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1. 发明授权

US06521294B2 Aluminiding of a metallic surface using an aluminum-modified maskant, and aluminum-modified maskant 失效
标题翻译：使用铝改性掩蔽剂对铝金属表面进行铝化，以及铝改性掩蔽剂
公开(公告)号：US06521294B2
公开(公告)日：2003-02-18
申请号：US09373267
申请日：1999-08-11
申请人： Joseph D. Rigney , Jeffrey A. Pfaendtner , Michael J. Weimer , Ramgopal Darolia
发明人： Joseph D. Rigney , Jeffrey A. Pfaendtner , Michael J. Weimer , Ramgopal Darolia
IPC分类号： B05D132
CPC分类号： C23C10/04
摘要： A metallic substrate has a substrate surface having a substrate surface of nickel, a substrate aluminum content, and other alloying elements. A maskant is applied overlying the substrate surface to produce a masked substrate surface having an exposed region and a protected region. The maskant includes a plurality of maskant particles, each particle having a maskant particle composition comprising a maskant metal selected from the group of nickel, cobalt, titanium, chromium, iron, and combinations thereof, and a maskant aluminum content. The substrate is aluminided by contacting a source of aluminum to the masked substrate surface, whereby aluminum deposits on the exposed region and does not deposit on the protected region.
摘要翻译：金属基板具有基板表面，其具有镍的基底表面，基底铝含量和其它合金元素。将掩蔽剂施加在衬底表面上以产生具有暴露区域和受保护区域的掩蔽衬底表面。掩模剂包括多个掩蔽剂颗粒，每个颗粒具有包含选自镍，钴，钛，铬，铁及其组合的掩蔽剂金属的掩蔽剂颗粒组合物和掩蔽铝含量。通过使铝源与掩蔽的基底表面接触来将基底铝化，由此铝沉积在暴露的区域上并且不沉积在受保护区域上。

2. 发明授权

US06332926B1 Apparatus and method for selectively coating internal and external surfaces of an airfoil 失效
标题翻译：用于选择性地涂覆翼型的内表面和外表面的装置和方法
公开(公告)号：US06332926B1
公开(公告)日：2001-12-25
申请号：US09373433
申请日：1999-08-11
申请人： Jeffrey A. Pfaendtner , Joseph D. Rigney , Nripendra N. Das , Ramgopal Darolia
发明人： Jeffrey A. Pfaendtner , Joseph D. Rigney , Nripendra N. Das , Ramgopal Darolia
IPC分类号： C23C1600
CPC分类号： C23C16/042 , C23C16/045 , Y02T50/67
摘要： A gas turbine airfoil has an external surface and an internal passage therethrough. The internal passage is selectively coated by providing a source of a flowable precursor coating material in contact with the internal passage of the airfoil, and providing a coating prevention structure overlying at least a portion of the external surface. The flowable precursor coating material is flowed from the source of the flowable precursor coating material and through the internal passage of the airfoil. The coating prevention structure prevents contact of the flowable precursor coating material with the external surface of the airfoil.
摘要翻译：燃气涡轮机翼型件具有外表面和穿过其的内部通道。通过提供与翼型件的内部通道接触的可流动的前体涂料的源，选择性地涂覆内部通道，并且提供覆盖在外表面的至少一部分上的防涂层结构。可流动的前体涂层材料从可流动的前体涂层材料的源头流过翼型件的内部通道。涂层防止结构防止可流动的前体涂层材料与翼型件的外表面的接触。

3. 发明授权

US06616969B2 Apparatus and method for selectively coating internal and external surfaces of an airfoil 失效
标题翻译：用于选择性地涂覆翼型的内表面和外表面的装置和方法
公开(公告)号：US06616969B2
公开(公告)日：2003-09-09
申请号：US09929595
申请日：2001-08-14
申请人： Jeffrey A. Pfaendtner , Joseph D. Rigney , Nripendra N. Das , Ramgopal Darolia
发明人： Jeffrey A. Pfaendtner , Joseph D. Rigney , Nripendra N. Das , Ramgopal Darolia
IPC分类号： C23C1608
CPC分类号： C23C16/042 , C23C16/045 , Y02T50/67
摘要： A gas turbine airfoil has an external surface and an internal passage therethrough. The internal passage is selectively coated by providing a source of a flowable precursor coating material in contact with the internal passage of the airfoil, and providing a coating prevention structure overlying at least a portion of the external surface. The flowable precursor coating material is flowed from the source of the flowable precursor coating material and through the internal passage of the airfoil. The coating prevention structure prevents contact of the flowable precursor coating material with the external surface of the airfoil.
摘要翻译：燃气涡轮机翼型件具有外表面和穿过其的内部通道。通过提供与翼型件的内部通道接触的可流动的前体涂料的源，选择性地涂覆内部通道，并且提供覆盖在外表面的至少一部分上的防涂层结构。可流动的前体涂层材料从可流动的前体涂层材料的源头流过翼型件的内部通道。涂层防止结构防止可流动的前体涂层材料与翼型件的外表面的接触。

4. 发明授权

US06283714B1 Protection of internal and external surfaces of gas turbine airfoils 失效
标题翻译：燃气轮机翼型内外表面的保护
公开(公告)号：US06283714B1
公开(公告)日：2001-09-04
申请号：US09373271
申请日：1999-08-11
申请人： Joseph D. Rigney , Michael J. Weimer , Ramgopal Darolia
发明人： Joseph D. Rigney , Michael J. Weimer , Ramgopal Darolia
IPC分类号： F01D514
CPC分类号： C23C30/00 , C23C10/04 , Y02T50/67
摘要： A gas turbine airfoil includes an internal cooling passage defined by an internal airfoil surface, and an external airfoil surface. The gas turbine airfoil is protected on both the internal airfoil surface and the external airfoil surface. The internal airfoil surface is protected by forming a diffusion aluminide protective layer at the internal airfoil surface of the internal cooling passage, with substantially no aluminum deposited on the external airfoil surface during the step of forming. The external airfoil surface is protected by depositing an overlay protective coating on the external airfoil surface, with substantially no aluminum or diffusion aluminide between the overlay protective coating and the external airfoil surface. The gas turbine airfoil is operated in a gas turbine engine, and may later be removed for repair. Repair is accomplished by removing the overlay protective coating from the external airfoil surface of the airfoil, restoring the airfoil dimensions as needed, and depositing a second overlay protective coating on the external airfoil surface of the gas turbine airfoil, with substantially no diffusion aluminide layer between the second overlay protective coating and the external airfoil surface of the airfoil.
摘要翻译：燃气轮机翼型件包括由内部翼型件表面限定的内部冷却通道和外部翼型件表面。燃气轮机翼型件在内翼面和外翼面上都受到保护。内部翼面表面通过在内部冷却通道的内部翼型表面处形成扩散铝化物保护层而被保护，在成形步骤期间基本上没有铝沉积在外部翼型件表面上。通过在外部翼型件表面上沉积覆盖保护涂层来保护外部翼型件表面，在覆盖保护涂层和外部翼型件表面之间基本上不存在铝或扩散铝化物。燃气涡轮机翼型在燃气涡轮发动机中操作，并且可以稍后被去除以进行修理。通过从翼型件的外部翼面表面去除覆盖层保护涂层，根据需要恢复翼面尺寸并在燃气轮机翼型的外部翼型表面上沉积第二覆盖保护涂层，基本上没有扩散铝化物层之间第二覆盖保护涂层和翼型的外部翼面表面。

5. 发明授权

US06444057B1 Compositions and single-crystal articles of hafnium-modified and/or zirconium-modified nickel-base superalloys 有权
标题翻译：铪改性和/或锆改性的镍基超级合金的组合物和单晶制品
公开(公告)号：US06444057B1
公开(公告)日：2002-09-03
申请号：US09318636
申请日：1999-05-26
申请人： Ramgopal Darolia , Jeffrey A. Pfaendtner , William S. Walston
发明人： Ramgopal Darolia , Jeffrey A. Pfaendtner , William S. Walston
IPC分类号： C22C1905
CPC分类号： C22C19/057
摘要： An article is formed of a single crystal having a composition, in weight percent, of a modifying element in an amount of from about 0.2 to about 2.0 percent by weight hafnium, from about 0.1 to about 0.5 percent by weight zirconium, or combinations thereof, and a base alloy composition of from about 4 to about 20 percent cobalt, from about 1 to about 10 percent chromium, from about 5 to about 7 percent aluminum, from 0 to about 2 percent molybdenum, from about 3 to about 8 percent tungsten, from about 4 to about 12 percent tantalum, from 0 to about 2 percent titanium, from 0 to about 8 percent rhenium, from 0 to about 6 percent ruthenium, from 0 to about 1 percent niobium, from 0 to about 0.1 percent carbon, from 0 to about 0.01 percent boron, from 0 to about 0.1 percent yttrium, and balance nickel and incidental impurities.
摘要翻译：一种制品由具有约0.2至约2.0重量％的铪，约0.1至约0.5重量％的锆或其组合的量的改性元素的组合物的重量百分比形成，以及约4至约20％的钴，约1至约10％的铬，约5至约7％的铝，0至约2％的钼，约3至约8％的钨，约4至约12％的钽，0至约2％的钛，0至约8％的铼，0至约6％的钌，0至约1％的铌，0至约0.1％的碳，来自 0至约0.01％的硼，0至约0.1％的钇，并平衡镍和附带的杂质。

6. 发明授权

US07078073B2 Method for repairing coated components 有权
标题翻译：修复涂层部件的方法
公开(公告)号：US07078073B2
公开(公告)日：2006-07-18
申请号：US10714213
申请日：2003-11-13
申请人： Joseph D. Rigney , Ching-Pang Lee , Ramgopal Darolia
发明人： Joseph D. Rigney , Ching-Pang Lee , Ramgopal Darolia
IPC分类号： B05D1/36 , B05D3/12
CPC分类号： C23C28/321 , C23C26/00 , C23C28/325 , C23C28/3455 , F01D5/005 , F01D5/288 , F05D2230/80 , F05D2230/90 , F05D2300/501 , Y10T29/49318
摘要： According to an embodiment of the invention, a method for repairing a coated high pressure turbine blade, which has been exposed to engine operation, to restore coated airfoil contour dimensions of the blade, is disclosed. The method comprises providing an engine run high pressure turbine blade including a base metal substrate made of a nickel-based alloy and having thereon a thermal barrier coating system. The thermal barrier coating system comprises a diffusion bond coat on the base metal substrate and a top ceramic thermal barrier coating comprising a yttria stabilized zirconia material. The top ceramic thermal barrier coating has a nominal thickness t. The method further comprises removing the thermal barrier coating system, wherein a portion of the base metal substrate also is removed, and determining the thickness of the base metal substrate removed. The portion of the base metal substrate removed has a thickness, Δt. The method also comprises reapplying the diffusion bond coat to the substrate, wherein the bond coat is reapplied to a thickness, which is about the same as applied prior to the engine operation; and reapplying the top ceramic thermal barrier coating to a nominal thickness of t+Δt, wherein Δt compensates for the portion of removed base metal substrate. Advantageously, the coated airfoil contour dimensions of the high pressure turbine blade are restored to about the coated dimensions preceding the engine run.
摘要翻译：根据本发明的实施例，公开了一种已经暴露于发动机操作的用于修复涂覆的高压涡轮机叶片以恢复叶片的被覆翼型轮廓尺寸的方法。该方法包括提供一种发动机运行的高压涡轮叶片，其包括由镍基合金制成的基底金属基底并且具有热障涂层系统。热障涂层系统包括在基底金属基底上的扩散粘合涂层和包含氧化钇稳定的氧化锆材料的顶部陶瓷热障涂层。顶部陶瓷热障涂层具有标称厚度t。该方法还包括去除热障涂层系统，其中基底金属衬底的一部分也被去除，并且确定移除的母体金属衬底的厚度。去除的贱金属基材的部分厚度为Deltat。该方法还包括将扩散粘合涂层重新施加到基底上，其中粘结涂层重新施加到与发动机操作前相同的厚度; 并将顶部陶瓷热障涂层重新施加到标称厚度t + Deltat，其中Deltat补偿去除的基底金属基底的部分。有利地，高压涡轮机叶片的被覆翼型轮廓尺寸恢复到发动机运行之前的涂层尺寸。

7. 发明授权

US06514629B1 Article with hafnium-silicon-modified platinum-aluminum bond or environmental coating 失效
标题翻译：文章用铪硅改性的铂铝键或环保涂层
公开(公告)号：US06514629B1
公开(公告)日：2003-02-04
申请号：US09210855
申请日：1998-12-15
申请人： Joseph D. Rigney , Ramgopal Darolia , William S. Walston
发明人： Joseph D. Rigney , Ramgopal Darolia , William S. Walston
IPC分类号： B32B1504
CPC分类号： C23C28/321 , C23C10/52 , C23C28/325 , C23C28/345 , C23C28/3455 , F01D5/284 , F01D5/288 , Y02T50/67 , Y02T50/671 , Y10S428/941 , Y10T428/12611 , Y10T428/1275 , Y10T428/12764 , Y10T428/12875 , Y10T428/12944
摘要： An article such as a gas turbine blade or vane has a superalloy substrate, and a coating system deposited on the substrate. The coating system includes a protective layer overlying the substrate, and, optionally, a ceramic thermal barrier coating layer overlying the bond coat. The protective layer has an uppermost layer with a composition including platinum, aluminum, and, in atom percent, from about 0.14 to about 2.8 percent hafnium and from about 2.7 to about 7.0 percent silicon, with the atomic ratio of silicon:hafnium being from about 1.7:1 to about 5.6:1.
摘要翻译：诸如燃气轮机叶片或叶片的物品具有超级合金基底和沉积在基底上的涂层系统。涂层系统包括覆盖在基底上的保护层，以及任选的覆盖粘结涂层的陶瓷热障涂层。保护层具有最上层，其组成包括铂，铝，原子百分比为约0.14至约2.8％的铪和约2.7至约7.0％的硅，硅：铪的原子比为约 1.7：1至约5.6：1。

8. 发明授权

US07371426B2 Method for repairing components using environmental bond coatings and resultant repaired components 有权
标题翻译：使用环境粘合剂涂层修补部件的方法以及由此修复的部件
公开(公告)号：US07371426B2
公开(公告)日：2008-05-13
申请号：US10713938
申请日：2003-11-13
申请人： Joseph D. Rigney , Ramgopal Darolia
发明人： Joseph D. Rigney , Ramgopal Darolia
IPC分类号： B32B15/01 , B32B15/20 , B05D3/12
CPC分类号： C23C10/02 , C23C18/54 , C23C28/321 , C23C28/3215 , C23C28/325 , C23C28/345 , C23C28/3455 , C25D7/04 , Y10T428/1259 , Y10T428/12736 , Y10T428/12771 , Y10T428/12937 , Y10T428/12944 , Y10T428/265
摘要： According to an embodiment of the invention, a repaired component is disclosed. The repaired component comprises an engine run component having a base metal substrate, a portion of the base metal substrate between about 1-3 mils in thickness and an overlying bond coat having been removed to create a remaining base metal substrate of reduced thickness. The repaired component further comprises a lower growth environmental bond coating comprising an alloy having an aluminum content of about 10-60 atomic percent applied to the remaining base metal substrate so that upon subsequent repair of the component, less than about 1-3 mils in thickness of the remaining base metal substrate is removed because of less environmental coating growth into the substrate than the prior bond coat. Advantageously, the repaired component has extended component life and increased repairability.
摘要翻译：根据本发明的实施例，公开了修理的部件。被修复的部件包括具有贱金属基底的发动机运行部件，贱金属基底的厚度在约1-3密耳之间的部分和已经去除的上覆接合涂层，以产生厚度减小的剩余基底金属基底。修复的部件还包括较低生长环境粘合涂层，其包含施加到剩余的贱金属基底上的约10-60原子百分比的铝含量的合金，使得在随后修复部件时，厚度小于约1-3密耳剩余的贱金属基底被去除，因为比现有的粘合涂层更少的环境涂层生长到基底中。有利地，修复的部件具有延长的部件寿命和增加的可修复性。

9. 发明授权

US07094444B2 Method for repairing coated components using NiAl bond coats 有权
标题翻译：使用NiAl粘合涂层修复涂层部件的方法
公开(公告)号：US07094444B2
公开(公告)日：2006-08-22
申请号：US10714430
申请日：2003-11-13
申请人： Joseph D. Rigney , Ching-Pang Lee , Ramgopal Darolia
发明人： Joseph D. Rigney , Ching-Pang Lee , Ramgopal Darolia
IPC分类号： B05C13/00 , B05D1/36
CPC分类号： B23P6/002 , C23C10/02 , C23C10/60 , C23C28/321 , C23C28/3215 , C23C28/345 , C23C28/3455 , C23C28/36 , C25D3/50 , C25D7/00 , C25D7/008 , F05B2230/31 , F05B2230/90 , F05C2253/12
摘要： According to an embodiment of the invention, a method for repairing a coated high pressure turbine blade, which has been exposed to engine operation, to restore coated airfoil contour dimensions of the blade, and improve upon the prior bond coat is disclosed. The method comprises providing an engine run high pressure turbine blade including a base metal substrate made of a nickel-based alloy and having thereon a thermal barrier coating system. The thermal barrier coating system comprises a diffusion bond coat on the base metal substrate and a top ceramic thermal barrier coating comprising a yttria stabilized zirconia material. The top ceramic thermal barrier coating has a nominal thickness t. The method further comprises removing the thermal barrier coating system, wherein a portion of the base metal substrate also is removed, and determining the thickness of the base metal substrate removed. The portion of the base metal substrate removed has a thickness, Δt. The method also comprises applying a β phase NiAl overlay coating to the substrate, and determining the difference in thickness, Δx, between the β phase NiAl overlay coating and the previously removed bond coat. The method further comprises reapplying the top ceramic thermal barrier coating to a nominal thickness of t+Δt−Δx, wherein Δt compensates for the portion of removed base metal substrate. Advantageously, the coated airfoil contour dimensions of the high pressure turbine blade are restored to about the coated dimensions preceding the engine run.
摘要翻译：根据本发明的实施例，公开了一种已经暴露于发动机操作的用于修复涂覆的高压涡轮机叶片以恢复叶片的被覆翼型轮廓尺寸并改进先前的粘结涂层的方法。该方法包括提供一种发动机运行的高压涡轮叶片，其包括由镍基合金制成的基底金属基底并且具有热障涂层系统。热障涂层系统包括在基底金属基底上的扩散粘合涂层和包含氧化钇稳定的氧化锆材料的顶部陶瓷热障涂层。顶部陶瓷热障涂层具有标称厚度t。该方法还包括去除热障涂层系统，其中基底金属衬底的一部分也被去除，并且确定移除的母体金属衬底的厚度。去除的贱金属基材的部分厚度为Deltat。该方法还包括将β相NiAl覆盖涂层施加到基底上，并确定β相NiAl覆盖涂层与先前去除的粘结涂层之间的厚度差异Deltax。该方法还包括将顶部陶瓷热障涂层重新施加到t + Deltat-Deltax的标称厚度，其中Deltat补偿去除的基底金属基底的部分。有利地，高压涡轮机叶片的被覆翼型轮廓尺寸恢复到发动机运行之前的涂层尺寸。

10. 发明授权

US06582772B2 Method for preparing an article with a hafnium-silicon-modified platinum-aluminide bond or environmental coating 失效
标题翻译：制备具有铪硅改性的铂 - 铝化物键或环境涂层的制品的方法
公开(公告)号：US06582772B2
公开(公告)日：2003-06-24
申请号：US10262114
申请日：2002-09-30
申请人： Joseph D. Rigney , Ramgopal Darolia , William S. Walston
发明人： Joseph D. Rigney , Ramgopal Darolia , William S. Walston
IPC分类号： B05D136
CPC分类号： C23C28/321 , C23C10/52 , C23C28/325 , C23C28/345 , C23C28/3455 , F01D5/284 , F01D5/288 , Y02T50/67 , Y02T50/671 , Y10S428/941 , Y10T428/12611 , Y10T428/1275 , Y10T428/12764 , Y10T428/12875 , Y10T428/12944
摘要： An article such as a gas turbine blade or vane has a superalloy substrate, and a coating system deposited on the substrate. The coating system includes a protective layer overlying the substrate, and, optionally, a ceramic thermal barrier coating layer overlying the bond coat. The protective layer has an uppermost layer with a composition including platinum, aluminum, and, in atom percent, from about 0.14 to about 2.8 percent hafnium and from about 2.7 to about 7.0 percent silicon, with the atomic ratio of silicon:hafnium being from about 1.7:1 to about 5.6:1.
摘要翻译：诸如燃气轮机叶片或叶片的物品具有超级合金基底和沉积在基底上的涂层系统。涂层系统包括覆盖在基底上的保护层，以及任选的覆盖粘结涂层的陶瓷热障涂层。保护层具有最上层，其组成包括铂，铝，原子百分比为约0.14至约2.8％的铪和约2.7至约7.0％的硅，硅：铪的原子比为约 1.7：1至约5.6：1。

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