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公开(公告)号：US07078073B2
公开(公告)日：2006-07-18
申请号：US10714213
申请日：2003-11-13
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。
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2.发明授权Aluminiding of a metallic surface using an aluminum-modified maskant, and aluminum-modified maskant 失效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
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。
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3.发明授权公开(公告)号：US06514629B1
公开(公告)日：2003-02-04
申请号：US09210855
申请日：1998-12-15
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。
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4.发明授权Method for repairing components using environmental bond coatings and resultant repaired components 有权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
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。
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公开(公告)号：US07094444B2
公开(公告)日：2006-08-22
申请号：US10714430
申请日：2003-11-13
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。
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6.发明授权Method for preparing an article with a hafnium-silicon-modified platinum-aluminide bond or environmental coating 失效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
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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公开(公告)号：US06283714B1
公开(公告)日：2001-09-04
申请号：US09373271
申请日：1999-08-11
IPC分类号： F01D514
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。
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8.发明授权公开(公告)号：US06632480B2
公开(公告)日：2003-10-14
申请号：US10264451
申请日：2002-10-03
申请人： Ramgopal Darolia , Joseph D. Rigney
发明人： Ramgopal Darolia , Joseph D. Rigney
IPC分类号： B05D136
CPC分类号： C23C28/321 , C23C28/325 , C23C28/3455 , C23C30/00 , F01D5/288 , Y02T50/67 , Y10T428/12611 , Y10T428/12771 , Y10T428/12931 , Y10T428/12944
摘要： A nickel-base superalloy article has a surface protective layer comprising nickel, from about 20 to about 35 weight percent aluminum, and from about 0.5 to about 10 weight percent rhenium. The protective layer, which is preferably an overlay coating of the beta (&bgr;) phase NiAl form, is formed by depositing nickel, aluminum, rhenium, and modifying elements onto the substrate surface. A ceramic layer may be deposited overlying the protective layer.
摘要翻译： 镍基超级合金制品具有包含镍的表面保护层，约20至约35重量％的铝和约0.5至约10重量％的铼。 通过将镍，铝，铼和修饰元素沉积在基底表面上而形成保护层，其优选为β（β）相NiAl形式的覆盖层。 陶瓷层可以沉积在保护层的上方。
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公开(公告)号：US06436473B1
公开(公告)日：2002-08-20
申请号：US09929594
申请日：2001-08-14
IPC分类号： C23C1608
摘要： A diffusion aluminide coating having a graded structure is applied over a nickel base superalloy substrate. The coating has an inner region of a diffusion aluminide adjacent to the substrate rich in a reactive element, typically Hf, Si or combinations of the two. The near surface region is a diffusion aluminide which is substantially free of reactive elements. Such coatings when used as bond coats in thermal barrier coating systems exhibit improved spallation performance.
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公开(公告)号：US07070866B2
公开(公告)日：2006-07-04
申请号：US10855687
申请日：2004-05-27
CPC分类号： C04B35/486 , C04B2235/3206 , C04B2235/3208 , C04B2235/3224 , C04B2235/3225 , C04B2235/3227 , C04B2235/3229 , C04B2235/3232 , C23C4/18 , C23C8/02 , C23C28/321 , C23C28/345 , C23C28/3455 , Y10T428/12493 , Y10T428/12535 , Y10T428/12618 , Y10T428/12736 , Y10T428/12944
摘要： In one embodiment of the invention, a NiAl overlay bond coating composition comprises a NiAl alloy. The alloy comprises Zr and at least one modifying element in an amount effective to form a stabilized oxide structure comprising stabilized zirconia including a substantially tetragonal structure upon oxidation of the alloy. The tetragonal structure is stabilized such that it does not change phases and revert to a monoclinic or monoclinic and tetragonal structure, which is not substantially tetragonal, upon thermal cycling.
摘要翻译： 在本发明的一个实施方案中，NiAl覆盖层涂层组合物包含NiAl合金。 合金包含Zr和至少一种修饰元素，其量有效地形成稳定的氧化物结构，其包含在合金氧化时包括基本上四方晶结构的稳定的氧化锆。 四方结构被稳定，使得其在热循环时不改变相并恢复为单斜晶体或单斜晶体和四方晶体结构，其基本上不是四边形。
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