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1. 发明授权

US08815371B2 Structure and method for forming detailed channels for thin walled components using thermal spraying 有权
标题翻译：使用热喷涂形成薄壁部件的详细通道的结构和方法
公开(公告)号：US08815371B2
公开(公告)日：2014-08-26
申请号：US12420135
申请日：2009-04-08
申请人： Douglas J. Arrell , Allister W. James , Anand A. Kulkarni
发明人： Douglas J. Arrell , Allister W. James , Anand A. Kulkarni
IPC分类号： B32B3/00 , B32B3/20 , F01D5/08 , F01D5/20 , F01D5/28 , C23C4/18 , B23P15/00 , C23C4/08 , F01D5/18 , B23P15/04 , F01D25/12 , C23C4/06 , F02C7/12
CPC分类号： F01D5/18 , B23P15/00 , B23P15/04 , B23P2700/06 , B23P2700/13 , C23C4/06 , C23C4/073 , C23C4/185 , F01D5/288 , F01D25/12 , F02C7/12 , F05D2230/90 , F05D2300/21 , Y10T428/24612 , Y10T428/24744
摘要： A coated substrate with a subsurface cooling channel having no corner disposed proximate a seam between the substrate and the coating. A method for forming such a structure, including forming a groove in a surface of a substrate, forming a preform having a cooperating portion and a protruding portion, inserting the cooperating portion of the preform into the groove, leaving the protruding portion of the preform protruding beyond the surface of the substrate, applying a layer of a coating material to the surface of the substrate and the protruding portion of the perform, and removing the preform, thereby creating a cooling channel.
摘要翻译：具有地下冷却通道的涂覆的基底，其没有靠近基底和涂层之间的接缝设置角部。一种用于形成这种结构的方法，包括在基板的表面中形成凹槽，形成具有配合部分的预成型件和突出部分，将预成型件的配合部分插入凹槽中，使预成型件的突出部分突出超过基板的表面，将涂层材料层施加到基板的表面和执行的突出部分，并且移除预成型件，从而形成冷却通道。

2. 发明授权

US07900458B2 Turbine airfoils with near surface cooling passages and method of making same 有权
标题翻译：具有近表面冷却通道的涡轮翼型及其制造方法
公开(公告)号：US07900458B2
公开(公告)日：2011-03-08
申请号：US11807389
申请日：2007-05-29
申请人： Allister W. James , Anand A. Kulkarni
发明人： Allister W. James , Anand A. Kulkarni
IPC分类号： B31D3/00
CPC分类号： F01D5/187 , B23P15/04 , B23P2700/06 , C23C28/321 , C23C28/322 , C23C28/3455 , F01D5/186 , F01D5/288 , F05D2230/30 , F05D2230/90 , F05D2300/611 , Y10T29/49337
摘要： The present invention provides near-surface cooled airfoils that can be made with near-surface cooling passages that are completely free of any leachable or otherwise sacrificial material in the recessed portion of the outer surface of the core. The turbine airfoil comprises a metallic core or substrate having an outer surface and one or a plurality of recessed portions of the outer surface; an intermediate metallic skin or foil having a back surface and a top surface, the back surface of the intermediate skin being bonded to the outer surface of the core such that the recessed portion(s) is sufficiently enclosed so as to form at least one or more near-surface cooling passages or pathways; and at least one or more metallic coatings of a high temperature-resistant metallic material deposited on a top surface of the intermediate skin.
摘要翻译：本发明提供了近表面冷却的翼型件，其可以由在芯体的外表面的凹陷部分中完全没有任何可浸出或以其他方式牺牲的材料的近地表面冷却通道制成。涡轮机翼片包括具有外表面和外表面的一个或多个凹部的金属芯或基板; 具有后表面和顶表面的中间金属表皮或箔，所述中间表皮的后表面结合到所述芯的外表面，使得所述凹陷部分被充分地封闭，从而形成至少一个或多个更接近地面的冷却通道或路径; 以及沉积在中间皮肤的顶表面上的耐高温金属材料的至少一种或多种金属涂层。

3. 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。

4. 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。

5. 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。

6. 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。

7. 发明授权

US08914976B2 Turbine airfoil to shroud attachment method 有权
标题翻译：涡轮机翼到护罩附件方法
公开(公告)号：US08914976B2
公开(公告)日：2014-12-23
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： B21K25/00 , B22D19/00 , F01D9/04 , F01D11/00
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：在端部上形成短暂材料（56）的涂层之后，将平台（50）浇铸到涡轮机翼（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。

8. 发明授权

US08039117B2 Combustion turbine component having rare earth NiCoCrAl coating and associated methods 有权
标题翻译：具有稀土NiCoCrAl涂层的燃烧涡轮机组件及相关方法
公开(公告)号：US08039117B2
公开(公告)日：2011-10-18
申请号：US12194567
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 , B22F1/0085 , B22F1/0088 , B22F9/082 , B22F2998/10 , B22F2999/00 , C22C19/007 , C22C19/05 , C22C30/00 , C23C4/073 , C23C4/10 , C23C24/04 , C23C28/321 , C23C28/3215 , C23C28/3455 , C23C30/00 , Y10T428/12028 , Y10T428/12535 , Y10T428/12611 , Y10T428/1266 , C23C24/00 , B22F2201/01 , B22F2201/03
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 a first amount, by weight percent, of nickel (Ni) and a second amount, by weight percent, of cobalt (Co), the first amount being greater than the second amount. The alloy coating also includes chromium (Cr), aluminum (Al), and yttrium (Y). The alloy coating further includes at least one of titanium (Ti), tantalum (Ta), tungsten (W), and rhenium (Re). Moreover, the alloy coating includes at least one rare earth element, and an oxide of at least one of the yttrium 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）包含第一量（按重量百分比计）的镍（Ni），第二量含有以钴（Co）计的重量百分数，第一量大于第二量。合金涂层还包括铬（Cr），铝（Al）和钇（Y）。合金涂层还包括钛（Ti），钽（Ta），钨（W）和铼（Re）中的至少一种。此外，合金涂层包括至少一种稀土元素和至少一种钇至少一种稀土元素的氧化物。

9. 发明申请

US20100061875A1 Combustion Turbine Component Having Rare-Earth Elements and Associated Methods 审中-公开
标题翻译：具有稀土元素和相关方法的燃烧涡轮机组件
公开(公告)号：US20100061875A1
公开(公告)日：2010-03-11
申请号：US12205956
申请日：2008-09-08
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： B22F3/12
CPC分类号： B22F5/009 , B22F2998/10 , B22F1/0096 , B22F3/12 , B22F3/24
摘要： A method of making a combustion turbine component includes forming a nanosized powder including a plurality of metals and at least one rare-earth element and agglomerating the nanosized powder to form a microsized powder including a plurality of metals and at least one rare-earth element. The microsized powder is processed to form a cohesive metallic mass and a primary aging heat treating is performed on the cohesive metallic mass. A solution heat treating may be performed on the cohesive metallic mass prior to the primary aging heat treating. A secondary aging treating may be performed on the cohesive metallic mass after the primary aging treating.
摘要翻译：制造燃气轮机部件的方法包括形成包含多种金属和至少一种稀土元素的纳米尺寸粉末，并且使纳米尺寸粉末附聚以形成包含多种金属和至少一种稀土元素的微细粉末。将微细粉末加工成粘结金属物质，并对粘性金属物质进行初期时效热处理。在一次老化热处理之前，可以对内聚金属质量进行固溶热处理。二次老化处理可以在一次老化处理后对粘性金属块进行。

10. 发明申请

US20090075110A1 Combustion Turbine Component Having Rare Earth NiCoCrAl Coating and Associated Methods 有权
标题翻译：具有稀土NiCoCrAl涂层的燃烧涡轮机组件及相关方法
公开(公告)号：US20090075110A1
公开(公告)日：2009-03-19
申请号：US12194567
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 , C23C4/08
CPC分类号： C23C28/347 , B22F1/0085 , B22F1/0088 , B22F9/082 , B22F2998/10 , B22F2999/00 , C22C19/007 , C22C19/05 , C22C30/00 , C23C4/073 , C23C4/10 , C23C24/04 , C23C28/321 , C23C28/3215 , C23C28/3455 , C23C30/00 , Y10T428/12028 , Y10T428/12535 , Y10T428/12611 , Y10T428/1266 , C23C24/00 , B22F2201/01 , B22F2201/03
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 a first amount, by weight percent, of nickel (Ni) and a second amount, by weight percent, of cobalt (Co), the first amount being greater than the second amount. The alloy coating also includes chromium (Cr), aluminum (Al), and yttrium (Y). The alloy coating further includes at least one of titanium (Ti), tantalum (Ta), tungsten (W), and rhenium (Re). Moreover, the alloy coating includes at least one rare earth element, and an oxide of at least one of the yttrium 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）包含第一量（按重量百分比计）的镍（Ni），第二量含有以钴（Co）计的重量百分数，第一量大于第二量。合金涂层还包括铬（Cr），铝（Al）和钇（Y）。合金涂层还包括钛（Ti），钽（Ta），钨（W）和铼（Re）中的至少一种。此外，合金涂层包括至少一种稀土元素和至少一种钇至少一种稀土元素的氧化物。

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