝的内层和外层之间的中间层。该涂层可用于提供具有金属基底和任选的与金属基底相邻并覆盖金属基底的粘合涂层的热保护制品。可以通过形成包含陶瓷热障材料的内层，任选地在内层上形成包含氧化铝的中间层，然后在中间（内）层上形成包含氧化钽的外层来制备热障涂层。

2. 发明授权

US06582834B2 Anti-stick coating for internal passages of turbine components 失效
公开(公告)号：US06582834B2
公开(公告)日：2003-06-24
申请号：US09879691
申请日：2001-06-12
申请人： Bangalore Aswatha Nagaraj , Ching-Pang Lee , William Randolph Stowell , Aaron Dennis Gastrich
发明人： Bangalore Aswatha Nagaraj , Ching-Pang Lee , William Randolph Stowell , Aaron Dennis Gastrich
IPC分类号： B32B1504
CPC分类号： C23C16/045 , C23C16/40 , C23C28/00 , F01D5/288 , F05D2230/90 , F05D2300/611 , Y10T428/12458 , Y10T428/12611 , Y10T428/12618 , Y10T428/12736 , Y10T428/12944 , Y10T428/24975 , Y10T428/265
摘要： An anti-stick coating that inhibits the adhesion of contaminants that form deposits on the internal cooling passages of gas turbine engine components. The anti-stick coating is formed as an outer coating of the internal cooling passages, and preferably overlies an environmental coating such as a diffusion aluminide coating formed on the passage surfaces. The outer coating has a thickness of not greater than three micrometers, and is resistant to adhesion by dirt contaminants as a result of comprising at least one layer of tantala, titania, hafnia, niobium oxide, yttria, silica and/or alumina. The outer coating is preferably deposited directly on the environmental coating by chemical vapor deposition.

3. 发明授权

US06921251B2 Aluminide or chromide coating of turbine engine rotor component 失效
标题翻译：涡轮发动机转子部件的铝酸盐或铬酸盐涂层
公开(公告)号：US06921251B2
公开(公告)日：2005-07-26
申请号：US10655835
申请日：2003-09-05
申请人： John Frederick Ackerman , Michael James Weimer , Joseph Aloysius Heaney , Robert George Zimmerman, Jr. , Bangalore Aswatha Nagaraj , Brian Thomas Hazel , Nripendra Nath Das
发明人： John Frederick Ackerman , Michael James Weimer , Joseph Aloysius Heaney , Robert George Zimmerman, Jr. , Bangalore Aswatha Nagaraj , Brian Thomas Hazel , Nripendra Nath 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.
摘要翻译：诸如压缩机或涡轮盘或密封元件的涡轮发动机转子部件通过在组件上沉积铝或铬涂层来防止腐蚀。沉积可以通过气相沉积工艺（例如金属有机化学气相沉积（MOCVD））进行，涂层厚度为约0.2至约50微米，通常为约0.5至约3微米。在一个实施方案中，该方法在具有中空内部涂覆室的蒸气涂覆容器中进行，并且包括以下步骤：将涂覆室与要涂覆的组分装载; 并在规定的温度，压力和时间下将三烷基铝或铬羰基涂覆气体流入装载的涂覆室，以在组件的表面上沉积铝或铬涂层。然后将涂覆的组分在非氧化气氛中加热至特定温度，以在表面上形成铝化物或铬酸盐涂层。然后通常在氧存在下将涂覆的组分加热或保持在升高的温度，以在组分的表面上形成氧化物涂层。

4. 发明授权

US06905730B2 Aluminide coating of turbine engine component 失效
公开(公告)号：US06905730B2
公开(公告)日：2005-06-14
申请号：US10615094
申请日：2003-07-08
申请人： John Frederick Ackerman , Michael James Weimer , Joseph Aloysius Heaney , William Scott Walston , Bangalore Aswatha Nagaraj
发明人： John Frederick Ackerman , Michael James Weimer , Joseph Aloysius Heaney , William Scott Walston , Bangalore Aswatha Nagaraj
IPC分类号： C23C10/08 , C23C16/04 , C23C16/20 , C23C16/56
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.

5. 发明授权

US07208230B2 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：US07208230B2
公开(公告)日：2007-04-24
申请号：US10651420
申请日：2003-08-29
申请人： John Frederick Ackerman , Paul Vincent Arszman , Bangalore Aswatha Nagaraj , Nicole Justis
发明人： John Frederick Ackerman , Paul Vincent Arszman , Bangalore Aswatha Nagaraj , Nicole Justis
IPC分类号： B32B15/00 , B32B15/04
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。

6. 发明授权

US06627323B2 Thermal barrier coating resistant to deposits and coating method therefor 失效
标题翻译：隔热涂层耐沉积及其涂布方法
公开(公告)号：US06627323B2
公开(公告)日：2003-09-30
申请号：US10079036
申请日：2002-02-19
申请人： Bangalore Aswatha Nagaraj , Jeffrey Lawrence Williams , John Frederick Ackerman
发明人： Bangalore Aswatha Nagaraj , Jeffrey Lawrence Williams , John Frederick Ackerman
IPC分类号： B32B1504
CPC分类号： C23C28/321 , C23C28/3215 , C23C28/325 , C23C28/345 , C23C28/3455 , C23C28/42 , F01D5/288 , F05D2230/90 , F05D2300/611 , Y10T428/12611 , Y10T428/26 , Y10T428/265
摘要： A protective coating system and method for protecting a thermal barrier coating from CMAS infiltration. The coating system comprises inner and outer alumina layers and a platinum-group metal layer therebetween. The outer alumina layer is intended as a sacrificial layer that reacts with molten CMAS, forming a compound with a melting temperature significantly higher than CMAS. As a result, the reaction product of the outer alumina layer and CMAS resolidifies before it can infiltrate the TBC. The platinum-group metal layer is believed to serve as a barrier to infiltration of CMAS into the TBC, while the inner alumina layer appears to enhance the ability of the platinum-group metal layer to prevent CMAS infiltration.
摘要翻译：保护涂层系统和保护热障涂层免受CMAS渗透的方法。涂层系统包括内氧化铝层和外氧化铝层以及铂族金属层。外氧化铝层旨在作为与熔融CMAS反应的牺牲层，形成熔点显着高于CMAS的化合物。结果，外部氧化铝层和CMAS的反应产物在其可以渗透TBC之前再次固化。认为铂族金属层可以作为CMAS渗透到TBC中的屏障，而内层氧化铝层似乎增强了铂族金属层防止CMAS渗透的能力。

7. 发明申请

US20080080978A1 Coated turbine engine components and methods for making the same 审中-公开
标题翻译：涂层涡轮发动机部件及其制造方法
公开(公告)号：US20080080978A1
公开(公告)日：2008-04-03
申请号：US11542444
申请日：2006-10-03
申请人： Robert George Zimmerman , John Frederick Ackerman , Joseph Aloysius Heaney , Bangalore Aswatha Nagaraj , Michael James Weimer
发明人： Robert George Zimmerman , John Frederick Ackerman , Joseph Aloysius Heaney , Bangalore Aswatha Nagaraj , Michael James Weimer
IPC分类号： F03B3/12
CPC分类号： C25D5/34 , C25D3/50 , C25D5/50 , F01D5/00 , F05D2230/313 , F05D2230/314 , F05D2230/40 , F05D2230/90 , F05D2300/143 , Y02T50/67
摘要： Methods for coating a turbine engine rotor component involving depositing at least one platinum group metal selected from platinum, palladium, rhodium, ruthenium, iridium and osmium on the rotor component, and heating the rotor component to a temperature of from about 500° C. to about 800° C.
摘要翻译：用于涂覆涡轮发动机转子部件的方法包括将选自铂，钯，铑，钌，铱和锇中的至少一种铂族金属沉积在转子部件上，以及将转子部件加热至约500℃至约800℃

8. 发明授权

US07341427B2 Gas turbine nozzle segment and process therefor 有权
标题翻译：燃气轮机喷嘴段及其工艺
公开(公告)号：US07341427B2
公开(公告)日：2008-03-11
申请号：US11306221
申请日：2005-12-20
申请人： Andrew David Farmer , Bangalore Aswatha Nagaraj , Wenfeng Lu , Ching-Pang Lee , Joseph Michael Guentert
发明人： Andrew David Farmer , Bangalore Aswatha Nagaraj , Wenfeng Lu , Ching-Pang Lee , Joseph Michael Guentert
IPC分类号： F04D9/02
CPC分类号： F01D5/288 , F01D9/041 , F05D2220/31 , F05D2230/21 , F05D2230/31 , F05D2230/90 , F05D2260/95 , F05D2300/15 , F05D2300/611
摘要： A gas turbine engine nozzle segment and process for producing such a nozzle segment to exhibit improved durability and aerodynamic performance. The process produces a nozzle segment having at least one vane between and interconnecting a pair of platforms. The nozzle segment is cast from a gamma prime-strengthened nickel-base superalloy, on whose surface is thermal sprayed an environmental coating formed of a MCrAlX-type coating material. The surface of the environmental coating is then worked to cause the coating to have a surface finish of less than 2.0 micrometers Ra. Cooling holes are then drilled in the nozzle segment, after which an oxidation-resistant coating is applied on the smoothed surface of the nozzle segment so as to maintain an outermost surface on the nozzle segment having surface finish of less than 2.0 micrometers Ra.
摘要翻译：一种燃气涡轮发动机喷嘴段和用于生产这种喷嘴段的工艺，以显示出改善的耐久性和空气动力性能。该过程产生具有在一对平台之间并互连的至少一个叶片的喷嘴段。喷嘴段由伽马强化镍基超级合金铸造，其表面被热喷涂为由MCrAlX型涂层材料形成的环境涂层。然后对环境涂层的表面进行加工，使涂层的表面光洁度小于2.0微米。然后在喷嘴段中钻出冷却孔，然后在喷嘴段的平滑表面上施加耐氧化涂层，以便保持表面光洁度小于2.0微米Ra的喷嘴段上的最外表面。

9. 发明授权

US06926928B2 Protection of a gas turbine component by a vapor-deposited oxide coating 失效
标题翻译：通过气相沉积氧化物涂层保护燃气轮机部件
公开(公告)号：US06926928B2
公开(公告)日：2005-08-09
申请号：US10199185
申请日：2002-07-19
申请人： John Frederick Ackerman , Joseph Aloysius Heaney , Bangalore Aswatha Nagaraj , James Andrew Hahn , Michael James Weimer , Jon Conrad Schaeffer , William Scott Walston
发明人： John Frederick Ackerman , Joseph Aloysius Heaney , Bangalore Aswatha Nagaraj , James Andrew Hahn , Michael James Weimer , Jon Conrad Schaeffer , William Scott Walston
IPC分类号： C23C16/40 , F01D5/28 , C23C16/18
CPC分类号： F01D5/288 , C23C16/40 , F05D2230/314 , Y02T50/67
摘要： A gas turbine component, such as a turbine disk or a turbine seal element, is protected by depositing an oxide coating on the gas turbine component. The deposition is 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 micrometers, preferably from about 0.5 to about 3 micrometers. The deposited oxide may be an oxide of aluminum, silicon, tantalum, titanium, and chromium.
摘要翻译：诸如涡轮盘或涡轮密封元件的燃气涡轮机部件通过在燃气涡轮机部件上沉积氧化物涂层来保护。沉积通过诸如金属 - 有机化学气相沉积（MOCVD）的气相沉积工艺进行，涂层厚度为约0.2至约50微米，优选约0.5至约3微米。沉积的氧化物可以是铝，硅，钽，钛和铬的氧化物。

10. 发明授权

US09034479B2 Thermal barrier coating systems and processes therefor 有权
标题翻译：热障涂层系统及其工艺
公开(公告)号：US09034479B2
公开(公告)日：2015-05-19
申请号：US13542057
申请日：2012-07-05
申请人： Bangalore Aswatha Nagaraj , Douglas Gerard Konitzer , Julie Marie Chapman , Venkat Subramaniam Venkataramani
发明人： Bangalore Aswatha Nagaraj , Douglas Gerard Konitzer , Julie Marie Chapman , Venkat Subramaniam Venkataramani
IPC分类号： F01D25/00 , C04B35/48 , F01D5/28 , C23C4/10 , C23C4/18 , C23C30/00
CPC分类号： F01D25/007 , C04B35/48 , C23C4/11 , C23C4/18 , C23C28/3215 , C23C28/3455 , C23C28/347 , C23C30/00 , F01D5/284 , F01D5/288 , Y10T428/12549 , Y10T428/12618 , Y10T428/2495 , Y10T428/24967
摘要： Coating systems and processes by which the coating systems can be deposited to be resistant to contaminants, and particularly resistant to infiltration and damage caused by CMAS. The coating systems include inner and outer ceramic layers. The inner ceramic layer consists essentially of zirconia stabilized by about 6 to about 9 weight percent yttria and optionally contains greater than 0.5 to 10 weight percent hafnium oxide. The outer ceramic layer overlies and contacts the inner ceramic layer to define the outermost surface of the coating system. The outer ceramic layer consists essentially of zirconia stabilized by about 25 to about 75 weight percent yttria, has a thickness that is less than the thickness of the inner ceramic layer and further contains greater than 0.5 to 10 weight percent hafnium oxide and optionally 1 to 10 weight percent tantalum oxide. The outer ceramic layer has a porosity level that is lower than that of the inner ceramic layer.
摘要翻译：可以将涂层系统沉积以抵抗污染物，特别是对由CMAS引起的渗透和损害的涂层系统和工艺。涂层系统包括内部和外部陶瓷层。内部陶瓷层主要由由约6至约9重量％的氧化钇稳定的氧化锆组成，并且任选地包含大于0.5至10重量％的氧化铪。外陶瓷层覆盖并接触内陶瓷层以限定涂层系统的最外表面。外部陶瓷层基本上由约25至约75重量％的氧化钇稳定的氧化锆组成，其厚度小于内部陶瓷层的厚度，并且还包含大于0.5至10重量％的氧化铪和任选的1至10个重量百分比的氧化钽。外陶瓷层的孔隙率水平低于内陶瓷层的孔隙度。

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