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公开(公告)号：US5071678A
公开(公告)日：1991-12-10
申请号：US594455
申请日：1990-10-09
CPC分类号： C23C10/08
摘要： A process for forming a diffusion coating to the surface of a metal article. The process is particularly adapted for forming diffusion aluminide coatings on metal blades and vanes used in gas turbine engines. According to the invention, halide vapor is caused to react with a source of aluminum to form an aluminum rich halide gas. This gas then reacts with the part surface to form the aluminide coating. A key aspect of the invention relates to the timing of the reaction between the halide vapor and the source of aluminum.
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公开(公告)号：US4933239A
公开(公告)日：1990-06-12
申请号：US319593
申请日：1989-03-06
申请人： Walter E. Olson , Dinesh K. Gupta
发明人： Walter E. Olson , Dinesh K. Gupta
CPC分类号： C23C10/02 , C23C10/48 , Y10T428/1209 , Y10T428/12493 , Y10T428/1275 , Y10T428/12806 , Y10T428/12826 , Y10T428/12931 , Y10T428/31678
摘要： A protective coating system for superalloys is described. The coating is an active element enriched aluminide, and can be formed by aluminizing an overlay coated superalloy, wherein during the aluminizing process, aluminum diffuses completely through the overlay coating and into the substrate. The coating system exhibits desirable oxidation resistance and resistance to thermal fatigue cracking, due to the presence of oxygen active elements in the overlay.
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公开(公告)号：US06435826B1
公开(公告)日：2002-08-20
申请号：US09835809
申请日：2001-04-16
IPC分类号： F04D2944
CPC分类号： C23C30/00 , C23C4/00 , F01D5/288 , F05D2300/132 , F05D2300/143 , F05D2300/15 , F05D2300/21 , Y02T50/67 , Y02T50/671
摘要： According to the invention, an article that is exposed to high temperatures, e.g., over 1000° C. during operation is disclosed. In one embodiment, a turbine blade for a gas turbine engine includes a directionally solidified metallic substrate, e.g., a superalloy, which defines an airfoil, a root and a platform located between the blade and root. The platform has an underside adjacent the root, and a corrosion resistant noble metal-containing aluminide coating is located on portions of the blade susceptible to corrosion and/or stress corrosion cracking, such as the underside of the platform and the neck. The applied coating prevents corrosion and stress corrosion cracking of blade in these regions.
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公开(公告)号：US4910092A
公开(公告)日：1990-03-20
申请号：US131481
申请日：1987-12-03
申请人： Walter E. Olson , Dinesh K. Gupta
发明人： Walter E. Olson , Dinesh K. Gupta
CPC分类号： C23C10/48 , C23C10/02 , Y10S428/941 , Y10T428/1209 , Y10T428/12458 , Y10T428/12778 , Y10T428/12931 , Y10T428/12944
摘要： A protective coating system for superalloys is described. The coating is an yttrium enriched aluminide, and can be formed by aluminizing an MCrAlY coated superalloy, wherein during the aluminizing process, aluminum diffuses completely through the MCrAlY coating and into the substrate. The coating system exhibits desirable oxidation resistance and resistance to thermal fatigue cracking.
摘要翻译： 描述了用于超级合金的保护涂层系统。 涂层是富铝钇铝化合物，可以通过镀化MCrAlY涂层的高温合金来形成，其中在铝化过程中，铝完全扩散通过MCrAlY涂层并进入衬底。 涂层体系具有所需的抗氧化性和耐热疲劳裂纹性。
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5.发明申请Apparatus and Method for Coating Internal Surfaces of a Turbine Engine Component 审中-公开用于涂覆涡轮发动机部件的内表面的装置和方法公开(公告)号：US20110293826A1
公开(公告)日：2011-12-01
申请号：US13193764
申请日：2011-07-29
申请人： Mark A. Livings , Walter E. Olson
发明人： Mark A. Livings , Walter E. Olson
CPC分类号： C23C16/045 , C23C10/06 , C23C16/4488
摘要： A coating apparatus for coating interior surfaces of internal passages of a workpiece, such as a turbine engine component is provided. The coating apparatus comprises a vessel defining an internal space, a plate dividing the internal space into a first chamber and a second chamber, a divider supporting the plate, and the plate having at least one cut-out for receiving a portion of the workpiece having the internal passages to be coated.
摘要翻译： 提供一种用于涂覆诸如涡轮发动机部件的工件的内部通道的内表面的涂覆装置。 涂覆装置包括限定内部空间的容器，将内部空间分成第一室和第二室的板，支撑板的分隔板，以及具有至少一个切口的板，用于接收工件的一部分， 要涂层的内部通道。
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公开(公告)号：US07700154B2
公开(公告)日：2010-04-20
申请号：US11284611
申请日：2005-11-22
申请人： Walter E. Olson
发明人： Walter E. Olson
CPC分类号： C23C8/04 , C23C10/04 , C23C10/06 , F01D5/18 , F01D5/28 , F05D2230/313 , F05D2300/121
摘要： A method for coating internal surfaces of a turbine engine component comprises flowing an aluminide containing gas into passages in the turbine engine component so as to coat the internal surfaces formed by the passages, allowing the aluminide containing gas to flow through the passages and out openings in external surfaces of the turbine engine component, and flowing a volume of a gas selected from the group consisting of argon, hydrogen, and mixtures thereof over the external surfaces to minimize any build-up of an aluminide coating on the external surfaces.
摘要翻译： 一种用于涂覆涡轮发动机部件的内表面的方法包括将含铝化物的气体流入涡轮发动机部件中的通道，以便涂覆由通道形成的内表面，允许含铝化物的气体流过通道，并将出口 涡轮发动机部件的外表面，并且将一批体积的选自氩，氢及其混合物的气体流过外表面，以最小化铝表面在外表面上的积聚。
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7.发明申请Apparatus and method for coating internal surfaces of a turbine engine component 有权用于涂覆涡轮发动机部件的内表面的装置和方法公开(公告)号：US20090017205A1
公开(公告)日：2009-01-15
申请号：US11825782
申请日：2007-07-09
申请人： Mark A. Livings , Walter E. Olson
发明人： Mark A. Livings , Walter E. Olson
IPC分类号： B05D7/22
CPC分类号： C23C16/045 , C23C10/06 , C23C16/4488
摘要： A coating apparatus for coating interior surfaces of internal passages of a workpiece, such as a turbine engine component is provided. The coating apparatus comprises a vessel defining an internal space, a plate dividing the internal space into a first chamber and a second chamber, a divider supporting the plate, and the plate having at least one cut-out for receiving a portion of the workpiece having the internal passages to be coated.
摘要翻译： 提供一种用于涂覆诸如涡轮发动机部件的工件的内部通道的内表面的涂覆装置。 涂覆装置包括限定内部空间的容器，将内部空间分成第一室和第二室的板，支撑板的分隔板，以及具有至少一个切口的板，用于接收工件的一部分， 要涂层的内部通道。
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公开(公告)号：US06435835B1
公开(公告)日：2002-08-20
申请号：US09467517
申请日：1999-12-20
IPC分类号： F01D514
CPC分类号： C23C30/00 , C23C4/00 , F01D5/288 , F05D2300/132 , F05D2300/143 , F05D2300/15 , F05D2300/21 , Y02T50/67 , Y02T50/671
摘要： According to the invention, an article that is exposed to high temperatures, e.g., over 1000° C. during operation is disclosed. In one embodiment, a turbine blade for a gas turbine engine includes a directionally solidified metallic substrate, e.g., a superalloy, which defines an airfoil, a root and a platform located between the blade and root. The platform has an underside adjacent the root, and a corrosion resistant noble metal-containing aluminide coating is located on portions of the blade susceptible to corrosion and/or stress corrosion cracking, such as the underside of the platform and the neck. The applied coating prevents corrosion and stress corrosion cracking of blade in these regions.
摘要翻译： 根据本发明，公开了在操作期间暴露于高温例如超过1000℃的制品。 在一个实施例中，用于燃气涡轮发动机的涡轮机叶片包括定向凝固的金属基底，例如超合金，其定义了叶片，根部和位于叶片和根部之间的平台。 该平台具有邻近根部的下侧，并且耐腐蚀的含贵金属的铝化物涂层位于易受腐蚀和/或应力腐蚀开裂的刀片的部分上，例如平台和颈部的下侧。 涂覆的涂层防止了这些区域中刀片的腐蚀和应力腐蚀开裂
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公开(公告)号：US07360678B2
公开(公告)日：2008-04-22
申请号：US11044938
申请日：2005-01-27
摘要： Novel materials and methods for repairing/reclassifying superalloy components are described herein. These materials are non-traditional blends of materials having a much higher base material content than traditional repair/reclassification materials. In embodiments used to repair/reclassify nickel-based components, these materials may comprise about 5-18.9 weight percent of a low melting point alloy and about 81.1-95 weight percent of a base material. In embodiments used to repair/reclassify cobalt-based components, these materials may comprise about 15-30 weight percent of a low melting point alloy and about 70-85 weight percent of a base material. These materials can be used to repair surface defects and/or build up worn or eroded areas of a component to meet precise dimensional and metallurgical requirements. These materials create robust repaired components having a dense, isothermally solidified structure having minimal borides and a high re-melt temperature.
摘要翻译： 本文描述了用于修复/重新分级超级合金部件的新型材料和方法。 这些材料是非传统的材料混合物，其具有比传统的修复/重新分类材料高得多的基础材料含量。 在用于修复/重新分类镍基组分的实施方案中，这些材料可以包含约5-18.9重量％的低熔点合金和约81.1-95重量％的基材。 在用于修复/重新分类钴基组分的实施方案中，这些材料可以包含约15-30重量％的低熔点合金和约70-85重量％的基材。 这些材料可用于修复表面缺陷和/或构建组件的磨损或侵蚀区域，以满足精确的尺寸和冶金要求。 这些材料产生具有致密的，等温凝固的具有最小硼化物和高再熔融温度的结构的稳固的修复组分。
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公开(公告)号：US06435830B1
公开(公告)日：2002-08-20
申请号：US09467516
申请日：1999-12-20
IPC分类号： F01D522
CPC分类号： C23C30/00 , C23C4/00 , F01D5/288 , F05D2300/132 , F05D2300/143 , F05D2300/15 , F05D2300/21 , Y02T50/67
摘要： According to the invention, an article that is exposed to high temperatures, e.g., over 1000° C. during operation is disclosed. In one embodiment, a turbine blade for a gas turbine engine includes a directionally solidified metallic substrate, e.g., a superalloy, which defines an airfoil, a root and a platform located between the blade and root. The platform has an underside adjacent the root, and a corrosion resistant overlay coating such as an MCrAlY is located on the underside of the platform and the neck. The applied coating prevents corrosion and stress corrosion cracking of blade in these regions. Where the airfoil is also coated, the airfoil coating may have a composition different from that of the coating on the underplatform surfaces.
摘要翻译： 根据本发明，公开了在操作期间暴露于高温例如超过1000℃的制品。 在一个实施例中，用于燃气涡轮发动机的涡轮机叶片包括定向凝固的金属基底，例如超合金，其定义了叶片，根部和位于叶片和根部之间的平台。 该平台具有邻近根部的下侧，并且诸如MCrAlY的耐腐蚀覆盖涂层位于平台和颈部的下侧。 涂覆的涂层防止了这些区域中刀片的腐蚀和应力腐蚀开裂。 在翼面也被涂覆的情况下，翼型涂层可以具有与底板表面上的涂层不同的组成
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