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1. 发明授权

EP2298951B1 Composition and method for a thermal coating system 有权
标题翻译：热涂层系统的组合物和方法
公开(公告)号：EP2298951B1
公开(公告)日：2013-06-19
申请号：EP10175416.6
申请日：2010-09-06
申请人： General Electric Company
发明人： Skoog, Andrew Jay , Murphy, Jane Ann
IPC分类号： C23C4/12 , C23C4/18 , C23C24/00 , B05B5/043 , B05B5/03 , B05B5/16 , B05B15/12
CPC分类号： C23C24/00 , B05B5/043 , C23C4/12 , C23C4/18 , Y02T50/67 , Y10T428/26 , Y10T428/263 , Y10T428/264 , Y10T428/265

2. 发明授权

EP2141138B1 Method of repairing a thermal barrier coating and repaired coating formed thereby 有权
标题翻译：一种用于修复的热障涂层和由此形成的修补涂布方法
公开(公告)号：EP2141138B1
公开(公告)日：2012-03-14
申请号：EP09162700.0
申请日：2009-06-15
申请人： General Electric Company
发明人： Skoog, Andrew Jay , Murphy, Jane Ann
IPC分类号： C04B35/18 , C04B35/63 , C04B35/626 , C04B35/622 , B23P6/00 , F01D5/00 , F01D5/28 , C23C24/08
CPC分类号： C23C24/08 , C04B35/18 , C04B35/6263 , C04B35/6316 , C04B2235/3206 , C04B2235/3208 , C04B2235/3232 , C04B2235/3418 , F01D5/288 , F05D2230/80 , F05D2300/2112 , Y02T50/67 , Y02T50/671 , Y02T50/673

3. 发明公开

EP1785194A1 Electrostatic spray method for coating aircraft engine components 有权
标题翻译：方法zum elektrostatischen Beschichten von Flugzeugtriebwerkskomponenten
公开(公告)号：EP1785194A1
公开(公告)日：2007-05-16
申请号：EP06255763.2
申请日：2006-11-09
申请人： General Electric Company
发明人： Buczek, Matthew Bernard , Skoog, Andrew Jay , Rechtsteiner, Mark , Murphy, Jane Ann
IPC分类号： B05B5/00 , C23C4/00 , B05B5/03 , C23C4/02
CPC分类号： C23C24/00 , B05B5/032 , B05B5/1683 , B05B14/48 , C23C4/12 , C23C4/18 , Y02T50/67
摘要： Electrostatic deposition of high performance powdered materials [8] onto gas turbine surfaces. The process also includes post-deposition thermal staging of the deposited powder [8] to provide a durable coating that will satisfy the demands of turbine engine operation. The process envisions application of organic-based powdered materials, glass/ceramic powdered materials and metal-based powdered materials and combinations thereof using electrostatic techniques to components [12] exposed to low temperature operations, such as may be found in the front section of a gas turbine engine or to the exterior portions of an aircraft engine, and metal-containing glass ceramics, glass-ceramic materials, or materials that can be transformed into glass ceramic materials, when applied to components [12] exposed to high temperature operations, such as may be found in the turbine and exhaust sections of a gas turbine engine or the flaps of an aircraft.
摘要翻译：将高性能粉末材料[8]静电沉积到燃气轮机表面上。该方法还包括沉积粉末的沉积后分级[8]，以提供可满足涡轮发动机运行要求的耐用涂层。该方法设想使用静电技术将有机基粉末材料，玻璃/陶瓷粉末材料和金属基粉末材料及其组合应用于暴露于低温操作的组分[12]，例如可以在燃气涡轮发动机或飞机发动机的外部部分，以及当应用于暴露于高温操作的部件[12]时，可以转化成玻璃陶瓷材料的含金属玻璃陶瓷，玻璃陶瓷材料或材料，例如如在燃气涡轮发动机的涡轮机和排气部分或飞行器的翼片中可以看到的那样。

4. 发明公开

EP1574595A1 Powder coating of gas turbine engine components 审中-公开
标题翻译： Pulverbeschichtung von Gasturbinentriebwerkskomponenten
公开(公告)号：EP1574595A1
公开(公告)日：2005-09-14
申请号：EP05251399.1
申请日：2005-03-08
申请人： GENERAL ELECTRIC COMPANY
发明人： Skoog, Andrew Jay , Rechtsteiner, Mark , Buczek, Matthew
IPC分类号： C23C4/12
CPC分类号： C23D5/04 , C23C24/08 , C23C24/082 , Y10T428/12611 , Y10T428/24893
摘要： In accordance with one embodiment of the invention, there is provided a method of coating a gas turbine engine component using a powder coating process. The method comprises providing a gas turbine engine component; and applying a powder coating to the gas turbine engine component using the powder coating process. The powder coating is applied in a dry form without an organic solvent. The method further comprises heating the applied powder coating to melt and fuse particles of the powder coating to the gas turbine engine component and cure the powder coating.
摘要翻译：根据本发明的一个实施例，提供了一种使用粉末涂覆工艺涂覆燃气涡轮发动机部件的方法。该方法包括提供燃气涡轮发动机部件; 以及使用所述粉末涂覆方法将所述粉末涂料施加到所述燃气涡轮发动机部件。粉末涂料以没有有机溶剂的干燥形式施用。该方法还包括加热所施加的粉末涂层以将粉末涂料的颗粒熔化并熔合到燃气涡轮发动机部件并固化粉末涂层。

5. 发明公开

EP1531192A1 Thermal barrier coating having a heat radiation absorbing topcoat 审中-公开
标题翻译： WärmeaufnehmendeDeckbeschichtungfüreineWärmedämmschicht
公开(公告)号：EP1531192A1
公开(公告)日：2005-05-18
申请号：EP04256966.5
申请日：2004-11-10
申请人： GENERAL ELECTRIC COMPANY
发明人： Stowell, William Randolph , Skoog, Andrew Jay , Ackerman, John Frederick , Nagaraj, Bangalore Aswatha , Murphy, Jane Ann , Ivkovick, Daniel Peter
IPC分类号： C23C28/00 , F01D5/28
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 , 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 are described. A multilayer thermal barrier coating (TBC) system (10, 110) is characterized by a low coefficient of thermal conductivity and having a heat-absorbing topcoat (20, 120) comprised of the thermal decomposition product of at least one metallic element and at least one ceramic precursor binder component.
摘要翻译：描述了适用于保护暴露于高温环境的组分的涂覆系统，例如通过燃气涡轮发动机的热气流路径。多层热障涂层（TAB）系统（10,110）的特征在于低导热系数，并且具有由至少一种金属元素的热分解产物组成的吸热顶涂层（20,120），并且至少一种陶瓷前体粘合剂组分。

6. 发明公开

EP1939325A3 Strain tolerant corrosion protecting coating and tape method of application 审中-公开
标题翻译：应变宽容的防腐蚀保护层和磁带方法应用
公开(公告)号：EP1939325A3
公开(公告)日：2011-08-03
申请号：EP07122504.9
申请日：2007-12-06
申请人： GENERAL ELECTRIC COMPANY
发明人： Skoog, Andrew Jay , Bojanovski, Bryan , Hazel, Brian Thomas , Murphy, Jane Ann , Weimer, Michael James , Doyle, Timothy A.
IPC分类号： C23C26/00 , C23C28/00 , F01D5/28
CPC分类号： C23C26/00 , C23C28/321 , C23C28/3215 , C23C28/324 , C23C28/34 , C23C28/345 , C23C28/3455 , C23C28/36 , F01D5/28 , F01D5/288 , F05D2300/21 , F05D2300/2102 , F05D2300/211 , Y02T50/67
摘要： A corrosion resistant tape coating (64) for gas turbine engine includes a glassy ceramic matrix wherein the glassy matrix is silica-based, and includes corrosion resistant particles (65) selected from refractory particles and non-refractory MCrAIX particles, and combinations thereof. The corrosion resistant particles (65) are substantially uniformly distributed within the matrix, and provide the coating with corrosion resistance. Importantly the coating (64) of the present invention has a coefficient of thermal expansion (CTE) greater than that of alumina at engine operating temperatures. The CTE of the coating (64) is sufficiently close to the substrate (60) such that the coating (64) does not spall after frequent engine cycling at temperatures above 1200°F.

7. 发明公开

EP1739204A2 Field repairable high temperature smooth wear coating 有权
标题翻译：现场可修复的高温光滑耐磨涂层
公开(公告)号：EP1739204A2
公开(公告)日：2007-01-03
申请号：EP06253305.4
申请日：2006-06-26
申请人： The General Electric Company
发明人： Skoog, Andrew Jay , Stowell, William Randolph , Murphy, Jane Ann , Caldwell, David E.
IPC分类号： C23C24/08
CPC分类号： C23C24/08 , C09D1/00 , F01D5/288 , F05D2230/80 , F05D2230/90 , F23R2900/00019 , Y02T50/67 , Y02T50/671
摘要： A chemical composition (24) and method for repairing a thermal barrier coating (12) on a component (10) designed for use in a hostile thermal environment, such as turbine, combustor and augmentor components of a gas turbine engine. The method repairs a thermal barrier coating (12) on a component (10) that has suffered localized damage to the thermal barrier coating (12). After cleaning the surface area of the component (10) exposed by the localized spallation, a paste-like mixture of a ceramic composition (24) comprising ceramic powders and nano-sized ceramic materials in a binder, further including an accelerant, is applied to the surface (22) of the component (10), and is smoothed using mechanical means. The composition (24) is then allowed to dry and cure to form a dried repair coating (26) having polymeric characteristics. Upon subsequent heating, the dried coating (26) reacts to produce a glassy ceramic repair coating (26). Due to the thixotropic properties of the coating composition (24) upon application to a component (10), the repair method can be performed in-situ while the component (10) remains installed in its operating environment.
摘要翻译：一种化学组合物（24）和方法，用于修复设计用于恶劣热环境的部件（10）上的隔热涂层（12），例如燃气涡轮发动机的涡轮机，燃烧器和增压器部件。该方法修复已经遭受热障涂层（12）局部损坏的部件（10）上的热障涂层（12）。在清洁通过局部散裂而暴露的部件（10）的表面区域之后，将包含陶瓷粉末和纳米尺寸陶瓷材料的陶瓷组合物（24）的糊状混合物（其还包含促进剂）应用于粘合剂部件（10）的表面（22），并且使用机械手段进行平滑。然后使组合物（24）干燥并固化以形成具有聚合物特性的干燥修复涂层（26）。在随后的加热过程中，干燥的涂层（26）反应以产生玻璃状陶瓷修补涂层（26）。由于涂覆到部件（10）上时涂层组合物（24）的触变性质，修理方法可以在部件（10）保持安装在其操作环境中的同时原位进行。

8. 发明公开

EP1538238A3 Sprayable noble metal coating for high temperature use directly on aircraft engine alloys 审中-公开
标题翻译：对于在高温下使用的贵金属可喷雾涂料组合物直接施加到飞行器发动机合金
公开(公告)号：EP1538238A3
公开(公告)日：2006-04-26
申请号：EP04257468.1
申请日：2004-12-01
申请人： GENERAL ELECTRIC COMPANY
发明人： Skoog, Andrew Jay , Murphy, Jane Ann , Bojanowski, Bryan Thomas
IPC分类号： C23C28/00 , C23C30/00 , C23C26/00 , F01D5/28 , B05D1/00
CPC分类号： F01D5/288 , B05D1/00 , C23C4/02 , C23C4/10 , C23C4/18 , C23C24/04 , C23C28/042 , C23C30/00 , F05D2230/90 , F05D2300/14 , F05D2300/611 , Y02T50/67 , Y02T50/671
摘要： A method of applying a heat-rejection coating directly on a substrate of a metallic component is disclosed. The steps include supplying a metallic component, such as of a gas turbine engine, before applying a reflective-coating mixture onto the component, wherein the reflective-coating mixture comprises a metallic pigment and a reflective-coating-mixture carrier, and wherein the step of applying is accomplished by a method selected from the group consisting of air-assisted spraying, airless spraying, brushing, and decal transfer. The component having the reflective-coating mixture thereon is fired to form a reflective coating on the component.

9. 发明公开

EP1538239A2 Sprayable noble metal coating for high temperature use on ceramic and smoothcoat coated aircraft engine parts 审中-公开
标题翻译：使用在升高的温度下的陶瓷，并提供经涂覆的飞机发动机部件贵金属可喷雾涂料组合物
公开(公告)号：EP1538239A2
公开(公告)日：2005-06-08
申请号：EP04257466.5
申请日：2004-12-01
申请人： GENERAL ELECTRIC COMPANY
发明人： Skoog, Andrew Jay , Lattire, Timothy Ray , Murphy, Jane Ann
IPC分类号： C23C28/00 , C23C24/08 , C23C30/00 , C23C26/00 , C23C4/18 , F01D5/28
CPC分类号： C23C30/00 , C23C4/02 , C23C4/123 , C23C4/18 , C23C24/04 , C23C28/345 , F01D5/28 , F02K1/00 , F05D2300/14 , F05D2300/142 , F05D2300/143 , F05D2300/21 , F05D2300/502 , Y02T50/67 , Y02T50/672
摘要： A method applies a heat-rejection coating directly on a substrate of a ceramic component. The steps include supplying a ceramic component (40), such as of a gas turbine engine, before applying a reflective-coating mixture onto the component (54), wherein the reflective-coating mixture comprises a metallic pigment and a reflective-coating-mixture carrier, and wherein the step of applying is accomplished by a method selected from the group consisting of air-assisted spraying, airless spraying, brushing, and decal transfer. The component having the reflective-coating mixture thereon is fired (56) to form a reflective coating on the component.
摘要翻译：一种方法，适用热排斥在陶瓷部件的基板直接涂布。这些步骤包括供给的陶瓷构件（40）：如燃气涡轮发动机的，走上worin反射涂覆混合物的组分（54）施加反射涂层混合物之前包括金属颜料和反射涂覆混合物载体，和worin的施用通过选自由空气辅助喷涂，无空气喷涂，刷涂，和贴花转移中选择的方法来实现的步骤。在其上具有反射涂层混合物组分进行烧成（56），以形成部件上的反射涂层。

10. 发明公开

EP1739204A3 Field repairable high temperature smooth wear coating 有权
标题翻译： Vor Ort reparierbare hohe Temperatur glatte verschleissfeste Beschichtung
公开(公告)号：EP1739204A3
公开(公告)日：2007-01-24
申请号：EP06253305.4
申请日：2006-06-26
申请人： The General Electric Company
发明人： Skoog, Andrew Jay , Stowell, William Randolph , Murphy, Jane Ann , Caldwell, David E.
IPC分类号： C23C24/08
CPC分类号： C23C24/08 , C09D1/00 , F01D5/288 , F05D2230/80 , F05D2230/90 , F23R2900/00019 , Y02T50/67 , Y02T50/671
摘要： A chemical composition (24) and method for repairing a thermal barrier coating (12) on a component (10) designed for use in a hostile thermal environment, such as turbine, combustor and augmentor components of a gas turbine engine. The method repairs a thermal barrier coating (12) on a component (10) that has suffered localized damage to the thermal barrier coating (12). After cleaning the surface area of the component (10) exposed by the localized spallation, a paste-like mixture of a ceramic composition (24) comprising ceramic powders and nano-sized ceramic materials in a binder, further including an accelerant, is applied to the surface (22) of the component (10), and is smoothed using mechanical means. The composition (24) is then allowed to dry and cure to form a dried repair coating (26) having polymeric characteristics. Upon subsequent heating, the dried coating (26) reacts to produce a glassy ceramic repair coating (26). Due to the thixotropic properties of the coating composition (24) upon application to a component (10), the repair method can be performed in-situ while the component (10) remains installed in its operating environment.
摘要翻译：一种用于修复设计用于恶劣热环境的部件（10）上的热障涂层（12）的化学组合物（24）和方法，所述部件（10）用于燃气涡轮发动机的涡轮机，燃烧器和增压器部件。该方法修复已经对热障涂层（12）局部损坏的部件（10）上的热障涂层（12）。在清洁通过局部剥落暴露的组分（10）的表面积之后，将包含陶瓷粉末和纳米尺寸陶瓷材料的陶瓷组合物（24）的糊状混合物在粘合剂中进一步包含促进剂，被施加到（10）的表面（22），并且使用机械装置进行平滑。然后将组合物（24）干燥并固化以形成具有聚合物特性的干燥的修复涂层（26）。随后加热，干燥的涂层（26）反应以产生玻璃状陶瓷修补涂层（26）。由于涂料组合物（24）在施用于组分（10）时的触变性能，可以在组分（10）保持安装在其操作环境中时原位进行修复方法。

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