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61. 发明授权

US08595929B2 Repair of a turbine engine surface containing crevices 有权
标题翻译：修复含有缝隙的涡轮发动机表面
公开(公告)号：US08595929B2
公开(公告)日：2013-12-03
申请号：US12909183
申请日：2010-10-21
申请人： Navin J. Manjooran , Zafir A. M. Abdo , Anita Marie Hunt , Anand A. Kulkarni , Diego L. Caso, Jr.
发明人： Navin J. Manjooran , Zafir A. M. Abdo , Anita Marie Hunt , Anand A. Kulkarni , Diego L. Caso, Jr.
IPC分类号： B23P6/00
CPC分类号： F01D5/005 , B23P6/007 , F05D2230/30
摘要： A composition and method for cleaning turbine engine components (10) during servicing. An embodiment of the invention includes a colloidal mixture or slurry (22) of nanoparticles. The slurry may be nontoxic and provide optimal cleaning of tiny surface-exposed crevices (18) of braze joints and components. When a colloidal mixture is in a polar solvent, the pH of the slurry is maintained at about 5 to 9 and at the isoelectric point of the nanoparticles to minimize or prevent agglomeration. When a colloidal mixture is in a nonpolar solvent, the pH of the slurry is maintained at about 5 to 9 and at the isoelectric point of the nanoparticles to minimize or prevent agglomeration by use of surfactant additives.
摘要翻译：在维修期间清洁涡轮发动机部件（10）的组合物和方法。本发明的一个实施方案包括纳米颗粒的胶态混合物或浆液（22）。浆料可以是无毒的并且提供对钎焊接头和部件的微小表面暴露缝隙（18）的最佳清洁。当胶体混合物在极性溶剂中时，浆料的pH值保持在约5至9，并且在纳米颗粒的等电点处以最小化或防止聚集。当胶体混合物在非极性溶剂中时，浆料的pH保持在约5至9，并且在纳米颗粒的等电点处，以通过使用表面活性剂添加剂来最小化或防止团聚。

62. 发明授权

US08420238B2 Use of a tungsten bronze structured material and turbine component with a thermal barrier coating 失效
标题翻译：使用具有热障涂层的钨青铜结构材料和涡轮机部件
公开(公告)号：US08420238B2
公开(公告)日：2013-04-16
申请号：US12227567
申请日：2007-01-10
申请人： Anand A. Kulkarni , Stefan Lampenscherf , Ashkan Naeini , Ramesh Subramanian
发明人： Anand A. Kulkarni , Stefan Lampenscherf , Ashkan Naeini , Ramesh Subramanian
IPC分类号： F01D25/08 , F01D5/14 , F04D29/58 , F04D29/38 , F03D11/02 , B64C11/16 , B32B9/00 , B32B19/00
CPC分类号： C23C30/00 , C04B35/462 , C04B2235/3215 , C04B2235/3224 , C04B2235/76 , C23C28/3215 , C23C28/345 , C23C28/3455 , Y02T50/67
摘要： A tungsten bronze structured ceramic material as a thermal barrier coating is described wherein the tungsten bronze structured ceramic coating material has the formula AO—BvOw—CyOz where O stands for Oxygen, A stands for a 2+ or a 1+ cation, B stands for a 2+ or 3+ cation and C stands for a 4+ or a 5+ cation. The thermal barrier coating may be applied for gas turbine components.
摘要翻译：描述了作为热障涂层的钨青铜结构陶瓷材料，其中钨青铜结构陶瓷涂层材料具有式AO-BvOw-CyOz，其中O代表氧，A代表2+或1+阳离子，B代表一个2+或3+阳离子，C代表4+或5+阳离子。热障涂层可用于燃气轮机部件。

63. 发明申请

US20120128525A1 Metallic Bondcoat or Alloy with a High y/y' Transition Temperature and a Component 审中-公开
公开(公告)号：US20120128525A1
公开(公告)日：2012-05-24
申请号：US12953520
申请日：2010-11-24
申请人： Anand A. Kulkarni , Jonathan E. Shipper , Werner Stamm
发明人： Anand A. Kulkarni , Jonathan E. Shipper , Werner Stamm
IPC分类号： C22C19/05 , C22C19/03
CPC分类号： C22C30/00 , C22C19/055 , C22C19/056 , C22C19/057 , C22C19/07 , C23C4/073 , Y02T50/67
摘要： A nickel-based coating or alloy is provided. The coating includes tantalum preferably without rhenium. The coating or alloy has stabilized the formation of phases γ/γ′ at high temperatures leading to a reduction of local stresses. A component is also provided. The substrate of the component includes a nickel-based or cobalt-based superalloy.

64. 发明申请

US20120034101A1 TURBINE BLADE SQUEALER TIP 审中-公开
公开(公告)号：US20120034101A1
公开(公告)日：2012-02-09
申请号：US12852679
申请日：2010-08-09
申请人： Allister W. James , Anand A. Kulkarni
发明人： Allister W. James , Anand A. Kulkarni
IPC分类号： F01D5/18 , F01D5/30 , F01D5/14
CPC分类号： F01D5/20 , B33Y80/00 , F05D2230/22 , F05D2230/234 , F05D2230/31
摘要： A turbine blade having a squealer tip coupled to a radially outer end of the turbine blade that is usable in a gas turbine engine is disclosed. The squealer tip may require less cooling air and may therefore be more efficient than conventional configurations. The squealer tip may be formed from one or more materials such as oxide dispersion strengthened alloys and FeCrAl alloys. The squealer tip may be formed from a plurality of segmented tips extending radially outward and spaced apart from each other. For example, the squealer tip may be formed from two rails extending radially outward and spaced apart from each other. The two rails may be formed from outer and inner rails that each form a continuous ring. The squealer tip may be attached to the tip with a transient liquid phase bond or an additive manufacturing process, such as, a selective laser melting process.
摘要翻译：公开了一种涡轮叶片，其具有联接到可用于燃气涡轮发动机的涡轮叶片的径向外端的尖叫尖端。尖叫尖端可能需要较少的冷却空气，因此可能比传统配置更有效。尖叫尖端可以由一种或多种材料形成，例如氧化物分散强化合金和FeCrAl合金。尖叫尖端可以由径向向外延伸并且彼此间隔开的多个分段末端形成。例如，尖叫尖端可以由径向向外延伸并彼此间隔开的两个轨道形成。两个轨道可以由每个形成连续环的外轨和内轨形成。尖叫尖端可以用瞬态液相结合或附加制造工艺（例如选择性激光熔化法）附着到尖端。

65. 发明申请

US20110297344A1 TURBINE AIRFOIL TO SHROUD ATTACHMENT METHOD 有权
标题翻译：涡轮机空气对SHROUD附件方法
公开(公告)号：US20110297344A1
公开(公告)日：2011-12-08
申请号：US13195959
申请日：2011-08-02
申请人： Christian X. Campbell , Anand A. Kulkarni , Allister W. James , Brian J. Wessell , Paul J. Gear
发明人： Christian X. Campbell , Anand A. Kulkarni , Allister W. James , Brian J. Wessell , Paul J. Gear
IPC分类号： B22D19/00
CPC分类号： F01D9/044 , B22C9/10 , B22D19/00 , B22D19/0081 , B22D29/001 , F01D11/005 , F05B2230/21 , F05B2240/80 , F05D2230/21 , F05D2240/80 , Y10T29/49321 , Y10T29/4981 , Y10T29/49826 , Y10T29/49982 , Y10T29/49984
摘要： Bi-casting a platform (50) onto an end portion (42) of a turbine airfoil (31) after forming a coating of a fugitive material (56) on the end portion. After bi-casting the platform, the coating is dissolved and removed to relieve differential thermal shrinkage stress between the airfoil and platform. The thickness of the coating is varied around the end portion in proportion to varying amounts of local differential process shrinkage. The coating may be sprayed (76A, 76B) onto the end portion in opposite directions parallel to a chord line (41) of the airfoil or parallel to a mid-platform length (80) of the platform to form respective layers tapering in thickness from the leading (32) and trailing (34) edges along the suction side (36) of the airfoil.
摘要翻译：在端部上形成缓冲材料（56）的涂层之后，将平台（50）压铸在涡轮机翼（31）的端部（42）上。在双面浇铸平台之后，涂层被溶解和去除，以减轻翼型和平台之间的不同的热收缩应力。涂层的厚度随着局部差动过程收缩量的变化量的比例而在端部周围变化。涂层可以在平行于翼型的弦线（41）的平行方向上平行于平台的中平台长度（80）喷射（76A，76B）到端部上，以形成相应的层沿着翼型的吸力侧（36）的引导（32）和尾部（34）边缘。

66. 发明授权

US08043718B2 Combustion turbine component having rare earth NiCrAl coating and associated methods 有权
标题翻译：具有稀土NiCrAl涂层的燃烧涡轮机组件及相关方法
公开(公告)号：US08043718B2
公开(公告)日：2011-10-25
申请号：US12194582
申请日：2008-08-20
申请人： Anand A. Kulkarni , Allister W. James , Douglas J. Arrell
发明人： Anand A. Kulkarni , Allister W. James , Douglas J. Arrell
IPC分类号： B32B15/04 , C23C4/06
CPC分类号： C23C28/347 , B22F1/0018 , B22F7/04 , B22F2998/10 , C22C19/058 , C22C32/0026 , C23C4/073 , C23C4/10 , C23C24/04 , C23C28/321 , C23C28/3215 , C23C28/3455 , Y10T428/12028 , Y10T428/12535 , Y10T428/12611 , Y10T428/1266 , B22F9/082 , B22F9/04 , B22F3/115
摘要： A combustion turbine component (10) includes a combustion turbine component substrate (16) and an alloy coating (14) on the combustion turbine component substrate. The alloy coating (14) includes nickel (Ni), chromium (Cr), aluminum (Al), and yttrium (Y). Furthermore, the alloy coating includes at least one of titanium (Ti), tantalum (Ta), tungsten (W), and rhenium (Re). The alloy coating also includes at least one rare earth element, and an oxide of at least one of the yttrium (Y) and the at least one rare earth element.
摘要翻译：燃气涡轮机部件（10）包括燃气轮机部件基板（16）和燃烧涡轮部件基板上的合金涂层（14）。合金涂层（14）包括镍（Ni），铬（Cr），铝（Al）和钇（Y）。此外，合金涂层包括钛（Ti），钽（Ta），钨（W）和铼（Re）中的至少一种。合金涂层还包括至少一种稀土元素和至少一种钇（Y）和至少一种稀土元素的氧化物。

67. 发明授权

US07846561B2 Engine portions with functional ceramic coatings and methods of making same 有权
标题翻译：具有功能性陶瓷涂层的发动机部分及其制造方法
公开(公告)号：US07846561B2
公开(公告)日：2010-12-07
申请号：US12019931
申请日：2008-01-25
申请人： Anand A. Kulkarni
发明人： Anand A. Kulkarni
IPC分类号： B32B9/00
CPC分类号： C23C4/02 , C23C4/10 , F01D5/284 , F01D5/288 , F05D2230/90 , F05D2300/21 , Y10T428/249961 , Y10T428/25
摘要： A ceramic coating for imparting one or more of a variety of functional characteristics (e.g., reducing vibration levels) to one or more components or portions of an engine (e.g., ring segments, transition ducts, combustors, blades, vanes and shrouds of a turbine engine, portions thereof, and portions of a diesel engine), the components or portions comprising such a coating, and methods of making same. The ceramic coating exhibits a gradient or other change in the functional characteristic(s) through the thickness of the coating, across the surface area of the coating or both.
摘要翻译：陶瓷涂层，其用于将发动机的一个或多个部件或部分（例如，环形部分，过渡管道，燃烧器，叶片，叶轮和涡轮机的护罩）的各种功能特性（例如，降低振动水平）中的一种或多种发动机，其部分和柴油发动机的部分），包括这种涂层的部件或部件及其制造方法。陶瓷涂层通过涂层的厚度，穿过涂层的表面积或两者都显示出功能特性的梯度或其它变化。

68. 发明授权

US07582359B2 Apparatus and method of monitoring operating parameters of a gas turbine 有权
标题翻译：监测燃气轮机运行参数的装置和方法
公开(公告)号：US07582359B2
公开(公告)日：2009-09-01
申请号：US11269043
申请日：2005-11-08
申请人： Stephen M. Sabol , Ramesh Subramanian , Anand A. Kulkarni
发明人： Stephen M. Sabol , Ramesh Subramanian , Anand A. Kulkarni
IPC分类号： B32B9/00
CPC分类号： F01D17/02 , B33Y80/00 , F01D17/08 , F01D21/003 , F05D2230/30 , F05D2230/90 , F05D2260/80
摘要： A component for use in a combustion turbine (10) is provided that includes a substrate (212) and a microelectromechanical system (MEMS) device (50, 250) affixed to the substrate (212). At least one connector (52) may be deposited in electrical communication with the MEMS device (50, 250) for routing a data signal from the MEMS device (50, 250) to a termination location (59). A barrier coating (216) may be deposited on the substrate (212) wherein the MEMS device (50, 250) is affixed beneath a surface of the barrier coating (216). A plurality of trenches (142) may be formed in the barrier coating (216) at respective different depths below the surface of the barrier coating (216) and a MEMS device (50, 250) deposited within each of the plurality of trenches (142). A monitoring system (30) is provided that may include a processing module (34) programmed for receiving data from the MEMS device (50, 250).
摘要翻译：提供了一种用于燃气轮机（10）的部件，其包括固定到基板（212）上的基板（212）和微机电系统（MEMS）装置（50,250）。至少一个连接器（52）可以沉积成与MEMS器件（50,250）电连通，用于将来自MEMS器件（50,250）的数据信号路由到终止位置（59）。阻挡涂层（216）可以沉积在衬底（212）上，其中MEMS器件（50,250）被固定在阻挡涂层（216）的表面下方。多个沟槽（142）可以在阻挡涂层（216）的表面下方的相应不同深度处形成在阻挡涂层（216）中，以及沉积在多个沟槽（142）的每一个内的MEMS装置（50,250））。提供了一种监视系统（30），其可包括被编程用于从MEMS装置（50,250）接收数据的处理模块（34）。

69. 发明申请

US20090075111A1 Combustion Turbine Component Having Rare Earth NiCrAl Coating and Associated Methods 有权
标题翻译：具有稀土NiCrAl涂层的燃烧涡轮机组件及相关方法
公开(公告)号：US20090075111A1
公开(公告)日：2009-03-19
申请号：US12194582
申请日：2008-08-20
申请人： Anand A. Kulkarni , Allister W. James , Douglas J. Arrell
发明人： Anand A. Kulkarni , Allister W. James , Douglas J. Arrell
IPC分类号： B32B15/00 , B22F9/00 , C23C4/08
CPC分类号： C23C28/347 , B22F1/0018 , B22F7/04 , B22F2998/10 , C22C19/058 , C22C32/0026 , C23C4/073 , C23C4/10 , C23C24/04 , C23C28/321 , C23C28/3215 , C23C28/3455 , Y10T428/12028 , Y10T428/12535 , Y10T428/12611 , Y10T428/1266 , B22F9/082 , B22F9/04 , B22F3/115
摘要： A combustion turbine component (10) includes a combustion turbine component substrate (16) and an alloy coating (14) on the combustion turbine component substrate. The alloy coating (14) includes nickel (Ni), chromium (Cr), aluminum (Al), and yttrium (Y). Furthermore, the alloy coating includes at least one of titanium (Ti), tantalum (Ta), tungsten (W), and rhenium (Re). The alloy coating also includes at least one rare earth element, and an oxide of at least one of the yttrium (Y) and the at least one rare earth element.
摘要翻译：燃气涡轮机部件（10）包括燃气轮机部件基板（16）和燃烧涡轮部件基板上的合金涂层（14）。合金涂层（14）包括镍（Ni），铬（Cr），铝（Al）和钇（Y）。此外，合金涂层包括钛（Ti），钽（Ta），钨（W）和铼（Re）中的至少一种。合金涂层还包括至少一种稀土元素和至少一种钇（Y）和至少一种稀土元素的氧化物。

70. 发明申请

US20090074961A1 ENGINE PORTIONS WITH FUNCTIONAL CERAMIC COATINGS AND METHODS OF MAKING SAME 有权
标题翻译：具有功能陶瓷涂料的发动机部件及其制造方法
公开(公告)号：US20090074961A1
公开(公告)日：2009-03-19
申请号：US12019931
申请日：2008-01-25
申请人： Anand A. Kulkarni
发明人： Anand A. Kulkarni
IPC分类号： B32B18/00 , B05D1/12 , B32B3/26 , B32B5/02
CPC分类号： C23C4/02 , C23C4/10 , F01D5/284 , F01D5/288 , F05D2230/90 , F05D2300/21 , Y10T428/249961 , Y10T428/25
摘要： A ceramic coating for imparting one or more of a variety of functional characteristics (e.g., reducing vibration levels) to one or more components or portions of an engine (e.g., ring segments, transition ducts, combustors, blades, vanes and shrouds of a turbine engine, portions thereof, and portions of a diesel engine), the components or portions comprising such a coating, and methods of making same. The ceramic coating exhibits a gradient or other change in the functional characteristic(s) through the thickness of the coating, across the surface area of the coating or both.
摘要翻译：陶瓷涂层，其用于将发动机的一个或多个部件或部分（例如，环形部分，过渡管道，燃烧器，叶片，叶轮和涡轮机的护罩）的各种功能特性（例如，降低振动水平）中的一种或多种发动机，其部分和柴油发动机的部分），包括这种涂层的部件或部件及其制造方法。陶瓷涂层通过涂层的厚度，穿过涂层的表面积或两者都显示出功能特性的梯度或其它变化。

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