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1. 发明授权

US06929825B2 Method for aluminide coating of gas turbine engine blade 有权
标题翻译：燃气轮机发动机叶片铝化物涂层方法
公开(公告)号：US06929825B2
公开(公告)日：2005-08-16
申请号：US10357987
申请日：2003-02-04
申请人： Roger Dale Wustman , William Scott Walston , Matthew David Saylor , Brian Harvey Pilsner , Jeffrey Allan Pfaendtner
发明人： Roger Dale Wustman , William Scott Walston , Matthew David Saylor , Brian Harvey Pilsner , Jeffrey Allan Pfaendtner
IPC分类号： C23C10/08 , C23C16/44 , F01D5/28 , C23C16/06
CPC分类号： F01D5/288 , C23C10/08 , Y02T50/67
摘要： A method for applying an aluminide coating on a gas 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. 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 blade to be coated; providing an aluminide coating gas in the loaded coating chamber; flowing an inert carrier gas into the loaded coating chamber comprising the aluminide coating gas at a specified gas flow rate and time to move the aluminide coating gas through the cooling holes and internal cooling cavity and deposit an aluminide coating on the internal surface of the blade; and then flowing an inert carrier gas into the loaded coating chamber comprising the aluminide coating gas at a specified higher temperature and time to deposit an aluminide coating on the external surface of the blade.
摘要翻译：一种在具有外表面的燃气涡轮发动机叶片上施加铝化物涂层的方法和具有通过冷却孔连接到外表面的内表面的内部冷却腔。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刀片装载; 在装载的涂覆室中提供铝化物涂覆气体; 将惰性载气以特定的气体流量和时间流动到包含铝化物涂层气体的负载涂层室中，以移动铝化物涂层气体通过冷却孔和内部冷却腔，并将铝化物涂层沉积在刀片的内表面上; 然后使惰性载气在特定的较高温度和时间下流入包含铝化物涂层气体的装载的涂覆室中，以将铝化物涂层沉积在刮板的外表面上。

2. 发明授权

US07026011B2 Aluminide coating of gas turbine engine blade 失效
标题翻译：燃气轮机发动机叶片的铝酸盐涂层
公开(公告)号：US07026011B2
公开(公告)日：2006-04-11
申请号：US10357972
申请日：2003-02-04
申请人： Roger Dale Wustman , William Scott Walston , Matthew David Saylor , Brian Harvey Pilsner , Jeffrey Allan Pfaendtner
发明人： Roger Dale Wustman , William Scott Walston , Matthew David Saylor , Brian Harvey Pilsner , Jeffrey Allan Pfaendtner
IPC分类号： C23C16/08
CPC分类号： C23C10/08 , F01D5/288 , F05D2230/313 , Y02T50/67 , Y02T50/671
摘要： A method for applying an aluminide coating on a gas 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. 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 blade to be coated; providing an aluminide coating gas in the loaded coating chamber; maintaining the loaded coating chamber comprising the aluminide coating gas at a specified temperature and time to deposit an aluminide coating on the external surface of the blade; and then flowing an inert carrier gas into the loaded coating chamber comprising the aluminide coating gas at a specified gas flow rate and time to move the aluminide coating gas through the cooling holes and internal cooling cavity and deposit an aluminide coating on the internal surface of the blade.
摘要翻译：一种在具有外表面的燃气涡轮发动机叶片上施加铝化物涂层的方法和具有通过冷却孔连接到外表面的内表面的内部冷却腔。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刀片装载; 在装载的涂覆室中提供铝化物涂覆气体; 将包含铝化物涂层气体的装载涂层室保持在规定温度和时间，以将铝化物涂层沉积在叶片的外表面上; 然后使惰性载体气体以特定的气体流速和时间流入包含铝化物涂层气体的装载的涂覆室中，以移动铝化物涂层气体通过冷却孔和内部冷却腔，并将铝化物涂层沉积在刀。

3. 发明授权

US07910173B2 Thermal barrier coating and process therefor 失效
标题翻译：热障涂层及其工艺
公开(公告)号：US07910173B2
公开(公告)日：2011-03-22
申请号：US12183665
申请日：2008-07-31
申请人： Irene Spitsberg , Brett Allen Rohrer Boutwell , Robert William Bruce , Curtis Alan Johnson , Bangalore Aswatha Nagaraj , William Scott Walston , Rudolfo Viguie , Joshua Leigh Miller , Roger Dale Wustman
发明人： Irene Spitsberg , Brett Allen Rohrer Boutwell , Robert William Bruce , Curtis Alan Johnson , Bangalore Aswatha Nagaraj , William Scott Walston , Rudolfo Viguie , Joshua Leigh Miller , Roger Dale Wustman
IPC分类号： B05D5/00 , B05D1/36 , C23C26/00 , B32B9/00
CPC分类号： C23C28/321 , C23C28/3215 , C23C28/325 , C23C28/345 , C23C28/3455 , Y10T428/249953 , Y10T428/249955
摘要： A thermal barrier coating and deposition process for a component intended for use in a hostile thermal environment, such as the turbine, combustor and augmentor components of a gas turbine engine. The TBC has a first coating portion on at least a first surface portion of the component. The first coating portion is formed of a ceramic material to have at least an inner region, at least an outer region overlying the inner region, and a columnar microstructure whereby the inner and outer regions comprise columns of the ceramic material. The columns of the inner region are more closely spaced than the columns of the outer region so that the inner region of the first coating portion is denser than the outer region of the first coating portion, wherein the higher density of the inner region promotes the impact resistance of the first coating portion.
摘要翻译：用于在敌对热环境中使用的部件的热障涂层和沉积工艺，例如燃气轮机的涡轮机，燃烧器和增压器部件。所述TBC在所述部件的至少第一表面部分上具有第一涂覆部分。第一涂覆部分由陶瓷材料形成，至少具有内部区域，至少覆盖内部区域的外部区域和柱状微结构，由此内部和外部区域包括陶瓷材料的列。内部区域的列与外部区域的列紧密地间隔开，使得第一涂覆部分的内部区域比第一涂覆部分的外部区域更致密，其中内部区域的较高密度促进了冲击第一涂布部分的电阻。

4. 发明授权

US06863925B1 Method for vapor phase aluminiding including a modifying element 失效
标题翻译：包括改性元素的气相铝化方法
公开(公告)号：US06863925B1
公开(公告)日：2005-03-08
申请号：US09670189
申请日：2000-09-26
申请人： Gary Eugene Wheat , Terri Kay Brown , Roger Dale Wustman , Joseph David Rigney
发明人： Gary Eugene Wheat , Terri Kay Brown , Roger Dale Wustman , Joseph David Rigney
IPC分类号： C23C10/02 , C23C10/06 , C23C16/08 , C23C28/00
CPC分类号： C23C10/02 , C23C10/14 , C23C16/08 , C23C28/021 , C23C28/028 , C23C28/321 , C23C28/325 , C23C28/345 , C23C28/3455 , Y02T50/67
摘要： An article is coasted by preparing a coating source having an aluminum halide, a fluoride or an iodide of a modifying element as a source of the modifying element, and a carrier gas. The modifying element is zirconium, hafnium, and yttrium, or combinations thereof. The coating source is contacted to the article, and the coating source and the article are heated to a coating temperature of at least about 1850° F. for a period of time sufficient to permit aluminum and the modifying element to coat onto the surface of the article. The preferred fluorides of modifying elements are zirconium tetrafluoride and hafnium tetrafluoride.
摘要翻译：通过制备具有改性元素的卤化铝，氟化物或碘化物作为改性元素的来源的涂料源和载气来制备物品。改性元素是锆，铪和钇，或其组合。将涂料源与制品接触，并将涂料源和制品加热至至少约1850°F的涂布温度一段足以允许铝和改性元素涂覆在表面上的时间文章。改性元素的优选氟化物是四氟化锆和四氟化铪。

5. 发明授权

US08545185B2 Turbine engine components with environmental protection for interior passages 有权
标题翻译：涡轮发动机部件具有环境保护用于内部通道
公开(公告)号：US08545185B2
公开(公告)日：2013-10-01
申请号：US11959595
申请日：2007-12-19
申请人： David John Wortman , Roger Dale Wustman , Nicole Marie Polley , Kathleen Diana Brammer , Brian Thomas Hazel
发明人： David John Wortman , Roger Dale Wustman , Nicole Marie Polley , Kathleen Diana Brammer , Brian Thomas Hazel
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/288 , F05D2230/30 , F05D2230/31 , F05D2230/80 , F05D2230/90 , Y02T50/67 , Y02T50/671 , Y02T50/676
摘要： Turbine airfoil components with protective layers and methods therefore. The components are each formed to have a platform, an airfoil extending upwardly from the platform, and a shank extending downwardly from the platform. The shank has an exterior wall and an internal passage, and the airfoil has a cooling flow channel inside the airfoil for flowing a cooling flow therethrough. The component has an interior chromide coating contacting at least a portion of an interior surface of the shank and interdiffused with a base metal thereof, and an exterior chromide coating contacting at least a portion of an exterior surface of the shank and interdiffused with the base metal thereof. The interior and exterior chromide coatings do not have an aluminide coating deposited thereon.
摘要翻译：涡轮机翼部件具有保护层和方法。这些部件各自形成为具有平台，从平台向上延伸的翼型件和从平台向下延伸的柄部。柄具有外壁和内部通道，并且翼型件具有用于使冷却流通过其中的翼型件内的冷却流动通道。该组件具有内部铬化物涂层，其接触柄的内表面的至少一部分并且与其基体金属相互扩散，并且外部铬化物涂层与柄的外表面的至少一部分接触并与基底金属相互扩散其中。内部和外部铬酸盐涂层不具有沉积在其上的铝化物涂层。

6. 发明申请

US20090162209A1 TURBINE ENGINE COMPONENTS WITH ENVIRONMENTAL PROTECTION FOR INTERIOR PASSAGES 有权
标题翻译：具有内部通道环境保护的涡轮发动机部件
公开(公告)号：US20090162209A1
公开(公告)日：2009-06-25
申请号：US11959595
申请日：2007-12-19
申请人： DAVID JOHN WORTMAN , Roger Dale Wustman , Nicole Marie Polley , Kathleen Diana Brammer , Brian Thomas Hazel
发明人： DAVID JOHN WORTMAN , Roger Dale Wustman , Nicole Marie Polley , Kathleen Diana Brammer , Brian Thomas Hazel
IPC分类号： F01D5/18 , F04D29/58
CPC分类号： F01D5/187 , F01D5/288 , F05D2230/30 , F05D2230/31 , F05D2230/80 , F05D2230/90 , Y02T50/67 , Y02T50/671 , Y02T50/676
摘要： A gas turbine blade comprises a base metal, a platform, an airfoil extending upwardly from the platform, a shank extending downwardly from the platform. The shank has an exterior wall and an internal passage, and the airfoil has a cooling flow channel inside the airfoil for flowing a cooling flow therethrough. The blade has a first chromide coating contacting the base metal of at least a portion of an interior surface of the shank and interdiffused therewith, wherein the first chromide coating does not have an aluminide coating deposited over it. The blade has a second chromide coating contacting the base metal of at least a portion of an interior surface of the airfoil and interdiffused therewith. A method for preparing a gas turbine blade comprises the steps of applying chromide coatings, sealing the interior passages of the shank and airfoil and applying an aluminide or platinum aluminide coating and an optional ceramic layer on the airfoil.
摘要翻译：燃气轮机叶片包括贱金属，平台，从平台向上延伸的翼型件，从平台向下延伸的柄部。柄具有外壁和内部通道，并且翼型件具有用于使冷却流通过其中的翼型件内的冷却流动通道。刀片具有与柄的内表面的至少一部分的贱金属接触并与之相互扩散的第一铬化物涂层，其中第一铬化物涂层不具有沉积在其上的铝化物涂层。叶片具有与翼型件的内表面的至少一部分的基底金属接触并与其相互扩散的第二铬化物涂层。制备燃气轮机叶片的方法包括以下步骤：施加铬酸盐涂层，密封柄和翼型件的内部通道，并在翼型件上施加铝化物或铂铝化物涂层和可选的陶瓷层。

7. 发明授权

US06434876B1 Method of applying a particle-embedded coating to a substrate 有权
标题翻译：将颗粒包埋的涂层施加到基底的方法
公开(公告)号：US06434876B1
公开(公告)日：2002-08-20
申请号：US09670187
申请日：2000-09-26
申请人： Gary Eugene Wheat , Terri Kay Brown , Roger Dale Wustman
发明人： Gary Eugene Wheat , Terri Kay Brown , Roger Dale Wustman
IPC分类号： B05D136
CPC分类号： C23C26/00 , C23C10/52 , Y02T50/67
摘要： A turbine blade is coated by first applying a particle-entrapped tip coating to the tip of the airfoil. An aluminum-containing coating is thereafter applied to the airfoil, including to the tip of the airfoil overlying the particle-entrapped tip coating. The aluminum-containing coating is applied by providing a source of aluminum contacting the airfoil that deposits aluminum onto the airfoil at a coating temperature, and heating the airfoil to the coating temperature so that the aluminum-containing coating is deposited onto the airfoil, and so that the aluminum-containing coating and the particle-entrapped tip coating are diffused into the turbine blade substrate. The step of applying the aluminum-containing coating occurs without substantial prior interdiffusing of the particle-entrapped tip coating with the tip of the airfoil as a separate step.
摘要翻译：通过首先将颗粒捕获的尖端涂层施加到翼型的尖端来涂覆涡轮叶片。然后将含铝涂层施加到翼型件，包括覆盖颗粒捕获的尖端涂层的翼型的末端。通过在涂覆温度下提供与铝箔接触而将铝沉积在翼型上的铝源，通过提供含铝涂层，并将翼型加热到涂层温度，使含铝涂层沉积在翼型上，等等含铝涂层和颗粒捕获的尖端涂层扩散到涡轮叶片基板中。作为单独的步骤，施加含铝涂层的步骤发生在与翼型件的尖端之间的颗粒捕获的尖端涂层没有实质的先前相互扩散的情况下。

8. 发明授权

US6146692A Caustic process for replacing a thermal barrier coating 有权
标题翻译：用于更换热障涂层的苛刻工艺
公开(公告)号：US6146692A
公开(公告)日：2000-11-14
申请号：US210655
申请日：1998-12-14
申请人： D. Sangeeta , Howard John Farr , Roger Dale Wustman
发明人： D. Sangeeta , Howard John Farr , Roger Dale Wustman
IPC分类号： B08B3/08 , C23C4/02 , C23C10/02 , C23C16/00 , C23F1/00 , C23F1/40 , C23G1/14 , C23G1/20 , C23G3/00 , F01D5/00 , F01D5/28 , B05D3/10
CPC分类号： C23C10/02 , C23C4/02 , C23G1/20 , F01D5/005 , F01D5/288 , Y02T50/67 , Y02T50/671 , Y10T29/49318
摘要： An aqueous caustic process can be used for replacing a thermal barrier coating on a metal surface. In the process, the metal surface is contacted with a caustic solution to remove the thermal barrier coating. The processing conditions for contacting the caustic solution are selected to avoid the formation of a peel layer during a subsequent application of a replacement thermal barrier coating and heat treatment. A replacement thermal barrier coating is then reapplied to the metal surface.
摘要翻译：可以使用苛性碱水处理来替代金属表面上的热障涂层。在此过程中，金属表面与苛性碱溶液接触以除去热障涂层。选择与苛性碱溶液接触的处理条件，以避免在随后施加置换热障涂层和热处理期间形成剥离层。然后将替代的热障涂层重新施加到金属表面。

9. 发明申请

US20090162562A1 Methods for Applying Thermal Barrier Coating Systems 审中-公开
标题翻译：应用热障涂层系统的方法
公开(公告)号：US20090162562A1
公开(公告)日：2009-06-25
申请号：US11963995
申请日：2007-12-24
申请人： Bangalore Aswatha Nagaraj , David John Wortman , Nicole Marie Polley , William Bryan Connor , Roger Dale Wustman
发明人： Bangalore Aswatha Nagaraj , David John Wortman , Nicole Marie Polley , William Bryan Connor , Roger Dale Wustman
IPC分类号： C23C16/00 , B05D3/02 , B05D1/36 , B05D1/38 , C23C4/08 , H05H1/24
CPC分类号： B32B15/017 , C22C19/056 , C23C28/321 , C23C28/3215 , C23C28/325 , C23C28/3455 , Y02T50/67 , Y02T50/6765
摘要： Methods for coating a substrate includes depositing on the substrate, a inner bond coat layer of a bond coat composition comprising, in weight percent, 14-20% Cr, 5-8% Al, 8-12% Co, 3-7% Ta, 0.1-0.6% Hf, 0.1-0.5% Y, up to about 1% Si, 0.005-0.020% Zr, 0.04-0.08% C, 0.01-0.02% B, with a remainder including nickel (Ni) and incidental impurities, wherein the bond coat composition is substantially free of rhenium; forming an aluminum-containing layer overlying the inner bond coat layer; and, optionally, depositing a thermal barrier coating composition overlying the aluminum-containing layer.
摘要翻译：用于涂覆基材的方法包括在基材上沉积粘合涂层组合物的内粘合涂层，其包含重量百分比为14-20％的Cr，5-8％的Al，8-12％的Co，3-7％的Ta ，0.1-0.6％Hf，0.1-0.5％Y，至多约1％Si，0.005-0.020％Zr，0.04-0.08％C，0.01-0.02％B，余量包括镍（Ni）和附带杂质，其中所述粘合涂层组合物基本上不含铼; 形成覆盖在内粘合涂层上的含铝层; 以及任选地沉积覆盖在含铝层上的热障涂层组合物。

10. 发明授权

US07270764B2 Method for removing aluminide coating from metal substrate and turbine engine part so treated 失效
标题翻译：从金属基底和如此处理的涡轮发动机零件上去除铝化物涂层的方法
公开(公告)号：US07270764B2
公开(公告)日：2007-09-18
申请号：US11171686
申请日：2005-06-30
申请人： Roger Dale Wustman , Mark Alan Rosenzweig , William Clarke Brooks , Brian H. Pilsner , James Douglas Risbeck , Richard Roy Worthing, Jr.
发明人： Roger Dale Wustman , Mark Alan Rosenzweig , William Clarke Brooks , Brian H. Pilsner , James Douglas Risbeck , Richard Roy Worthing, Jr.
IPC分类号： B44C1/22 , C03C15/00 , C03C25/68 , C23F1/00 , B23P6/00
CPC分类号： C23F1/44 , F01D5/005 , F05D2230/80 , F05D2230/90 , F05D2300/611 , Y02T50/67 , Y02T50/671 , Y10T29/49318
摘要： A method for selectively removing an aluminide coating from at least one surface of a metal-based substrate by: (a) contacting the surface of the substrate with at least one stripping composition comprising nitric acid at a temperature less than about 20° C. to degrade the coating without damaging the substrate; and (b) removing the degraded coating without damaging the substrate. Also disclosed is a method for replacing a worn or damaged aluminide coating on at least one surface of a metal-based substrate by selectively removing the coating using the above steps, and then applying a new aluminide coating to the surface of the substrate. Turbine engine parts, such as high-pressure turbine blades, treated using the above methods are also disclosed.
摘要翻译：一种用于通过以下步骤从金属基底材的至少一个表面选择性去除铝化物涂层的方法：（a）使基底的表面与至少一种包含硝酸的汽提组合物在小于约20℃的温度下接触至降低涂层而不损坏基材; 和（b）除去降解的涂层而不损坏基材。还公开了一种用于通过使用上述步骤选择性地除去涂层来替代金属基底材的至少一个表面上的磨损或损坏的铝化物涂层的方法，然后将新的铝化物涂层施加到衬底的表面。还公开了使用上述方法处理的涡轮发动机部件，例如高压涡轮机叶片。

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