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公开(公告)号：US07927709B2
公开(公告)日：2011-04-19
申请号：US10568697
申请日：2004-12-22
CPC分类号： F01D5/288 , C23C28/321 , C23C28/322 , C23C28/34 , C23C28/347 , C23C28/36 , C23C28/42 , F01D5/286 , F05D2230/313 , F05D2230/90 , F05D2300/611 , Y10T428/12542 , Y10T428/12576
摘要： A wear-resistant coating, in particular an erosion-resistant coating for a component that is exposed to fluidic loads, is disclosed. The wear-resistant coating has one or more multilayer systems applied repeatedly to the surface to be coated, where each of the applied multilayer systems has at least four different layers. A first layer of each multilayer system facing the surface to be coated is made of a metallic material adapted to the composition of the component surface to be coated. A second layer applied to the first layer of each multilayer system is made of a metal alloy material adapted to the composition of the component surface to be coated. A third layer applied to the second layer of each multilayer system is made of a gradated metal-ceramic material and a fourth layer applied to the third layer of each multilayer system is made of a nanostructured ceramic material.
摘要翻译： 公开了耐磨涂层，特别是用于暴露于流体负载的部件的抗侵蚀涂层。 耐磨涂层具有重复施加到待涂覆表面的一个或多个多层系统，其中每个施加的多层系统具有至少四个不同的层。 面向待涂覆表面的每个多层体系的第一层由适于要涂覆的组分表面的组成的金属材料制成。 施加到每个多层系统的第一层的第二层由适于待涂覆的部件表面的组成的金属合金材料制成。 施加到每个多层系统的第二层的第三层由渐变金属陶瓷材料制成，并且施加到每个多层系统的第三层的第四层由纳米结构的陶瓷材料制成。
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公开(公告)号：US20070190351A1
公开(公告)日：2007-08-16
申请号：US10568697
申请日：2004-12-22
CPC分类号： F01D5/288 , C23C28/321 , C23C28/322 , C23C28/34 , C23C28/347 , C23C28/36 , C23C28/42 , F01D5/286 , F05D2230/313 , F05D2230/90 , F05D2300/611 , Y10T428/12542 , Y10T428/12576
摘要： A wear-resistant coating, in particular an erosion-resistant coating for a component that is exposed to fluidic loads, is disclosed. The wear-resistant coating has one or more multilayer systems applied repeatedly to the surface to be coated, where each of the applied multilayer systems has at least four different layers. A first layer of each multilayer system facing the surface to be coated is made of a metallic material adapted to the composition of the component surface to be coated. A second layer applied to the first layer of each multilayer system is made of a metal alloy material adapted to the composition of the component surface to be coated. A third layer applied to the second layer of each multilayer system is made of a gradated metal-ceramic material and a fourth layer applied to the third layer of each multilayer system is made of a nanostructured ceramic material.
摘要翻译： 公开了耐磨涂层，特别是用于暴露于流体负载的部件的抗侵蚀涂层。 耐磨涂层具有重复施加到待涂覆表面的一个或多个多层系统，其中每个施加的多层系统具有至少四个不同的层。 面向待涂覆表面的每个多层体系的第一层由适于要涂覆的组分表面的组成的金属材料制成。 施加到每个多层系统的第一层的第二层由适于待涂覆的部件表面的组成的金属合金材料制成。 施加到每个多层系统的第二层的第三层由渐变金属陶瓷材料制成，并且施加到每个多层系统的第三层的第四层由纳米结构的陶瓷材料制成。
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公开(公告)号：US07942638B2
公开(公告)日：2011-05-17
申请号：US11472626
申请日：2006-06-21
IPC分类号： F01D5/28
CPC分类号： F01D5/28 , F01D5/284 , F01D5/286 , F05D2300/21 , F05D2300/611 , Y02T50/672 , Y02T50/673 , Y10T428/12458 , Y10T428/12549 , Y10T428/12576 , Y10T428/12806 , Y10T428/12847 , Y10T428/12875
摘要： A blade of a turbomachine such as a gas turbine includes a blade vane with a blade tip and a blade base. A blade tip armor cladding is applied on the blade tip. A coating covers at least the armor cladding and includes at least one multilayer coating system, and preferably plural such coating systems stacked repetitively on one another. Each coating system includes at least two different layers stacked successively on one another, with one layer of a metal material closer to the blade tip and one layer of a ceramic material farther from the blade tip.
摘要翻译： 诸如燃气轮机的涡轮机的叶片包括具有叶片尖端和叶片基座的叶片叶片。 叶片尖端装甲包层被施加在叶片尖端上。 涂层至少覆盖铠装包层，并且包括至少一个多层涂层系统，并且优选地多个相互重复堆叠的多个这样的涂层系统。 每个涂层系统包括至少两个彼此层叠的不同层，其中一层金属材料更靠近叶片尖端，一层陶瓷材料与叶片尖端更远。
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公开(公告)号：US20090269207A1
公开(公告)日：2009-10-29
申请号：US11908092
申请日：2006-03-03
IPC分类号： F01D5/14
CPC分类号： F01D5/286 , C23C28/021 , C23C28/023 , F05C2201/0466 , F05D2230/90 , F05D2300/131 , F05D2300/143 , F05D2300/611
摘要： A component, specifically a component for a gas turbine, having a main body of a base material and a wear protection coating applied to a surface of the main body, specifically a protective coating against corrosion and/or oxidation and/or erosion, is disclosed. A barrier coat is applied between the main body and the wear protection coating to protect the main body during chemical or electrochemical decoating of the component.
摘要翻译： 公开了一种组件，特别是用于燃气轮机的部件，其具有施加到主体的表面的基材的主体和耐磨保护涂层，特别是防止腐蚀和/或氧化和/或侵蚀的保护涂层 。 在主体和磨损保护涂层之间施加阻隔涂层，以在组件的化学或电化学去油化过程中保护主体。
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公开(公告)号：US20080124469A1
公开(公告)日：2008-05-29
申请号：US11665415
申请日：2005-10-07
IPC分类号： B05D3/12
摘要： The invention relates to a method for the production of a component, especially gas turbine component, coated with a wear-protection coating, especially a corrosion-protection coating or erosion-protection coating, with the following steps: a) providing a component (10) to be coated on a component surface (13); b) at least partially coating the component (11) on its component surface with an at least two-layered or at least two-plied wear-protection coating (14), whereby the wear-protection coating (14) encompasses at least one relatively soft layer (15) and at least one relatively hard layer (16); c) surface densifying the at least partially coated component on its coated component surface.
摘要翻译： 本发明涉及一种用于生产涂覆有耐磨保护涂层，特别是防腐蚀涂层或侵蚀保护涂层的部件，特别是燃气轮机部件的方法，具有以下步骤：a）提供部件（10 ）被涂覆在部件表面（13）上; b）用至少两层或至少两层的耐磨保护涂层（14）至少部分地将组件（11）涂覆在其构件表面上，由此防磨损涂层（14）包含至少一个相对 软层（15）和至少一个相对硬的层（16）; c）使其涂覆的部件表面上的至少部分涂覆的部件表面致密化。
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公开(公告)号：US08920881B2
公开(公告)日：2014-12-30
申请号：US11665415
申请日：2005-10-07
摘要： For producing a component, especially a gas turbine component, coated with a wear-protection, corrosion-protection or erosion-protection coating, a method includes the following steps: providing a component (10) to be coated on a component surface (13); at least partially coating the component (11) on its component surface with an at least two-layered protective coating (14), which includes at least one relatively soft layer (15) and at least one relatively hard layer (16); and then surface densifying the at least partially coated component on its coated component surface by ball blasting or shot peening.
摘要翻译： 为了制造涂覆有耐磨保护，防腐蚀或侵蚀保护涂层的部件，特别是燃气轮机部件，该方法包括以下步骤：提供要涂覆在部件表面（13）上的部件（10） ; 至少部分地用至少两层保护涂层（14）将组件（11）部分地涂覆在其部件表面上，所述保护涂层包括至少一个相对软的层（15）和至少一个相对硬的层（16）; 然后通过球磨或喷丸硬化将其涂覆的部件表面上的至少部分涂覆的部件表面致密化。
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公开(公告)号：US20100226782A1
公开(公告)日：2010-09-09
申请号：US11472626
申请日：2006-06-21
IPC分类号： F01D5/14
CPC分类号： F01D5/28 , F01D5/284 , F01D5/286 , F05D2300/21 , F05D2300/611 , Y02T50/672 , Y02T50/673 , Y10T428/12458 , Y10T428/12549 , Y10T428/12576 , Y10T428/12806 , Y10T428/12847 , Y10T428/12875
摘要： A blade of a turbomachine such as a gas turbine includes a blade vane with a blade tip and a blade base. A blade tip armor cladding is applied on the blade tip. A coating covers at least the armor cladding and includes at least one multilayer coating system, and preferably plural such coating systems stacked repetitively on one another. Each coating system includes at least two different layers stacked successively on one another, with one layer of a metal material closer to the blade tip and one layer of a ceramic material farther from the blade tip.
摘要翻译： 诸如燃气轮机的涡轮机的叶片包括具有叶片尖端和叶片基座的叶片叶片。 叶片尖端装甲包层被施加在叶片尖端上。 涂层至少覆盖铠装包层，并且包括至少一个多层涂层系统，并且优选地多个相互重复堆叠的多个这样的涂层系统。 每个涂层系统包括至少两个彼此层叠的不同层，其中一层金属材料更靠近叶片尖端，一层陶瓷材料与叶片尖端更远。
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8.发明申请VANE FOR A COMPRESSOR OR A TURBINE OF AN AIRCRAFT ENGINE, AIRCRAFT ENGINE COMPRISING SUCH A VANE AND A METHOD FOR COATING A VANE OF AN AIRCRAFT ENGINE 审中-公开压缩机的风扇或飞机发动机的涡轮机，包括这种风扇的飞机发动机和用于涂覆飞机发动机的空气的方法公开(公告)号：US20100143110A1
公开(公告)日：2010-06-10
申请号：US12513281
申请日：2007-10-27
CPC分类号： C23C28/044 , C23C30/00 , F01D5/288
摘要： An aircraft engine comprising a compressor and at least one turbine is disclosed. The compressor and the turbine are each provided with vanes, each of which has a blade that forms a suction side and a pressure side, where at least one first of the blades is coated with a protective layer in order to reduce the erosion or wear. The layer is applied such that at least two areas are formed that adjoin each other at a boundary line. The first area has a protective layer that has a substantially constant first thickness and the second area is free of the protective layer or has the protective layer with a substantially constant second thickness, the second thickness differing from the first thickness. The boundary line has at least two points, of which the connecting line differs from the course of the boundary line between the two points.
摘要翻译： 公开了一种包括压缩机和至少一个涡轮机的飞机发动机。 压缩机和涡轮机各自设置有叶片，每个叶片具有形成吸力侧和压力侧的叶片，其中至少一个叶片的第一叶片被涂覆有保护层，以减少侵蚀或磨损。 施加该层，使得在边界线处形成彼此相邻的至少两个区域。 第一区域具有保持层，该保护层具有基本恒定的第一厚度，第二区域不含保护层，或具有基本上恒定的第二厚度的保护层，第二厚度与第一厚度不同。 边界线至少有两点，其连接线与两点之间的边界线的路线不同。
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9.发明申请Device for the Protection of Components Having A Flammable Titanium Alloy From Titanium Fire, and Method for the Production Thereof 审中-公开用于保护具有钛火焰的易燃钛合金的部件的设备及其制造方法公开(公告)号：US20100143108A1
公开(公告)日：2010-06-10
申请号：US12449184
申请日：2008-01-29
CPC分类号： C23C28/321 , C23C28/322 , C23C28/34 , C23C28/42 , F01D5/288 , Y02T50/67 , Y02T50/672 , Y02T50/673 , Y10T428/12458 , Y10T428/31678
摘要： The use of titanium-based materials in the manufacturing of gas turbines, especially of engines, and, in particular, of compressors is made possible in that a device is devised that protects the components (guide vanes, guide vane stages, rotor blades, rotor blade stages) that are subject to the action of titanium fire and/or FODs by employing a layer system that includes at least two layers, is situated on the surface of the components to be protected, and is bonded thereto, as the case may be, via an adhesion-promoting layer is disclosed. The outermost layer is ceramic; the layer that is subjacent thereto is of metallic nature. Additional layers can optionally follow, ceramic and metallic layers alternating with one another. Moreover, a method is provided for producing the device. Through the at least partial use of titanium alloys, in particular for guide vanes of gas turbines, the weight of compressors can be significantly reduced in that the need for the nickel- or steel-based structural materials used under the related art is eliminated in favor of lighter titanium alloys.
摘要翻译： 在制造燃气涡轮机，特别是发动机，特别是压缩机中使用钛基材料是可能的，因为设计了一种保护部件（导向叶片，导叶片，转子叶片，转子 通过使用包含至少两层的层系统而受到钛火和/或FOD的作用的刀片台）位于要保护的部件的表面上，并且根据情况可以粘合到其上 ，通过粘附促进层。 最外层是陶瓷; 其下面的层具有金属性质。 附加层可以任选地跟随，陶瓷和金属层彼此交替。 此外，提供了一种用于制造该装置的方法。 通过至少部分使用钛合金，特别是对于燃气轮机的导向叶片，可以显着地减少压缩机的重量，因为对现有技术中使用的基于镍或钢的结构材料的需求被消除 较轻的钛合金。
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10.发明申请DECOATING DEVICE FOR AXIALLY SYMMETRIC COMPONENTS, PARTICULARLY FROM AIRCRAFT ENGINES 审中-公开用于轴对称组件的特殊装置，特别是来自飞机发动机公开(公告)号：US20100263694A1
公开(公告)日：2010-10-21
申请号：US12312273
申请日：2007-10-27
申请人： Thomas Uihlein , Wolfgang Eichmann , Falko Heutling , Markus Uecker , Thomas Brendel , Georgios Paronis , Anton Albrecht , Manfred Berger
发明人： Thomas Uihlein , Wolfgang Eichmann , Falko Heutling , Markus Uecker , Thomas Brendel , Georgios Paronis , Anton Albrecht , Manfred Berger
IPC分类号： B08B3/00
摘要： A decoating device for axially symmetric components, particularly from aircraft engines is provided, the decoating process being carried out through the use of a decoating fluid-which is brought on a localized basis into contact with the component to be decoated, a receptacle for holding the decoating fluid being provided that rotates at least about one axis of rotation, and the decoating fluid surface forming a rotation paraboloid in response to the rotation, the component(s) to be decoated on a localized basis being accommodated in the receptacle and being dipped on the radially outer side into the decoating fluid. A decoating device is thereby devised which makes it possible for radially symmetric components to be decoated in the radially outer region in a simple process.
摘要翻译： 提供了一种用于轴向对称部件的脱色装置，特别是来自飞机发动机的脱色装置，其通过使用与局部基准成一体的脱色液体进行脱色处理，与脱漆部件接触， 提供了旋转至少约一个旋转轴线的旋转流体，并且旋转流体表面响应于旋转而形成旋转抛物面，待局部放置的待分解的部件被容纳在容器中并被浸入 径向外侧进入脱水流体。 从而设计出一种可以在简单的过程中将径向对称的部件在径向外部区域中解体的装置。
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